EP2763897A1 - Aircraft propulsion assembly - Google Patents

Aircraft propulsion assembly

Info

Publication number
EP2763897A1
EP2763897A1 EP12775819.1A EP12775819A EP2763897A1 EP 2763897 A1 EP2763897 A1 EP 2763897A1 EP 12775819 A EP12775819 A EP 12775819A EP 2763897 A1 EP2763897 A1 EP 2763897A1
Authority
EP
European Patent Office
Prior art keywords
longitudinal axis
suspension
turbojet engine
axis
upstream
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP12775819.1A
Other languages
German (de)
French (fr)
Inventor
Nicolas Dezeustre
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Nacelles SAS
Original Assignee
Aircelle SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Aircelle SA filed Critical Aircelle SA
Publication of EP2763897A1 publication Critical patent/EP2763897A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type 
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B64D27/404—Suspension arrangements specially adapted for supporting vertical loads
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B64D27/406—Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links

Definitions

  • the present invention relates generally to a propulsion unit for aircraft.
  • An aircraft propulsion unit is formed by a nacelle and a turbojet, the assembly being intended to be suspended from a fixed structure of the aircraft, for example a wing or the fuselage, via a pylon attached to the turbojet engine and / or the nacelle.
  • the turbojet engine usually comprises an upstream section comprising a blower equipped with blades and a downstream section housing a gas generator.
  • the blades of the fan are surrounded by a fan casing for mounting the turbojet engine on the nacelle.
  • the pylon comprises, for example, a rigid structure of the box type, formed by the assembly of spars and side panels.
  • a suspension assembly is provided between the turbojet engine and the pylon, this assembly comprising a plurality of suspension fasteners forming a force recovery system distributed along the pylon.
  • such a suspension assembly comprises several upstream suspension fasteners integral with the fan casing or the intermediate casing and downstream suspension fasteners integral, for their part, with a central casing of the turbojet engine.
  • This suspension assembly furthermore, comprises a device for taking up the thrust forces generated by the turbojet engine.
  • Such a device can take the form of two lateral rods, located at the outlet of the annular fan duct and connected firstly to a downstream portion of the fan casing and, secondly, to a downstream fastener fixed on the central casing. of the turbojet.
  • a recurring problem of this type of suspension assembly lies in the torque exerted in a transverse direction of the aircraft, present in the makes the shift between the thrust recovery point of the connecting rods on the fan casing and the longitudinal central axis of the turbojet engine.
  • Such distortion of the turbojet generates friction between the fan casing and the rotating parts of the propulsion unit such as the blades or blades of the fan and / or between the blades of the turbojet engine and the central casing of the latter.
  • Such distortion can also cause games between the rotating parts of the propulsion unit and the fan casing and / or turbojet engine, which also reduce the performance of the turbojet engine.
  • a suspension assembly comprising a plurality of hyperstatic upstream suspension fasteners, each designed to take up forces acting in the three directions and three moments and a downstream suspension fastener mounted between the pylon and an outer casing, is known in particular. or ejection of the turbojet engine designed to take up forces exerted in the vertical direction of the turbojet engine.
  • the thrust force recovery device is removed.
  • Such a suspension assembly also involves the use of large suspension clips and provided with many stiffeners to cope with the suppression of the force recovery device and this adversely affects the mass of the propulsion unit. 'aircraft. This excess mass of the propulsion unit and the size associated with the suspension fasteners of the turbojet engine are detrimental to the performance of the turbojet engine.
  • An object of the present invention is to provide such a suspension assembly.
  • Another object of the present invention is to provide an aircraft propulsion unit which effectively limits the turbojet engine distortion while offering a saving in mass relative to existing suspension assemblies, thus significantly improving the engine performance of the propulsion unit.
  • the invention proposes an aircraft propulsion unit comprising a turbojet engine, a support providing the transfer of a torsor of forces towards the aircraft from a suspension assembly as well as a suspension assembly interposed between said support and the turbojet engine, the suspension assembly comprising a device for taking up the thrust forces of the turbojet engine mounted on an intermediate casing or in front of a central casing of said turbojet engine and on said support,
  • suspension assembly further comprises the following upstream suspension fasteners mounted on a fan casing and / or on said intermediate casing of said turbojet engine:
  • At least one main upstream suspension fastener configured so as to take up at least one moment along a longitudinal axis of the turbojet engine as well as the forces in a plane perpendicular to the longitudinal axis of said turbojet engine, and
  • At least one of the strikes of the complementary suspension distinct from the main suspension fastener and configured to resume at least one moment along the axis leading axis longitudinal axis of the turbojet engine to the longitudinal axis of the support and, associated with the ispos of repetitive thrust forces, a moment along the axis perpendicular to the longitudinal axis of the turbojet and the axis leading to the longitudinal axis of the turbojet engine to the longitudinal axis of the support and efforts along the longitudinal axis of the turbojet engine.
  • said suspension device comprises redundancies of the force paths by means of pairs of suspension fasteners, to ensure the recovery of the useful force paths in the event of rupture of the main effort path;
  • the suspension assembly is isostatic
  • said pair of complementary upstream suspension fasteners extends in a plane defined by the longitudinal axis of the turbojet and the axis leading from the longitudinal axis of the turbojet engine to the longitudinal axis of the support, each fastener being connected to an upstream end, upstream of the support and, at a downstream end, at the outer periphery of an outer shell of the intermediate casing or the fan casing;
  • said pairs of complementary upstream suspension fasteners are mounted on the outer ring of the intermediate casing or on the fan casing, symmetrically with respect to the median plane defined by the long axial axis of the turbojet engine and by the axis leading to the longitudinal axis of the turbojet to the longitudinal axis of the support.
  • said complementary upstream suspension fasteners are mounted from one side to the other of the upstream suspension fastener main, the latter attachment extends to n pl sun perpend perpendicular to the longitudinal axis of the turbojet engine;
  • each pair of complementary upstream suspension fasteners comprises two connecting rods parallel to each other and extending in a plane defined by the axis leading from the longitudinal axis of the turbojet to the longitudinal axis of the passenger and by the longitudinal axis of the turbojet engine, connected to an upstream end, by means of a spreader bar, to a fastening support integral with the support and, at a downstream end, to the intermediate casing or to the fan casing via a hooking support.
  • one of the fasteners of the pair of complementary upstream suspension fasteners is configured in such a way that it resumes in association with said main suspension fastener, the moment along the axis leading from the longitudinal axis of the turbojet engine to the longitudinal axis of the support.
  • the pair of complementary upstream suspension fasteners extends in a plane perpendicular to the longitudinal axis, making it possible to recover forces perpendicular to this axis and to the axis leading from the longitudinal axis to the axis longitudinal of said support.
  • the invention also relates to an aircraft comprising at least one propulsion unit such as that which has just been presented.
  • FIG. 1 is a side view of an aircraft propulsion unit comprising a suspension assembly according to one embodiment of the present invention
  • FIG. 2 is a front view of the aircraft propulsion unit of FIG. 1;
  • FIG. 3 is a rear perspective view of the aircraft propulsion unit of FIG. 1;
  • FIG. 4 is an enlarged view of zone A of FIG. 3;
  • FIG. 5 is an enlarged view of the zone B of FIG. 1;
  • FIG. 6 is an enlarged view of zone C of FIG. 1;
  • FIG. 7 is a partial perspective view of upstream suspension fasteners interposed between an intermediate casing shell of the turbojet engine and a pylon of the assembly of FIG. 1, seen downstream of the propulsion unit;
  • FIG. 8 is a perspective view of the suspension fasteners of FIG. 7, viewed from below;
  • FIG. 9 illustrates in partial perspective another embodiment of upstream suspension fasteners interposed between an intermediate casing shell of the turbojet engine and a pylon, seen downstream of the propulsion unit;
  • FIG. 10 is an axial view of the suspension fasteners of FIG.
  • FIG. 11 represents a diagrammatic section of a propulsion unit on which the suspension assemblies according to the invention can be attached;
  • FIG. 12 illustrates the axis system used in the aircraft propulsion systems described.
  • the Z axis is generally vertical.
  • the vertical axis will be assimilated to the Z axis, even if the propulsion unit is mounted in another configuration, such as for example in the rear fuselage, this for simplification purposes.
  • upstream and downstream terms refer to the direction of advancement of the aircraft encountered following a thrust exerted by the turbojet engine.
  • effort generally describes the component "force" of the force torsor, composed of three forces and three moments, along each of the three axes X, Y and Z.
  • the stress recoveries in the three main directions and the times of moments are substantially in the X, Y and Z directions defined above.
  • part of a propulsion unit 1 for an aircraft is observed according to a first embodiment of the invention.
  • this propulsion unit 1 of aircraft is formed in particular by a nacelle (not shown), a turbojet 2, a pylon 10 and a suspension assembly 100 ensuring the attachment of the turbojet engine 2 under this pylon 10.
  • This aircraft propulsion unit 1 is intended to be suspended from a fixed structure of the aircraft (not shown), for example under a wing or on the fuselage, by means of the pylon 10.
  • the pylon 10 takes the form of a rigid longitudinal structure 1 1 and, more particularly, of a structure comprising a rigid box 12 capable of transmitting the torsor of forces between the turbojet engine 2 and the structure of the aircraft .
  • This box 12 extends substantially in the direction X.
  • the tower 10 is known to those skilled in the art and will not be detailed in more detail later.
  • Figure 1 1 describes the environment of the turbojet 2, by way of non-limiting example for the invention.
  • the turbojet engine 2 comprises a blower 42 delivering an annular flow with a primary flow that imputes the turbojet engine 2 driving the fan 42 and a secondary flow 38 that is ejected into the atmosphere while providing a significant fraction of the engine thrust. the aircraft.
  • the fan 42 is contained, as can be seen in FIG. 1, in a fan casing 34 which channels downstream the secondary flow 38.
  • This housing 34 defines an inner wall portion of the nacelle and has substantially the shape of an annular shell.
  • this fan casing 34 is adapted to surround the blower 42 of turbojet engine 2 essentially consisting of a rotary shaft and a plurality of fan blades.
  • the casing 34 may carry a plurality of flow rectification vanes 33 for redrawing the flow of secondary air 38 generated by the blower.
  • the blower 42 is rotatably mounted on a fixed hub 43 which can be connected to the fan casing 34 by a plurality of fixed arms 32 situated downstream of the blades 33 or directly by these blades 33.
  • the straightening vanes 33 act as force transmission in addition to or instead of the link arms 32.
  • the fan casing 34 is connected at its downstream end to an intermediate casing 30 belonging to the median section of the nacelle.
  • the flow of secondary air 38 generated by the blower also passes through the wheel formed by the intermediate casing 30.
  • the intermediate casing 30 is a structural element which comprises the hub 43, an annular outer shell 31 and optionally, the radial link arms 32 and the flow rectifiers 33 which connect the hub 43 to the outer shell 31.
  • This housing 30 may be made of several parts or not.
  • the secondary flow stream 38 is delimited internally by the outer 40 and inner 39 walls of the possible thrust reverser.
  • the inner wall 39 surrounds a cylindrical shell called central casing 35 which surrounds the body of the turbojet engine 2 and extends from the hub 43 of the intermediate casing 30 to an exhaust casing 37 located at the outlet of the turbine.
  • the different housings can be integral with each other.
  • suspension assembly 1 00 it makes it possible to transmit to the aircraft the mechanical forces of the turbojet engine 2 and the forces coming from the nacelle transmitted by the turbojet engine 2 during its various operating modes.
  • the loads to be considered are oriented along the three main directions (forces and moments).
  • the suspension assembly 100 comprises a device for taking up the thrust forces 1 10 of the turbojet engine 2 mounted, upstream, on the intermediate casing 30 or on the front of the central casing 35 and, downstream, on the pylon 10.
  • the suspension assembly also comprises upstream suspension fasteners mounted on the outer shell 31 of the intermediate casing 30 and / or on the fan casing 34:
  • a main upstream suspension fastener 130 configured in such a way as to take in particular the moment Mx along the longitudinal axis of the rboreactor, insinuating the forces Fy and Fz following respectively the transverse and vertical directions, and
  • the device 1 10 of thrust force recovery is associated with the pair 120, 140 suspension fasteners 120a, 1 20b, 140a, 140b upstream to resume the moment My and Fx efforts along the longitudinal axis.
  • This device 1 1 0 of thrust force recovery comprises two connecting rods 1 1 1, 1 12 of force recovery disposed on either side of the axis of the median plane XZ of the turbojet engine symmetrically.
  • connecting rods are mounted, at their upstream end, via anchoring points on the central part of the intermediate casing 30 and at their downstream end by means of a spreader 1 13 on the lower face of the lower spar 13.
  • Each rod 1 1 1, 1 12 are articulated each, at their downstream end, on the spreader 1 13 for example by pins rotated.
  • Each rod can be provided with yokes, in particular two, to cooperate with a yoke formed on the rudder 1 13 or vice versa.
  • This lifter 1 13 itself is pivotally mounted relative to a hooking support 1 14 along an axis parallel to the axial links of the connecting rods 1 1 1, 1 12 with said lifter 1 13 (see Figure 4).
  • the lifter 1 13 comprises at its two opposite extremes l ibres, two parallel attachment screeds 1 15 adapted to form with a yoke 1 1 6 connecting the support 1 14 ensuring the redundancy of stress paths.
  • the rudder 1 1 3 may itself be provided with a yoke to cooperate with two yokes formed on the support 1 14 hooking.
  • hooking support 1 14 is fixedly secured to the lower beam 13 of the box 12 of the mast 10 by means of several axial links 17 and possibly to shear pins according to Z.
  • any fastener secured to the rear of the central casing 35 of the turbojet engine and / or the exhaust casing 37 is advantageously eliminated.
  • This thrust force recovery device 1 10 may be designed to provide redundancy, in a non-limiting example, by doubling it.
  • the two pairs of upstream suspension fasteners 120, 140 complementary, associated with the thrust recovery device 1 1 0, are configured to take axial forces Fx whose points d ' application are offset in the vertical direction Z of the turbojet 2.
  • the two complementary upstream suspension straps 120, 140 are configured to take up axial forces Fx according to the approximately longitudinal direction, the points of which application are shifted in Y direction.
  • the component of the force in the two regions of upstream suspension fasteners 120, 140, out of the longitudinal direction X, is taken up by the main upstream suspension fastener 130 described later.
  • the presence of two rods 120a, 1 20b and 1 40a, 1 40b for each of the upstream suspension clips 120, 140 makes these redundant fasteners. The loss of some of the fasteners does not lead to breaking the stress path.
  • the first pair 120 of upstream suspension fasteners comprise two connecting rods 120a, 120b, and the second pair of first 40 upstream suspension fasteners comprises two further links 140a, 140b.
  • These four rods are mounted on the outer periphery of the outer shell 31 of the intermediate casing 30, at the downstream end of this shell 31.
  • These two pairs of fasteners 120, 140 are mounted symmetrically two by two with respect to the median plane XZ, defined by the axis X and the axis Z of the turbojet engine.
  • upstream fasteners 120, 140 extend in an XZ plane, and are connected to an upstream end upstream of the caisson 12 of the tower 10.
  • pairs of the first complementary upstream supension clamps 1 20, 140 may be the following: a connecting rod of each of the first and second pair of first upstream suspension fasteners, namely 120a, 140a, 120a, 140b, 120b; , 140a, 120b, 140b.
  • the upstream suspension clips 120, 130, 140 are thus grouped on the upper part of the outer periphery of the outer shell 31 of the intermediate casing 30.
  • each pair of complementary upstream suspension fasteners 1, 20, 140 are mounted at each lateral end of the casing 12 of the mast 10, on either side of the main upstream suspension clip 130. .
  • the complementary upstream suspension attachment strips 1, 20, 140 are thus offset along Y, starting from their peripheral lateral end, typically from the width of the box 12 of the mast 10.
  • the two pairs 120, 140 of connecting rods 120a, 120b on the one hand and 140a, 140b on the other hand are connected to an upstream end by means of a rudder 1 50 to an attachment support 1 62 secured to the lower beam 13 of the casing 12 of the mast 10 and at one end to the outer wall 31 of the cross section 30 via a hooking support 160.
  • the hooking support 160 is mounted on the periphery of the outer shell 31 by means of suitable fastening means.
  • It can also be split so as to have one or two yokes per rod 120, 140 to improve the redundancy of the fastener.
  • This attachment support 1 60 comprises two pairs of attachment shackles 161 parallel to the XZ plane, spaced along Y and intended to cooperate with a constituent element of the corresponding fastener and, more particularly with the downstream end of the connecting rod. 120a, 120b, 140a, 140b corresponding snap.
  • the support 160 may be provided with a clevis rod to cooperate with two clevises on the corresponding rod.
  • This hooking support 160 is bent to present the two pairs of yokes 161 projecting outwardly from the periphery of the outer shell 31 extending along Z and at the same altitude Z.
  • each of these screeds 161 is formed an eyelet 164 adapted to receive connecting means (not shown) for connecting the yoke 160 and the connecting rod 120a, 120b, 140a, 140b corresponding.
  • These eyelets 162 are arranged opposite eyelets formed on the ends of the connecting rods 120a, 120b, 140a, 140b corresponding.
  • the one or more clevises of the hooking support 160 and each connecting rod 120a, 120b, 140a, 140b can be connected, for example, by suitable pivoted shafts.
  • rods 120a, 1 20b, 140a, 140b of attachment are hinged, at their upstream end, on the spreader 150 by a rotated connection.
  • the rudder 150 is, in turn, mounted on the upstream end of the lower spar 13 of the box 12 by means of the attachment support 162.
  • the rudder 1 50 is provided with a system for limiting rotation about its central axis, for example by pins or pins mounted with clearance between the rudder 150 and external tabs 163 of the attachment support 162.
  • the fixing support 162 is secured to the upstream end of the lower beam 1 3 of the box 1 2 of the mat 1 0 through several axial links according to Z (for example: screws, pins, ...) .
  • All rods 1 20a, 1 20b, 140a, 140b, associated with their attachment system is designed to be redundant. The loss of any element of the stress path does not lead to the total loss of this stress path.
  • the pairs 1 20, 140 of complementary suspension fasteners 120a, 120b, 140a, 140b upstream may also be directed upstream of the tower 10 or downstream of the tower 10 for all the embodiments described.
  • the main upstream suspension clip 130 is fixed on the outer ring 31 of the intermediate casing 30.
  • This upstream main suspension clip 1 is configured to resume, in addition to the moment Mx, transverse forces Fy and vertical Fz.
  • FIG. 2 One example of embodiment of this fastener can be observed in FIG. 2 in particular.
  • This fastener 130 is a fitting 131 comprising two half-fasteners symmetrical with respect to the median plane XYYZ.
  • This fitting 1 31 is connected at its two lateral ends to two attachment lugs C 1, C 2 integral with the outer shell 31 of the intermediate casing 30 on which hinges 36 are respectively hinged at two or three points.
  • the fixing means of the clevises C1, C2, C3 can be any suitable fastening means and, in particular screws and shear pins.
  • the shackle fixing means 36 may be any suitable fixing means and, in particular, rotated shafts.
  • fitting 131 is also attached to the lower spar
  • suitable fastening means which may include, but not limited to, screwing means forming an axial lnaison Z and pions.
  • the shackles 36 may be of the "fail-safe" type as well as the shear pins, the clevises C1, C2, C3 and / or the screwing means.
  • the pair of upstream suspension brackets 200 is configured to take up Fy forces associated with the recovery of force Fy according to Y of the main suspension fastener 130.
  • main upstream suspension clip 130 is displaced, taking up the moment Mx upstream of the outer shell 31 of the intermediate casing 30.
  • the reverse is carried out, namely an upstream suspension fastener configured to take up a force along the Y axis at the upstream end of ferrule 31 is provided, and the attachment is further moved downstream. suspension upstream 130.
  • the two suspension clips 200a, 200b are symmetrical with respect to the median plane XZ and offset along Y.
  • These two suspension fasteners 200a, 200b extend in a plane YZ, connected at one end upstream of the box 12 of the pylon 10 and at an end opposite to the outer periphery of the outer shell 31 of the intermediate casing 30 or the blower housing 34.
  • One of these two suspension fasteners 200a, 200b is a waiting path, mounted for example with play, in case the other suspension fastener 200a, 200b breaks.
  • any other redundant system such as for example a double rod is within the scope of this invention, the two fasteners 200a, 200b being an example of real isation of the redundancy function related to the principle of upstream suspension fasteners 200.
  • a single suspension clip 200a will be described in connection with these figures.
  • a connecting rod 201 has hooking extending in a YZ plane and fixed at one end respectively to a hooking support 202a integral with the outer ring 31 of the intermediate casing 30 or the fan casing 34, and to opposite end to a hooking support 203a secured to the lower beam 13 of the pylon 10.
  • Each hooking support 202a, 203a comprises two parallel yokes intended to cooperate with a yoke formed at the end of the connecting rod 201a of the corresponding suspension clip 200a.
  • each connecting rod end 201a the three clevises are interconnected, for example by a suitable rotated pin.
  • This pair of fasteners 1 20 is formed between the two fasteners
  • This pair fasteners 1 20 is similar to that described in connection with the other embodiments and will not be described in detail later.
  • the pairs of complementary upstream suspension fasteners configured so as to take up at least one moment Mz along the vertical axis of the turbojet engine and, associated with the device for taking up the thrust forces 1 1 0, a moment My along the transverse axis of the turbojet engine and Fx forces along the longitudinal axis of the turbojet engine may be the following:
  • a connecting rod of the first pair of first upstream suspension fasteners namely 1 21 a or 121 b and the upstream suspension fastener 200 a, 200 b configured to take up a force along the Y axis, namely the pairs 1 21 a , 200a or 121b, 200b or 121a, 200b or 1b1b,
  • suspension fasteners for all the embodiments described, they may be made in any form known to those skilled in the art, such as, for example, that relating to the assembly of shackles, spreaders and fittings intended for to cooperate with a system of articulation of the biel type, or else of shearing ions.
  • these suspension fasteners can, by themselves, be m unies of systems ensuring the redundancy of the transmission of forces (forces and moments), for example, doubled effort chem ins, standby effort path, "fail safe" axes in English terms, namely, provided with main connection axes housed in concentric sleeves ensuring the transmission of the force in the event of breakage of the main link axis or the sleeve, or others.
  • the contacts between the rotating parts of the turbojet 2 and the corresponding housings are reduced, which improves the life of the engine.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)

Abstract

The invention concerns an aircraft propulsion assembly of which the suspension assembly comprises the following upstream suspension fasteners mounted on a blower housing (34) and/or on said intermediate housing (30) of the turbojet engine: at least one main upstream suspension fastener (130), configured in such a way as to absorb at least a moment (Mx) along the longitudinal axis (X) of the turbojet engine and the forces (Fy and Fz) in a plane perpendicular to the longitudinal axis, and at least one pair (120, 140, 200) of additional upstream suspension fasteners (120a, 120b, 140a, 140b, 121a, 121b, 200a, 200b) separate from the main suspension fastener (130) and configured in such a way as to absorb at least a moment (Mz) according to the vertical axis of the turbojet engine and, associated with a device for absorbing thrust forces (110), a moment (My) along the transverse axis of the turbojet engine and forces (Fx) along the longitudinal axis of the turbojet engine.

Description

Ensemble propulsif d'aéronef  Propulsion unit of aircraft
La présente invention se rapporte de façon générale à un ensemble propulsif pour aéronef. The present invention relates generally to a propulsion unit for aircraft.
Un ensemble propulsif d'aéronef est formé d'une nacelle et d'un turboréacteur, l'ensemble étant destiné à être suspendu à une structure fixe de l'aéronef, par exemple une aile ou le fuselage, par l'intermédiaire d'un pylône rattaché au turboréacteur et/ou à la nacelle.  An aircraft propulsion unit is formed by a nacelle and a turbojet, the assembly being intended to be suspended from a fixed structure of the aircraft, for example a wing or the fuselage, via a pylon attached to the turbojet engine and / or the nacelle.
Le turboréacteur comprend, usuellement, une section d ite amont comprenant une soufflante munies d'aubes et une section dite aval abritant un générateur de gaz.  The turbojet engine usually comprises an upstream section comprising a blower equipped with blades and a downstream section housing a gas generator.
Les aubes de la soufflante sont entourées d'un carter de soufflante permettant de monter le turboréacteur sur la nacelle.  The blades of the fan are surrounded by a fan casing for mounting the turbojet engine on the nacelle.
Par ailleurs, afin d'assurer la transmission des efforts à l'interface entre le turboréacteur et la structure fixe de l'aéronef, le pylône comporte, par exemple, une structure rigide du type caisson, formée par l'assemblage de longerons et de panneaux latéraux.  Furthermore, in order to ensure the transmission of forces at the interface between the turbojet and the fixed structure of the aircraft, the pylon comprises, for example, a rigid structure of the box type, formed by the assembly of spars and side panels.
Un ensemble de suspension est prévu entre le turboréacteur et le pylône, cet ensemble comprenant une plural ité d'attaches de suspension formant un système de reprise d'efforts réparties le long du pylône.  A suspension assembly is provided between the turbojet engine and the pylon, this assembly comprising a plurality of suspension fasteners forming a force recovery system distributed along the pylon.
Plus précisément, un tel ensemble de suspension comprend plusieurs attaches de suspension amont solidaires du carter de soufflante ou du carter intermédiaire et des attaches de suspension aval solidaires, quant à elles, d'un carter central du turboréacteur.  More specifically, such a suspension assembly comprises several upstream suspension fasteners integral with the fan casing or the intermediate casing and downstream suspension fasteners integral, for their part, with a central casing of the turbojet engine.
Cet ensemble de suspension, comprend, par ailleurs, un dispositif de reprise des efforts de poussée générés par le turboréacteur.  This suspension assembly, furthermore, comprises a device for taking up the thrust forces generated by the turbojet engine.
Un tel dispositif peut prendre la forme de deux bielles latérales, situées en sortie du canal annulaire de soufflante et raccordées d'une part à une partie aval du carter de soufflante et, d'autre part, à une attache aval fixée sur le carter central du turboréacteur.  Such a device can take the form of two lateral rods, located at the outlet of the annular fan duct and connected firstly to a downstream portion of the fan casing and, secondly, to a downstream fastener fixed on the central casing. of the turbojet.
Un problème récurrent de ce type d'ensemble de suspension réside dans le couple exercé selon une direction transversale de l'aéronef, présent du fait du décalage entre le point de reprise de poussée des bielles sur le carter de soufflante et l'axe central longitudinal du turboréacteur. A recurring problem of this type of suspension assembly lies in the torque exerted in a transverse direction of the aircraft, present in the makes the shift between the thrust recovery point of the connecting rods on the fan casing and the longitudinal central axis of the turbojet engine.
De ce couple et de l'ensemble de suspension classique prévu pour prendre les efforts de poussée du turboréacteur, résulte une distorsion du turboréacteur.  Of this pair and the conventional suspension assembly designed to take thrust forces of the turbojet, results in a distortion of the turbojet engine.
Une telle distorsion du turboréacteur engendre des frottements entre le carter de soufflante et les pièces tournantes de l'ensemble propulsif comme les aubes ou pales de la soufflante et/ou entre des pales du turboréacteur et le carter central de ce dernier.  Such distortion of the turbojet generates friction between the fan casing and the rotating parts of the propulsion unit such as the blades or blades of the fan and / or between the blades of the turbojet engine and the central casing of the latter.
Ces frottements détériorent les pièces tournantes, réduisent la durée de vie du turboréacteur et diminuent les performances de ce dernier.  This friction deteriorates the rotating parts, reduce the life of the turbojet and reduce the performance of the latter.
Une telle distorsion peut également engendrer des jeux entre les pièces tournantes de l'ensemble propulsif et le carter de soufflante et/ou central du turboréacteur, qui réduisent également les performances du turboréacteur.  Such distortion can also cause games between the rotating parts of the propulsion unit and the fan casing and / or turbojet engine, which also reduce the performance of the turbojet engine.
De nombreux ensembles de suspension ont été conçus pour diminuer ce problème récurrent de distorsion du turboréacteur. Ils ne sont toutefois pas totalement satisfaisants.  Many suspension assemblies have been designed to reduce this recurring problem of turbojet distortion. However, they are not totally satisfactory.
On connaît, notamment, un ensemble de suspension comprenant plusieurs attaches de suspension amont hyperstatiques, chacune conçue de manière à reprendre des efforts s'exerçant selon les trois directions et les trois moments et une attache de suspension aval montée entre le pylône et un carter externe ou d'éjection du turboréacteur conçue de manière à reprendre des efforts s'exerçant selon la direction verticale du turboréacteur.  A suspension assembly comprising a plurality of hyperstatic upstream suspension fasteners, each designed to take up forces acting in the three directions and three moments and a downstream suspension fastener mounted between the pylon and an outer casing, is known in particular. or ejection of the turbojet engine designed to take up forces exerted in the vertical direction of the turbojet engine.
Dans un tel ensemble, le dispositif de reprise d'effort de poussée est supprimé.  In such an assembly, the thrust force recovery device is removed.
Un tel ensemble de suspension rend dél icate la redondance des chemins d'effort et nécessite donc une politique d'inspection complexe.  Such a suspension assembly makes the redundancy of the stress paths more delicate and therefore requires a complex inspection policy.
Un tel ensemble de suspension implique en outre l'utilisation d'attaches de suspension de grandes dimensions et munis de nombreux raidisseurs pour faire face à la suppression du dispositif de reprise d'efforts et, ceci affecte défavorablement la masse de l'ensemble propulsif d'aéronef. Cet excès de masse de l'ensemble propulsif et l'encombrement associé aux attaches de suspension du turboréacteur sont néfastes pou r les performances du turboréacteur. Such a suspension assembly also involves the use of large suspension clips and provided with many stiffeners to cope with the suppression of the force recovery device and this adversely affects the mass of the propulsion unit. 'aircraft. This excess mass of the propulsion unit and the size associated with the suspension fasteners of the turbojet engine are detrimental to the performance of the turbojet engine.
Ainsi, il existe un besoin pour un ensemble de suspension permettant de remédier aux inconvénients susmentionnés.  Thus, there is a need for a suspension assembly to overcome the aforementioned drawbacks.
Un but de la présente invention est de fournir un tel ensemble de suspension.  An object of the present invention is to provide such a suspension assembly.
Un autre but de la présente invention est de proposer un ensemble propulsif d'aéronef qui limite efficacement la distorsion du turboréacteur tout en offrant un gain de masse relativement aux ensembles de suspension existants, améliorant ainsi significativement les performances du moteur de l'ensemble propulsif.  Another object of the present invention is to provide an aircraft propulsion unit which effectively limits the turbojet engine distortion while offering a saving in mass relative to existing suspension assemblies, thus significantly improving the engine performance of the propulsion unit.
Il est également désirable de considérer les aspects de maintenance du turboréacteur avec un ensemble propulsif d'aéronef dont l'ensemble de suspension est simple, efficace et facile à monter.  It is also desirable to consider the maintenance aspects of the turbojet engine with an aircraft propulsion unit whose suspension assembly is simple, efficient and easy to assemble.
A cet effet, l 'invention propose un ensemble propulsif d'aéronef comprenant un turboréacteur, un support assurant le transfert d'un torseur d'efforts vers l'aéronef depu is un ensemble de suspension ainsi qu'un ensemble de suspension interposé entre ledit support et le turboréacteur, l'ensemble de suspension comprenant un dispositif de reprise des efforts de poussée du turboréacteur monté sur un carter intermédiaire ou à l'avant d'un carter central dudit turboréacteur et sur ledit support,  For this purpose, the invention proposes an aircraft propulsion unit comprising a turbojet engine, a support providing the transfer of a torsor of forces towards the aircraft from a suspension assembly as well as a suspension assembly interposed between said support and the turbojet engine, the suspension assembly comprising a device for taking up the thrust forces of the turbojet engine mounted on an intermediate casing or in front of a central casing of said turbojet engine and on said support,
caractérisé en ce que l'ensemble de suspension comprend, en outre, les attaches de suspension amont su ivantes montées sur un carter de soufflante et/ ou sur ledit carter intermédiaire dudit turboréacteur :  characterized in that the suspension assembly further comprises the following upstream suspension fasteners mounted on a fan casing and / or on said intermediate casing of said turbojet engine:
au moins une attache de suspension amont principale, configurée de manière à reprendre au moins un moment selon un axe longitudinal du turboréacteur ainsi que les efforts dans un plan perpend iculaire à l'axe longitudinal dudit turboréacteur, et  at least one main upstream suspension fastener, configured so as to take up at least one moment along a longitudinal axis of the turbojet engine as well as the forces in a plane perpendicular to the longitudinal axis of said turbojet engine, and
- a u m o i n s u n e pa i re d ' atta ch es d e s u s pe n s i o n a m o n t complémentaires distinctes de l'attache de suspension principale et configurée de manière à reprendre au moins un moment selon l'axe menant de l'axe longitudinal du turboréacteur à l'axe longitudinal du support et, associée au d ispos itif de reprise des efforts de poussée, u n moment selon l 'axe perpendiculaire à l'axe longitudinal du turboréacteur et à l'axe menant de l'axe longitudinal du turboréacteur à l'axe longitudinal du support et des efforts selon l'axe longitudinal du turboréacteur. - At least one of the strikes of the complementary suspension distinct from the main suspension fastener and configured to resume at least one moment along the axis leading axis longitudinal axis of the turbojet engine to the longitudinal axis of the support and, associated with the ispos of repetitive thrust forces, a moment along the axis perpendicular to the longitudinal axis of the turbojet and the axis leading to the longitudinal axis of the turbojet engine to the longitudinal axis of the support and efforts along the longitudinal axis of the turbojet engine.
Ainsi, en prévoyant un ensemble d'attaches amont complet apte à reprendre l'ensemble des six composantes d'efforts et de moments de manière largement localisée en amont de al chambre de combustion du turboréacteur, il est possible de mieux gérer les reprise d'efforts, et notamment jusqu'à pouvoir supprimer l'attache arrière le cas échéant.  Thus, by providing a set of upstream fasteners complete able to take all six components of forces and moments largely localized upstream of the combustion chamber of the turbojet, it is possible to better manage recovery of efforts, including until you can remove the rear attachment if necessary.
Suivant d'autres caractéristiques optionnelles de l'invention, prises seules ou en combinaison :  According to other optional features of the invention, taken alone or in combination:
- ledit dispositif de suspension comprend des redondances des chemins d'effort au moyen de paires d'attaches de suspension, pour assurer la reprise des chemins d'effort utile en cas de rupture du chemin d'effort principal ;  said suspension device comprises redundancies of the force paths by means of pairs of suspension fasteners, to ensure the recovery of the useful force paths in the event of rupture of the main effort path;
- l'ensemble de suspension est isostatique ;  the suspension assembly is isostatic;
- ladite paire d'attaches de suspension amont complémentaire s'étend dans un plan défini par l'axe longitudinal du turboréacteur et l'axe menant de l'axe longitudinal du turboréacteur à l'axe longitudinal du support, chaque attache étant rel iée à une extrém ité amont, à l'amont du support et, à une extrémité aval, à la périphérie externe d'une virole externe du carter interméd iaire ou du carter de soufflante;  said pair of complementary upstream suspension fasteners extends in a plane defined by the longitudinal axis of the turbojet and the axis leading from the longitudinal axis of the turbojet engine to the longitudinal axis of the support, each fastener being connected to an upstream end, upstream of the support and, at a downstream end, at the outer periphery of an outer shell of the intermediate casing or the fan casing;
- lesdites paires d'attaches de suspension amont complémentaire sont montées sur la virole externe du carter intermédiaire ou sur le carter de soufflante, symétriquement par rapport au plan médian défini par l'axe long itud inal du turboréacteur et par l'axe menant de l'axe longitudinal du turboréacteur à l'axe longitudinal du support. - lesdites d'attaches de suspension amont complémentaires sont montées d e pa rt et d 'a utre de l'attache de suspension amont principale, cette dernière attache s'étend a nt d an s u n pl a n perpendiculaire à l'axe longitudinal du turboréacteur; said pairs of complementary upstream suspension fasteners are mounted on the outer ring of the intermediate casing or on the fan casing, symmetrically with respect to the median plane defined by the long axial axis of the turbojet engine and by the axis leading to the longitudinal axis of the turbojet to the longitudinal axis of the support. said complementary upstream suspension fasteners are mounted from one side to the other of the upstream suspension fastener main, the latter attachment extends to n pl sun perpend perpendicular to the longitudinal axis of the turbojet engine;
- chaque paire d'attaches de suspension amont complémentaire comprend deux bielles d'accrochage parallèles entre elles et s'étendant dans un plan défini par l'axe menant de l'axe longitudinal du turboréacteur à l 'axe long itud inal du su pport et par l 'axe longitudinal du turboréacteur, reliées à une extrémité amont, grâce à un palonnier, à un support de fixation solidaire du support et, à une extrémité aval, au carter intermédiaire ou au carter de soufflante via un support d'accrochage.  each pair of complementary upstream suspension fasteners comprises two connecting rods parallel to each other and extending in a plane defined by the axis leading from the longitudinal axis of the turbojet to the longitudinal axis of the passenger and by the longitudinal axis of the turbojet engine, connected to an upstream end, by means of a spreader bar, to a fastening support integral with the support and, at a downstream end, to the intermediate casing or to the fan casing via a hooking support.
- une des attaches de la paire des attaches de suspension amont complémentaires est config u rée d e ma n ière à reprend re en association avec ladite attache de suspension principale, le moment selon l'axe menant de l'axe longitudinal du turboréacteur à l'axe longitudinal du support.  one of the fasteners of the pair of complementary upstream suspension fasteners is configured in such a way that it resumes in association with said main suspension fastener, the moment along the axis leading from the longitudinal axis of the turbojet engine to the longitudinal axis of the support.
- lad ite attache de la paire des attaches de suspension amont complémentaires s'étend dans un plan perpendiculaire à l'axe longitudinal, permettant de reprendre des efforts perpendiculaires à cet axe et à l'axe menant de l'axe longitudinal à l'axe longitudinal dudit support.  the pair of complementary upstream suspension fasteners extends in a plane perpendicular to the longitudinal axis, making it possible to recover forces perpendicular to this axis and to the axis leading from the longitudinal axis to the axis longitudinal of said support.
L'invention a également pour objet un aéronef comprenant au moins un ensemble propulsif tel que celui qui vient d'être présenté. The invention also relates to an aircraft comprising at least one propulsion unit such as that which has just been presented.
D'autres caractéristiq ues et avantages de la présente invention apparaîtront à la lumière de la description qui va suivre, et à l'examen des figures ci-annexées, dans lesquelles :  Other features and advantages of the present invention will emerge in the light of the description which follows, and on examining the appended figures, in which:
- la figure 1 est une vue latérale d'un ensemble propulsif d'aéronef comprenant un ensemble de suspension selon un mode de réalisation de la présente invention ;  FIG. 1 is a side view of an aircraft propulsion unit comprising a suspension assembly according to one embodiment of the present invention;
- la figure 2 est une vue de face de l'ensemble propulsif d'aéronef de la figure 1 ; - la figure 3 est une vue en perspective arrière de l'ensemble propulsif d'aéronef de la figure 1 ; FIG. 2 is a front view of the aircraft propulsion unit of FIG. 1; FIG. 3 is a rear perspective view of the aircraft propulsion unit of FIG. 1;
- la figure 4 est une vue agrandie de la zone A de la figure 3 ;  FIG. 4 is an enlarged view of zone A of FIG. 3;
- la figure 5 est une vue agrandie de la zone B de la figure 1 ;  FIG. 5 is an enlarged view of the zone B of FIG. 1;
- la figure 6 est une vue agrandie de la zone C de la figure 1 ;  FIG. 6 is an enlarged view of zone C of FIG. 1;
-la figure 7 est une vue en perspective partielle d'attaches de suspension amont interposées entre une virole de carter intermédiaire du turboréacteur et un pylône de l'ensemble de la figure 1 , vu en aval de l'ensemble propulsif ;  FIG. 7 is a partial perspective view of upstream suspension fasteners interposed between an intermediate casing shell of the turbojet engine and a pylon of the assembly of FIG. 1, seen downstream of the propulsion unit;
- la figure 8 est une vue en perspective des attaches de suspension de la figure 7, vues de dessous ;  FIG. 8 is a perspective view of the suspension fasteners of FIG. 7, viewed from below;
- la figure 9 illustre en perspective partielle un autre mode de réalisation d'attaches de suspension amont interposées entre une virole de carter intermédiaire du turboréacteur et un pylône, vu en aval de l'ensemble propulsif ;  FIG. 9 illustrates in partial perspective another embodiment of upstream suspension fasteners interposed between an intermediate casing shell of the turbojet engine and a pylon, seen downstream of the propulsion unit;
- la figure 10 est une vue axiale des attaches de suspension de la figure FIG. 10 is an axial view of the suspension fasteners of FIG.
9 ; 9;
-la figure 11 représente une coupe schématique d'un ensemble propulsif, sur lequel peuvent venir s'attacher les ensembles de suspension selon l'invention ;  FIG. 11 represents a diagrammatic section of a propulsion unit on which the suspension assemblies according to the invention can be attached;
-la figure 12 illustre le système d'axe utilisé dans les ensembles propulsif d'aéronef décrits.  FIG. 12 illustrates the axis system used in the aircraft propulsion systems described.
A noter que sur l'ensemble de ces figures, les axes qui relient les pièces entre elles ne sont généralement pas représentés.  Note that on all these figures, the axes that connect the parts together are generally not represented.
Sur l'ensemble de ces figures, des numéros identiques ou analogues désignent des organes ou ensembles d'organes identiques ou analogues.  In all of these figures, identical or similar numbers denote identical or similar organs or sets of members.
En référence à la figure 12, on notera que l'on a pris soin de définir dans la description un repère à trois axes X, Y Z, ces trois axes étant représentatifs :  With reference to FIG. 12, it will be noted that care has been taken to define in the description a reference with three axes X, Y Z, these three axes being representative:
-de la direction longitudinale du turboréacteur pour l'axe X,  the longitudinal direction of the turbojet engine for the X axis,
-de la direction menant de l'axe longitudinal du turboréacteur à l'axe longitudinal du pylône pour la direction Z et,  the direction from the longitudinal axis of the turbojet to the longitudinal axis of the pylon for the Z direction and,
- de la direction orthogonale à X et Z pour l'axe Y. Dans le cas d'un ensemble propulsif monté sous aile, l'axe Z est généralement vertical. - from the orthogonal direction to X and Z for the Y axis. In the case of a propulsion unit mounted under wing, the Z axis is generally vertical.
Dans la description ci-après, l'axe vertical sera assimilé à l'axe Z, même si l'ensemble propulsif est monté dans une autre configuration, tel que par exemple en fuselage arrière, ceci à des fins de simplification.  In the description below, the vertical axis will be assimilated to the Z axis, even if the propulsion unit is mounted in another configuration, such as for example in the rear fuselage, this for simplification purposes.
On notera également que les termes amont et aval s'entendent par rapport à la direction d'avancement de l'aéronef rencontré suite à une poussée exercée par le turboréacteur.  It will also be noted that the upstream and downstream terms refer to the direction of advancement of the aircraft encountered following a thrust exerted by the turbojet engine.
Par ailleurs, seront considérés les efforts et les moments suivants :  In addition, the following efforts and moments will be considered:
- Fx les efforts suivant un axe sensiblement parallèle à l'axe X, et un - Fx the forces along an axis substantially parallel to the axis X, and a
Moment Mx sensiblement autour de cet axe ; Moment Mx substantially around this axis;
- Fy, les efforts suivant un axe sensiblement parallèle à l'axe Y, et un Moment My sensiblement autour de cet axe ;  - Fy, the forces along an axis substantially parallel to the Y axis, and Moment My substantially around this axis;
- Fz, les efforts suivant un axe sensiblement parallèle à l'axe Z, et un Moment Mz sensiblement autour de cet axe.  - Fz, the forces along an axis substantially parallel to the Z axis, and a Moment Mz substantially around this axis.
Dans la description qui suit, le terme effort décrit généralement la composante « force » du torseur d'effort, composé de trois forces et de trois moments, suivant chacun des trois axes X,Y et Z.  In the description which follows, the term effort generally describes the component "force" of the force torsor, composed of three forces and three moments, along each of the three axes X, Y and Z.
De même, dans la description qui suit les reprises d'effort dans les trois directions principales et les reprises de moments sont sensiblement dans les directions X, Y et Z définies ci-dessus.  Likewise, in the following description, the stress recoveries in the three main directions and the times of moments are substantially in the X, Y and Z directions defined above.
Un angle limité par rapport à ces directions dû aux contraintes de design tel q ue décrit ci-dessous ne change pas le fonctionnement général des suspensions et reste dans le cadre de cette invention.  A limited angle to these directions due to design constraints as described below does not change the overall operation of the suspensions and remains within the scope of this invention.
En référence à la figure 1 , on observe une partie d'un ensemble propulsif 1 pour aéronef selon un premier mode de réalisation de l'invention.  With reference to FIG. 1, part of a propulsion unit 1 for an aircraft is observed according to a first embodiment of the invention.
De façon générale, cet ensemble propulsif 1 d'aéronef est formé notamment par une nacelle (non représentée), un turboréacteur 2, un pylône 10 et un ensemble de suspension 100 assurant la fixation du turboréacteur 2 sous ce pylône 10. Cet ensemble propulsif 1 d'aéronef est destiné à être suspendu à une structure fixe de l'aéronef (non représentée), par exemple sous une aile ou sur le fuselage, par l'intermédiaire du pylône 10. In general, this propulsion unit 1 of aircraft is formed in particular by a nacelle (not shown), a turbojet 2, a pylon 10 and a suspension assembly 100 ensuring the attachment of the turbojet engine 2 under this pylon 10. This aircraft propulsion unit 1 is intended to be suspended from a fixed structure of the aircraft (not shown), for example under a wing or on the fuselage, by means of the pylon 10.
Concernant le pylône 10, il prend la forme d'une structure rigide 1 1 longitudinale et, plus particulièrement, d'une structure comprenant un caisson 12 rigide capable de transmettre le torseur d'efforts entre le turboréacteur 2 et la structure de l'aéronef.  Concerning the pylon 10, it takes the form of a rigid longitudinal structure 1 1 and, more particularly, of a structure comprising a rigid box 12 capable of transmitting the torsor of forces between the turbojet engine 2 and the structure of the aircraft .
Ce caisson 12 s'étend sensiblement selon la direction X.  This box 12 extends substantially in the direction X.
Il est formé de longerons supérieur et inférieur 1 3, reliés entre eux par des panneaux latéraux.  It is formed of upper and lower rails 1 3, interconnected by side panels.
Le pylône 10 est connu de l'homme du métier et ne sera pas détaillé plus en détails par la suite.  The tower 10 is known to those skilled in the art and will not be detailed in more detail later.
La figure 1 1 décrit l'environnement du turboréacteur 2, à titre d'exemple non limitatif pour l'invention.  Figure 1 1 describes the environment of the turbojet 2, by way of non-limiting example for the invention.
Le turboréacteur 2 comprend une soufflante 42 dél ivrant u n fl ux annulaire avec un flux primaire qu i al imente le turboréacteur 2 entraînant la soufflante 42 et un flux secondaire 38 qui est éjecté dans l'atmosphère tout en fournissant une fraction importante de la poussée de l'aéronef.  The turbojet engine 2 comprises a blower 42 delivering an annular flow with a primary flow that imputes the turbojet engine 2 driving the fan 42 and a secondary flow 38 that is ejected into the atmosphere while providing a significant fraction of the engine thrust. the aircraft.
La soufflante 42 est contenue, comme on peut voir sur la figure 1 , dans un carter de soufflante 34 qui canalise vers l'aval le flux secondaire 38.  The fan 42 is contained, as can be seen in FIG. 1, in a fan casing 34 which channels downstream the secondary flow 38.
Ce carter 34 définit une partie de paroi interne de la nacelle et présente sensiblement la forme d'une virole annulaire.  This housing 34 defines an inner wall portion of the nacelle and has substantially the shape of an annular shell.
Comme cela est connu en soi, ce carter de soufflante 34 est adapté pour entourer la soufflante 42 de turboréacteur 2 composée essentiellement d'un arbre rotatif et d'une pluralité d'aubes de soufflante.  As is known per se, this fan casing 34 is adapted to surround the blower 42 of turbojet engine 2 essentially consisting of a rotary shaft and a plurality of fan blades.
Le carter 34 peut porter une pluralité d'aubes de redressement 33 de flux permettant de red resser le flux d'a ir secondaire 38 engendré par la soufflante.  The casing 34 may carry a plurality of flow rectification vanes 33 for redrawing the flow of secondary air 38 generated by the blower.
La soufflante 42 est montée rotative sur un moyeu 43 fixe pouvant être relié au carter de soufflante 34 par une pluralité de bras 32 fixes situés en aval des aubes 33 ou directement par ces aubes 33. Dans cette seconde configuration, les aubes de redressement 33 font office de transmission des efforts en complément ou à la place des bras de liaison 32. The blower 42 is rotatably mounted on a fixed hub 43 which can be connected to the fan casing 34 by a plurality of fixed arms 32 situated downstream of the blades 33 or directly by these blades 33. In this second configuration, the straightening vanes 33 act as force transmission in addition to or instead of the link arms 32.
Elles peuvent ainsi être placées dans le carter intermédiaire 30 au lieu du carter de soufflante 34.  They can thus be placed in the intermediate casing 30 instead of the fan casing 34.
Le carter de soufflante 34 est rel ié à son extrém ité aval à un carter intermédiaire 30 appartenant à la section médiane de la nacelle.  The fan casing 34 is connected at its downstream end to an intermediate casing 30 belonging to the median section of the nacelle.
Le fl ux d 'a i r secondaire 38 engend ré par la soufflante traverse également la roue formée par le carter intermédiaire 30.  The flow of secondary air 38 generated by the blower also passes through the wheel formed by the intermediate casing 30.
Le carter intermédiaire 30 est un élément structural qui comprend le moyeu 43, une virole externe annulaire 31 et éventuellement, les bras de liaison radiaux 32 et les redresseurs 33 de flux qui relient le moyeu 43 à la virole externe 31 .  The intermediate casing 30 is a structural element which comprises the hub 43, an annular outer shell 31 and optionally, the radial link arms 32 and the flow rectifiers 33 which connect the hub 43 to the outer shell 31.
Ce carter 30 peut être réalisé en plusieurs parties ou non.  This housing 30 may be made of several parts or not.
En aval de ce carter intermédiaire 30, la veine de flux secondaire 38 est délimitée intérieurement par les parois externe 40 et interne 39 de l'éventuel inverseur de poussée.  Downstream of this intermediate casing 30, the secondary flow stream 38 is delimited internally by the outer 40 and inner 39 walls of the possible thrust reverser.
La paroi interne 39 entoure une enveloppe cylindrique nommée carter central 35 qui entoure le corps du turboréacteur 2 et qu i s'étend depuis le moyeu 43 du carter intermédiaire 30 jusqu'à un carter d'échappement 37 situé en sortie de la turbine.  The inner wall 39 surrounds a cylindrical shell called central casing 35 which surrounds the body of the turbojet engine 2 and extends from the hub 43 of the intermediate casing 30 to an exhaust casing 37 located at the outlet of the turbine.
Les différents carters peuvent être solidaires les uns des autres.  The different housings can be integral with each other.
Concernant l'ensemble de suspension 1 00, il permet de transmettre à l'aéronef les efforts mécaniques du turboréacteur 2 et les efforts en provenance de la nacelle transmis par le turboréacteur 2 pendant ses différents régimes de fonctionnement.  As regards the suspension assembly 1 00, it makes it possible to transmit to the aircraft the mechanical forces of the turbojet engine 2 and the forces coming from the nacelle transmitted by the turbojet engine 2 during its various operating modes.
Les charges à prendre en considération sont orientées selon les trois directions principales (forces et moments).  The loads to be considered are oriented along the three main directions (forces and moments).
Ce sont, notamment, des charges inertielles du turboréacteur 2, engendrées par la rotation des éléments tournants de ce turboréacteur, la poussée de ce dernier, des charges aérodynamiques ou encore la reprise d'un couple autour de l'axe X du turboréacteur 2. Selon l'invention, dans un premier mode de réalisation illustré sur les figures 1 à 8, l'ensemble de suspension 100 comprend un dispositif de reprise des efforts de poussée 1 10 du turboréacteur 2 monté, en amont, sur le carter intermédiaire 30 ou sur l'avant du carter central 35 et, en aval, sur le pylône 10. These are, in particular, inertial loads of the turbojet 2, generated by the rotation of the rotating elements of this turbojet, the thrust of the latter, aerodynamic loads or the recovery of a torque around the axis X of the turbojet engine 2. According to the invention, in a first embodiment illustrated in FIGS. 1 to 8, the suspension assembly 100 comprises a device for taking up the thrust forces 1 10 of the turbojet engine 2 mounted, upstream, on the intermediate casing 30 or on the front of the central casing 35 and, downstream, on the pylon 10.
L'ensemble de suspension comprend également des attaches de suspension amont montées sur la virole 31 externe du carter intermédiaire 30 et/ ou sur le carter de soufflante 34 :  The suspension assembly also comprises upstream suspension fasteners mounted on the outer shell 31 of the intermediate casing 30 and / or on the fan casing 34:
Ces attaches de suspension amont sont les suivantes :  These upstream suspension clips are as follows:
- une attache de suspension amont 130 principale, configurée de manière à reprendre notamment le moment Mx selon l'axe longitudinal du tu rboréacteu r a insi q ue les efforts Fy et Fz su ivant respectivement l es directions transverse et verticale, et  a main upstream suspension fastener 130, configured in such a way as to take in particular the moment Mx along the longitudinal axis of the rboreactor, insinuating the forces Fy and Fz following respectively the transverse and vertical directions, and
- au moins une paire 1 20, 140 d'attaches de suspension 120a, 120b, 140a, 140b amont complémentaires distinctes de l'attache de suspension 130 principale et configurée de manière à reprendre notamment un moment Mz selon l'axe vertical du turboréacteur et, associé au d ispositif de reprise de poussée 1 10, un moment My selon l'axe transversal du turboréacteur et l'effort FX suivant l'axe du turboréacteur.  at least one pair 1 20, 140 of suspension fasteners 120a, 120b, 140a, 140b complementary to the main suspension attachment 130 main suspension and configured to include a particular moment Mz along the vertical axis of the turbojet and associated with the thrust recovery device 1 10, a moment My along the transverse axis of the turbojet and the force FX along the axis of the turbojet engine.
Concernant le dispositif de reprise d'efforts de poussée 1 10, ce dernier est décrit en relation avec les figures 1 et 3 à 5.  With regard to the thrust force recovery device 1 10, the latter is described in relation to FIGS. 1 and 3 to 5.
Le dispositif 1 10 de reprise d'efforts de poussée est associé à la paire 120, 140 d'attaches de suspension 120a, 1 20b, 140a, 140b amont pour reprendre le moment My et les efforts Fx selon l'axe longitudinal .  The device 1 10 of thrust force recovery is associated with the pair 120, 140 suspension fasteners 120a, 1 20b, 140a, 140b upstream to resume the moment My and Fx efforts along the longitudinal axis.
Ce dispositif 1 1 0 de reprise d'efforts de poussée comprend deux bielles 1 1 1 , 1 12 de reprise d'efforts disposées de part et d'autre de l'axe du plan médian XZ du turboréacteur de façon symétrique.  This device 1 1 0 of thrust force recovery comprises two connecting rods 1 1 1, 1 12 of force recovery disposed on either side of the axis of the median plane XZ of the turbojet engine symmetrically.
Ces bielles sont montées, à leur extrémité amont, via des points d'ancrage sur la partie centrale du carter intermédiaire 30 et à leur extrémité aval par l'intermédiaire d'un palonnier 1 13 sur la face inférieure du longeron inférieur 13.  These connecting rods are mounted, at their upstream end, via anchoring points on the central part of the intermediate casing 30 and at their downstream end by means of a spreader 1 13 on the lower face of the lower spar 13.
Ces deux bielles latérales 1 1 1 , 1 12 sont articulées chacune, à leur extrémité aval, sur le palonnier 1 13 par exemple par des axes rotulés. Chaque bielle peut être munie de chapes, notamment deux, pour coopérer avec une chape ménagée sur le palonnier 1 13 ou inversement. These two lateral rods 1 1 1, 1 12 are articulated each, at their downstream end, on the spreader 1 13 for example by pins rotated. Each rod can be provided with yokes, in particular two, to cooperate with a yoke formed on the rudder 1 13 or vice versa.
Ce palonnier 1 13 est lui-même monté pivotant par rapport à un support d'accrochage 1 14 selon un axe parallèle aux liaisons axiales des bielles 1 1 1 , 1 12 avec ledit palonnier 1 13 (voir figure 4).  This lifter 1 13 itself is pivotally mounted relative to a hooking support 1 14 along an axis parallel to the axial links of the connecting rods 1 1 1, 1 12 with said lifter 1 13 (see Figure 4).
Plus précisément, le palonnier 1 13 comprend à ses deux extrém ités opposées l ibres, deux chapes d'accrochage parallèles 1 15 adaptées pour former avec une chape 1 1 6 de raccordement du support 1 14 assurant la redondance des chemins d'effort.  More specifically, the lifter 1 13 comprises at its two opposite extremes l ibres, two parallel attachment screeds 1 15 adapted to form with a yoke 1 1 6 connecting the support 1 14 ensuring the redundancy of stress paths.
Le palonnier 1 1 3 peut lui-même être muni d'une chape pour coopérer avec deux chapes ménagées sur le support 1 14 d'accrochage.  The rudder 1 1 3 may itself be provided with a yoke to cooperate with two yokes formed on the support 1 14 hooking.
Par ailleurs, le support d'accrochage 1 14 est fixé de façon solidaire au longeron inférieur 13 du caisson 12 du mât 10 grâce à plusieurs liaisons 1 17 axiales et éventuellement à des pions de cisaillement selon Z.  Moreover, the hooking support 1 14 is fixedly secured to the lower beam 13 of the box 12 of the mast 10 by means of several axial links 17 and possibly to shear pins according to Z.
Dans un tel d ispositif de reprise d'efforts de poussée 1 10, toute attache solidaire de l'arrière du carter central 35 du turboréacteur et/ou du carter d'échappement 37 est avantageusement supprimée.  In such a device for taking up thrust forces 1 10, any fastener secured to the rear of the central casing 35 of the turbojet engine and / or the exhaust casing 37 is advantageously eliminated.
Ce dispositif de reprise d'efforts de poussée 1 10 peut être conçu afin d'assurer la redondance, dans un exemple non limitatif, en le doublant.  This thrust force recovery device 1 10 may be designed to provide redundancy, in a non-limiting example, by doubling it.
Pour reprendre le moment My autour de l'axe transversal, les deux paires d'attaches de suspension amont 120, 140 complémentaires, associées au dispositif de reprise de poussée 1 1 0, sont configurées pour reprendre des efforts axiaux Fx dont les points d'application sont décalés selon la direction verticale Z du turboréacteur 2.  To take up the moment My around the transverse axis, the two pairs of upstream suspension fasteners 120, 140 complementary, associated with the thrust recovery device 1 1 0, are configured to take axial forces Fx whose points d ' application are offset in the vertical direction Z of the turbojet 2.
Pour reprendre le moment Mz autour de l'axe vertical, les deux pa ires d 'attaches de suspension amont 120, 140 complémentaires sont config u rées pou r reprend re d es efforts axiaux Fx selon la d i rection approximativement longitudinale, dont les points d'appl ication sont décalés suivant la direction Y.  To take up the moment Mz around the vertical axis, the two complementary upstream suspension straps 120, 140 are configured to take up axial forces Fx according to the approximately longitudinal direction, the points of which application are shifted in Y direction.
La composante de l'effort dans les deux pa ires d 'attaches de suspension amont 120, 140, hors de la direction longitudinale X, est reprise par l'attache de suspension amont 130 principale décrite plus loin. La présence de deux bielles 120a , 1 20b et 1 40a , 1 40b pour chacune des attaches de suspension amont 120, 140 permet de rendre ces attaches redondantes. La perte d'une partie des attaches ne conduit de la sorte pas à la rupture du chemin d'effort. The component of the force in the two regions of upstream suspension fasteners 120, 140, out of the longitudinal direction X, is taken up by the main upstream suspension fastener 130 described later. The presence of two rods 120a, 1 20b and 1 40a, 1 40b for each of the upstream suspension clips 120, 140 makes these redundant fasteners. The loss of some of the fasteners does not lead to breaking the stress path.
En référence plus particulièrement aux figures 1 et 2, la première paire 120 d'attaches de suspension amont comprend deux bielles 120a, 120b, et l a deuxième pa ire 1 40 d e prem ières attaches de suspens ion amont comprend deux autres bielles 140a, 140b.  Referring more particularly to FIGS. 1 and 2, the first pair 120 of upstream suspension fasteners comprise two connecting rods 120a, 120b, and the second pair of first 40 upstream suspension fasteners comprises two further links 140a, 140b.
Ces quatre bielles sont montées sur la périphérie externe de la virole externe 31 du carter intermédiaire 30, à l'extrémité aval de cette virole 31 .  These four rods are mounted on the outer periphery of the outer shell 31 of the intermediate casing 30, at the downstream end of this shell 31.
Ces deux paires d'attaches 120, 140 sont montées symétriques deux à deux par rapport au plan médian XZ, défini par l'axe X et l'axe Z du turboréacteur.  These two pairs of fasteners 120, 140 are mounted symmetrically two by two with respect to the median plane XZ, defined by the axis X and the axis Z of the turbojet engine.
Ces attaches amont 120, 140 s'étendent dans un plan XZ, et sont reliées à une extrémité amont à l'amont du caisson 12 du pylône 10.  These upstream fasteners 120, 140 extend in an XZ plane, and are connected to an upstream end upstream of the caisson 12 of the tower 10.
Elles son décalées selon Y.  They are offset according to Y.
Il est à noter que les paires des premières attaches de supension amont complémentaires 1 20, 140 peuvent être les suivantes : une bielle de chacune des première et seconde paire des premières attaches de suspension amont, à savoir 120a,140a ;120a,140b ;120b,140a ;120b,140b.  It should be noted that the pairs of the first complementary upstream supension clamps 1 20, 140 may be the following: a connecting rod of each of the first and second pair of first upstream suspension fasteners, namely 120a, 140a, 120a, 140b, 120b; , 140a, 120b, 140b.
Ces paires d'attaches amont 1 20, 1 40 sont montées de part et d'autre de l'attache de suspension amont 130 principale.  These pairs of upstream fasteners 1 20, 1 40 are mounted on either side of the main upstream suspension fastener 130.
Les attaches de suspension amont 120, 130, 140 sont ainsi regroupées sur la partie supérieure de la périphérie externe de la virole externe 31 du carter intermédiaire 30.  The upstream suspension clips 120, 130, 140 are thus grouped on the upper part of the outer periphery of the outer shell 31 of the intermediate casing 30.
Comme illustré sur la figure 2 plus particulièrement, chaque paire d'attaches de suspension amont 1 20, 140 complémentaires est montée à chaque extrémité latérale du caisson 12 du mât 10, de part et d'autre de l'attache de suspension amont 130 principale. Les d eux pa i res d'attache d e suspens ion amont 1 20 , 140 complémentaires sont ainsi décalées selon Y, en partant de leur extrémité latérale périphérique, typiquement de la largeur du caisson 12 du mât 10. As illustrated in FIG. 2 more particularly, each pair of complementary upstream suspension fasteners 1, 20, 140 are mounted at each lateral end of the casing 12 of the mast 10, on either side of the main upstream suspension clip 130. . The complementary upstream suspension attachment strips 1, 20, 140 are thus offset along Y, starting from their peripheral lateral end, typically from the width of the box 12 of the mast 10.
Comme cela est visible aux figures 2 et 6 à 8, les deux paires 120, 140 de bielles 120a, 120b d'une part et 140a, 140b d'autre part, sont reliées à une extrémité amont, grâce à un palonnier 1 50 à un support de fixation 1 62 solidaire du longeron 13 inférieur du caisson 12 du mât 10 et à une extrémité ava l à l a vi rol e extern e 31 d u ca rter i nterm éd ia i re 30 via un support d'accrochage 160.  As can be seen in FIGS. 2 and 6 to 8, the two pairs 120, 140 of connecting rods 120a, 120b on the one hand and 140a, 140b on the other hand, are connected to an upstream end by means of a rudder 1 50 to an attachment support 1 62 secured to the lower beam 13 of the casing 12 of the mast 10 and at one end to the outer wall 31 of the cross section 30 via a hooking support 160.
Comme illustré sur les figures 7 et 8, le support d'accrochage 160 est monté su r la périphérie de la virole externe 31 par l 'interméd iaire de moyens de fixation adaptés.  As illustrated in FIGS. 7 and 8, the hooking support 160 is mounted on the periphery of the outer shell 31 by means of suitable fastening means.
Il peut notamment être formé d'un seul tenant avec la virole externe 31 du carter 30.  It can in particular be formed in one piece with the outer shell 31 of the housing 30.
II peut également être dédoublé de façon à avoir u ne ou deux chapes par bielle 120, 140 afin d'améliorer la redondance de l'attache.  It can also be split so as to have one or two yokes per rod 120, 140 to improve the redundancy of the fastener.
Ce support d'accrochage 1 60 comprend deux paires de chapes d'accrochage 161 parallèles au plan XZ , espacés selon Y et destinées à coopérer avec un élément constitutif de l'attache correspondante et, plus particulièrement avec l'extrémité aval de la bielle d'accrochage 120a, 120b, 140a, 140b correspondante.  This attachment support 1 60 comprises two pairs of attachment shackles 161 parallel to the XZ plane, spaced along Y and intended to cooperate with a constituent element of the corresponding fastener and, more particularly with the downstream end of the connecting rod. 120a, 120b, 140a, 140b corresponding snap.
En variante, le support 160 peut être muni d'une chape par bielle pour coopérer avec deux chapes ménagées sur la bielle correspondante.  Alternatively, the support 160 may be provided with a clevis rod to cooperate with two clevises on the corresponding rod.
Ce support d'accrochage 160 est coudé de manière à présenter les deux paires de chapes 161 en saillie vers l'extérieur de la périphérie de la virole 31 externe s'étendant selon Z et à la même altitude Z.  This hooking support 160 is bent to present the two pairs of yokes 161 projecting outwardly from the periphery of the outer shell 31 extending along Z and at the same altitude Z.
Dans chacune de ces chapes 161 est ménagé un œillet 164 adapté pour recevoir des moyens de liaison (non illustrés) destinés à relier la chape 160 et la bielle 120a, 120b, 140a, 140b correspondante.  In each of these screeds 161 is formed an eyelet 164 adapted to receive connecting means (not shown) for connecting the yoke 160 and the connecting rod 120a, 120b, 140a, 140b corresponding.
Ces oeillets 162 sont ménagés en regard d'œillets ménagés sur les extrémités des bielles d'accrochage 120a, 120b, 140a, 140b correspondantes. La ou les chapes du support d'accrochage 160 et chaque bielle 120a, 120b, 140a, 140b peuvent être reliés, par exemple, par des axes rotulés adaptés. These eyelets 162 are arranged opposite eyelets formed on the ends of the connecting rods 120a, 120b, 140a, 140b corresponding. The one or more clevises of the hooking support 160 and each connecting rod 120a, 120b, 140a, 140b can be connected, for example, by suitable pivoted shafts.
Par ailleurs, ces bielles 120a, 1 20b, 140a, 140b d'accrochage sont articulées, à leur extrémité amont, sur le palonnier 150 par une liaison rotulée.  Moreover, these rods 120a, 1 20b, 140a, 140b of attachment are hinged, at their upstream end, on the spreader 150 by a rotated connection.
Le palonnier 150 est, quant à lui, monté sur l'extrémité amont du longeron inférieur 13 du caisson 12 par l'intermédiaire du support de fixation 162.  The rudder 150 is, in turn, mounted on the upstream end of the lower spar 13 of the box 12 by means of the attachment support 162.
Il est monté pivotant par rapport à ce support 1 62 selon son axe central perpendiculaire au plan des deux bielles 120a, 120b, 140a, 140b...  It is pivotally mounted relative to this support 1 62 along its central axis perpendicular to the plane of the two connecting rods 120a, 120b, 140a, 140b ...
Le palonnier 1 50 est muni d'un système de limitation de rotation autour de son axe central par exemple par des axes ou des pions montés avec jeu entre le palonnier 150 et des pattes externes 163 du support de fixation 162.  The rudder 1 50 is provided with a system for limiting rotation about its central axis, for example by pins or pins mounted with clearance between the rudder 150 and external tabs 163 of the attachment support 162.
Par ailleurs, le support de fixation 162 est fixé de façon solidaire à l'extrémité amont du longeron inférieur 1 3 du caisson 1 2 du mat 1 0 grâce à plusieurs liaisons axiales selon Z (par exemple : vis, pions, ...).  Furthermore, the fixing support 162 is secured to the upstream end of the lower beam 1 3 of the box 1 2 of the mat 1 0 through several axial links according to Z (for example: screws, pins, ...) .
L'ensemble des bielles 1 20a, 1 20b, 140a, 140b, associées à leur système d'accrochage (palonnier 150, support d'accrochage 160 et de fixation 162) est conçu de manière à être redondant. La perte d'un élément quelconque du chemin d'effort ne conduit pas à la perte totale de ce chemin d'effort.  All rods 1 20a, 1 20b, 140a, 140b, associated with their attachment system (rudder 150, hooking bracket 160 and attachment 162) is designed to be redundant. The loss of any element of the stress path does not lead to the total loss of this stress path.
D'autres principes pour obtenir la redondance du chemin d'effort sont envisageables sans sortir du cadre de cette invention tel que par exemple une bielle montée sans jeu et une bielle montée avec jeu pour que cette bielle avec jeu ne soit active que si le chemin d'effort de l'autre bielle est rompu.  Other principles for obtaining the redundancy of the effort path are conceivable without departing from the scope of this invention such as for example a rod mounted without clearance and a rod mounted with clearance so that this rod with play is active only if the path of the other connecting rod is broken.
Les paires 1 20, 140 d'attaches de suspension 120a, 120b, 140a, 140b amont complémentaires peuvent également être dirigées vers l'amont du pylône 10 ou vers l'aval du pylône 10 pour tous les modes de réalisation décrits.  The pairs 1 20, 140 of complementary suspension fasteners 120a, 120b, 140a, 140b upstream may also be directed upstream of the tower 10 or downstream of the tower 10 for all the embodiments described.
Pou r reprend re l e mom ent Mx selon l'axe longitudinal du turboréacteur, l'attache de suspension amont 130 principale est fixée sur la virole externe 31 du carter intermédiaire 30. Cette attache de suspension amont 1 30 principale est configurée pour reprendre, en plus du moment Mx, les efforts transversaux Fy et verticaux Fz. To recover the moment Mx along the longitudinal axis of the turbojet, the main upstream suspension clip 130 is fixed on the outer ring 31 of the intermediate casing 30. This upstream main suspension clip 1 is configured to resume, in addition to the moment Mx, transverse forces Fy and vertical Fz.
On peut observer un exemple de réalisation de cette attache sur la figure 2 notamment.  One example of embodiment of this fastener can be observed in FIG. 2 in particular.
Cette attache 130 se présente comme une ferrure 131 comprenant deux demi-attaches symétriques par rapport au plan médian XYYZ.  This fastener 130 is a fitting 131 comprising two half-fasteners symmetrical with respect to the median plane XYYZ.
Cette ferrure 1 31 est reliée à ses deux extrémités latérales à deux chapes d'accrochage C 1 , C2 solidaires de la virole externe 31 du carter intermédiaire 30 sur lesquelles sont articulées respectivement des manilles 36 à deux ou trois points.  This fitting 1 31 is connected at its two lateral ends to two attachment lugs C 1, C 2 integral with the outer shell 31 of the intermediate casing 30 on which hinges 36 are respectively hinged at two or three points.
Elle est également reliée à une chape d'accrochage C3 solidaire de la virole externe 31 du carter intermédiaire 30 en son centre qui fait office de chemin d'effort redondant en cas par exemple de rupture d'une des manilles 36.  It is also connected to an attachment screed C3 integral with the outer shell 31 of the intermediate casing 30 at its center which serves as a redundant effort path in the event, for example, of breaking one of the shackles 36.
Les moyens de fixation des chapes C1 , C2, C3 peuvent être tout moyen de fixation adaptés et, notamment des vis et des pions de cisaillement. Les moyens de fixation des manilles 36 peuvent être tout moyen de fixation adaptés et, notamment des axes rotulés.  The fixing means of the clevises C1, C2, C3 can be any suitable fastening means and, in particular screws and shear pins. The shackle fixing means 36 may be any suitable fixing means and, in particular, rotated shafts.
Par ailleurs, la ferrure 131 est également fixée au longeron inférieur Furthermore, the fitting 131 is also attached to the lower spar
1 3 par des moyens de fixation adaptés, pouvant comprendre, de façon non limitative, des moyens de vissage formant une l iaison axiale suivant Z et des pions. 1 3 by suitable fastening means, which may include, but not limited to, screwing means forming an axial lnaison Z and pions.
Il est à noter que les manilles 36 peuvent être du type « fail-safe » tout comme les pions de cisaillement, les chapes C1 , C2, C3 et/ ou les moyens de vissage.  It should be noted that the shackles 36 may be of the "fail-safe" type as well as the shear pins, the clevises C1, C2, C3 and / or the screwing means.
D'autres ensembles propulsifs d'aéronef 1 peuvent être envisagés sans sortir du cadre de la présente invention. Other aircraft propulsion units 1 can be envisaged without departing from the scope of the present invention.
Ainsi, dans une variante de réalisation illustrée sur les figures 9 et Thus, in an embodiment variant illustrated in FIGS.
10, on peut prévoir de reprendre le moment Mz par une paire d'attaches de suspension amont 200 distinctes de l'attache de suspension 130 et configurée de manière à reprendre en association avec ladite attache de suspension 130 principale, un moment Mz selon l'axe vertical du turboréacteur. 10, it is possible to take the moment Mz back by a pair of upstream suspension clips 200 separate from the suspension clip 130 and configured so as to resume in association with said main suspension link 130, a moment Mz along the vertical axis of the turbojet engine.
La paire d'attaches de suspension amont 200 est configurée pour reprendre des efforts Fy associé avec la reprise d'effort Fy selon Y de l'attache de suspension principale 130.  The pair of upstream suspension brackets 200 is configured to take up Fy forces associated with the recovery of force Fy according to Y of the main suspension fastener 130.
Ces efforts Fy ont des points d'application décalés suivant la direction X.  These efforts Fy have application points offset in direction X.
On décale, en outre, l'attache de suspension amont 130 principale reprenant le moment Mx vers l'amont de la virole externe 31 du carter intermédiaire 30.  In addition, the main upstream suspension clip 130 is displaced, taking up the moment Mx upstream of the outer shell 31 of the intermediate casing 30.
Dans une autre variante de réalisation, on réalise l'inverse, à savoir on prévoit une attache de suspension amont configurée pour reprendre un effort suivant l'axe Y à l'extrémité amont de la virole 31 et on décale plus en aval l'attache de suspension amont 130.  In another variant embodiment, the reverse is carried out, namely an upstream suspension fastener configured to take up a force along the Y axis at the upstream end of ferrule 31 is provided, and the attachment is further moved downstream. suspension upstream 130.
Plus précisément, les deux attaches de suspension 200a, 200b sont symétriques par rapport au plan médian XZ et décalées selon Y.  More specifically, the two suspension clips 200a, 200b are symmetrical with respect to the median plane XZ and offset along Y.
Ces deux attaches de suspension 200a, 200b s'étendent dans un plan YZ, reliées à une extrémité à l'amont du caisson 12 du pylône 10 et à une extrémité opposée à la périphérie externe de la virole externe 31 du carter intermédiaire 30 ou du carter de soufflante 34.  These two suspension fasteners 200a, 200b extend in a plane YZ, connected at one end upstream of the box 12 of the pylon 10 and at an end opposite to the outer periphery of the outer shell 31 of the intermediate casing 30 or the blower housing 34.
U ne de ces deux attaches de suspension 200a , 200b est un chemin en attente, monté par exemple avec du jeu, au cas où l'autre attache de suspension 200a, 200b casse.  One of these two suspension fasteners 200a, 200b is a waiting path, mounted for example with play, in case the other suspension fastener 200a, 200b breaks.
Tout autre système redondant, tel que par exemple une bielle double entre dans le cadre de cette invention, les deux attaches 200a, 200b étant un exemple de réal isation de la fonction de redondance lié au principe des attaches de suspension amont 200.  Any other redundant system, such as for example a double rod is within the scope of this invention, the two fasteners 200a, 200b being an example of real isation of the redundancy function related to the principle of upstream suspension fasteners 200.
Une seule attache de suspension 200a sera décrite en relation avec ces figures.  A single suspension clip 200a will be described in connection with these figures.
Elle comprend une bielle 201 a d'accrochage s'étendant dans un plan YZ et fixée à une extrémité respectivement à un support d'accrochage 202a solidaire de la virole 31 externe du carter intermédiaire 30 ou du carter de soufflante 34, et à l 'extrém ité opposée à un support d'accrochage 203a solidaire du longeron 13 inférieur du pylône 10. Chaque support d'accrochage 202a, 203a comprend deux chapes parallèles destinées à coopérer avec une chape ménagée à l'extrémité de la bielle 201 a de l'attache de suspension 200a correspondante. It comprises a connecting rod 201 has hooking extending in a YZ plane and fixed at one end respectively to a hooking support 202a integral with the outer ring 31 of the intermediate casing 30 or the fan casing 34, and to opposite end to a hooking support 203a secured to the lower beam 13 of the pylon 10. Each hooking support 202a, 203a comprises two parallel yokes intended to cooperate with a yoke formed at the end of the connecting rod 201a of the corresponding suspension clip 200a.
A chaque extrémité de bielle 201 a, les trois chapes sont reliées entre elles, par exemple par un axe rotulé adapté.  At each connecting rod end 201a, the three clevises are interconnected, for example by a suitable rotated pin.
A noter qu'il est également possible d'avoir deux chapes parallèles sur chaque bielle 201 a et une chape sur chaque support d'accrochage 202a, 203a correspondant.  Note that it is also possible to have two parallel clevises on each connecting rod 201a and a clevis on each hooking bracket 202a, 203a corresponding.
Dans cette variante de réalisation, il n'y a plus qu'une seule paire 121 a, 121 b de premières attaches de suspension amont 1 20 placée dans le plan XZ.  In this variant embodiment, there is only one pair 121a, 121b of first upstream suspension clips 1 20 placed in the XZ plane.
Cette paire attaches 1 20 est ménagée entre les deux attaches This pair of fasteners 1 20 is formed between the two fasteners
200a, 200b. 200a, 200b.
Cette paire attaches 1 20 est similaire à celle décrite en lien avec les autres modes de réalisation et ne sera pas décrite en détail par la suite.  This pair fasteners 1 20 is similar to that described in connection with the other embodiments and will not be described in detail later.
Ainsi, dans cette variante de réalisation, les paires d'attaches de suspension amont complémentaires configurées de manière à reprendre au moins un moment Mz selon l'axe vertical du turboréacteur et, associée au dispositif de reprise des efforts de poussée 1 1 0, un moment My selon l'axe transversal du turboréacteur et des efforts Fx selon l'axe longitudinal du turboréacteur peuvent être les suivantes :  Thus, in this variant embodiment, the pairs of complementary upstream suspension fasteners configured so as to take up at least one moment Mz along the vertical axis of the turbojet engine and, associated with the device for taking up the thrust forces 1 1 0, a moment My along the transverse axis of the turbojet engine and Fx forces along the longitudinal axis of the turbojet engine may be the following:
- une bielle de la première paire des premières attaches de suspension amont, à savoir 1 21 a ou 121 b et l'attache de suspension amont 200a, 200b configurée pour reprendre un effort suivant l'axe Y, à savoir les paires 1 21 a,200a ou 121 b,200b ou 121 a, 200b ou 1 21 b , a connecting rod of the first pair of first upstream suspension fasteners, namely 1 21 a or 121 b and the upstream suspension fastener 200 a, 200 b configured to take up a force along the Y axis, namely the pairs 1 21 a , 200a or 121b, 200b or 121a, 200b or 1b1b,
200a. 200a.
A titre de synthèse, les tableaux ci-dessous résument les forces et moments repris par chacun des moyens de l'ensemble de suspension selon l'invention (dispositif de reprise de poussée et attaches de suspension amont) : Premier mode de réalisation (figures 1 à 8) : As a summary, the tables below summarize the forces and moments taken up by each of the means of the suspension assembly according to the invention (thrust recovery device and upstream suspension fasteners): First embodiment (Figures 1 to 8):
Deuxième mode de réalisation (figures 9 et 10) : Second embodiment (FIGS. 9 and 10)
Concernant les différentes attaches de suspension, pour tous les modes de réalisation décrits, elles peuvent être réalisées selon toute forme connue de l'homme du métier, telle que par exemple celle relative à l'assemblage de manilles, de palonniers et de ferrures destinées à coopérer avec u n système d 'articu lation de type biel les, ou encore de p ion s de cisaillement. As regards the various suspension fasteners, for all the embodiments described, they may be made in any form known to those skilled in the art, such as, for example, that relating to the assembly of shackles, spreaders and fittings intended for to cooperate with a system of articulation of the biel type, or else of shearing ions.
Pour tous les modes de réalisation décrits, ces attaches de suspension peuvent, par a il leu rs, être m un ies de systèmes assurant la redondance de la transmission des efforts (forces et moments), par exemple, chem ins d'effort doublés, chemin d'effort en attente, axes « fail safe » en termes anglosaxons à savoir munies d'axes principaux de liaison logés dans des manchons concentriques assurant la transm ission de l'effort en cas de rupture de l'axe principal de liaison ou du manchon, ou autres.  For all the embodiments described, these suspension fasteners can, by themselves, be m unies of systems ensuring the redundancy of the transmission of forces (forces and moments), for example, doubled effort chem ins, standby effort path, "fail safe" axes in English terms, namely, provided with main connection axes housed in concentric sleeves ensuring the transmission of the force in the event of breakage of the main link axis or the sleeve, or others.
Quelle que soit la variante de réalisation, l'ensemble de suspension Whatever the variant embodiment, the suspension assembly
100 est généralement isostatique. Grâce à l'ensemble de suspension 10 selon la présente invention, on reprend l'ensemble des charges (forces et moments) sur un plan amont du turboréacteur 2. 100 is usually isostatic. Thanks to the suspension assembly 10 according to the present invention, all the loads (forces and moments) are taken up on an upstream plane of the turbojet engine 2.
Toute attache sur l'arrière du carter central du turboréacteur 2 ou sur le carter d'échappement est absente, ce qui diminue fortement les risques de déformation du turboréacteur 2 et notamment les flexions de ce dernier lors de ses différents régimes de fonctionnement.  Any attachment on the rear of the central casing of the turbojet 2 or on the exhaust casing is absent, which greatly reduces the risk of deformation of the turbojet 2 and in particular the bending of the latter during its different operating conditions.
Les contacts entre les pièces tournantes du turboréacteur 2 et les carters correspondants sont diminués, ce qui améliore la durée de vie du moteur.  The contacts between the rotating parts of the turbojet 2 and the corresponding housings are reduced, which improves the life of the engine.
De plus, le nombre d'attaches situées dans le canal de flux secondaire étant diminué, les pertubations dues à la présence de ces attaches dans ce canal sont elle mêmes diminuées, ce qui améliore les performances de l'ensemble propulsif.  In addition, the number of fasteners in the secondary flow channel being reduced, the disturbances due to the presence of these fasteners in this channel are themselves decreased, which improves the performance of the propulsion system.
Bien que l'invention ait été décrite avec un exemple particulier de réal isation, il est bien évident qu'elle n'y est nullement limitée et qu'elle comprend tous les équivalents techniques des moyens décrits ainsi que leurs combinaisons si celles-ci entrent dans le cadre de l'invention.  Although the invention has been described with a particular example of real isation, it is obvious that it is in no way limited and that it includes all the technical equivalents of the means described and their combinations if they enter in the context of the invention.

Claims

REVENDICATIONS
1 . Ensemble propulsif d'aéronef comprenant un turboréacteur (2), un support (10) assurant le transfert d'un torseur d'efforts vers l'aéronef depu is un ensemble de suspension ainsi qu'un ensemble de suspension interposé entre led it support (1 0) et le turboréacteur (2), l'ensemble de suspension comprenant un dispositif de reprise des efforts de poussée (1 10) du turboréacteur monté sur un carter intermédiaire (30) ou à l'avant d'un carter central (35) dudit turboréacteur et sur ledit support (10), 1. Aircraft propulsion assembly comprising a turbojet engine (2), a support (10) for transferring a torsor of forces to the aircraft from a suspension assembly and a suspension assembly interposed between it and the carrier ( 1 0) and the turbojet engine (2), the suspension assembly comprising a device for taking up the thrust forces (1 10) of the turbojet engine mounted on an intermediate casing (30) or in front of a central casing (35). ) of said turbojet and on said support (10),
caractérisé en ce que l'ensemble de suspension comprend, en outre, les attaches de suspension amont suivantes montées sur un carter de soufflante (34) et/ ou sur ledit carter intermédiaire (30) dudit turboréacteur :  characterized in that the suspension assembly further comprises the following upstream suspension fasteners mounted on a fan casing (34) and / or on said intermediate casing (30) of said turbojet engine:
- au moins une attache de suspension amont (130) principale, configurée de manière à reprendre au moins un moment (Mx) selon un axe longitudinal (X) du turboréacteur ainsi que les efforts (Fy et Fz) dans un plan perpendiculaire à l'axe longitudinal dudit turboréacteur, et  at least one main upstream suspension clip (130), configured so as to take up at least one moment (Mx) along a longitudinal axis (X) of the turbojet engine as well as the forces (Fy and Fz) in a plane perpendicular to the longitudinal axis of said turbojet, and
- au moins une paire (120, 140,121 , 200) d'attaches de suspension (1 20a, 1 20b, 140a, 140b, 1 21 a, 1 21 b, 200a, 200b) amont complémentaires distinctes de l'attache de suspension (130) principale et configurée de manière à reprendre au moins un moment (Mz) selon l'axe menant de l'axe longitudinal du turboréacteur à l'axe longitudinal du support et, associée à un dispositif de reprise d es efforts d e pou ssée ( 1 1 0) , u n mom ent (My) selon l 'axe perpendiculaire à l'axe longitudinal du turboréacteur et à l'axe menant de l'axe longitudinal du turboréacteur à l'axe longitudinal du support du turboréacteur et, des efforts (Fx) selon l'axe longitudinal du turboréacteur.  at least one pair (120, 140, 121, 200) of suspension fasteners (1 20a, 1bb, 140a, 140b, 121a, 121b, 200a, 200b) complementary upstream distinct from the suspension fastener ( 130) and configured to take up at least one moment (Mz) along the axis leading from the longitudinal axis of the turbojet engine to the longitudinal axis of the support and, associated with a device for resuming stresses ( 1 1 0), a mom ent (My) along the axis perpendicular to the longitudinal axis of the turbojet and the axis leading from the longitudinal axis of the turbojet engine to the longitudinal axis of the turbojet engine support and, efforts ( Fx) along the longitudinal axis of the turbojet engine.
2. Ensemble selon la revendication 1 caractérisé en ce que l'ensemble de suspension comprend des redondances des chemins d'effort au moyen de paires d'attaches de suspension, notamment dans le but d'assurer la reprise des chemins d'effort utile en cas de rupture du chemin d'effort principal. 2. The assembly of claim 1 characterized in that the suspension assembly comprises redundancies of the stress paths by means of pairs of suspension fasteners, in particular for the purpose of ensuring the recovery of the useful effort paths in case of rupture of the main effort path.
3. Ensemble selon l'une quelconque des revendications 1 ou 2 caractérisé en ce que l'ensemble de suspension est isostatique. 3. An assembly according to any one of claims 1 or 2 characterized in that the suspension assembly is isostatic.
4. Ensemble selon la revendication 1 caractérisé en ce que lad ite pa i re d'attaches de suspension amont ( 1 20a , 1 20b, 1 40a , 1 40b) complémentaire s'étend dans un plan défin i par l'axe long itud inal (X) du turboréacteur (2) et l'axe (Z) menant de l'axe longitudinal du turboréacteur à l'axe longitudinal du support (10), chaque attache étant reliée, à une extrémité amont, à l'amont du support (10) et, à une extrémité aval , à la périphérie externe d'une virole externe (31 ) du carter intermédiaire ou d u carter de soufflante (34). 4. An assembly according to claim 1 characterized in that lad ite Pa i re suspension fasteners upstream (1 20a, 1 20b, 1 40a, 1 40b) complementary extends in a plane defined i by the long axis itud inal (X) of the turbojet engine (2) and the axis (Z) leading from the longitudinal axis of the turbojet engine to the longitudinal axis of the support (10), each attachment being connected, at an upstream end, upstream of the support (10) and, at a downstream end, at the outer periphery of an outer shell (31) of the intermediate casing or the fan casing (34).
5. Ensemble selon la revendication 4 caractérisé en ce que lesdites paires d'attaches de suspension amont (1 20a, 1 20b, 1 40a, 140b) complémentaires so nt mo n tées s u r l a v i rol e exte rn e (31 ) d u carter intermédiaire (30) ou sur le carter de soufflante (34), symétriquement par rapport au plan médian défini par l'axe longitudinal (X) du turboréacteur (2) et par l'axe (Z) menant de l'axe longitudinal du turboréacteur à l'axe longitudinal du support (10). 5. An assembly according to claim 4 characterized in that said pairs of upstream suspension brackets (1 20a, 1 20b, 1 40a, 140b) are complemented by supernatural means (31) of the intermediate casing ( 30) or on the fan casing (34), symmetrically with respect to the median plane defined by the longitudinal axis (X) of the turbojet engine (2) and by the axis (Z) leading from the longitudinal axis of the turbojet engine to the longitudinal axis of the support (10).
6. Ensemble selon la revendication 5 caractérisé en ce que lesdites paires d'attaches de suspension amont complémentaires (120a, 120b, 140a, 140b) sont montées de part et d'autre de l'attache de suspension amont principale (130), cette dernière attache s'étendant dans un plan perpendiculaire à l'axe longitudinal (X) du turboréacteur (2). 6. The assembly of claim 5 characterized in that said pairs of complementary upstream suspension brackets (120a, 120b, 140a, 140b) are mounted on either side of the main upstream suspension clip (130), this last fastener extending in a plane perpendicular to the longitudinal axis (X) of the turbojet engine (2).
7. Ensemble selon la revendication 6 caractérisé en ce que lesdites paires d'attaches de suspension amont (1 20a, 1 20b, 1 40a, 140b) complémentaires sont configurées pour reprendre des efforts axiaux (Fx) dont les points d'application sont décalés selon la direction verticale (Z) menant de l'axe longitudinal du turboréacteur à l'axe longitudinal du support (10). 7. The assembly of claim 6 characterized in that said pairs of upstream suspension brackets (1 20a, 1 20b, 1 40a, 140b) complementary are configured to take axial forces (Fx) whose application points are offset in the vertical direction (Z) leading from the longitudinal axis of the turbojet to the longitudinal axis of the support (10).
8. Ensemble selon la revendication 6 caractérisé en ce que lesdites paires d'attaches de suspension amont (120a, 120b, 140a, 140b) complémentaires sont configurées pour reprendre des efforts axiaux (Fx) selon la direction longitudinale, dont les points d'application sont décalés suivant la direction (Y). 8. The assembly of claim 6 characterized in that said pairs of upstream suspension brackets (120a, 120b, 140a, 140b) complementary are configured to take axial forces (Fx) in the longitudinal direction, the points of application are shifted in the direction (Y).
9. Ensemble selon l'une des revendications 3 à 8 caractérisé en ce que chaque paire d'attaches de suspension amont complémentaire comprend deux bielles d'accrochage (120a, 120b, 140a, 140b) parallèles entre elles et s'étendant dans un plan défini par l'axe (Z) menant de l'axe longitudinal (X) du turboréacteur (2) à l'axe longitudinal du support et par l'axe longitudinal du turboréacteur, reliées à une extrémité amont, grâce à un palonnier (150), à un support de fixation solidaire du support (10) et, à une extrémité aval, au carter intermédiaire (30) ou au carter de soufflante (34) via un support d'accrochage (162). 9. Assembly according to one of claims 3 to 8 characterized in that each pair of complementary upstream suspension fasteners comprises two connecting rods (120a, 120b, 140a, 140b) parallel to each other and extending in a plane defined by the axis (Z) leading from the longitudinal axis (X) of the turbojet engine (2) to the longitudinal axis of the support and the longitudinal axis of the turbojet engine, connected to an upstream end, by means of a rudder (150 ), to a fastening support secured to the support (10) and, at a downstream end, to the intermediate casing (30) or to the fan casing (34) via a hooking support (162).
10. Ensemble selon l'une des revendications 1 à 2 caractérisé en ce que la paire (120, 140,121, 200) d'attaches de suspension (120a, 120b,10. Assembly according to one of claims 1 to 2 characterized in that the pair (120, 140, 121, 200) of suspension fasteners (120a, 120b,
140a, 140b, 121a, 121b, 200a, 200b) amont complémentaires comprend: 140a, 140b, 121a, 121b, 200a, 200b) complementary upstream comprises:
- une attache d'une paire d'attaches de suspension amont (121a, 121b) s'étendant dans un plan défini par l'axe longitudinal (X) du turboréacteur (2) et l'axe (Z) menant de l'axe longitudinal du turboréacteur à l'axe longitudinal du support (10), chaque attache étant reliée au support (10) et, à une extrémité aval, à la périphérie externe du carter intermédiaire ou du carter de soufflante (34) et, a clip of a pair of upstream suspension clips (121a, 121b) extending in a plane defined by the longitudinal axis (X) of the turbojet (2) and the axis (Z) leading from the axis longitudinal axis of the turbojet engine to the longitudinal axis of the support (10), each attachment being connected to the support (10) and, at a downstream end, to the outer periphery of the intermediate casing or of the fan casing (34) and,
- une attache (200a, 200b) configurée de manière à reprendre en association avec ladite attache de suspension (130) principale, le moment (Mz) selon l'axe (Z) menant de l'axe longitudinal (X) du turboréacteur (2) à l'axe longitudinal du support. a fastener (200a, 200b) configured so as to take up in association with said main suspension fastener (130), the moment (Mz) along the axis (Z) leading to the longitudinal axis (X) of the turbojet engine (2); ) to the longitudinal axis of the support.
1 1 . Ensemble selon la revendication 10 caractérisé en ce que lad ite attache (200a, 200b) s'étend dans u n plan perpend icu laire à l'axe longitudinal (X), permettant de reprendre des efforts (Fy) perpendiculaires à cet axe (X) et à l'axe (Z) menant de l'axe longitudinal (X) à l'axe longitudinal dudit support (10). 1 1. Assembly according to Claim 10, characterized in that the said tie (200a, 200b) extends in a plane perpendicular to the longitudinal axis (X), making it possible to take up forces (Fy) perpendicular to this axis (X) and to the axis (Z) leading from the longitudinal axis (X) to the longitudinal axis of said support (10).
12. Ensemble selon la revendication 1 1 caractérisé en ce que ladite attache (200a, 200b) comprend une bielle (201 a) d'accrochage s'étendant dans u n pl an YZ et fixée à u ne extrém ité respectivement à u n su pport d'accrochage (202a) sol idaire du carter interméd iaire (30) ou du carter de soufflante (34), et à l'extrémité opposée à un support d'accrochage (203a) solidaire du pylône (10). 12. The assembly of claim 1 1 characterized in that said fastener (200a, 200b) comprises a connecting rod (201 a) extending in a YZ pl y and fixed at u extremity respectively to a su pport d fastening (202a) sol idaire intermediate housing (30) or the fan casing (34), and the end opposite to a hooking bracket (203a) integral with the pylon (10).
13. Ensemble selon les revendications 2 et 10 à 12 caractérisé en ce q u e l'attache (200a,200b) configu rée de man ière à reprend re en association avec ladite attache de suspension (130) principale, le moment (Mz) selon l'axe (Z) menant de l'axe longitud inal (X) du turboréacteur (2) à l'axe longitudinal du support comprend deux attaches (200a, 200b) symétriques par rapport au plan médian (XZ) et décalées selon l'axe (Y). 13. An assembly according to claims 2 and 10 to 12 characterized in that the fastener (200a, 200b) configured so resumes re in association with said main suspension clip (130), the moment (Mz) according to l axis (Z) leading from the longitudinal axis (X) of the turbojet engine (2) to the longitudinal axis of the support comprises two fasteners (200a, 200b) symmetrical with respect to the median plane (XZ) and offset along the axis (Y).
EP12775819.1A 2011-10-06 2012-10-05 Aircraft propulsion assembly Withdrawn EP2763897A1 (en)

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FR1159010A FR2981047B1 (en) 2011-10-06 2011-10-06 PROPELLANT AIRCRAFT ASSEMBLY
PCT/FR2012/052259 WO2013050714A1 (en) 2011-10-06 2012-10-05 Aircraft propulsion assembly

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CA2849239A1 (en) 2013-04-11
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RU2014117114A (en) 2015-11-20
BR112014006998A2 (en) 2017-04-11
US20140217234A1 (en) 2014-08-07
CN103874633A (en) 2014-06-18
WO2013050714A1 (en) 2013-04-11

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