Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/64—Reversing fan flow
  • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
  • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/06—Varying effective area of jet pipe or nozzle
  • F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/78—Other construction of jet pipes
  • F02K1/82—Jet pipe walls, e.g. liners
  • F02K1/827—Sound absorbing structures or liners
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2240/00—Components
  • F05D2240/10—Stators
  • F05D2240/12—Fluid guiding means, e.g. vanes
  • F05D2240/129—Cascades, i.e. assemblies of similar profiles acting in parallel
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2240/00—Components
  • F05D2240/90—Mounting on supporting structures or systems
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2250/00—Geometry
  • F05D2250/30—Arrangement of components
  • F05D2250/34—Arrangement of components translated

Definitions

• the invention lies in the field of turbojet engine nacelles and more specifically relates to a thrust reverser device.
• An aircraft is propelled by one or more propulsion units comprising a turbojet engine housed in a tubular nacelle.
• Each propulsion unit is attached to the aircraft by a mast located generally under a wing or at the fuselage.
• a nacelle generally has a structure comprising an upstream air intake section, upstream of the engine, a median section intended to surround a fan of the turbojet engine, and a downstream section intended to surround the combustion chamber of the turbojet engine and housing a device. reverse thrust.
• the displacement device is able to comprise a cowl that is movable in translation along the axis of the nacelle, this translation being effected most often by means of a sliding connection made between the mobile cowl and the mast of attachment of a propulsion unit to the aircraft.
• the thrust reverser device can implement translational grids which are retracted on the fan casing (or fan casing) in the direct jet position and which, at the moment of passing into the reverse thrust position, slide towards downstream of the nacelle in concert with the movable thrust reverser hood (or transcowl) to deploy and reach their thrust reversal position.
• the translating grids are slideably connected to the fan casing, but they are also connected to the movable thrust reverser cowl which brings them to their thrust reversal position.
• This type of device has drawbacks in particular in that, in operation of the turbojet, there are relative displacements between the fan casing and the movable thrust reverser cowl which induces unwanted forces on the slide connection between the fan casing and the translating grids.
• the object of the invention is to provide a thrust reversal device freed from the aforementioned drawbacks.
• the present invention relates to a thrust reverser device for an aircraft turbojet engine comprising:
• translating grids connected to the movable cowl moved between a jet position in which they are retracted in a fan casing on the one hand, and on the other hand an indirect jet position where they are out said fan casing,
• a front suspension means of said turbojet engine remarkable in that the translating grids are slidably connected to the mast via at least one strut connected to the mast downstream of the front suspension.
• the thrust reverser device comprises one or more of the following optional features considered alone or according to all the possible combinations:
• the spacer is removably attached to the mast;
• the spacer comprises fixed grids;
• the translating grids comprise a rear frame downstream of which is embedded a ring of flaps of inversion of thrust whose dimensions relative to a main axis of the thrust reversal device is enlarged to the downstream end of the thrust reversing flaps, the shutter ring allows to extend the guide distance of the translating grids on the spacer;
• the assembly formed by the rear frame and the flap shell is in slide connection with the mast;
• the assembly formed by the rear frame and the flap shell is in sliding connection directly with the mast;
• a second spacer located between the mast and the translating grids is attached to the main course of the translatant gyrules on which they come to rest on the one hand and is linked to a connecting member connected to the mast somewhere else ;
• the second spacer is located between the first spacer and the axis of the thrust reverser device;
• the second spacer has a bead, extending radially outwardly of the thrust reverser device, substantially straight, parallel to the
• An acoustic panel capable of cooperating with the recessed portion of the inner wall of the movable cowl is fixed on the shutter ring and located under the fixed grids so that the acoustic panel does not rotate with the rest of the movable cowl when an opening thereof in a maintenance position;
• the acoustic panel attached to the shutter ring is also fixed on a translation slide, in slide connection with the fixed grids, translational grids, so as to keep with it a stress path in the deployed position;
• the acoustic panel has an angle of 45 ° between its downstream edge and its edge farthest from the mast in order to optimize the transmission of forces towards the hinges of the beam, the inner wall of the movable cowl being hollowed so that the wall inside the mobile hood and the acoustic panel have a complementary shape;
• the rear frame and the flap shell are relaxed, in particular so as not to transmit parasitic bending moment between the mast and the assembly formed by the rear frame and the flap shell;
• an area to be relaxed is the area of the flap shell located under the fixed gates when the movable cowl is in the direct jet position;
• the invention also relates to a nacelle comprising such a thrust reversal device.
• the invention also relates to a method for respectively detaching (attaching) an engine from an aircraft to (the) mast including a dismantling step (mounting) of the fixed grids of the (to) mast and a dismantling step (mounting) of the suspensions which connect the engine to the mast.
• FIG. 1 is a perspective view of a thrust reverser device according to a preferred embodiment of the present invention, the outer covers having been removed,
• FIG. 2 is a perspective view of the zone (II) defined in FIG. 1 of the thrust reverser device according to the preferred embodiment of the present invention
• FIG. 3 is a partial sectional view of the thrust reverser device according to the preferred embodiment of the present invention taken along the direction (III) defined in FIG. 2;
• FIG. 4 is a partial sectional view of the thrust reverser device according to another preferred embodiment of the present invention taken in a similar manner to FIG. 3;
• FIG. 5 is a perspective view of the device in an intermediate disassembly / assembly phase
• FIG. 6 is a schematic partial view of the device in an intermediate disassembly / assembly phase taken along the direction (VI) of FIG. 5.
• a thrust reverser device for an aircraft turbojet engine comprising: a mobile cover (not shown),
• translational grids 1 connected to the movable cowl, movable between a positron de j and di rect in which the elements are retracted in a fan casing on the one hand, and on the other hand an indirect jet position where they came out of said fan case,
• the translating grids 1 are slidably connected to the mast 2 via fixed grids 3 connected to the mast 2 downstream of the front suspension 4.
• the front suspension 4 is the upstream suspension of the engine or turbojet engine of the aircraft.
• An airplane may comprise two means of suspensions for a turbojet engine, one before and one behind.
• Upstream means what comes before the point or element considered, in the direction of the flow of air in a turbojet, and downstream which comes after the point or element considered, in the direction of flow air in a turbojet.
• the fixed grids 3 are removably mounted on the mast 2 via a set 5 of fittings 5a and 5b, the brackets 5b preferably being integrated in the mast 2, the brackets 5a being integrated with the edge of the fixed grids 3 closest to the mast 2 when positioned relative to the mast 2 in a manner suitable for thrust reversal.
• the fixed grids 3 form a rectangle and are extended on the upstream edge of the rectangle by a bracket 6, the bracket 6 and the rectangle having a common edge and being manufactured in a monolithic manner; orthogonal to this common song is another song of the square 6 q u i fits in the continuity of the singing of the rectangle farthest from the mast 2.
• chanting 7 we will call these last two songs chanting 7.
• the translating grids are located substantially in the fan casing (also called in the English terminology “fan casing”). ").
• the link between the translating gates 1 and the fixed gates 3 is described: the translating gates 1 and the fixed gates 3 are in slide connection.
• the edge 7 has a rail 8 (FIG 3) for this purpose shaped in such a way as to be able to hold the translating gates 1 in sliding connection.
• the translating grids 1 are situated substantially upstream of the fixed grids 3 on the part of the edge 7 forming one side of the bracket 6, whereas in the reverse thrust position, they are located substantially in the extension of the blades of the fixed gates 3.
• a spacer 9 is described between the mast 2 and the translating gates 1, and fixed on a lateral frame 10 of the translating gates 1 on which they come to rest on the one hand and linked to a connecting member 1 1 linked to the mast 2 on the other hand.
• the spacer 9 is situated between the fixed grids 3 and the axis ⁇ (FIG.1) of the thrust reverser device.
• the spacer 9 has a bead 1 2, extending radially outwardly of the thrust reverser device, substantially rectilinear, parallel to the axis ⁇ of the thrust reverser device, and located on the edge of the spacer 9 closest to the mast 2.
• the spacer 9 is in sliding connection with the connecting member 1 1 through a groove 13 of the connecting member 1 1, and the bead 12.
• the bead 12 has a substantially half-moon shaped contour and the groove 13 has an outline of a substantially complementary shape.
• the connecting member 1 1 is fixed relative to the mast 2 and it is integrated aum t 2, grassilau rs s hird ibs can be ra p po rt surlem 2 2.
• the connecting member 1 1 falls within the continuity of a primary rail 14, to which it is integrated, for guiding in translation of the movable reverse thrust cover (or transcowl), the primary rail 14 being integrated in the mast 2.
• the connecting member 1 1 is integrated with the edge 15 of the movable cover to be inserted in the primary rail 14.
• the connecting member 1 1 is in sliding connection by report to the mast 2.
• the thrust reverser device when the thrust reverser device is actuated in deployment to its inverted jet position (in reverse thrust mode), the movable cowl translates from a retracted position to an extended position downstream of the mast. 2 and along this mast 2 through the primary rail 14 in which its edge 15 is inserted.
• the movable cowl As the movable cowl is in connection with the translational grids 1, it pulls the translatant grids 1 at least over part of its travel in order to bring them into the inverted downstream position of the inverted jet.
• the translating grids 1 then translate downstream of the mast 2 and along the mast 2 thanks to the edge rail 7 of the fixed grids 3.
• the spacer 9 translates along the connecting groove 13.
• the spacer 9 serves not only to optimize the translational guidance of the translational grids 1, but also to take up the radial forces induced in the translational grids 1.
• the modus operandi is the same as in the previously described, except that the connecting member 1 1 translate in concert with the movable cover (not shown).
• the invention also relates to a nacelle (not shown) comprising a thrust reverser device as described above.
• a method for detaching is described above.
• an aircraft engine (respectively) to the mast 2 comprising a step of disassembling (respectively mounting) the fixed grids 3 of (re s pect i ve mentau) m et 2 and a sta ded d eted my tag e (respectively mounting) suspensions 4 which connect the engine to the mast 2.
• the device as described above is particularly visible in the disassembled position in Figure 6 where the connection between the fixed grids 3 and the mast 2 has been dismantled and where the spacer 9 is disengaged from the connecting member January 1.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=48521243

Family Applications (1)

Country Status (6)

Families Citing this family (19)

Family Cites Families (9)

• 2013
  • 2013-03-01 FR FR1351833A patent/FR3002785B1/fr active Active
• 2014
  • 2014-03-03 EP EP14711834.3A patent/EP2961974A1/de not_active Withdrawn
  • 2014-03-03 WO PCT/FR2014/050460 patent/WO2014132011A1/fr active Application Filing
  • 2014-03-03 CN CN201480011742.2A patent/CN105026741A/zh active Pending
  • 2014-03-03 RU RU2015141367A patent/RU2015141367A/ru not_active Application Discontinuation
• 2015
  • 2015-08-31 US US14/841,407 patent/US10190538B2/en active Active - Reinstated

Non-Patent Citations (1)

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