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
  • F02K1/06—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
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C7/00—Structures or fairings not otherwise provided for
  • B64C7/02—Nacelles
• • 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
• • 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
  • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
  • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
  • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
  • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
  • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
  • F02K9/84—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using movable nozzles
• • 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
  • F05D2240/14—Casings or housings protecting or supporting assemblies within
• • 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
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
  • F23R3/60—Support structures; Attaching or mounting means
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• Patent application FR06 / 05512 filed by the applicant on June 21, 2006, discloses an aircraft engine nacelle comprising a thrust reverser with gates defining a nozzle of variable section.
• Such nacelle is shown schematically in Figures 1 to 3 appended hereto. It comprises in particular a thrust reverser 1 delimiting a cold air vein 3 with an internal structure 5 surrounding an aircraft engine (not shown). The direction of air circulation in this vein is indicated by the arrow F1.
• the thrust reverser 1 comprises an outer wall 1a, capable of moving axially under the action of a first series of jacks 7, and an inner wall 1b capable of moving under the action of a second series of cylinders (not shown).
• FIG. 1 represents the outer wall 1a in a nozzle configuration of minimum section, in which configuration the upstream zone 11 (with respect to the direction F1) of the outer wall 1a of the thrust reverser 1 is slid between a cover 13 surrounding the fan casing 21 and an annular wall 17 fixed to the front frame 19 of the thrust reverser, itself attached to the fan casing 21 of the engine (here being recalled that the front frame 19 supports grids 23 allowing implement the thrust reversal function).
• FIG. 2 indicates (arrow F2) the sliding movement of which the cover 13 may be endowed for maintenance operations on the housing 21.
• FIG. 3 indicates (arrow F3) the sliding movement of which both the outer wall 1a and the inner wall 1b can be endowed in thrust reversal configuration, making it possible to circulate the cold air of the vein 3 outwards through the thrust reversal grids 23 (arrow F4).
• One of the problems related to a nacelle having the aforementioned architecture relates to the interface between the outer wall 1a of the thrust reverser 1 and the cover 13.
• step 25 formed by the cover 13 relative to the outer wall 1a is as thin as possible.
• the minimum thickness constraint for the cover 13 prevents providing reinforcements (ribs or other) of this cover in said overlap area. This has the consequence that this cover 13 is likely to undergo deformations in this area, which deformations can lead to a blockage of the relative movement of the outer wall 1a relative to the cover 13, given the small clearance between these two bodies .
• the present invention is intended in particular to eliminate this risk of blockage.
• a nacelle for an aircraft engine of the type comprising a front cover and a rear cover, this rear cover being slidably mounted between an upstream position defining a reduced nozzle section and a downstream position defining a enlarged nozzle section, remarkable in that it comprises an intermediate member disposed edge-to-edge with said front cover, this member defining a housing adapted to receive the upstream edge of said rear cover when the cover is in its upstream position.
• this intermediate member makes it possible to create aerodynamic continuity between the front cover and the rear cover without these two parts interacting directly: in this way, it is possible to overcome the problems of deformation and weak play that could lead to a blockage. of these parts relative to each other.
• said intermediate member comprises a reception range of said front cover, this area being disposed upstream of said housing: this receiving range allows the centering of the front cover with respect to the intermediate member;
• said front cowl comprises reinforcements situated just upstream of said beach: these reinforcing members make it possible to stiffen the front cowl, in particular in the vicinity of its downstream edge;
• said front cowl comprises reinforcements situated in line with said strip, said strip being offset radially inwards by a distance substantially corresponding to the cumulative radial thickness of said front cowl and said reinforcements: this arrangement makes it possible to arrange the reinforcement in the immediate vicinity of the downstream edge of the front hood;
• - Said housing comprises a radially inner edge defining a ramp for the upstream edge of said rear cover: this ramp allows the centering of the downstream cover relative to the housing of the intermediate member;
• said housing comprises a radially outer edge defining a ramp for the upstream edge of said rear cover: this particular arrangement makes it possible to place reinforcements on the inside face of the rear cover, in the vicinity of the upstream edge of this cover;
• this nacelle comprises a seal adjacent to said ramp: such a seal makes it possible to seal the connection between the intermediate member and the rear cover;
• said rear cover comprises, on its inner face, reinforcements disposed in the vicinity of its upstream edge: the presence of these reinforcements stiffens the upstream portion of the rear cover;
• the joining line between said front cover and said intermediate member is included in a plane that is not perpendicular to the axis of said nacelle: such a joining line, authorized by the presence of the intermediate member, notably allows better access to some fixed members of the nacelle when the front cover is in the maintenance position, slid forward;
• Said intermediate member comprises a foot supporting actuating means in particular said rear cover: this arrangement allows a particularly simple implementation of the actuating means (jacks for example); - said intermediate member is adapted to be fixed on the fan casing of said motor;
• said intermediate member comprises two halves able to be mounted articulated on a support pylon of said motor; said intermediate member is part of a hood of the blower of said engine;
• this nacelle comprises a thrust reverser with grids, the outer part of which forms said rear cover;
• said thrust reverser comprises, in addition to said outer portion, an inner portion movable independently of said outer portion: this particular embodiment corresponds to that which has been explained in the preamble of the present description;
• said intermediate member is an integral part of the fixed structure of said thrust reverser: this intermediate member may in particular be fixed to the front frame of the thrust reverser;
• said front cover incorporates the air intake lip of this nacelle
• FIG. 4 shows, in axial section, an intermediate member according to the invention mounted on the front frame of a thrust reverser
• FIGS. 5 to 7 similar to FIGS. 1 to 3, show a thrust reverser equipped with the intermediate member of FIG. 4, in three different configurations of the external wall of this thrust reverser;
• FIG. 10 shows a variant of the intermediate member according to the invention adapted to receive actuating members of the outer wall of the thrust reverser
• FIG. 11 represents a thrust reverser comprising the intermediate member of FIG. 10;
• - Figures 12 to 15 show the opening kinematics during maintenance operations of an intermediate member according to another embodiment of the invention;
• FIG. 16 represents a thrust reverser equipped with yet another variant of intermediate member according to the invention.
• FIG. 17 and 18 show, in side view, a nacelle equipped with the intermediate member of Figure 16, the front cover of this nacelle being slidably mounted relative to the fan casing, and integrating the inlet lip d 'air.
• the front cover is respectively in operating and maintenance positions.
• an intermediate member 25 is fixed on the front frame 19 of the thrust reverser 1, this intermediate member defining a housing 27 adapted to receive the upstream edge 11 of the outer wall 1a of the thrust reverser 1.
• This thrust reverser may optionally be of the same type as that of Figures 1 to 3, that is to say variable section nozzle.
• the intermediate member 25 extends over at least a portion of the circumference of the front frame 19, so that the housing 27 has an annular shape.
• This intermediate member is connected to the front frame 19 via a foot 29, which also has a substantially annular shape.
• Downstream of the housing 27 (the downstream being determined with respect to the direction of flow of the air in the vein 3, as indicated by the arrow F1 in FIGS. 1 and 2) is preferably a ramp 31, facilitating centering and placing the upstream edge 11 of the outer wall 1a inside the housing 27.
• a seal 33 disposed just upstream of the ramp 31, so as to allow a sealed connection of the outer wall 1a with the intermediate member 25.
• This beach 35 may itself comprise a ramp 37 to facilitate this centering.
• the front cover 13 releases access to the fan casing 21 during maintenance operations, by sliding relative to this casing.
• FIGS. 5 to 7 three different positions of the external wall 1a of the thrust reverser 1 can be seen, corresponding to different desired nozzle sections during the different flight phases of an aircraft.
• the inner wall 1b of the thrust reverser is maintained in the upstream position, that is to say, it closes the grids 23 of the inverter, so that the inverting function thrust is not active.
• the outer cowl 1a and the inner cowl 1b slide downstream from their positions shown in FIG. 7, thus making it possible to disengage the grids 23 and to reverse the flow of air flowing in the member 3.
• FIG. 8 shows that it is possible to provide circumferential reinforcements 39 under the internal face of the cover 13, these reinforcements being axially separated from the downstream edge of the cover 13 or by a distance d1 substantially corresponding to the axial length of the beach 35.
• the reinforcements 39 can be placed as shown in FIG. 9, that is to say in a manner directly adjacent to the downstream edge of this cover, in which case it is necessary to provide that the range 35 is offset radially with respect to the outer face 41 of the intermediate member 25, a distance of the d2 substantially equal to the cumulative radial thickness of the cover 13 and reinforcements 39.
• holes 43 can be provided in the foot 29 of the intermediate member 25, these orifices being able to receive cylinders 7 making it possible to actuate the outer wall 1 a of the thrust reverser 1 (see in particular FIG. 11).
• FIGS. 12 to 15 show the opening kinematics of a nacelle equipped with a variant of an intermediate member 25 according to the invention, a variant in which this intermediate member may be formed of two halves each mounted pivoting on a pylon (not shown) supporting the nacelle, about axes substantially parallel to the axis of this nacelle.
• each foot 19 of the intermediate member half 25 associated can separate from the frame before 19 during maintenance operations.
• the outer and inner walls 1a and 1b of the thrust reverser are then slid downstream of the nacelle, in particular by means of the jacks 7, as shown in FIG.
• each half of intermediate member 25 is rotated around the pylon (not shown) supporting the nacelle, ("butterfly" opening).
• FIGS. 16 to 18 it can be seen that, by providing an appropriate variation of the thickness e between the upstream edge 51 of the front 53 of the housing 27 of the intermediate member 25, a joining line 55 can be obtained between the front cover 13 and the outer wall 1a of the thrust reverser, having any inclination ⁇ relative to the axis A of a nacelle 57.
• the lower part 59 of the joining line 55 is disposed further upstream of the nacelle than the upper part 61 of this joining line.
• the intermediate member 25 constitutes a fixed part cooperating independently with firstly the front cover 13 and secondly the outer wall 1a of the thrust reverser. . Thanks to this intermediate member 25, it falls into a simple problem of kinematics moving part / fixed part, and it overcomes the risk of blockage inherent in the prior art systems.
• the present invention is not limited to the embodiments described and shown, provided as simple examples. It is understood in particular that the present invention can also be applied to so-called “smooth" nacelles, that is to say to nacelles devoid of means of thrust reversal.
• the outer wall described above forms in fact the simple rear cover of a rear part of a nozzle of variable section nozzle, and no longer the outer wall of a thrust reverser.
• intermediate member 25 it is thus also possible for the intermediate member 25 to form an integral part of a cover covering the casing 21, this cover being able to slide open like the cover 13 described above, or else " butterfly ", for example around the pylon supporting the nacelle.

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

Applications Claiming Priority (2)

Publications (1)

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ID=39708413

Family Applications (1)

Country Status (8)

Families Citing this family (22)

Family Cites Families (18)

• 2007
  • 2007-12-21 FR FR0708974A patent/FR2925607B1/fr not_active Expired - Fee Related
• 2008
  • 2008-12-19 CN CN200880119902XA patent/CN101896712A/zh active Pending
  • 2008-12-19 RU RU2010129772/11A patent/RU2494273C2/ru not_active IP Right Cessation
  • 2008-12-19 WO PCT/FR2008/001803 patent/WO2009103905A1/fr active Application Filing
  • 2008-12-19 US US12/747,294 patent/US9133789B2/en not_active Expired - Fee Related
  • 2008-12-19 BR BRPI0821504A patent/BRPI0821504A2/pt not_active IP Right Cessation
  • 2008-12-19 EP EP08872509A patent/EP2225453A1/fr not_active Withdrawn
  • 2008-12-19 CA CA 2705136 patent/CA2705136A1/fr not_active Abandoned

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