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
• • 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
  • B64D29/00—Power-plant nacelles, fairings, or cowlings
  • B64D29/06—Attaching of nacelles, fairings or cowlings
• • 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
  • F02K1/80—Couplings or connections
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/40—Organic materials
  • F05D2300/44—Resins
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/603—Composites; e.g. fibre-reinforced
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/612—Foam
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/614—Fibres or filaments
• • 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

• the present invention relates to a particular beam for thrust reverser grids.
• an aircraft engine which is generally of the turbojet type, is placed inside a nacelle which, among other functions:
• connection of the engine to the aircraft is carried out by means of a support structure comprising two upper longitudinal beams, often called 12-hour beams because of their position at the top of the nacelle, two lower longitudinal beams, conventionally called beams 6 hours because of their position in the lower part of the nacelle, and an assembly having a substantially annular shape called front frame, actually formed of two half-frames each extending between said upper and lower longitudinal beams, and intended for be attached to the periphery of the downstream edge of the engine blower housing.
• FIG. 1 Such a conventional configuration is visible in FIG. 1, appended hereto, in which a rear portion of a nacelle incorporating a thrust reverser is shown, this rear part comprising:
• two half-covers 7a, 7b each mounted respectively sliding on a 12-hour beam 1a, 1b and on a 6-hour beam 2a, 2b, so as to be able to discover the deflection gates 5a, 5b in order to effect the inversion of thrust.
• each 12 hour beam is conventionally formed in a ribbed metal alloy 1 1 based on aluminum, and typically comprises, on its outer face, rails. primary 13 and secondary 15 able to allow movement of the associated half-cover 7b (not shown), and a plurality of hinge clevises 17a, 17b, 17c, 17d able to allow the articulation of the beam 1b on the mast associated nacelle.
• the beam 1b is attached by riveting 20 to the upper part of a fixed inner half-structure panel 18b, generally formed of composite material, and defining, with the half-cover 7b of associated thrust reverser, cold air vein 9b.
• US2007 / 0294996 discloses a 1 2 hour carbon fiber composite beam having a closed and hollow section.
• the present invention is intended in particular to provide a thrust reverser beam composite material that is much simpler to achieve than that mentioned above.
• core material is meant a material sufficiently rigid to allow this material to serve as a lost molding core during resin infusion-type molding, such as a RTM (Resin Transfer Molding) process, and light enough otherwise not to be penalizing from the point of view of the weight gain concern.
• RTM Resin Transfer Molding
• the beam can be produced in a very simple manner: it suffices for this purpose to choose a core material having the desired geometry for the beam, then to use this material as a molding core: For this purpose, plies of carbon fibers (or others) are wrapped, the assembly thus obtained is placed between two molding matrices, and the resin which impregnates the plies of fibers is injected between these two matrices and then polymerized under effect of a rise in temperature.
• the core material remains within the skin formed by the fiber webs, in the manner of a lost molding core.
• said beam comprises closed ends formed by said skin: the fact of using a cored core core material and of realizing such a beam, contrary to the prior art in which it was necessary to relate elements for closing the ends of the beam after having extracted the molding core;
• said beam comprises internal stiffeners: these stiffeners, which may be arranged, for example, at the level of the hinge clevises, make it possible to increase the strength of the beam with respect to buckling; these stiffeners, which one for effect of compartmentalizing the inner cavity of the beam, are very easy to achieve because it is not necessary to remove the core material after molding;
• the shades are formed from the same composite material as said skin;
• said beam comprises at least one thrust reverser cowl guiding rail
• said rail is formed of the same composite material as said skin
• said beam comprises at least one hinge clevis: such a clevis can make it possible to connect the beam 1 2 hours to the pylon of the aircraft, while allowing its articulation around this pylon for the maintenance operations; or to connect the 2 beams 1 2 hours on the one hand and the two beams 6 hours on the other hand by means of suitable flanges, to ensure the structural cohesion of the two halves thrust reverser during flight;
• said clevis is formed of the same composite material as said skin
• said core material is chosen from the group comprising foams and honeycomb structures: these materials achieve an excellent resistance / weight compromise;
• said beam is a 12-hour beam
• said beam is a beam 6 hours.
• the present invention also relates to an aircraft engine nacelle, remarkable in that it comprises a thrust reverser comprising at least one beam in accordance with the foregoing.
• the present invention also relates to a method of manufacturing a beam according to the above, in which:
• a core is made whose shape corresponds to that of said beam
• the assembly thus formed is placed between the matrices of a resin infusion mold, resin is injected into this mold so as to impregnate the fiber fabrics, and
• this resin is heated so as to polymerize it and thereby form said skin.
• FIGS. 1 to 5 relate to the state of the art exhibited. in the preamble to the present description and Figure 6 relates to the present invention.
• FIG. 2 shows the assembly formed by the left 12-hour beam, the left-front half-frame and the left 6-hour beam of the inverter of FIG. 1;
• FIGS. 3 and 4 represent, in perspective, from two different angles of view, the left 12-hour beam of the thrust reverser of FIG. 1,
• FIG. 5 represents, in cross-sectional view with respect to the thrust reverser axis, the 12-hour beam of FIGS. 3 and 4 fastened to the upper part of a fixed internal half-structure panel of FIG. thrust reverser of FIG. 1, and
• FIG. 6 is a view similar to that of Figure 5, the beam 12 hours being this time according to the invention.
• the beam 12 hours 1b is delimited by a skin of composite material 21, which can be formed for example by carbon fibers impregnated with a cured epoxy resin by polymerization.
• This skin may be formed by one or more fiber fabrics. This skin surrounds a core material 23, so that this skin defines a closed section cavity filled with this core material.
• This core material is chosen to be rigid enough to form a molding core, and light enough not to interfere with weight gain. inherent to the choice of a composite material to form the skin of the beam 12 hours: as indicated above, hard synthetic foams such as ROHACELL® WF 100, or honeycomb structures, may for example be suitable.
• Rings 13, 15 allowing the sliding of the corresponding reverse thrust reverser half-cover, may be formed in the same composite material as the skin 21, either at the same time as this skin, or by subsequent fixing or gluing.
• these rails may be formed in another material than that of the skin 21, such as a metal alloy, and in this case also be reported on this skin.
• the beam 1b may also comprise hinge clevises similar to those of the beam of the prior art, which can be seen in particular in FIGS. in one piece with or be attached to the skin 21, such as rails 13 and 15.
• the beam 1b according to the invention may also comprise internal stiffeners (not shown) for increasing the resistance of this beam buckling, and can be arranged in particular to the aforementioned hinges of said hinges.
• stiffeners can be formed in the same composite material as the skin 21.
• the 12-hour beam according to the invention can be fixed by riveting or gluing on the upper part of the fixed internal structure panel 18b of the thrust reverser.
• An aerodynamic fairing 25 may be fixed for example by riveting or gluing on the skin 21 on the one hand and on the panel 18b on the other hand, so as to improve the flow of fresh air into the interior of the duct. cold air 9b (see Figure 1).
• This material is coated with one or more fiber fabrics, for example carbon, and the assembly thus formed is placed between the matrices of a resin infusion mold.
• the resin is then injected between these matrices, according to an infusion method, of RTM (Resin Transfer Molding) type for example, and the resin is heated so that it polymerises around the carbon fibers and thus forms the skin 21.
• RTM Resin Transfer Molding
• the core material 23 thus forms the molding core of the beam, and it is not necessary to extract it afterwards, because of its lightness compatible with the search for weight gain.
• the beam according to the invention can easily have fairings (or “fairings”) aerodynamic, made during molding.
• This beam may furthermore exhibit acoustic absorption characteristics when a core material 23 having such acoustic absorption properties is chosen. It may especially be foams or a honeycomb structure. In such a case, one or more walls of the beam exposed to the air flow may have suitable perforations and be made at least partially from a perforated acoustic skin.
• the invention has been described in relation to a beam 12 hours, but it should of course be understood that it is also applicable to a beam 6 hours, and more generally to any beam involved in the design of aircraft nacels, and more generally aircraft structures.

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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)
• Moulding By Coating Moulds (AREA)
• Laminated Bodies (AREA)
• Casting Or Compression Moulding Of Plastics Or The Like (AREA)
• Rod-Shaped Construction Members (AREA)

Applications Claiming Priority (2)

Publications (1)

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Family Applications (1)

Country Status (8)

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Family Cites Families (14)

• 2010
  • 2010-08-18 FR FR1056647A patent/FR2963949A1/fr not_active Withdrawn
• 2011
  • 2011-07-28 CN CN2011800387409A patent/CN103069141A/zh active Pending
  • 2011-07-28 WO PCT/FR2011/051826 patent/WO2012022900A1/fr active Application Filing
  • 2011-07-28 BR BR112013003126A patent/BR112013003126A2/pt not_active IP Right Cessation
  • 2011-07-28 RU RU2013110613/06A patent/RU2013110613A/ru not_active Application Discontinuation
  • 2011-07-28 CA CA2807430A patent/CA2807430A1/fr not_active Abandoned
  • 2011-07-28 EP EP11757367.5A patent/EP2606217A1/de not_active Withdrawn
• 2013
  • 2013-02-19 US US13/770,653 patent/US9341142B2/en not_active Expired - Fee Related

Non-Patent Citations (1)

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