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
  • B64D29/00—Power-plant nacelles, fairings or cowlings
  • B64D29/06—Attaching of nacelles, fairings or cowlings
• • 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
  • B64D27/40—Arrangements for mounting power plants in aircraft
  • B64D27/402—Arrangements for mounting power plants in aircraft comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant
• • 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
  • Y02T50/40—Weight reduction

Definitions

• the present invention relates to the field of nacelles for aircraft engines and more specifically to a support structure for thrust reverser including grids.
• an aircraft engine which is generally of the turbojet type, is placed inside a nacelle which, among other functions:
• a thrust reverser with grids comprises two half-mounted jacks ch acu n l issa nt su r u n e d em i-beam longitudinal support said beam 12h generally pivotally mounted on a nacelle support mast.
• each half-beam on the platform support pole makes it possible to rotate each half-cowl with respect to this mast for maintenance operations.
• 6h comprising two half-beams adapted to open by pivoting with the half-covers and therefore generally equipped with connection means between them and locking the two half-structures.
• Each half-beam 6h is conventionally connected to the corresponding half-beam 12h via an internal structure surrounding the turbojet engine.
• the beam 12h can be fixed and the opening dem i-covers for maintenance be carried out by complete translation of said sliding covers.
• each half-beam 12h will have a structure, on its outer face, primary and secondary rails capable of allowing the movement of the half-cover (not shown) associated, and a plurality of hinge clevis adapted to allow the articulation of the half-beam on the associated nacelle mast.
• the beams 12h and 6h are interconnected by a substantially annular structure called front frame and generally formed of two half-spacers apart from each other in the respective beams of the parts and other of a median plane of the basket.
• This front frame is intended to be attached to the periphery of a downstream edge of a crankcase of the engine blower and thus contribute to the recovery and transmission of forces between the different parts of the nacelle and the turbojet engine.
• the front frame is also used to support said gates of the thrust reverser.
• each half-beam 12h with its associated front frame part is effected by means of a mounted or integrated extension (see for example the document FR 2 920 192) on the upstream part (with respect to the direction of the air flow in the nacelle) of the half-beam, and intended to cooperate by interlocking with a corresponding receptacle of the front frame.
• This receptacle of the front frame is classically called "ashtray".
• the half-beams 6h have substantially the same structure with the difference that they do not include hinge clevises but latches and / or locking means corresponding.
• the working junction zone represents substantially only half of the total height of the assembly.
• the more frequent use of composite materials, in particular to make parts or all of these beams and / or front frame raises issues when the relative orientation and continuity of the fibers of the materials between them so as to optimize the passages of forces and resistances.
• the application FR 10/53338 relates to a half-support structure for an aircraft engine nacelle, comprising at least one longitudinal beam and a front half-frame, characterized in that said beam and said half-frame are formed of composite materials , in that said front half-frame has an open section, and in that said beam and said front half-frame form a one-piece piece.
• the invention also makes it possible to move the junction between the beam and its associated front half-frame away from the highly charged transition zone between the 12-hour sail (substantially vertical) of the beam with its front half-frame, by lengthening the length of the beam. extension of the beam (or front half-frame, depending on the variant considered).
• this assembly is designed in a modular manner from subassemblies assembled together to form a preform before polymerization and final treatment leading to make the piece monobloc .
• the beam structure substantially forms an L comprising a longitudinal web and a generally Omega-shaped foot.
• the front frame is integrated with a web and attached to the beam structure at an upstream lateral end of the omega floor via right angle returns glued to the beam structure.
• This same sail attached will also be assembled by fixing and with a connecting flange of the front frame with the fan housing.
• the front frame generates twisting and traction forces on the beam.
• the efforts go through perpendicular sails.
• connection flange to the fan casing generates a significant tensile force on the beam. At the moment the efforts go through perpendicular sails and only through the omega floor of the beam.
• the present application relates to a longitudinal beam for a turbojet engine support structure, said beam being made mainly of composite material and having substantially an L shape comprising, on the one hand, at least one longitudinal sail intended to come into contact with a pylon of attachment of the nacelle, and secondly, at least one foot, characterized in that the foot is shaped so as to achieve at least one receiving piece adapted to cooperate directly or indirectly by embedding with at least one end of an associated front frame.
• the fibers of the composite material participate fully in the recovery efforts in an optimal manner.
• the conformation of the fibers of the material can be carried out gradually with slopes and curves gentle, thus avoiding sudden and significant folds of fibers along the stress paths.
• the foot of the beam has a ceiling and a floor.
• the receiving part has a hollow shape, called female, adapted to cooperate with a so-called corresponding male form of the front half-frame.
• the receiving part has a so-called male shape capable of cooperating with a so-called corresponding female hollow form of the front half-frame.
• the receiving room incorporates an ashtray adapted to receive a corresponding portion of the front frame. It is indeed possible to provide an intermediate piece around which will be shaped the receiving part of the beam.
• the receiving part is able to receive complementary fastenings between the beam and the front frame.
• the receiving part has a polygonal section. It is also possible to make a substantially circular section, but such a section will be less suitable for the recovery of the moments of efforts.
• it is a 12h beam.
• the present invention also relates to a half-support structure for an aircraft engine nacelle comprising at least one longitudinal beam and a front half-frame, characterized in that the beam is a beam according to the invention.
• the beam and the frame are inserted into the receiving part before the final polymerization of the composite materials so as to form a one-piece half-structure.
• the half structure comprises a beam 12H and / or a beam 6H according to any one of claims 1 to 7, a front frame and / or a rear grid frame and possibly link reinforcements between the rear frame & front frame, front frame and / or frame rear being bonded by embedding in the receiving part of the beams before final polymerization of the composite materials so as to form a half-piece structure.
• the reinforcements will have a geometry adapted to the forces between the front frame and the rear grid support frame and may be added (before or after polymerization) to improve the strength of the structure thus created. These reinforcements may be installed preferentially at the level of reversing opening actuators. These reinforcements will preferably have an aerodynamic shape so as not to hinder the flow of air in reverse operation.
• the integration of the rear frame becomes possible if the material of the gates & the half structure has the same coefficient of expansion.
• the present invention finally relates to a nacelle for an aircraft engine, characterized in that it comprises at least one structure according to the invention.
• FIG. 1 is a schematic representation of a connection between a beam and a front frame according to the prior art.
• FIG. 2 is a schematic representation of a connection between a beam and a front frame of composite material according to a first improvement and described in the application FR 10/53338.
• FIGS 3 and 4 are perspective views respectively side and rear side of a beam according to the present invention.
• - Figure 5 is an exploded view of the constituent elements of the beam of Figures 3 and 4.
• FIGS. 6 and 7 are representations of the principle of variants of realisation respectively for a closed-section beam and an open-section beam.
• Figures 1 and 2 relate to elements of the prior art.
• a conventional configuration of support structure of a downstream thrust reversal section of a turbojet engine nacelle comprises:
• the two front half frames form a single front frame and 6h beams are removed.
• the beams and the front frame thus form the support structure for supporting the deflection grids and the movable covers of the thrust reverser device.
• FIG. 1 illustrates the assembly of a beam 12h 1 with its front half-frame 3 according to the prior art. According to the prior art, these elements are mainly made from an aluminum structure.
• the beam 12h has an L-shaped structure having a longitudinal web 10 intended to be fixed on the pylon of attachment and a foot January 1.
• the front half-frame 3 has a partly annular shape with a substantially C-shaped section and is equipped with a front frame box 31.
• connection of the beam 12h 1 with its dem i front frame 3 is realis ized classically by providing an extension 12, called ashtray, which is nested inside a cavity the front frame box 31 of corresponding shape.
• fasteners (not shown) are fixed to secure the extension 12 of the beam 1 with the wall of the front frame box 31.
• 1 1 having an Omega structure comprising a ceiling 1 1 a and a floor 1 1 b.
• a beam 100 of composite material is assembled to a front frame 300 also made of composite material no longer comprising a front frame box 31.
• connection between the beam 100 and the front frame 300 is effected by overlapping between a transition zone 1 19 open section of the beam and a corresponding transition zone 319, also open section, of the front frame. Bonding is by gluing or riveting.
• the assembly can be made monoblock by assembly before final polymerization of the composite material.
• the passage is made by imposing the curvature at 90 ° to the fibers of the composite material, which is not optimal in terms of transmission of forces along the fibers.
• a beam 500 according to the invention is shown in Figures 3 to 5.
• this beam 500 has an L-shaped structure comprising, firstly, a longitudinal web 10 equipped with a longitudinal guide rail 15 of a movable cowl thrust reverser, and secondly, a foot 1 1.
• Longitudinal reinforcements 16, which can serve as articulated clevises, are arranged regularly along the beam between the web 10 and the foot 11.
• This beam is made mainly of composite material.
• the foot 1 1 of the beam is shaped so as to achieve at least one receiving part 501 adapted to cooperate directly or indirectly by embedding with at least one end of an associated front frame.
• the foot is shaped to recreate an ashtray shape for receiving the front frame. This allows progressive deformation of the fibers to the desired shape.
• FIG. 5 is an exploded representation of the various elements constituting the beam 500. Each element constitutes a preform assembled with the other elements before final polymerization of the beam.
• the receiving part 501 receives an interface ashtray 502 forming an outgrowth for receiving the front frame which will then have a corresponding hollow and open shape.
• Conventional fasteners for example of the rivet type, will provide the connection between the two structures.
• An extension 503 may also be provided to close the foot 1 1 of the beam and provide partial overlap with a corresponding end of the front frame so as to further strengthen the connection.
• This extension 503 may in particular be used for a direct connection of the beam to a system of b rid e with the ca rte of so uffl a te, commonly called J-ring.
• J-ring a system of b rid e with the ca rte of so uffl a te, commonly called J-ring.
• the extension 503 may also receive the axis of a connecting rod for the connection between the two beams 12H.
• 501 has a hollow shape, called female, adapted to cooperate with a so-called corresponding male form of the front half-frame.
• the embedding can be carried out before the final polymerization of the beam 500 and the front frame, thus making it possible to obtain a one-piece assembly.
• the junction can be made by gluing, sewing, etc ... before final polymerization. In this case, it is obviously no longer necessary to use rivets for fixing.
• FIG. 6 is a block diagram of a closed-section beam having a hollow reception piece obtained by local deformation, the geometry of which will be adapted to ensure a good recovery of the forces, in particular by stamping, which can in particular accommodate an intermediate receiving part Ashtray type as described above.
• the rear grid frame can directly present an integrable shape to the hollow form without adding ashtray.
• the assembly can be made monoblock by assembly before final polymerization of the composite material.
• This type of constitution may be used preferentially for fixing a rear frame of grids.
• Figure 7 is a block diagram of a closed section beam having a hollow receiving piece obtained by cutting.
• a female form on the beam is installed in the continuity of the front frame to be assembled by gluing and / or stitching.

Landscapes

• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Moulding By Coating Moulds (AREA)
• Wind Motors (AREA)
• Body Structure For Vehicles (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=46639576

Family Applications (1)

Country Status (8)

Families Citing this family (4)

Family Cites Families (17)

• 2011
  • 2011-08-03 FR FR1157108A patent/FR2978729B1/fr active Active
• 2012
  • 2012-07-05 RU RU2014106964/11A patent/RU2014106964A/ru not_active Application Discontinuation
  • 2012-07-05 CA CA2842570A patent/CA2842570A1/fr not_active Abandoned
  • 2012-07-05 WO PCT/FR2012/051582 patent/WO2013017759A2/fr not_active Ceased
  • 2012-07-05 EP EP12744050.1A patent/EP2739533A2/de not_active Withdrawn
  • 2012-07-05 CN CN201280038183.5A patent/CN103732494A/zh active Pending
  • 2012-07-05 BR BR112014001123A patent/BR112014001123A2/pt not_active IP Right Cessation
• 2014
  • 2014-02-03 US US14/170,982 patent/US9260193B2/en not_active Expired - Fee Related

Non-Patent Citations (1)

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