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

Definitions

• the present invention relates to the field of nacelles for aircraft engines.
• 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, conventionally called beams 1 2 hours 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 nacel le, and an assembly having a substantially annular shape called front frame, actually formed of two half front frames each extending between said upper longitudinal beams and lower, and intended to 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:
• the left 12-hour beam 1 a and its associated left-front half-frame 3 a are shown separately in FIG. 2 in the assembled state, and in FIG. 3 just before their assembly. As can be seen in FIG. 3, this assembly is conventionally performed by providing an extension 11 on the beam 1b, which is fitted into a cavity 13 of corresponding shape defined by the wall. 15 of the front half-frame 3b.
• rivets 17 are attached to secure the extension 1 1 of the beam 1a with the wall 15 of the front half-frame 3b (see FIG. 4).
• the present invention is intended in particular to improve the force transmission capacity of the link between each beam 1 2 hours and half-cad associated with it, and to overcome the drawbacks related to the blindness of the assembly of Ground rivets idarization of these two bodies.
• a half-support structure for the aircraft engine 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 half-frame has an open section, and in that said half-structure has one of the following three characteristics:
• said beam and the front frame frame form a single piece
• said beam has an extension of open section, whose shape corresponds to that of said front half-frame, this extension being fixed to this half-frame, or
• said front half-frame has an open-form extension, the shape of which corresponds to that of said beam, this extension being fixed to this beam.
• the open section of the half-frame and, where appropriate, the extension of the beam or the front half-frame, allow to implement each of these two solutions, and to overcome the aforementioned problems.
• the one-piece part is made in a single molding operation (according to known methods of the RTM (Resin Transfer Molding) type or by infusion, for example).
• 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 the front half-frame, depending on the variant considered).
• said beam is a 12-hour beam
• said beam is a beam 6 hours
• said open sections have substantially a shape of
• said extension is fixed on said front half-frame by means selected from the group comprising gluing and fastening by rivets;
• the present invention also relates to a nacelle for an aircraft engine, remarkable in that it comprises two half-structures in accordance with the foregoing.
• FIG. 1 represents a perspective view of a nacelle rear part of the prior art, comprising a thrust reversal system, and described in the preamble of the present description,
• FIG. 2 shows in perspective, and slightly larger scale, a left half-structure of the assembly shown in Figure 1, the half-structure comprising a beam 12 hours and a front half-frame.
• FIG. 3a represents, in perspective and on an even larger scale, the 12-hour beam of the half-structure of FIG. 2,
• FIG. 3b shows in perspective, on the same scale as in FIG. 3a, the front half-frame of the half-structure of FIG. 2,
• FIG. 4 represents a sectional view along a plane parallel to the XZ plane of FIG. 2, of the zone indicated by the line IV of this FIG. 2,
• FIG. 5 is a perspective view similar to that of FIG. 2, and at a slightly increased scale, of a left-hand demongation according to the invention, according to a first embodiment; in this figure are visible not only the beam 12 hours, but also the beam 6 hours,
• FIG. 6a similar to FIG. 3a, shows a 12-hour beam of a left half-structure according to the invention according to a second embodiment
• FIG. 6b similar to FIG. 3b, shows part of a left front half-frame of this left half-structure according to the invention according to the second embodiment.
• identical or similar references designate organs or groups of organs that are identical or similar.
• arrow of the X axis is oriented from downstream to upstream of the nacelle, the downstream and the upstream, which is in relation to the direction of air circulation inside this nacelle.
• nacelle as indicated by the arrow A1 of Figure 1.
• FIGS 1 to 4 relate to elements of the prior art, described in detail in the preamble of the present description: these elements will not be described again here.
• the left-handed structure according to the invention comprises a 12-hour left beam 1b and a half-frame left front 3b formed in one piece.
• the left 12-hour beam 1b has a generally L-shaped cross-section
• the left-front half-frame 3b has a generally open, substantially C-shaped cross section.
• open is meant that the volume defined i by the wall of the left front half frame 3b is an open volume trough or gutter, and not a closed volume in the manner of a box, contrary to what is visible in FIG. 4 concerning the prior art.
• the beam 1b and the foreframe 3b can have sections of different shapes.
• the beam 1b may for example have a box section, or even an omega section.
• the invention also proposes to ensure the continuity of the integrated aerodynamic fairings under the beam 1b and in the radially lower part of the demi-frame before 3b in the case where it would be integrated therein. This allows in particular to reduce the aerodynamic losses by removing the gap between these parts and between the rivets that attach them.
• Hinges 21 are provided in the hollow of the L of the beam 1b, allowing the establishment of connecting rods with the beam 1 2 hours associated right.
• reinforcing ribs 23 are regularly arranged in the hollow of the front half-frame 3b, so as to give it the necessary strength and rigidity.
• These composite materials may include in particular carbon fiber fabrics embedded in polymerized resin.
• the composite materials can be obtained by processes of LCM ("Liquid Composite Molding") type, including in particular the RTM ("Resin Transfer Molding") and LRI processes.
• LCM Liquid Composite Molding
• RTM Resin Transfer Molding
• LRI LRI
• the dry preform can be obtained by 2D or 3D weaving, by braiding, by automatic deposition of fibers (webs for example), or by stacking of fabrics.
• the fact of making these parts in one piece makes it possible to obtain a continuity of the fibers of the composite materials, especially in the transition zone 1 9, which is an area subjected to particularly important circumferential stresses. .
• the left front beam 1b and the front half-frame 3b form two distinct pieces made of composite materials, each obtained according to a manufacturing method similar to that described for the embodiment of Figure 5.
• the beam 1 2 heu res gamb 1 b comprises a transverse extension (that is to say substantially parallel to the YZ plane), having an open section of similar shape to the open section of the front half-frame 3b.
• This extension 25 can thus be superimposed perfectly correspondingly on the associated end 27 of the front half-frame 3b.
• the extension 25 of the beam 1b is attached to the corresponding end 27 of the front half-frame 3b, by any appropriate means, for example by gluing or setting in place of rivets.

Landscapes

• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Wind Motors (AREA)
• Moulding By Coating Moulds (AREA)
• Body Structure For Vehicles (AREA)
• Tires In General (AREA)

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• 2010
  • 2010-04-29 FR FR1053338A patent/FR2959486B1/fr not_active Expired - Fee Related
• 2011
  • 2011-03-14 CN CN2011800207707A patent/CN102858635A/zh active Pending
  • 2011-03-14 CA CA2796630A patent/CA2796630A1/fr not_active Abandoned
  • 2011-03-14 BR BR112012023770A patent/BR112012023770A2/pt not_active IP Right Cessation
  • 2011-03-14 EP EP11712999A patent/EP2563665A1/fr not_active Withdrawn
  • 2011-03-14 WO PCT/FR2011/050505 patent/WO2011135213A1/fr active Application Filing
  • 2011-03-14 RU RU2012150133/11A patent/RU2012150133A/ru not_active Application Discontinuation
• 2012
  • 2012-10-29 US US13/662,905 patent/US9010681B2/en not_active Expired - Fee Related

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