EP2668025A1 - Process of manufacturing a turbojet engine nacelle part - Google Patents

Process of manufacturing a turbojet engine nacelle part

Info

Publication number
EP2668025A1
EP2668025A1 EP12704882.5A EP12704882A EP2668025A1 EP 2668025 A1 EP2668025 A1 EP 2668025A1 EP 12704882 A EP12704882 A EP 12704882A EP 2668025 A1 EP2668025 A1 EP 2668025A1
Authority
EP
European Patent Office
Prior art keywords
manufacturing
lip
resin
air intake
nacelle
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP12704882.5A
Other languages
German (de)
French (fr)
Inventor
Bertrand Desjoyeaux
Olivier HUBIER
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Nacelles SAS
Original Assignee
Aircelle SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Aircelle SA filed Critical Aircelle SA
Publication of EP2668025A1 publication Critical patent/EP2668025A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/84—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks by moulding material on preformed parts to be joined
    • 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
    • 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
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
    • B29L2031/087—Propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/748—Machines or parts thereof not otherwise provided for
    • B29L2031/7504—Turbines
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]

Definitions

  • the present invention relates to an air intake lip structure for a turbojet nacelle.
  • an aircraft propulsion unit conventionally comprises a turbojet engine housed inside a nacelle.
  • the nacel generally has an annular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine and its housing, a downstream section intended to surround the combustion chamber of the turbojet engine and housing the engine. if necessary means of thrust reversal. It can be terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
  • the air intake structure serves to optimize the air intake necessary to supply the fan of the turbojet engine and to channel it towards this fan.
  • An air intake structure comprises in particular upstream a leading edge structure commonly called "lip" air inlet.
  • the air intake lip ensures the capture of air and is attached to the rest of the air intake structure which ensures the channeling of the air captured to the turbojet engine.
  • the rest of the air intake structure has a substantially annular structure comprising an outer surface ensuring the external aerodynamic continuity of the nacelle and an inner surface ensuring the aerodynamic continuity of the nacelle internal.
  • the air intake lip provides the upstream connection between these two surfaces.
  • the entire air intake structure is attached upstream of a central section of the nacelle and a fan casing.
  • An air intake lip structure may comprise many components. It conventionally comprises in particular a reinforcing partition, an aerodynamic skin that can be made in several areas spliced between them, one or more junction profiles for the partitions or for attachment to the rest of the air intake structure.
  • these elements can be made in heterogeneous materials, and in particular from different metal alloys, typically based on aluminum and / or titanium. Some elements can also be made of composite materials. Today, these elements must be assembled by fixing. It follows a significant assembly time and the loss of aerodynamic performance related to these fasteners and assemblies. In addition, the attachment points create areas of weakness in the structure.
  • the present invention aims at overcoming these drawbacks and consists for this purpose in a method of manufacturing a nacelle part comprising a plurality of constituent elements, characterized in that it comprises the following steps aimed at:
  • LCM type liquid composite molding, or liquid composite molding
  • the mass of the room is not impacted by the addition of fixings.
  • the assembly time is further greatly reduced.
  • the internal structures molded with the outer wall can allow assembly with the rest of the structure at the rear portion of the lip, without altering the aerodynamic surface.
  • the addition of resin is carried out according to a method of resin infusion type.
  • the addition of resin is carried out according to a resin injection method, in particular a resin transfer molding method (RTM).
  • a resin injection method in particular a resin transfer molding method (RTM).
  • cover plies are intended to form an outer skin and / or internal part.
  • the folds completely cover the whole.
  • these folds consist of woven fabrics or braids shaped in such a way as to be able to adapt to a desired geometric shape.
  • these folds can be linked together by sewing or other technique of adding son binding the layers together to enhance the texture.
  • At least one element is an internal stiffener, especially a radial stiffener.
  • the stiffening elements may for example be made of metal made from stacked fibrous folds.
  • the portions of the stiffener in connection with the wall are reinforced by stitching or any other technique of adding son binding the layers together to strengthen the bond, or to assist in the assembly operation for molding.
  • the piece comprises at least one means of interfacing and the ision designed to allow an attachment with another part of the nacelle.
  • this interface is constituted by an inner surface of the aerodynamic wall, which is capable of bonding.
  • the attachment is completed by a surface distinct from the outer wall, such as an internal structure described above, with which the attachment can be made using fasteners.
  • an internal structure is constituted by a circumferential radial partition, joining a rear zone of the inner surface of the lip, to a rear zone of the outer surface of the lip, in order to give the whole a great stiffness.
  • the partition is perforated openings or traps, allowing access to the front area.
  • At least one element is a honeycomb core and the honeycomb core is covered with at least one sealing film, said element being insertable into folds constituting at least one of the facings or partitions.
  • at least one element is a core of foam-type lightweight filling material or non-open cellular core.
  • the present invention also relates to a turbojet engine nacelle part, characterized in that it can be obtained by a method according to the invention.
  • the part is an air intake lip.
  • FIG. 1 is a general schematic representation of a turbojet engine nacelle comprising an air intake lip.
  • FIG. 2 is a view of an air intake lip structure obtained by a method according to the invention.
  • FIG. 3 is a cross-sectional view of the air intake lip of FIG. 2.
  • FIGS. 4 and 5 are diagrammatic cross sectional views of alternative embodiments of an air intake lip by a method according to the invention.
  • FIG. 6 is a schematic cross-sectional representation of a mold for manufacturing the lip of FIGS. 2 and 3.
  • FIG. 1 shows a nacelle 1 of a turbojet engine attached to a pylon 2 of a wing 3 of an aircraft.
  • this nacelle 1 constitutes a substantially tubular housing for the turbojet engine and comprises an upstream air inlet structure 4, a median section 5 surrounding a fan (not visible) of the turbojet engine and a downstream section 6 ensuring the ejection of the air flow and equipped, if necessary, with means of thrust reversal.
  • the air intake structure 4 comprises an air intake lip structure 4a that captures the air and is attached to the remainder 4b of the air intake structure. 4 that ensures the channeling of the air captured to the turbojet engine.
  • the air intake lip 4a alone is shown in FIG. 2. It has a one-piece structure obtained according to the method according to the invention.
  • a sectional view in FIG. 3 shows the internal structure of said air intake lip 4a.
  • the air inlet structure 4a comprises a plurality of constituent elements, namely in particular, a honeycomb acoustic attenuation structure 41, a profile 42, for example C or T , intended to allow the downstream junction with the remainder 4b of the air inlet structure 4, a profile 43 T to ensure the junction with a peripheral internal partition, ribs 44 longitudinal reinforcement. All of the constituent elements are covered with an aerodynamic outer skin 45. Of course, these elements are given by way of example and the air intake lip 4a may comprise others, or in different forms. .
  • Part of said fibrous folds will constitute, after resin injection and polymerization, the outer aerodynamic skin 45. Another part of the folds will constitute an internal skin if necessary.
  • the constituent elements 41, 42, 43, 44 are arranged over or between constituent fibrous folds 45.
  • an injection of resin is carried out according to a method of RTM (resin transfer mold ex mold 60) type, infusion of resin, or other type.
  • a sealing wire m may be placed before injection of the resin and removed thereafter.
  • the cavities of the acoustic attenuation structure will not be blocked by the resin.
  • one end 50 of the pleats of the air intake structure is intended for assembly bonding with the rear structure 4b and prepared for this purpose by a method known in itself.
  • Figures 4 and 5 show alternative embodiments of an air intake lip by a method according to the invention.
  • the lip of FIG. 4 notably has a connecting flange
  • the lip of FIG. 5 has in particular a partition 431 integrated and equipped with hatches 432 to allow access to the interior space of the lip (installation of deicing equipment for example).

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Composite Materials (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Architecture (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

Process for manufacturing a turbojet engine nacelle part. The present invention relates to a process for manufacturing a lip (4a) of an air intake (4) of a nacelle (1) comprising a plurality of constituent elements (41, 42, 43, 44, 421, 431), characterized in that it comprises the following steps that aim to: - place inside a mould at least one portion of the constituent elements within an assembly of fibrous layers (44, 45) completely or partly encompassing the constituent elements and thus forming a preform, - carry out an impregnation of the preform obtained in order to obtain the moulding of the part.

Description

Procédé de fabrication d'une pièce de nacelle de turboréacteur  Process for manufacturing a part of a turbojet engine nacelle
La présente invention se rapporte à une structure de lèvre d'entrée d'air pour nacelle de turboréacteur. The present invention relates to an air intake lip structure for a turbojet nacelle.
Comme cela est connu en soi, un ensemble propulsif d'aéronef comprend classiquement un turboréacteur logé à l'intérieur d'une nacelle.  As is known per se, an aircraft propulsion unit conventionally comprises a turbojet engine housed inside a nacelle.
La nacel le présente généralement u ne structu re annulaire comprenant une entrée d'air en amont du turboréacteur, une section médiane destinée à entourer une soufflante du turboréacteur et son carter, une section aval destinée à entourer la chambre de combustion du turboréacteur et abritant le cas échéant des moyens d'inversion de poussée. Elle peut être terminée par une tuyère d'éjection dont la sortie est située en aval du turboréacteur.  The nacel generally has an annular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine and its housing, a downstream section intended to surround the combustion chamber of the turbojet engine and housing the engine. if necessary means of thrust reversal. It can be terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
La structure d'entrée d'air sert à optimiser la captation d'air nécessaire à l'alimentation de la soufflante du turboréacteur et à le canaliser vers cette soufflante.  The air intake structure serves to optimize the air intake necessary to supply the fan of the turbojet engine and to channel it towards this fan.
Une structure d'entrée d'air comprend notamment en amont une structure de bord d'attaque couramment appelée « lèvre » d'entrée d'air.  An air intake structure comprises in particular upstream a leading edge structure commonly called "lip" air inlet.
La lèvre d'entrée d'air assure la captation de l'air et est rattachée au reste de la structure d'entrée d'air qui assure la canalisation de l'air capté vers le turboréacteur.  The air intake lip ensures the capture of air and is attached to the rest of the air intake structure which ensures the channeling of the air captured to the turbojet engine.
Pour ce faire, le reste de la structure d'entrée d'air présente une structure sensiblement annulaire comprenant une surface externe assurant la continuité aérodynamique externe de la nacelle et une surface interne assurant la continuité aérodynamique interne de la nacelle. La lèvre d'entrée d'air assure la liaison amont entre ces deux surfaces.  To do this, the rest of the air intake structure has a substantially annular structure comprising an outer surface ensuring the external aerodynamic continuity of the nacelle and an inner surface ensuring the aerodynamic continuity of the nacelle internal. The air intake lip provides the upstream connection between these two surfaces.
L'ensemble de la structure d'entrée d'air est rattaché en amont d'une section médiane de la nacelle et d'un carter de soufflante.  The entire air intake structure is attached upstream of a central section of the nacelle and a fan casing.
Une structure de lèvre d'entrée d'air peut comprendre de nombreux composants. Elle comporte classiquement notamment une cloison de renfort, une peau aérodynamique pouvant être réalisées en plusieurs secteurs éclissés entre eux, un ou plusieurs profils de jonction pour les cloisons ou pour un rattachement au reste de la structure d'entrée d'air.  An air intake lip structure may comprise many components. It conventionally comprises in particular a reinforcing partition, an aerodynamic skin that can be made in several areas spliced between them, one or more junction profiles for the partitions or for attachment to the rest of the air intake structure.
Actuellement, ces éléments peuvent être réalisés dans des matériaux hétérogènes, et notamment à partir d'alliages métalliques différents, typiquement à base d'aluminium et / ou de titane. Certains éléments peuvent également être réalisés en matériaux composites. Aujourd'hui, ces éléments doivent être assemblés par fixation. Il s'ensuit un temps d'assemblage important et la perte de performances aérodynamiques liée à ces fixations et assemblages. Par ailleurs, les points de fixation créent des zones de fragilité dans la structure. Currently, these elements can be made in heterogeneous materials, and in particular from different metal alloys, typically based on aluminum and / or titanium. Some elements can also be made of composite materials. Today, these elements must be assembled by fixing. It follows a significant assembly time and the loss of aerodynamic performance related to these fasteners and assemblies. In addition, the attachment points create areas of weakness in the structure.
La présente invention vise à pallier ces inconvénients et consiste pour ce faire en un procédé de fabrication d'une pièce de nacelle comprenant une pluralité d'éléments constitutifs, caractérisé en ce qu'il comprend les étapes suivantes visant à :  The present invention aims at overcoming these drawbacks and consists for this purpose in a method of manufacturing a nacelle part comprising a plurality of constituent elements, characterized in that it comprises the following steps aimed at:
- disposer à l'intérieur d'un moule au moins deux éléments constitutifs au sein d'un ensemble de plis fibreux englobant en tout ou partie les éléments constitutifs et formant ainsi une préforme,  placing inside a mold at least two constituent elements within a set of fibrous folds wholly or partly including the constituent elements and thus forming a preform,
- réaliser une imprégnation de la préforme obtenue pour obtenir le moulage de la pièce.  - Impregnating the preform obtained to obtain the molding of the part.
On pourra notamment util iser un procédé de type LCM (liquid composite molding, ou moulage composites liquide).  In particular, it will be possible to use a process of LCM type (liquid composite molding, or liquid composite molding).
Ainsi, en intégrant en une seule opération de moulage la peau structurale de lèvre d'entrée d'air, les éventuelles structures internes de raidissage, la ou les brides ou excroissances en face interne de liaison et d'intégration avec les autres composants de la nacelle et / ou du moteur à proximité immédiate, il est possible d'obtenir une pièce monobloc, auto-raidie, liant tous les éléments constitutifs entre eux sans avoir besoin de recourir à des moyens de fixation additionnels, éclissages, et autres.  Thus, by integrating in a single molding operation the structural skin of the air intake lip, the possible internal stiffening structures, the flange (s) or protuberances on the inner face of the connection and integration with the other components of the nacelle and / or the engine in the immediate vicinity, it is possible to obtain a monobloc piece, self-stiffening, linking all the constituent elements together without the need to resort to additional fastening means, splints, and others.
La masse de la pièce n'est donc pas impactée par l'ajout de fixations. Le temps d'assemblage est de plus grandement réduit. De plus, les structu res internes moulées avec la paroi externe peuvent permettre l'assemblage avec le reste de la structure à la partie arrière de la lèvre, sans altérations de la surface aérodynamique.  The mass of the room is not impacted by the addition of fixings. The assembly time is further greatly reduced. In addition, the internal structures molded with the outer wall can allow assembly with the rest of the structure at the rear portion of the lip, without altering the aerodynamic surface.
Selon une première variante de réalisation, l'addition de résine s'effectue selon un procédé de type infusion de résine.  According to a first variant embodiment, the addition of resin is carried out according to a method of resin infusion type.
Selon une deuxième variante de réalisation, l'addition de résine s'effectue selon un procédé d'injection de résine, notamment un selon procédé de moulage par transfert de résine (RTM).  According to a second variant embodiment, the addition of resin is carried out according to a resin injection method, in particular a resin transfer molding method (RTM).
De manière préférentielle, une partie des plis de recouvrement sont destinés à former une peau externe et/ou interne de la pièce.  Preferably, a portion of the cover plies are intended to form an outer skin and / or internal part.
Avantageusement, les plis recouvrent totalement l'ensemble. Avantageusement, ces plis sont constitués de tissus ou de tresses tissés en forme de telle manière à pouvoir s'adapter à une forme géométrique souhaitée. Advantageously, the folds completely cover the whole. Advantageously, these folds consist of woven fabrics or braids shaped in such a way as to be able to adapt to a desired geometric shape.
Avantageusement, ces plis peuvent être liés entre eux par de la couture ou autre technique d'ajout de fils liant les couches entre elles afin de renforcer la texture.  Advantageously, these folds can be linked together by sewing or other technique of adding son binding the layers together to enhance the texture.
Selon encore un autre mode de réalisation, au moins un élément est un raidisseur interne notamment radial. Les éléments raidisseurs pourront par exemple être métalliques réalisés à partir de plis fibreux empilés.  According to yet another embodiment, at least one element is an internal stiffener, especially a radial stiffener. The stiffening elements may for example be made of metal made from stacked fibrous folds.
Avantageusement, le ou les éléments raidisseurs sont constitués de plis de tissus ou de tresse, avec des parties rabattues en vis-à-vis de la paroi externe ou interne de la pièce.  Advantageously, the stiffening element or elements consist of folds of fabric or braid, with parts folded vis-à-vis the outer wall or internal part.
Avantageusement, les parties du raidisseur en liaison avec la paroi sont renforcées par couture ou toute autre technique d'ajout de fils liant les couches entre elles afin de renforcer la liaison, ou d'aider à l'opération d'assemblage pour le moulage.  Advantageously, the portions of the stiffener in connection with the wall are reinforced by stitching or any other technique of adding son binding the layers together to strengthen the bond, or to assist in the assembly operation for molding.
Selon encore un autre mode de réalisation, la pièce comprend au moi n s u n moyen d ' i nterfaçage et de l ia ison d esti n é à permettre u n rattachement avec une autre pièce de la nacelle. Avantageusement, cette interface est constituée par une surface interne de la paroi aérodynamique, qui soit apte au collage. Dans une variante du mode de réalisation, le rattachement est complété par une surface distincte de la paroi externe, telle qu'une structure interne décrite précédemment, avec laquelle, le rattachement peut être réalisé à l'aide de fixations.  According to yet another embodiment, the piece comprises at least one means of interfacing and the ision designed to allow an attachment with another part of the nacelle. Advantageously, this interface is constituted by an inner surface of the aerodynamic wall, which is capable of bonding. In a variant of the embodiment, the attachment is completed by a surface distinct from the outer wall, such as an internal structure described above, with which the attachment can be made using fasteners.
Dans un autre mode de réalisation encore, une structure interne est constituée par une cloison radiale circonférentielle, rejoignant une zone arrière de la surface interne de la lèvre, à une zone arrière de la surface externe de la lèvre, afin de conférer à l'ensemble une grande raideur.  In yet another embodiment, an internal structure is constituted by a circumferential radial partition, joining a rear zone of the inner surface of the lip, to a rear zone of the outer surface of the lip, in order to give the whole a great stiffness.
Dans une variante du mode de réalisation, la cloison est ajourée d'ouvertures ou trappes, permettant l'accès à la zone avant.  In a variant of the embodiment, the partition is perforated openings or traps, allowing access to the front area.
Selon un mode de réalisation préférentiel, au moins un élément est une âme à structure alvéolaire et l'âme alvéolaire est recouverte d'au moins un film d'étanchéité, ledit élément pouvant être inséré entré des plis constituants l'un au moins des parements ou cloisons. Selon un autre mode de réalisation préféré, au moins un élément est u ne âme en matériau de rempl issage léger de type mousse ou âme alvéolaire non ouverte. According to a preferred embodiment, at least one element is a honeycomb core and the honeycomb core is covered with at least one sealing film, said element being insertable into folds constituting at least one of the facings or partitions. According to another preferred embodiment, at least one element is a core of foam-type lightweight filling material or non-open cellular core.
La présente invention se rapporte également à une pièce de nacelle de turboréacteur, caractérisée en ce qu'elle peut être obtenue par un procédé selon l'invention.  The present invention also relates to a turbojet engine nacelle part, characterized in that it can be obtained by a method according to the invention.
Préférentiellement, la pièce est une lèvre d'entrée d'air.  Preferably, the part is an air intake lip.
La présente invention sera mieux comprise à la lumière de la description détaillée qui suit en regard du dessin annexé dans lequel : The present invention will be better understood in the light of the following detailed description with reference to the appended drawing in which:
- La figure 1 est une représentation schématique générale d'une nacelle de turboréacteur comprenant une lèvre d'entrée d'air. - Figure 1 is a general schematic representation of a turbojet engine nacelle comprising an air intake lip.
- La figure 2 est une vue d'une structure de lèvre d'entrée d'air obtenue par un procédé selon l'invention. FIG. 2 is a view of an air intake lip structure obtained by a method according to the invention.
- La figure 3 est une vue en coupe transversale de la lèvre d'entrée d'air de la figure 2.  FIG. 3 is a cross-sectional view of the air intake lip of FIG. 2.
- Les fig u res 4 et 5 sont d es vu e schématiques en coupes transversales de variantes de réalisation d'une lèvre d'entrée d'air par un procédé selon l'invention.  FIGS. 4 and 5 are diagrammatic cross sectional views of alternative embodiments of an air intake lip by a method according to the invention.
- La figure 6 est une représentation schématique en coupe transversale d'un moule de fabrication de la lèvre des figures 2 et 3.  FIG. 6 is a schematic cross-sectional representation of a mold for manufacturing the lip of FIGS. 2 and 3.
La figure 1 montre une nacelle 1 de turboréacteur rattachée à un pylône 2 d'une aile 3 d'un aéronef.  FIG. 1 shows a nacelle 1 of a turbojet engine attached to a pylon 2 of a wing 3 of an aircraft.
De manière habituelle, cette nacelle 1 constitue un logement sensiblement tubulaire pour le turboréacteur et comprend une structure amont d'entrée d'air 4, une section médiane 5 entourant une soufflante (non visible) du turboréacteur et une section aval 6 assu rant l'éjection du flux d'air et équipée le cas échéant de moyens d'inversion de poussée.  In the usual way, this nacelle 1 constitutes a substantially tubular housing for the turbojet engine and comprises an upstream air inlet structure 4, a median section 5 surrounding a fan (not visible) of the turbojet engine and a downstream section 6 ensuring the ejection of the air flow and equipped, if necessary, with means of thrust reversal.
Comme visible sur la figure 1 , la structure d'entrée d'air 4 comprend une structure de lèvre d'entrée d'air 4a assurant la captation de l'air et est rattachée au reste 4b de la structure d'entrée d'air 4 qu i assure la canalisation de l'air capté vers le turboréacteur.  As can be seen in FIG. 1, the air intake structure 4 comprises an air intake lip structure 4a that captures the air and is attached to the remainder 4b of the air intake structure. 4 that ensures the channeling of the air captured to the turbojet engine.
La lèvre d'entrée d'air 4a seule est représentée sur la figure 2. Elle présente une structure monobloc obtenue conformément au procédé selon l'invention. Une vue en coupe figure 3 montre la structure interne de ladite lèvre d'entrée d'air 4a. The air intake lip 4a alone is shown in FIG. 2. It has a one-piece structure obtained according to the method according to the invention. A sectional view in FIG. 3 shows the internal structure of said air intake lip 4a.
Conformément à l'invention la structure d'entrée d'air 4a comprend une pluralité d'éléments constitutifs, à savoir notamment, une structure d'atténuation acoustique en nid d'abeille 41 , un profilé 42, par exemple en C ou en T, destiné à permettre la jonction aval avec le reste 4b de la structure d'entrée d'air 4, un profil 43 en T pour assurer la jonction avec une cloison interne périphérique, des nervures 44 longitudinales de renfort. L'ensemble des éléments constitutifs est recouvert d'une peau externe aérodynamique 45. Bien évidemment, ces éléments sont donnés à titre d'exemple et la lèvre d'entrée d'air 4a peut en comprendre d'autres, ou sous des formes différentes.  According to the invention the air inlet structure 4a comprises a plurality of constituent elements, namely in particular, a honeycomb acoustic attenuation structure 41, a profile 42, for example C or T , intended to allow the downstream junction with the remainder 4b of the air inlet structure 4, a profile 43 T to ensure the junction with a peripheral internal partition, ribs 44 longitudinal reinforcement. All of the constituent elements are covered with an aerodynamic outer skin 45. Of course, these elements are given by way of example and the air intake lip 4a may comprise others, or in different forms. .
Une partie desdits plis fibreux constituera après injection de résine et polymérisation la peau aérodynamique externe 45. Une autre partie des plis constituera une peau interne si besoin.  Part of said fibrous folds will constitute, after resin injection and polymerization, the outer aerodynamic skin 45. Another part of the folds will constitute an internal skin if necessary.
Conformément au procédé selon l'invention, les éléments constitutifs 41 , 42, 43, 44 sont disposés par-dessus ou entre des plis fibreux constituant 45.  According to the method according to the invention, the constituent elements 41, 42, 43, 44 are arranged over or between constituent fibrous folds 45.
Ainsi disposés à l'intérieur d'un moule 60 (figure 6), il est procédé à une injection de résine selon un procédé de type RTM (moulage par transfert de résine ex moule 60), infusion de résine, ou autre.  Thus arranged inside a mold 60 (FIG. 6), an injection of resin is carried out according to a method of RTM (resin transfer mold ex mold 60) type, infusion of resin, or other type.
Il convient de noter qu'afin de conserver l'intégrité de la structure acoustique alvéolaire de 41 , un fil m d'étanchéité pourra être placé avant injection de la résine et retiré par la suite. Ainsi, les cavités de la structure d'atténuation acoustique ne seront pas bouchées par la résine.  It should be noted that in order to maintain the integrity of the cellular acoustic structure of 41, a sealing wire m may be placed before injection of the resin and removed thereafter. Thus, the cavities of the acoustic attenuation structure will not be blocked by the resin.
On pourra également prévoir qu'une extrémité 50 des plis de la structure d'entrée d'air soit destinée au collage d'assemblage avec la structure arrière 4b et préparée à cette fin par un procédé connu en soit.  It may also be provided that one end 50 of the pleats of the air intake structure is intended for assembly bonding with the rear structure 4b and prepared for this purpose by a method known in itself.
Les figures 4 et 5 présentent des variantes de réalisation d'une lèvre d'entrée d'air par un procédé selon l'invention.  Figures 4 and 5 show alternative embodiments of an air intake lip by a method according to the invention.
La lèvre de la figure 4 présente notamment une bride de jonction The lip of FIG. 4 notably has a connecting flange
421 en L pour jonction aval. 421 L for downstream junction.
La lèvre de la figure 5 présente notamment une cloison 431 intégrée et équipée de trappes 432 pour permettre l'accès à l'espace intérieur de la lèvre (mise en place d'équipements de dégivrage par exemple).  The lip of FIG. 5 has in particular a partition 431 integrated and equipped with hatches 432 to allow access to the interior space of the lip (installation of deicing equipment for example).
Bien que l'invention ait été décrite avec un exemple particulier de réal isation, il est bien évident qu'elle n'y est nullement limitée et qu'elle comprend tous les équivalents techniques des moyens décrits ainsi que leurs combinaisons si celles-ci entrent dans le cadre de l'invention. Although the invention has been described with a particular example of real isation, it is obvious that it is in no way limited and that it comprises all the technical equivalents of the means described and their combinations if they fall within the scope of the invention.

Claims

REVENDICATIONS
1. Procédé de fabrication d'une lèvre (4a) d'entrée d'air (4) de nacelle (1) comprenant une pluralité d'éléments constitutifs (41, 42, 43, 44, 421 , 431 ), caractérisé en ce qu'il comprend les étapes suivantes visant à : A method of manufacturing a nacelle air intake lip (4a) (4) comprising a plurality of constituent elements (41, 42, 43, 44, 421, 431), characterized in that it includes the following steps to:
- disposer à l'intérieur d'un moule au moins deux éléments constitutifs au sein d'un ensemble de plis fibreux (44, 45) englobant en tout ou partie les éléments constitutifs et formant ainsi une préformeT placing inside a mold at least two constituent elements within a set of fibrous folds (44, 45) wholly or partly covering the constituent elements and thus forming a preform T
- réaliser une imprégnation de la préforme obtenue pour obtenir le moulage de la pièce.  - Impregnating the preform obtained to obtain the molding of the part.
2. Procédé de fabrication selon la revendication 1, caractérisé en ce que l'addition de résine s'effectue selon un procédé de type infusion de résine. 2. The manufacturing method according to claim 1, characterized in that the addition of resin is carried out according to a resin infusion type process.
3. Procédé de fabrication selon la revendication 1, caractérisé en ce que l'addition de résine s'effectue selon un procédé d'injection de résine, notamment un selon procédé de moulage par transfert de résine (RTM). 3. The manufacturing method according to claim 1, characterized in that the addition of resin is carried out according to a resin injection method, in particular a resin transfer molding method (RTM).
4. Procédé de fabrication selon l'une quelconque des revendications 1 à 3, caractérisé en ce qu'au moins une partie de la préforme comprend des plis fibreux (44, 45), notamment en fibres de carbone, destinés à former une peau externe et/ou interne de la pièce. 4. Manufacturing process according to any one of claims 1 to 3, characterized in that at least a portion of the preform comprises fibrous folds (44, 45), in particular of carbon fibers, intended to form an outer skin and / or internal part.
5. Procédé selon l'une quelconque des revendications 1 à 4, caractérisé en ce que les plis (44, 45) sont constitués de tissus ou de tresses tissés en forme de telle manière à pouvoir s'adapter à une forme géométrique souhaitée. 5. Method according to any one of claims 1 to 4, characterized in that the folds (44, 45) consist of woven fabrics or braids shaped so as to be able to adapt to a desired geometric shape.
6. Procédé de fabrication selon l'une quelconque des revendications 1 à 5, caractérisé en ce qu'au moins un élément est une âme à structure alvéolaire (41) et en ce que l'âme alvéolaire est recouverte d'au moins un film d'étanchéité. 6. Manufacturing process according to any one of claims 1 to 5, characterized in that at least one element is a honeycomb core (41) and in that the cellular core is covered with at least one film sealing.
7. Procédé de fabrication selon l'une quelconque des revendications 1 à 6, caractérisé en ce qu'au moins un élément est une âme en matériau de remplissage léger de type mousse ou âme alvéolaire non ouverte. 7. The manufacturing method according to any one of claims 1 to 6, characterized in that at least one element is a core of lightweight filling material of the foam type or non-open cellular core.
8. Procédé de fabrication selon l'une quelconque des revendications 1 à 7, caractérisé en ce qu'au moins un élément est un raidisseur interne notamment radial. 8. Manufacturing process according to any one of claims 1 to 7, characterized in that at least one element is an internal stiffener including radial.
9. Procédé selon la revendication 8, caractérisé en ce qu'elle comprend une structure interne (431 ) formant raidisseur constituée par une cloison radiale circonférentielle, rejoignant une zone arrière de la surface interne de la lèvre, à une zone arrière de la surface externe de la lèvre. 9. A method according to claim 8, characterized in that it comprises an internal structure (431) forming a stiffener constituted by a circumferential radial wall, joining a rear zone of the inner surface of the lip, to a rear zone of the outer surface. of the lip.
10. Procédé de fabrication selon l'une quelconque des revendications 7 à 9, caractérisé en ce que au moins un raidisseur est réalisé à partir d'une structure fibreuse notamment à base de fibres de carbone. 10. Manufacturing process according to any one of claims 7 to 9, characterized in that at least one stiffener is made from a fibrous structure, in particular based on carbon fibers.
11. Procédé de fabrication selon l'une quelconque des revendications 1 à 10, caractérisé en ce qu'elle comprend au moins un moyen d'interfaçage (50) et de liaison destinée à permettre un rattachement avec une autre pièce de la nacelle (1). 11. Manufacturing process according to any one of claims 1 to 10, characterized in that it comprises at least one interfacing means (50) and connection intended to allow attachment to another part of the nacelle (1). ).
12. Lèvre (4a) d'entrée d'air (4) de nacelle (1) de turboréacteur, caractérisée en ce qu'elle peut être obtenue par un procédé selon l'une quelconque des revendications 1 à 11. 12. Air intake lip (4a) (4) of nacelle (1) of a turbojet, characterized in that it can be obtained by a method according to any one of claims 1 to 11.
EP12704882.5A 2011-01-28 2012-01-20 Process of manufacturing a turbojet engine nacelle part Withdrawn EP2668025A1 (en)

Applications Claiming Priority (2)

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FR1150654A FR2970899B1 (en) 2011-01-28 2011-01-28 PROCESS FOR MANUFACTURING A ROOM OF TURBOREACTOR NACELLE
PCT/FR2012/050126 WO2012101364A1 (en) 2011-01-28 2012-01-20 Process of manufacturing a turbojet engine nacelle part

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EP (1) EP2668025A1 (en)
CN (1) CN103338915A (en)
BR (1) BR112013016819A2 (en)
CA (1) CA2825116A1 (en)
FR (1) FR2970899B1 (en)
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FR2988407B1 (en) * 2012-03-22 2014-10-31 Aircelle Sa METHOD FOR MANUFACTURING A MONOBLOC PREFORM FOR COMPOSITE STRUCTURE
US9725190B2 (en) * 2015-02-13 2017-08-08 The Boeing Company Aircraft engine inlet assembly apparatus
FR3092871B1 (en) * 2019-02-15 2022-02-25 Airbus Operations Sas METHOD FOR ASSEMBLING AN AIR INTAKE OF AN AIRCRAFT TURBOJET

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US4147822A (en) * 1976-06-24 1979-04-03 Mcdonnell Douglas Corporation Composite structure and process and apparatus for making the same
FR2740383B1 (en) * 1995-10-27 1998-01-16 Aerospatiale METHOD FOR MANUFACTURING A COMPOSITE MATERIAL PANEL WITH RESIN TRANSFER MOLDING
EP1764307A1 (en) * 2005-09-14 2007-03-21 EADS Construcciones Aeronauticas, S.A. Process for manufacturing a monolithic leading edge
US20100080980A1 (en) * 2008-09-30 2010-04-01 Mra Systems, Inc. Molding process for core-containing composites and composites formed thereby
FR2948098B1 (en) * 2009-07-17 2011-07-22 Aircelle Sa ATTACK EDGE STRUCTURE, IN PARTICULAR FOR AN AIRCRAFT ENGINE NACELLE AIR INTAKE

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US20140026974A1 (en) 2014-01-30
CN103338915A (en) 2013-10-02
FR2970899A1 (en) 2012-08-03
CA2825116A1 (en) 2012-08-02
RU2013138867A (en) 2015-03-10
WO2012101364A1 (en) 2012-08-02
FR2970899B1 (en) 2014-08-22

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