WO2012101364A1 - Procédé de fabrication d'une pièce de nacelle de turboréacteur - Google Patents
Procédé de fabrication d'une pièce de nacelle de turboréacteur Download PDFInfo
- Publication number
- WO2012101364A1 WO2012101364A1 PCT/FR2012/050126 FR2012050126W WO2012101364A1 WO 2012101364 A1 WO2012101364 A1 WO 2012101364A1 FR 2012050126 W FR2012050126 W FR 2012050126W WO 2012101364 A1 WO2012101364 A1 WO 2012101364A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- manufacturing
- lip
- resin
- air intake
- nacelle
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract description 24
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 15
- 239000000470 constituent Substances 0.000 claims abstract description 14
- 238000000465 moulding Methods 0.000 claims abstract description 7
- 239000011347 resin Substances 0.000 claims description 16
- 229920005989 resin Polymers 0.000 claims description 16
- 239000003351 stiffener Substances 0.000 claims description 6
- 238000002347 injection Methods 0.000 claims description 5
- 239000007924 injection Substances 0.000 claims description 5
- 230000001413 cellular effect Effects 0.000 claims description 4
- 238000001802 infusion Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 238000001721 transfer moulding Methods 0.000 claims description 2
- 239000002759 woven fabric Substances 0.000 claims description 2
- 229920000049 Carbon (fiber) Polymers 0.000 claims 2
- 239000004917 carbon fiber Substances 0.000 claims 2
- 239000006260 foam Substances 0.000 claims 1
- 238000005470 impregnation Methods 0.000 abstract 1
- 238000005192 partition Methods 0.000 description 7
- 238000011144 upstream manufacturing Methods 0.000 description 5
- 239000002131 composite material Substances 0.000 description 3
- 230000005465 channeling Effects 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000006116 polymerization reaction Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000009958 sewing Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
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 stiffening element or elements consist of folds of fabric or braid, with parts folded vis-à-vis the outer wall or internal part.
- 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.
- 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)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN2012800067674A CN103338915A (zh) | 2011-01-28 | 2012-01-20 | 涡轮喷气发动机舱部件的制造方法 |
CA 2825116 CA2825116A1 (fr) | 2011-01-28 | 2012-01-20 | Procede de fabrication d'une piece de nacelle de turboreacteur |
RU2013138867/05A RU2013138867A (ru) | 2011-01-28 | 2012-01-20 | Способ изготовления детали гондолы турбореактивного двигателя |
EP12704882.5A EP2668025A1 (fr) | 2011-01-28 | 2012-01-20 | Procédé de fabrication d'une pièce de nacelle de turboréacteur |
BR112013016819A BR112013016819A2 (pt) | 2011-01-28 | 2012-01-20 | método de fabricação de um lábio de entrada de ar de nacela e lábio de entrada de ar de nacela de turbina de motor a jato |
US13/953,368 US20140026974A1 (en) | 2011-01-28 | 2013-07-29 | Process of manufacturing a turbojet engine nacelle part |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1150654A FR2970899B1 (fr) | 2011-01-28 | 2011-01-28 | Procede de fabrication d'une piece de nacelle de turboreacteur |
FR11/50654 | 2011-01-28 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/953,368 Continuation US20140026974A1 (en) | 2011-01-28 | 2013-07-29 | Process of manufacturing a turbojet engine nacelle part |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2012101364A1 true WO2012101364A1 (fr) | 2012-08-02 |
Family
ID=45688899
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/050126 WO2012101364A1 (fr) | 2011-01-28 | 2012-01-20 | Procédé de fabrication d'une pièce de nacelle de turboréacteur |
Country Status (8)
Country | Link |
---|---|
US (1) | US20140026974A1 (fr) |
EP (1) | EP2668025A1 (fr) |
CN (1) | CN103338915A (fr) |
BR (1) | BR112013016819A2 (fr) |
CA (1) | CA2825116A1 (fr) |
FR (1) | FR2970899B1 (fr) |
RU (1) | RU2013138867A (fr) |
WO (1) | WO2012101364A1 (fr) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2988407B1 (fr) * | 2012-03-22 | 2014-10-31 | Aircelle Sa | Procede de fabrication d'une preforme monobloc pour structure composite |
US9725190B2 (en) * | 2015-02-13 | 2017-08-08 | The Boeing Company | Aircraft engine inlet assembly apparatus |
FR3092871B1 (fr) * | 2019-02-15 | 2022-02-25 | Airbus Operations Sas | Procede d’assemblage d’une entree d’air d’un turboreacteur d’aeronef |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0770472A1 (fr) * | 1995-10-27 | 1997-05-02 | AEROSPATIALE Société Nationale Industrielle | Procédé de fabrication d'un panneau en matériau composite avec moulage par transfert de resine |
WO2011007074A1 (fr) * | 2009-07-17 | 2011-01-20 | Aircelle | Structure de bord d'attaque notamment pour entree d'air de nacelle de moteur d'aeronef |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4147822A (en) * | 1976-06-24 | 1979-04-03 | Mcdonnell Douglas Corporation | Composite structure and process and apparatus for making the same |
EP1764307A1 (fr) * | 2005-09-14 | 2007-03-21 | EADS Construcciones Aeronauticas, S.A. | Procédé de fabrication d'un bord d'attaque monolithique |
US20100080980A1 (en) * | 2008-09-30 | 2010-04-01 | Mra Systems, Inc. | Molding process for core-containing composites and composites formed thereby |
-
2011
- 2011-01-28 FR FR1150654A patent/FR2970899B1/fr not_active Expired - Fee Related
-
2012
- 2012-01-20 RU RU2013138867/05A patent/RU2013138867A/ru not_active Application Discontinuation
- 2012-01-20 WO PCT/FR2012/050126 patent/WO2012101364A1/fr active Application Filing
- 2012-01-20 BR BR112013016819A patent/BR112013016819A2/pt not_active IP Right Cessation
- 2012-01-20 EP EP12704882.5A patent/EP2668025A1/fr not_active Withdrawn
- 2012-01-20 CA CA 2825116 patent/CA2825116A1/fr not_active Abandoned
- 2012-01-20 CN CN2012800067674A patent/CN103338915A/zh active Pending
-
2013
- 2013-07-29 US US13/953,368 patent/US20140026974A1/en not_active Abandoned
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0770472A1 (fr) * | 1995-10-27 | 1997-05-02 | AEROSPATIALE Société Nationale Industrielle | Procédé de fabrication d'un panneau en matériau composite avec moulage par transfert de resine |
WO2011007074A1 (fr) * | 2009-07-17 | 2011-01-20 | Aircelle | Structure de bord d'attaque notamment pour entree d'air de nacelle de moteur d'aeronef |
Also Published As
Publication number | Publication date |
---|---|
CA2825116A1 (fr) | 2012-08-02 |
FR2970899B1 (fr) | 2014-08-22 |
RU2013138867A (ru) | 2015-03-10 |
BR112013016819A2 (pt) | 2017-04-04 |
US20140026974A1 (en) | 2014-01-30 |
FR2970899A1 (fr) | 2012-08-03 |
EP2668025A1 (fr) | 2013-12-04 |
CN103338915A (zh) | 2013-10-02 |
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