WO2013007937A2 - Procede de fabrication d'un carter de soufflante de turbomachine muni de revetement acoustique. - Google Patents
Procede de fabrication d'un carter de soufflante de turbomachine muni de revetement acoustique. Download PDFInfo
- Publication number
- WO2013007937A2 WO2013007937A2 PCT/FR2012/051611 FR2012051611W WO2013007937A2 WO 2013007937 A2 WO2013007937 A2 WO 2013007937A2 FR 2012051611 W FR2012051611 W FR 2012051611W WO 2013007937 A2 WO2013007937 A2 WO 2013007937A2
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- WO
- WIPO (PCT)
- Prior art keywords
- coating
- fibrous
- casing
- acoustic
- acoustic coating
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
- B29C70/06—Fibrous reinforcements only
- B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
- B29C70/088—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers and with one or more layers of non-plastics material or non-specified material, e.g. supports
-
- 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
- B29C70/06—Fibrous reinforcements only
- B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
-
- 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
-
- 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
- B29C70/86—Incorporated in coherent impregnated reinforcing layers, e.g. by winding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
-
- 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
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B11/00—Making preforms
- B29B11/14—Making preforms characterised by structure or composition
- B29B11/16—Making preforms characterised by structure or composition comprising fillers or reinforcement
-
- 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
- B29C70/462—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/40—Organic materials
- F05D2300/44—Resins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/614—Fibres or filaments
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/70—Treatment or modification of materials
- F05D2300/701—Heat treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/70—Treatment or modification of materials
- F05D2300/702—Reinforcement
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- 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
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49327—Axial blower or fan
Definitions
- a method of manufacturing a turbomachine fan casing with acoustic coating is described.
- the invention relates to a method for manufacturing a turbomachine fan casing, in particular for an aeronautical engine.
- the fan casing fulfills several functions. It defines the engine's air inlet vein, supports an abradable coating opposite the fan's blade tips, incorporates or supports a debris trap retention shield and supports a sound wave absorption structure for acoustic treatment at the motor input.
- acoustic panels on the internal face of the casing, in the downstream part and / or in the upstream part thereof, that is to say on one side or on either side of an abradable coating.
- the panels are in the form of juxtaposed sectors each extending over a portion of the inner periphery of the housing and the panels are fixed to the housing by means of inserts integrated into the panels and screws.
- Such a method of fixing acoustic panels has several disadvantages. It requires the use of a large number of small parts (inserts and screws). In addition, repeated drilling of the composite material housing can affect the mechanical properties of the composite material.
- the object of the invention is to avoid such drawbacks and proposes for this purpose a method of manufacturing a turbomachine fan casing provided on its inner face with an abradable coating extending over part of its axial dimension to distance of the upstream and downstream ends of the casing and acoustic coating disposed downstream and / or upstream of the abradable coating, the internal surfaces of the abradable coating and the acoustic coating defining at least in part the wall of a d air inlet, the housing being made of composite material comprising a fiber reinforcement densified by a resin precursor matrix, in which process:
- a fibrous structure intended to constitute a fibrous reinforcement of an internal skin made of composite material of the acoustic coating is deposited on the tooling element at a location corresponding to that of the acoustic coating;
- a fibrous preform intended to constitute the fibrous reinforcement of the casing is shaped on the tooling element with the interposition of the cellular structures of the acoustic coating;
- the fibrous preform of the casing maintained in its shape and impregnated with a precursor resin of the matrix of the composite material of the casing and the fibrous structure of the inner skin of the acoustic coating impregnated with a precursor resin of the matrix of the composite material of said inner skin; are subjected to the same heat treatment of resin polymerization, and
- a multiperforation of the internal skin of the acoustic coating is performed after polymerization of the resin precursor of the matrix of the composite material of said inner skin,
- An acoustic coating comprising a plurality of cellular structures forming sectors or panels with a multiperforated inner skin which reproduces the profile of the tooling element and thus precisely defines the air intake stream at the level of the acoustic coating.
- Profile irregularities due to deformations or geometric variations of prefabricated acoustic panels reported on a housing of prefabricated composite material are thus avoided.
- the same resin can be used for the matrix of the composite material of the inner skin of the acoustic coating and for the matrix of the composite material of the housing.
- the fibrous preform intended to constitute the fibrous reinforcement of the casing is shaped on the tooling element with further interposition of constituent elements of abradable coating cartridges so that after polymerization a set is obtained comprising the casing. with cartridges of abradable coating and acoustic coating integrated.
- An adhesive layer may be interposed between, on the one hand, the honeycomb structures of the acoustic coating and any cartridges of abradable coating and, on the other hand, the fibrous preform of the housing.
- a fibrous layer of galvanic isolation can be interposed between, on the one hand, the honeycomb structures of the acoustic coating and possible abradable coating cartridges and, on the other hand, the fibrous preform of the casing.
- This layer also has a protective function of the structure of the casing in case of retouching or repair of the acoustic coating or abradable coating.
- An adhesive coating may be interposed between the fibrous structure intended to constitute the fibrous reinforcement of the inner skin of the acoustic coating and the cellular structures of the acoustic coating.
- the fibrous preform forming the fibrous reinforcement of the casing and the fibrous structure forming the fibrous reinforcement of the inner skin of the acoustic coating are formed by fibrous textures pre-impregnated with resin.
- the resin impregnation of the fibrous preform intended to form the fibrous reinforcement of the casing as well as the resin impregnation of the fibrous structure intended to form the fibrous reinforcement of the internal skin of the acoustic coating. are performed after shaping the fiber preform.
- FIG. 1 is a very schematic view of an aircraft engine turbine engine
- FIGS. 2 and 3 are very schematic axial half-views of fan casings that can be made according to the invention for a turbomachine such as that of FIG. 1;
- FIGS. 4A to 4D illustrate successive steps for manufacturing a fan casing such as that of FIG. 2, according to a first embodiment of the invention.
- FIGS. 5A to 5C illustrate the successive steps of manufacturing a fan casing such as that of FIG. 2, according to a second embodiment of the invention. Detailed Description of the Embodiments
- such a turbomachine comprises, from upstream to downstream in the flow direction of the gas flow, a fan 1 disposed at the inlet of the turbomachine, a compressor 2, a combustion chamber 3 , a tall turbine pressure (HP) 4 and a low pressure turbine (LP) 5.
- the turbines 4 and 5 are respectively coupled to the compressor 2 and the fan 1 by respective coaxial shafts.
- the turbomachine is housed in a housing comprising several parts corresponding to different of its elements.
- the fan 1 is surrounded by a fan casing 10.
- the casing 10 has at its ends flanges 13, 14 and has in its portion located opposite the blade tips 11 of the blower an excess thickness forming retaining shield 15.
- the flanges 13, 14 allow the attachment of the fan casing.
- the retention shield 15 is a debris trap projected by centrifugation to prevent them from passing through the housing and reach other parts of the aircraft.
- the casing 10 is provided on its inner face with an abradable coating.
- the coating may be formed by a set of panels 12, or cartridges, juxtaposed, fixed to the housing 10 and lined with abradable material as described for example in the document EP 2 088 290.
- the casing 10 is provided on its inner face with at least one soundproofing coating or acoustic coating.
- the acoustic coating 20 is disposed in the downstream portion of the housing 10 between the abradable coating and the downstream end of the housing, while in its upstream portion, between its upstream end and the abradable coating, the housing 10 is shaped to define, with the internal surfaces of the abradable coating cartridges 12 and the acoustic coating 20, a substantially continuous wall air inlet vein.
- two acoustic coatings 20, 20 ' are provided, one disposed in the downstream portion of the housing 10, as in the case of Figure 2, and the other 20' disposed in the upstream portion of the housing 10 between its upstream end and the abradable coating 12, the internal surfaces of the coating 20 ', abradable coating cartridges 12 and the coating 20 defining the air inlet vein.
- An axisymmetric shape 30 is used whose outer surface 31 has a profile that reproduces that of the air inlet duct along the casing 10 of the turbomachine and which has flanges 33, 34 at its ends.
- the form 30 is in several parts assembled to allow its disassembly.
- An adhesive layer or adhesive film 42 for example epoxy resin, polyurethane or polyimide is preferably deposited on the fibrous structure 41 and on the shape 30 at the location of the abradable coating cartridges.
- honeycomb structures 21 of the acoustic coating are arranged on the adhesive film 42, above the fibrous structure 41 (FIG. 4B).
- Each honeycomb structure 21 forms a panel that extends over a sector around the axis of the shape 30, the honeycomb structures 21 being juxtaposed to cover the entire periphery of the shape 30 at the level of the fabric layers 41.
- honeycomb structures 21 such as honeycomb structures whose cells are delimited by radially extending walls.
- Abradable coating cartridges 12 are disposed on the adhesive film 42 at a location corresponding to that of the abradable coating. Each cartridge extends over a sector around the axis of the shape 30, the cartridges 12 being juxtaposed. For example, 4, 5 or 6 cartridges can be used.
- each cartridge 12 may comprise, on the exposed internal side, a honeycomb structure, for example honeycomb "Nomex" filled with material abradable and bonded to an aluminum honeycomb or "Nomex", possibly with interposition of glass cloth.
- the honeycomb "Nomex" can be replaced by a fibrous layer on which abradable material is deposited.
- the adhesive layer 42 facilitates the retention in place of the cellular structures 21 and the cartridges 12.
- an adhesive layer or adhesive film 45 is optionally deposited on the cellular structures 21 and the cartridges 12 and may be covered with at least one layer of fabric 46 (Figure 4C).
- the fabric layer 46 allows, if necessary, to provide a galvanic isolation between the housing, on the one hand, and the abradable coating cartridges and the acoustic coating, on the other hand. It also contributes to the protection of the housing structure in the event of retouching or repair of an abradable coating cartridge or part of the acoustic coating.
- the fabric layer may be fiberglass or other insulating material.
- the tissue layer 46 may also contribute to forming the outer skin thereof. Alternatively, this outer skin could be integrated with the honeycomb structures 21.
- the fibrous preform 50 of the casing 10 can be obtained by winding in several superimposed layers or turns of a fibrous texture 47 made for example by three-dimensional weaving or multilayer, as described in the document EP 1 961 923 and pre-impregnated with a resin.
- a fibrous texture with a progressive thickness is used, for example by varying the number of layers of warp and weft threads in the fabric to form an extra thickness 48 at the location of the retention shield.
- the fibrous preform 50 can be obtained by layering two-dimensional fabric layers or by braiding.
- the fibers of the fibrous structure 41 and the fibrous texture 47 are, for example, carbon, glass, aramid or ceramic.
- Each impregnating resin of the fibrous structure 41, the fibrous texture 47 and optionally the tissue layer 46 is, for example, a polymer matrix precursor resin such as an epoxide, bismaleimide or polyimide polymer. Different resins can be used to impregnate the fibrous structure 41, the fibrous texture 47 and the tissue layer 46. However, the same resin will preferably be used.
- Multi-sector tooling elements 35 are applied to the outer surface of the preform 50 (FIG. 4D) to maintain it in the desired shape and a polymerization heat treatment of the impregnating resin (s) is made.
- the adhesive layer 45 is for example made of epoxy resin and is optionally crosslinked during the heat treatment of polymerization of the impregnating resin (s). It is preferably present to ensure an effective connection between the housing, on the one hand, and the abradable coating cartridges and alveolar structures of the acoustic coating, on the other hand.
- the resulting casing provided with the abradable coating cartridges and the acoustic coating is extracted from the tooling constituted by the shape 30 and the elements 35.
- a final machining is carried out comprising in particular the multiperforation of the internal skin 23 of the acoustic coating and the formation of holes in the crankcase fixing flanges.
- FIGS. 5A to 5C illustrate another embodiment of the method according to the invention, the elements common to the embodiment of FIGS. 4A to 4D bearing the same references.
- FIGS. 4A to 4D A shape similar to that of the embodiment of FIGS. 4A to 4D is used.
- One or more layers of fabric forming a fibrous structure 41 intended to constitute the fibrous reinforcement of the internal skin made of composite material of the acoustic coating are deposited on the form 30 as in the case of FIG. 4A, but without pre-impregnation with a resin .
- honeycomb structures provided with an outer skin 22 are placed on the form 30, as well as abradable coating cartridges such as the cartridges 12 described above. ( Figure 5A).
- At least one layer 46 of non-pre-impregnated fabric of galvanic isolation and protection may be placed on the outer skin 22 of the honeycomb structures, the panels 20 and on the cartridges 12 with the interposition of a layer of adhesive or glue film 45 as described more high, then the fibrous preform 50 of the casing is made as described above but from a fibrous texture 47 not pre-impregnated with resin (Figure 5B).
- Multi-sector tooling elements 35 are applied to the outer surface of the preform 50 (FIG. 5C), these tooling elements being provided with channels (not shown) for injection or infusion of resin into the preform 50, the fibrous structure 41 and the eventual tissue layer 46.
- the resin is then polymerized and the resulting casing provided with the abradable coating cartridges and the acoustic coating is subjected to a final machining comprising the multi-perforation of the inner skin of the acoustic coating.
- the alveolar structures placed on the adhesive film 42 may possibly not be provided with external skin, as in the case of the elements 21 of Figure 4C.
- these cells may be filled with a material that can be subsequently removed or evacuated, for example "Teflon".
- Teflon a material that can be subsequently removed or evacuated
- the removal or disposal of this material is performed after formation and multiperforation of the inner skin of the acoustic coating.
- the method can easily be adapted to the production of a fan casing provided with acoustic coating in its upstream and downstream parts, as shown in FIG.
- blower housing forming an assembly with abradable coating cartridges and at least one acoustic coating.
- the manufacturing process can be implemented to manufacture a fan casing forming an assembly with only at least one acoustic coating, when the abradable coating is not in the form of cartridges but a layer of abradable material deposited directly on the internal face of the housing.
- the casing preform for the production of the casing preform, use is advantageously made of a shape having a geometry adapted to reserve the location of deposition of abradable material after manufacture of the casing.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Composite Materials (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1400494.9A GB2506321B (en) | 2011-07-13 | 2012-07-09 | Method for manufacturing a turbine-engine fan casing having an acoustic coating |
US14/232,514 US9316120B2 (en) | 2011-07-13 | 2012-07-09 | Method for manufacturing a turbine-engine fan casing having an acoustic coating |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1156446 | 2011-07-13 | ||
FR1156446A FR2977827B1 (fr) | 2011-07-13 | 2011-07-13 | Procede de fabrication d'un carter de soufflante de turbomachine muni de revetements abradable et acoustique |
Publications (3)
Publication Number | Publication Date |
---|---|
WO2013007937A2 true WO2013007937A2 (fr) | 2013-01-17 |
WO2013007937A3 WO2013007937A3 (fr) | 2013-03-28 |
WO2013007937A8 WO2013007937A8 (fr) | 2014-01-30 |
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PCT/FR2012/051611 WO2013007937A2 (fr) | 2011-07-13 | 2012-07-09 | Procede de fabrication d'un carter de soufflante de turbomachine muni de revetement acoustique. |
Country Status (4)
Country | Link |
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US (1) | US9316120B2 (fr) |
FR (1) | FR2977827B1 (fr) |
GB (1) | GB2506321B (fr) |
WO (1) | WO2013007937A2 (fr) |
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WO2017203135A1 (fr) * | 2016-05-24 | 2017-11-30 | Safran Aircraft Engines | Procédé de fabrication d'un carter à revêtement abradable de turbomachine |
CN109312627A (zh) * | 2016-05-24 | 2019-02-05 | 赛峰飞机发动机公司 | 用于制造装备涡轮机的环形壳体的方法 |
CN112739530A (zh) * | 2018-09-05 | 2021-04-30 | 赛峰航空器发动机 | 具有一体化加强件的复合材料壳体 |
FR3115315A1 (fr) * | 2020-10-15 | 2022-04-22 | Safran Aircraft Engines | Fixation d’un abradable sur une virole externe de turbomachine |
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FR3016187B1 (fr) * | 2014-01-09 | 2016-01-01 | Snecma | Protection contre le feu d'un carter de soufflante en materiau composite |
BE1022471B1 (fr) * | 2014-10-10 | 2016-04-15 | Techspace Aero S.A. | Carter externe de compresseur de turbomachine axiale avec joint d'etancheite |
FR3028882B1 (fr) * | 2014-11-20 | 2021-05-28 | Snecma | Procede de realisation d'un revetement abradable multicouches avec structure tubulaire integree, et revetement abradable obtenu par un tel procede |
US10030540B2 (en) * | 2014-11-25 | 2018-07-24 | Rolls-Royce North American Technologies Inc. | Fan case liner removal with external heat mat |
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EP1961923A2 (fr) | 2007-02-23 | 2008-08-27 | Snecma | Procédé de fabrication d'un carter de turbine à gaz en matériau composite et carter ainsi obtenu. |
EP2088290A1 (fr) | 2007-12-14 | 2009-08-12 | Snecma | Panneau de support d'abradable dans une turbomachine |
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RU2703206C2 (ru) * | 2014-08-22 | 2019-10-15 | Сафран Эркрафт Энджинз | Самоусиленный корпус, состоящий из композиционного материала с органической матрицей |
US11306608B2 (en) | 2014-08-22 | 2022-04-19 | Safran Aircraft Engines | Self-stiffened casing consisting of a composite material with an organic matrix |
WO2016027030A1 (fr) * | 2014-08-22 | 2016-02-25 | Snecma | Carter en matériau composite à matrice organique auto-raidi |
FR3031469A1 (fr) * | 2015-01-14 | 2016-07-15 | Snecma | Carter en materiau composite a matrice organique auto-raidi |
CN109312628B (zh) * | 2016-05-24 | 2021-08-24 | 赛峰飞机发动机公司 | 用于制造具有可磨耗涂层的涡轮发动机壳体的方法 |
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US11002145B2 (en) | 2016-05-24 | 2021-05-11 | Safran Aircraft Engines | Method for manufacturing a turbine engine casing with abradable coating |
CN109312627B (zh) * | 2016-05-24 | 2021-07-16 | 赛峰飞机发动机公司 | 用于制造装备涡轮机的环形壳体的方法 |
CN109312628A (zh) * | 2016-05-24 | 2019-02-05 | 赛峰飞机发动机公司 | 用于制造具有可磨耗涂层的涡轮发动机壳体的方法 |
WO2017203135A1 (fr) * | 2016-05-24 | 2017-11-30 | Safran Aircraft Engines | Procédé de fabrication d'un carter à revêtement abradable de turbomachine |
CN112739530A (zh) * | 2018-09-05 | 2021-04-30 | 赛峰航空器发动机 | 具有一体化加强件的复合材料壳体 |
CN112739530B (zh) * | 2018-09-05 | 2022-09-23 | 赛峰航空器发动机 | 具有一体化加强件的复合材料壳体 |
FR3115315A1 (fr) * | 2020-10-15 | 2022-04-22 | Safran Aircraft Engines | Fixation d’un abradable sur une virole externe de turbomachine |
Also Published As
Publication number | Publication date |
---|---|
GB201400494D0 (en) | 2014-02-26 |
WO2013007937A8 (fr) | 2014-01-30 |
FR2977827A1 (fr) | 2013-01-18 |
WO2013007937A3 (fr) | 2013-03-28 |
GB2506321B (en) | 2016-08-17 |
FR2977827B1 (fr) | 2015-03-13 |
US9316120B2 (en) | 2016-04-19 |
US20140150262A1 (en) | 2014-06-05 |
GB2506321A (en) | 2014-03-26 |
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