• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A method of manufacturing a casing (100) of variable thickness composite material for a gas turbine comprises: - the production by three-dimensional weaving or multilayer of a fibrous texture (140) in the form of a strip, - the winding the fibrous texture (140) in several superimposed layers (141, 142, 143, 144) on a mandrel (200) of profile corresponding to that of the casing to be manufactured, in order to obtain a fiber preform (300) of corresponding shape to that of the casing to be manufactured, - the densification of the fibrous preform (300) by a matrix. During winding of the fibrous texture (140) on the mandrel, a textile web (150) is interposed between the adjacent turns of the fibrous texture, the textile web (150) having a width less than the width of the fibrous texture (140) and defining a crankcase retention zone.
    公开号:FR3045448A1
    申请号:FR1563102
    申请日:2015-12-22
    公开日:2017-06-23
    发明作者:Hubert Jean Marie Fabre；Jeremy Hellot；Antoine Phelippeau
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    BACKGROUND OF THE INVENTION The invention relates to gas turbine casings, and more particularly, but not exclusively, gas turbine fan casings for aeronautical engines.
    In a gas turbine engine, the fan housing performs several functions. It defines the air inlet duct in the engine, supports an abradable material facing the fan blade tips, supports a possible sound wave absorption structure for acoustic processing at the engine inlet and incorporates or support a retention shield. The retention shield is a debris trap holding debris, such as ingested objects or damaged blade fragments, projected by centrifugation to prevent them from passing through the crankcase and reaching other parts of the aircraft .
    Previously made of metallic material, the housings, such as the fan casing, are now made of composite material, that is to say from a fiber preform densified by an organic matrix, which makes it possible to produce parts having a lower overall mass than these same parts when they are made of metallic material while having a mechanical strength at least equivalent if not greater.
    The manufacture of a fan casing made of organic matrix composite material is described in particular in document US 2013/082417. In the casing disclosed in the document US 2013/082417, the retaining shield is constituted by a portion of extra thickness obtained at the fibrous reinforcement of the casing which has a progressive thickness. The fibrous reinforcement is obtained by winding a 3D woven fibrous texture in which a gradual increase in thickness is obtained by changing the size of the warp yarns or strands.
    FIG. 8 illustrates a fan casing 50 of composite material which comprises a retaining zone or shield 51 which constitutes the thickest portion of the casing, the portion in which the fiber reinforcement comprises large-diameter warp wires or strands. The retention zone 51 is surrounded by two adjacent transition zones 52 and 53 which comprise both large-diameter warp yarns or strands as in the portion 51 and smaller diameter warp yarns or strands. The proportion of warp yarns increases progressively in the portions 52 and 53 as they approach the retention zone 51. Finally, the casing 50 comprises portions 54 and 55 farther away from the zone. retention 51 which comprise only small diameter strands or warp threads.
    However, with this manufacturing technique, the thickening of the fibrous reinforcement in the retention zone is limited by the weability of a texture comprising strands of too large (or too small) diameter (limit of wearability for 3D woven fabrics), on the one hand, and on the other hand, by the maximum allowable ratio-to-frame ratio (RCT). Regarding this last point, in the case for example of the manufacture of a housing, the weft son are continuous so that, as soon as we change the size or contexture of the warp son, the RCT is automatically changed.
    Object and summary of the invention
    It is therefore desirable to have a solution to have a composite material housing which comprises a retention zone whose maximum amplitude of the extra thickness is not imposed by a limit of wearability and in which the chain ratio -frame can be controlled so as not to exceed a specified maximum threshold. For this purpose, according to the invention, there is provided a method of manufacturing a variable thickness composite material casing for a gas turbine, comprising: the realization by three-dimensional or multi-layer weaving of a fibrous texture in the form of a strip, the winding of the fibrous texture in several layers superimposed on a profile mandrel corresponding to that of the casing to be manufactured, in order to obtain a form of fiber preform corresponding to that of the casing to be manufactured, the densification of the fibrous preform by a matrix, characterized in that, during the winding of the fibrous texture on the mandrel, a textile strip is interposed between the adjacent turns of the fibrous texture, the textile strip having a width less than the width of the fibrous texture and delimiting a crush retention zone.
    By thus interposing a textile layer between the adjacent layers of the fibrous texture used to form the fibrous reinforcement of the casing, it is possible to form in the casing a portion having a desired excess thickness capable of constituting a retention zone or shield while controlling the chain-to-frame ratio in this portion of the preform so that it does not exceed a predetermined value. Indeed, the textile band being independent of the fibrous texture, it is sufficient to adjust the chain-to-frame ratio in it to obtain the overall chain-to-frame ratio in the preform. In the case of the manufacture of a housing according to the method of the prior art described above, there is a quantity of weft son which is defined over the entire width of the preform (continuous frame) so that the increase of the size or number of warp strands has a direct impact on the warp / weft ratio. With the method of the invention, we add an independent textile band and therefore warp and weft son that can thicken the resulting preform without varying the chain-to-frame ratio. This is because the textile web, interposed in the wound fibrous texture, is of a width smaller than said texture that can have a "quantity" of width-variable weft yarns with a relatively stable RCT despite addition of warp threads.
    The method of the invention also makes it possible to obtain a large variation in thickness at a retention zone to be formed in the casing, which minimizes the overall mass of the resulting casing relative to a casing whose portion of extra thickness is achieved by increasing the size of the warp yarns or strands.
    The retention zone thus formed also reliably ensures its function, namely to retain debris, particles or objects ingested at the engine inlet, or from damage to the blades of the fan, and projected radially by rotation of the rotor. blowing against the crankcase.
    According to a particular characteristic of the process of the invention, the fibers may be chosen from at least one of the following types: carbon, glass, aramid and ceramic. According to another particular characteristic of the process of the invention, the textile strip is made with fibers of the same type as that of the fibers of the fibrous texture. This makes it possible to have a better coherence of mechanical behavior between the fibrous texture and the strip. while simplifying the choice of the matrix precursor to be injected into the preform.
    According to another particular characteristic of the invention, the textile strip is produced according to a three-dimensional weaving having the same weave as the three-dimensional weaving of the fibrous texture. This makes it possible to ensure efficient and homogeneous transmission of the forces between the fibrous texture layers and the interposed textile strip layers without zones of concentration of stresses or deformations.
    According to yet another particular characteristic of the invention, the textile band has a string-to-frame ratio substantially identical to that of the fibrous texture. In this case, the extra thickness portion of the fiber preform has a similar warp-to-weft ratio to that present in the other portions of the preform. The invention also proposes a gas turbine fan casing having a variable thickness and being made of a composite material with a fibrous reinforcement comprising a plurality of superimposed layers of a fibrous texture in the form of a strip having a three-dimensional or multilayer weave , said fibrous reinforcement being densified by a matrix, characterized in that a textile strip is interposed between two adjacent layers of the fibrous texture, the textile strip having a width less than the width of the fibrous texture and delimiting a retention zone of the casing .
    According to a particular characteristic of the casing of the invention, the fibers of the fibrous texture and the fibers of the textile strip are chosen from at least one of the following types: carbon, glass, aramid and ceramic.
    According to another particular characteristic of the casing of the invention, the textile strip is made with fibers of the same type as that of the fibers of the fibrous texture.
    According to yet another particular characteristic of the casing of the invention, the textile band has a three-dimensional weave having the same weave weave as three-dimensional weaving of the fibrous texture.
    According to yet another particular characteristic of the casing of the invention, the textile band has a string-to-frame ratio substantially identical to that of the fibrous texture.
    According to still another particular characteristic of the casing of the invention, the fibrous reinforcement comprises n layers of fibrous texture corresponding to n turns of winding of said fibrous texture and n-1 layers of textile strip corresponding to n-1 winding turns of said textile web. The subject of the invention is also an aeronautical gas turbine engine having a fan casing according to the invention.
    BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the invention will emerge from the following description of particular embodiments of the invention, given by way of non-limiting example, with reference to the appended drawings, in which: FIG. 1 is a perspective view in partial section of an aeronautical engine equipped with a composite material fan casing according to one embodiment of the invention, FIG. 2 is a sectional view along plane II-II of FIG. FIG. 3 is a schematic perspective view of a loom showing the weaving of a fibrous texture used for forming the fibrous reinforcement of the casing of FIGS. 1 and 2, FIG. in perspective showing the shaping of a fibrous texture and a textile strip intended to form the reinforcement of the fan casing of FIGS. 1 and 2, FIG. 5 is a schematic view showing the hoist 4 is a sectional view showing the profile of the fibrous preform obtained after winding up the fibrous structure and the textile strip of FIGS. 4 and 5; Figure 7 is a schematic view showing a tool for densifying with a matrix the fiber preform of Figure 6, Figure 8 is a schematic sectional view of a composite material housing according to the prior art.
    DETAILED DESCRIPTION OF EMBODIMENTS The invention will be described hereinafter in the context of its application to a gas turbine engine turbine engine fan casing.
    Such an engine, as shown very schematically in FIG. 1 comprises, from upstream to downstream in the direction of flow of gas flow, a fan 1 disposed at the engine inlet, a compressor 2, a combustion chamber 3, a high-pressure turbine 4 and a low-pressure turbine 5.
    The engine is housed inside a housing comprising several parts corresponding to different elements of the engine. Thus, the fan 1 is surrounded by a fan casing 100.
    FIG. 2 shows a fan casing profile 100 made of composite material as it can be obtained by a method according to the invention. The inner surface 101 of the casing defines the air inlet vein. It may be provided with an abradable coating layer 102 at the right of the trajectory of the blade tips of the fan, a blade 13 being partially shown very schematically. The abradable coating is thus disposed on only part of the length (in the axial direction) of the casing. An acoustic treatment coating (not shown) may also be disposed on the inner surface 101, in particular upstream of the abradable coating 102.
    The housing 100 may be provided with external flanges 104, 105 at its upstream and downstream ends to allow its mounting and its connection with other elements. Between its upstream and downstream ends, the housing 100 has a variable thickness, a thickening portion 110 of the housing having a greater thickness than the end portions 120 and 130 progressively connecting thereto.
    The portion of extra thickness 110 extends on either side of the location of the fan, upstream and downstream, to form a retention zone or shield capable of holding debris, particles or objects ingested at the engine inlet, or from damage to the blades of the fan, and projected radially by rotation of the fan, to prevent them through the housing and damage other parts of the aircraft.
    The housing 100 is made of composite material with fiber reinforcement densified by a matrix. The reinforcement is made of fibers, for example carbon, glass, aramid or ceramic, and the matrix is made of polymer, for example epoxide, bismaleimide or polyimide, carbon or ceramic.
    The fibrous reinforcement is formed by winding on a mandrel a fibrous texture produced by three-dimensional weaving with evolutionary thickness, the mandrel having a profile corresponding to that of the casing to be produced. Advantageously, the fibrous reinforcement constitutes a complete tubular fibrous preform of the housing 100 formed in one piece with reinforcing portions corresponding to the flanges 104, 105.
    According to the invention, the fibrous reinforcement of the casing 100 consists of a plurality of superimposed layers 141 to 144 of a fibrous texture 140 in the form of a strip having a three-dimensional or multilayer weave, each layer 141 to 144 corresponding to a winding turn of the fibrous texture 140 (in FIG. 2 the layers 141 to 144 are densified by a matrix). In addition, a textile strip 150 is interposed between two adjacent layers of the fibrous texture, the textile strip 150 having a width less than the width Imo lof the fibrous texture 140 (Figure 4) and defining the retention area of the housing 100. In the example described here, three layers 151 to 153 of textile strip 150 are interposed between the superposed layers 141 to 144 of the fibrous texture 140, each layer 151 to 153 corresponding to a winding turn of the textile strip 150. D In general, for n superposed fibrous texture layers each corresponding to a winding turn of said fibrous texture, there are n-1 layers of textile web each corresponding to a winding turn of said textile web.
    By thus interposing a layer of textile web between the adjacent layers of the fibrous texture used to form the fibrous reinforcement of the casing, it is possible to form a portion of extra thickness in the casing adapted to form a retention zone or shield while minimizing the overall mass of the resulting casing relative to a housing whose portion of extra thickness is achieved with a single fiber texture in which the size of the son or strand is increased to form a portion of extra thickness. As described below in detail, the housing according to the invention can be manufactured more economically than a housing whose variable thickness is made only with a fibrous texture whose size of the son or strand is varied. Indeed, in the latter case, it is necessary to use different types of son (son or strands with different titles) which increases the cost of supply son. By allowing the use of son or strands of the same type, the method of the invention thus reduces supply costs while simplifying the equipment required for weaving and winding. In addition, the method according to the invention makes it possible to produce more complex housing geometries, in particular in terms of thickness ratio because the variation in thickness no longer leads to a significant variation of the chain-to-frame ratio (RCT), the size of the warp and weft threads may be identical throughout the fibrous texture and in the textile band.
    The design of the casing according to the invention also makes it possible to obtain, apart from the portion of excess thickness, portions that are significantly thinner than those obtained with the housings made of composite material of the prior art. Indeed, in the casings of the prior art, the portions adjacent to the portion of extra thickness correspond to transition zones in which the size of the son or strands is gradually increased, which leads to an increase in the thickness of these portions. and the overall mass of the resulting casing.
    Preferably, but not exclusively, the textile strip may be made with fibers of the same type as those used to produce the fibrous texture, which makes it possible to have a coherence of mechanical behavior between the fibrous texture and the textile strip while simplifying the process. choice of the die precursor to be injected into the preform.
    Preferably, but not exclusively, the textile strip has the same three-dimensional weave weave as the fibrous texture, which makes it possible to ensure efficient and homogeneous transmission of the forces between the fibrous texture layers and the layers of interposed textile strip without concentration of stresses or deformations. Thus, the layers of the textile strip follow the movements of the layers of the fibrous texture without opposing it, that is to say without generating over stress, which would be more difficult with a textile band having a different weave weave. of that of the fibrous structure.
    Still more preferably but not exclusively, the textile web and the fibrous texture has a warp-to-weft ratio (RCT) substantially similar to that of the fiber texture. The percentage of variation of the RCT between the fibrous texture and the textile web is preferably ± 10%, preferably ± 5%, particularly preferably ± 2%. The overall RCT in the fibrous reinforcement of the casing is preferably between 35% and 85%.
    A method of manufacturing the fan casing 100 is now explained.
    As shown in FIG. 3, a fibrous texture 140 is made in known manner by weaving by means of a jacquard loom 10 on which a bundle of warp yarns or strands 20 has been arranged in a plurality of layers, the warp threads being bound by weft threads or strands 30. The fibrous texture is produced by three-dimensional weaving or multilayer weaving.
    By "three-dimensional weaving" or "3D weaving" is meant here a weaving mode whereby at least some of the weft yarns bind warp yarns on several layers of warp yarns or vice versa. An example of three-dimensional weaving is so-called "interlock" weaving. By "interlock" weaving is meant here a weave weave in which each layer of warp yarn binds several layers of weft yarns, with all the yarns of the same warp column having the same movement in the plane of the weave. armor.
    By "multilayer weaving" is meant here a 3D weave with several weft layers whose basic armor of each layer is equivalent to a conventional 2D fabric weave, such as a linen, satin or twill type armor, but with some points of the weave that bind the weft layers between them.
    The production of the fibrous texture by 3D or multilayer weaving makes it possible to obtain a bond between the layers, thus to have a good mechanical strength of the fibrous structure and of the composite material part obtained, in a single textile operation.
    3D or multilayer weaves may in particular correspond to a weave selected from one of the following armor: interlock, multi-fabric, multi-satin and multi-twill.
    By "multi-fabric weave or weave" is meant here a 3D weave with several layers of weft yarns whose basic weave of each layer is equivalent to a conventional linen-type weave but with certain points of the weave which bind the layers of weft threads together.
    By "multi-satin weave or fabric" is meant here a 3D weave with several layers of weft yarns whose basic weave of each layer is equivalent to a classic satin-like weave but with certain points of the weave which bind the layers of weft threads together.
    By "weave or multi-twill fabric" is meant here a 3D weave with several layers of weft threads whose basic armor of each layer is equivalent to a classic twill type armor but with some points of the armor that bind the layers of weft threads together.
    As illustrated in FIGS. 3 and 4, the fibrous texture 140 has a strip shape that extends in length in a direction X corresponding to the direction of travel of the warp yarns or strands 20 and in width or transversely in a Y direction corresponding to the direction of the weft yarns or strands 30.
    The fibrous structure may in particular be woven from carbon fiber type yarns, ceramic such as silicon carbide, glass, or aramid.
    The textile web 150 is independently woven from a Jacquard loom as described above. The textile strip is produced by three-dimensional weaving or multilayer with possibly fibers of the same type as those of the fibrous texture, the same three-dimensional weave weave as that of the fibrous texture and with a chain-to-frame ratio substantially identical to that of the texture fibrous.
    The fibrous texture and the textile web are stored on reels or drums for the purpose of their call during their joint winding under tension on a shaping tool.
    As illustrated in Figure 4, a fiber preform is formed by winding on a mandrel 200 of the fibrous texture 140 made by three-dimensional weaving, the mandrel having a profile corresponding to that of the housing to be produced. According to the invention, a textile band 150 is wound with the fibrous texture 140, the band 150 being positioned above the first layer 141 of the texture 140 wound on the mandrel 200 so as to interpose a layer of textile tape 150 of lower width between two adjacent layers of fibrous texture of greater width corresponding to two turns of winding fibrous texture 140. The band 150 is positioned at a location on the fibrous texture 140 corresponding to the retention zone to be formed in the housing .
    Advantageously, the fibrous preform constitutes a complete tubular fibrous reinforcement of the casing 100 formed in one piece with a portion of extra thickness corresponding to the retention zone of the casing. For this purpose, the mandrel 200 has an outer surface 201 whose profile corresponds to the inner surface of the housing to be produced. By winding it on the mandrel 200, the fibrous texture 140 matches the profile of the latter. The mandrel 200 also comprises two flanges 220 and 230 for forming fiber preform portions corresponding to the flanges 104 and 105 of the casing 100.
    In forming the fibrous preform by winding, the fibrous texture 140 and the textile web 150 are called from drums 60 and 70 respectively on which they are stored as illustrated in FIG. 5.
    FIG. 6 shows a sectional view of the fibrous preform 300 obtained after winding the fibrous texture 140 and the textile strip 150 in several layers on the mandrel 200. The number of layers or turns is a function of the desired thickness and the thickness of the fibrous texture. It is preferably at least equal to 2. In the example described here, the preform 300 comprises four layers 141 to 144 of fibrous texture 140 and three layers 151 to 153 of textile strip 150 interposed respectively between the adjacent layers 141 and 142, 142 and 143, and 143 and 144.
    A fibrous preform 300 is obtained with a thickening portion 310 formed by the interposition of the layers 151 to 153 of the textile strip 150 between the superimposed layers 141 to 144 of the fibrous texture 140. The fibrous preform 300 also comprises parts of end 320, 330 corresponding to the end portions 120, 130 of the housing.
    The fiber preform 300 is then densified by a matrix.
    The densification of the fiber preform consists in filling the porosity of the preform, in all or part of the volume thereof, with the constituent material of the matrix.
    The matrix can be obtained in a manner known per se according to the liquid method.
    The liquid process consists in impregnating the preform with a liquid composition containing an organic precursor of the matrix material. The organic precursor is usually in the form of a polymer, such as a resin, optionally diluted in a solvent. The fiber preform is placed in a sealable mold with a housing having the shape of the molded end piece. As illustrated in FIG. 7, the fiber preform 300 is here placed between a plurality of counter-mold sectors 240 and the support mandrel 200, these elements respectively having the outer shape and the inner shape of the casing to be produced. Then, the liquid matrix precursor, for example a resin, is injected throughout the housing to impregnate the entire fibrous portion of the preform.
    The transformation of the precursor into an organic matrix, namely its polymerization, is carried out by heat treatment, generally by heating the mold, after removal of the optional solvent and crosslinking of the polymer, the preform being always maintained in the mold having a shape corresponding to that of the piece to realize. The organic matrix may in particular be obtained from epoxy resins, such as, for example, a high-performance epoxy resin present in the trade, or liquid precursors of carbon or ceramic matrices.
    In the case of the formation of a carbon or ceramic matrix, the heat treatment consists in pyrolyzing the organic precursor to transform the organic matrix into a carbon or ceramic matrix according to the precursor used and the pyrolysis conditions. By way of example, liquid carbon precursors may be relatively high coke level resins, such as phenolic resins, whereas liquid precursors of ceramics, in particular of SiC, may be polycarbosilane type resins (PCS). or polytitanocarbosilane (PTCS) or polysilazane (PSZ). Several consecutive cycles, from impregnation to heat treatment, can be performed to achieve the desired degree of densification.
    According to one aspect of the invention, the densification of the fiber preform can be carried out by the well-known method of RTM ("Resin Transfer Molding") transfer molding. According to the RTM method, the fiber preform is placed in a mold having the shape of the casing to be produced. A thermosetting resin is injected into the internal space defined between the mandrel 200 and the counter-molds 240 and which comprises the fiber preform. A pressure gradient is generally established in this internal space between the place where the resin is injected and the evacuation ports of the latter in order to control and optimize the impregnation of the preform with the resin.
    The resin used may be, for example, an epoxy resin. Suitable resins for RTM methods are well known. They preferably have a low viscosity to facilitate their injection into the fibers. The choice of the temperature class and / or the chemical nature of the resin is determined according to the thermomechanical stresses to which the piece must be subjected. Once the resin is injected into the entire reinforcement, it is polymerized by heat treatment in accordance with the RTM method.
    After injection and polymerization, the part is demolded. Finally, the piece is cut away to remove the excess resin and the chamfers are machined to obtain the housing 100 illustrated in Figures 1 and 2.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    A method of manufacturing a variable thickness composite material casing (100) for a gas turbine, comprising: - producing by three-dimensional or multi-layer weaving a fibrous texture (140) in the form of a strip; winding the fibrous texture (140) in several superposed layers (141, 142, 143, 144) on a mandrel (200) of profile corresponding to that of the casing to be manufactured, in order to obtain a fibrous preform (300) of shape corresponding to that of the casing to be manufactured, - the densification of the fibrous preform (300) by a matrix, characterized in that, during the winding of the fibrous texture (140) on the mandrel (200), a textile strip (150) is interposed between the adjacent turns of the fibrous texture, the textile web (150) having a width less than the width of the fibrous texture (140) and delimiting a crush retention zone.
    [2" id="c-fr-0002]
    2. Method according to claim 1, characterized in that the fibers of the fibrous texture (140) and the fibers of the textile strip (150) are chosen from at least one of the following types: carbon, glass, aramid and ceramic.
    [3" id="c-fr-0003]
    3. Method according to claim 1 or 2, characterized in that the textile web (150) is made with fibers of the same type as that of the fibers of the fibrous texture.
    [4" id="c-fr-0004]
    4. Method according to claim 1, characterized in that the textile strip (150) is made in a three-dimensional weave having the same weave weave as the three-dimensional weave of the fibrous texture (140).
    [5" id="c-fr-0005]
    5. Method according to any one of claims 1 to 4, characterized in that the textile strip (150) has a substantially identical warp-field ratio to that of the fibrous texture (140).
    [6" id="c-fr-0006]
    A gas turbine blower housing (100) having a variable thickness and being of a composite material with fibrous reinforcement comprising a plurality of superposed layers (141, 142, 143, 144) of a fibrous texture (140) under form of a band having a three-dimensional or multilayer weave, said fibrous reinforcement being densified by a matrix, characterized in that a textile strip (150) is interposed between two adjacent layers of the fibrous texture, the textile strip (150) having a width less than the width of the fibrous texture (140) and delimiting a crush retention zone.
    [7" id="c-fr-0007]
    7. Carter according to claim 6, characterized in that the fibers of the fibrous texture (140) and the fibers of the textile strip (150) are chosen from at least one of the following types: carbon, glass, aramid and ceramic.
    [8" id="c-fr-0008]
    8. Carter according to claim 6 or 7, characterized in that the textile web (150) is made with fibers of the same type as that of the fibers of the fibrous texture (140).
    [9" id="c-fr-0009]
    The housing of claim 6, characterized in that the textile web (150) has a three-dimensional weave having the same weave as the three-dimensional weave of the fibrous texture (140).
    [10" id="c-fr-0010]
    10. Carter according to any one of claims 6 to 9, characterized in that the textile web (150) has a substantially identical warp-field ratio to that of the fibrous texture (140).
    [11" id="c-fr-0011]
    11. Carter according to any one of claims 6 to 10, characterized in that the fibrous reinforcement comprises n layers of fibrous texture (140) corresponding to n turns of said fibrous texture and n-1 layers of textile web ( 150) corresponding to n-1 winding turns of said textile web.
    [12" id="c-fr-0012]
    An aeronautical gas turbine engine having a blower housing (100) according to any one of claims 6 to 11.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3045448B1|2018-01-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2663412A1|1990-06-18|1991-12-20|Gen Electric|PROTECTION SHIELD AGAINST PROJECTILES.|
    US5447411A|1993-06-10|1995-09-05|Martin Marietta Corporation|Light weight fan blade containment system|
    EP1104837A2|1999-12-03|2001-06-06|General Electric Company|Contoured hardwall containment|
    EP1961923A2|2007-02-23|2008-08-27|Snecma|Method of producing a gas turbine casing from a composite material and casing thus obtained.|
    US20120099981A1|2010-10-22|2012-04-26|Snecma|Aeroengine fan casing made of composite material, and a method of fabricating it|FR3070402A1|2017-08-30|2019-03-01|Safran Aircraft Engines|FIBROUS TEXTURE WOVEN FOR FORMING A CARTER PREFORM|
    EP3557007A1|2018-04-19|2019-10-23|United Technologies Corporation|Integrally built up composite fan case|
    FR3085299A1|2018-09-05|2020-03-06|Safran Aircraft Engines|HOUSING IN COMPOSITE MATERIAL WITH INTEGRATED STIFFENER|
    CN109435272B|2018-09-30|2021-02-09|航天材料及工艺研究所|Variable-thickness composite material integral framework forming method and forming die thereof|
    法律状态:
    2016-12-09| PLFP| Fee payment|Year of fee payment: 2 |
    2017-06-23| PLSC| Publication of the preliminary search report|Effective date: 20170623 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1563102A|FR3045448B1|2015-12-22|2015-12-22|ALTERED CASE OF COMPOSITE MATERIAL AND METHOD OF MANUFACTURING THE SAME|
    FR1563102|2015-12-22|FR1563102A| FR3045448B1|2015-12-22|2015-12-22|ALTERED CASE OF COMPOSITE MATERIAL AND METHOD OF MANUFACTURING THE SAME|
    CN201680075858.1A| CN108430746B|2015-12-22|2016-12-21|Lightweight housing made of composite material and method for the production thereof|
    PCT/FR2016/053602| WO2017109403A1|2015-12-22|2016-12-21|Lighter-weight casing made of composite material and method of manufacturing same|
    US16/063,366| US11181011B2|2015-12-22|2016-12-21|Lighter-weight casing made of composite material and method of manufacturing same|
    EP16829413.0A| EP3393764A1|2015-12-22|2016-12-21|Lighter-weight casing made of composite material and method of manufacturing same|
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