• 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:
    The invention relates to a gas turbine casing (10) made of composite material from a fiber reinforcement densified by a matrix. The casing (10) comprises at least one stiffening portion (17) extending along a radius greater than the radius of the upstream and downstream portions (18, 19) of the casing adjacent to said stiffening portion (17) so as to form a annular recess (171) on the inner surface (11) of the housing (10).
    公开号:FR3031469A1
    申请号:FR1550278
    申请日:2015-01-14
    公开日:2016-07-15
    发明作者:Sebastien Marin；Quentin Damien Lombart
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] 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, in particular, the air intake duct in the engine, possibly supports an abradable material facing the fan blade tips and / or a sound wave absorption structure for the acoustic treatment at the inlet of the fan. motor and incorporates or supports a retention shield. 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 of organic matrix composite material is described in particular in US Pat. No. 8,322,971. If the use of composite material casings makes it possible to reduce the overall mass of the engine, this reduction in mass leads to a decrease in the eigenfrequencies of the casing which can result in a crossing with the wakes of the vanes of the blower, the housing entering then resonates when one of its own frequencies crosses an excitation harmonic produced by the wake of the vanes. In this case, stiffening of the composite material casing is necessary.
    [0002] OBJECT AND SUMMARY OF THE INVENTION It is an object of the invention to provide a gas turbine casing made of composite material having increased stiffness, without significantly increasing the space requirement and the mass of the casing. This object is achieved by means of a gas turbine casing of composite material comprising a reinforcement densified by a matrix, said casing having a form of revolution, characterized in that it comprises at least one stiffening portion extending along a upper radius 3031469 2 to the radius of the upstream and downstream portions of the housing adjacent to said stiffening portion so as to form an annular recess on the inner surface of the housing. By forming at least one recess in the profile of the casing which does not follow the aerodynamic stream profile usually defined over the entire inner surface of the casing, the casing according to the invention locally has a particular geometry that allows its self-stiffening. The casing according to the invention therefore has increased stiffness, without the addition of additional elements, such as dedicated stiffeners attached to the composite material casing, which make the casing more complex and increase its overall mass. According to one aspect of the housing of the invention, each stiffening portion has in axial section an omega-type shape. Advantageously, the annular recess formed by each stiffening portion is filled with a material or a filling structure so as to ensure continuity on the internal surface of the casing between the upstream and downstream portions of the casing adjacent to each stiffening portion. Advantageously, the annular hollow formed by each stiffening portion is filled with a material or an acoustic attenuation structure. According to another aspect of the housing of the invention, it comprises a retention zone having a greater thickness than the rest of the housing, the said stiffening portion or portions being located outside the retention zone. The invention also relates to an aeronautical gas turbine engine having a fan retention casing according to the invention and an aircraft comprising one or more of these aeronautical engines.
    [0003] The invention further relates to a method of manufacturing a composite material casing for a gas turbine, comprising the weaving in one piece by three-dimensional or multi-layer weaving of a fibrous texture in the form of a strip, the setting into forming said texture by winding on a support tool and densifying the fibrous reinforcement with a matrix, characterized in that, during shaping, the fibrous texture is shaped so as to obtain a fibrous preform comprising at least one recess portion extending along a radius greater than the radius of the upstream and downstream portions of the preform adjacent to said recess portion, said recess portion forming an annular recess on the internal surface of the housing after densification. According to one aspect of the method of the invention, each stiffening portion has in axial section an omega-type shape. Advantageously, the annular hollow formed by each stiffening portion is filled with a filling material or structure so as to ensure continuity on the inner surface of the casing between the upstream and downstream portions of the casing adjacent to each stiffening portion. Advantageously, the annular hollow formed by each stiffening portion is filled with a material or an acoustic attenuation structure. According to another aspect of the process of the invention, the fibrous preform comprises a zone of greater thickness than the rest of the fibrous preform which is intended to form a retention zone in the housing, the said part or portion of offset being located outside the thickest part. 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 of an aeronautical engine according to one embodiment of the invention, Figure 2 is a half-view in axial section of the fan casing of the engine of Figure 1, Figure 3 is a half in axial section of a fan casing according to another embodiment of the invention, FIG. 4 is a perspective view showing the shaping of a fibrous texture intended to form the reinforcement of the casing of the casing; FIG. 5 is a half-view in axial section of a preform of the casing of FIG. 2 obtained by winding up the fibrous texture as shown in FIG. 4; FIG. 6 is a view in FIG. chopped off showing the positioning of injection sectors on the preform of the casing of FIG. 2 obtained by winding up the fibrous texture as shown in FIG. 4. DETAILED DESCRIPTION OF EMBODIMENTS The invention is generally applicable any casing made of gas turbine organic matrix composite material. The invention will be described below 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 arranged at the engine inlet, a compressor 2, a fuel 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 10 having a shape of revolution. FIG. 2 shows the profile (in axial section) of the fan casing 10 which is here made of organic matrix composite material, that is to say from a fiber reinforcement, for example carbon, glass, aramid or ceramic, densified by a polymer matrix, for example epoxide, bismaleimide or polyimide. The manufacture of a composite material casing is described in particular in document US Pat. No. 8,322,971. The internal surface 11 of the casing defines the air intake duct 30 of the engine. The housing 10 may be provided with external flanges 14, 15 at its upstream and downstream ends to allow its mounting and its connection with other elements. Between its upstream and downstream ends, the housing 10 has a variable thickness, a portion 16 of the housing having a greater thickness than the end portions by progressively connecting thereto. Part 16 extends on either side of the blower location, upstream and downstream, to form a retention zone capable of holding debris, particles or objects ingested as input of the engine, or from blower blade damage, and radially projected by rotation of the blower, to prevent it from passing through the crankcase and damaging other parts of the aircraft. According to the invention, the housing 10 further comprises a stiffening portion 17 extending along a radius greater than the radius of the upstream portion 18 and downstream portion 19 of the housing which are adjacent to the stiffening portion 17 so as to form a annular recess 171 on the inner surface 11 of the housing 10. More specifically, the stiffening portion 17 is formed by an annular plate 173 offset radially outwardly of the housing relative to the inner surface 11 thereof. The annular plate 173 is connected to the upstream portions 18 and 15 downstream 19 which define a portion of the inner surface 11 of the housing respectively by annular uprights 172 and 174. The angles P 172 and P174 respectively formed between the amounts 172 and 174 and the Upstream 18 and downstream 19 portions are preferably greater than 90 ° and less than 180 °. These angles are defined in particular according to the stiffness that one wishes to confer on the casing and the manufacturing possibilities. The height H173 of the plate, corresponding to the radial offset thereof relative to the inner surface 11 of the housing also depends on the stiffness that it is desired to bring to the housing while taking into account the space requirements of the housing for the integration into the engine environment. In the embodiment described here, the plate 173 and the posts 172 and 174 have rectilinear profiles (in axial section). However, according to alternative embodiments, these elements may also have slightly curved or wavy profiles.
    [0004] In the embodiment described herein, the stiffening portion 17 has an omega-like shape which is a form well suited for stiffening. 3 illustrates a housing 20 according to the invention which differs from the housing 10 already described in that the annular recess 271, formed by the plate and the annular uprights 273, 272 and 274 defining a stiffening portion 27, is filled by a filling material or structure corresponding here to a honeycomb structure 275 for performing an acoustic attenuation. The filling of the annular hollow 271 formed by the stiffening portion 27 makes it possible to ensure continuity of the internal surface 21 between the upstream 28 and downstream 29 portions and, consequently, not to modify the vein defined by said internal surface of the casing. The filling can be carried out with any type of suitable material or structure and in particular a material (eg foam) or a structure (alveolar) for performing an acoustic attenuation treatment.
    [0005] In addition to the desired stiffness, the height of the plateau of the stiffening portion may also be defined according to the optimum height for acoustic treatment. The casing according to the invention may comprise several stiffening portions similar to the stiffening portions 17 and 27 described above. However, the stiffening portion or portions are preferably located outside the retention zone formed by the thickening portion corresponding to the parts 16 and 26 respectively of the casings 10 and 20 already described. A process for producing the matrix-densified fibrous reinforcing composite material casing 10 is now described. The construction of the casing begins with the formation of a fibrous texture in the form of a band. Figure 4 shows very schematically a fiber structure 100 woven in the form of a strip for forming a fibrous preform of an aircraft engine casing. The fibrous structure 100 is obtained by three-dimensional weaving or multilayer weaving carried out in a known manner by means of a jacquard weaving loom on which a bundle of warp yarns 101 or strands in a plurality of layers has been arranged, the warp yarns being bonded by weft yarns 102. In the illustrated example, the three-dimensional weave is an interlock weave weave. By "interlock" weaving herein is meant a weave weave in which each layer of weft threads binds several layers of warp yarns with all yarns of the same weft column having the same movement in the plane of the weave. armor.
    [0006] Other types of known multilayer weaving may be used, such as those described in document WO 2006/136755. The fibrous structure may in particular be woven from carbon fiber yarns, ceramic such as silicon carbide, glass, or aramid. As illustrated in FIG. 4, the fibrous reinforcement is formed by winding on a mandrel 200 of the fibrous texture 100 produced by three-dimensional weaving with progressive 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 10 forming a single piece with a stiffener corresponding to the stiffening portion 17. For this purpose, the mandrel 200 has an outer surface 201 whose profile corresponds to the inner surface of the casing to realize. By winding it on the mandrel 200, the fibrous texture 100 matches the profile thereof. The mandrel 200 has on its outer surface 201 an annular boss 210 whose shape and dimensions correspond to that of the stiffening portion 17 to form. Mandrel 200 also has two flanges 220 and 230 for forming fiber preform portions corresponding to flanges 14 and 15 of housing 10. Figure 5 shows a sectional view of fiber preform 300 obtained after winding fiber texture 100 into 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 2. In the example described here, the preform 300 comprises 4 layers of fibrous texture 100. A fibrous preform 300 is obtained with a recess portion 310 extending along a radius greater than the radius upstream and downstream parts 311 and 312 of the preform located on each side of the recess portion. The recess portion 310 corresponds to the stiffening portion 17 of the housing 10. The fiber preform also comprises a portion 320 of greater thickness, corresponding to the portion 16 (retention zone) of the housing and the end portions 330, 340 corresponding to the flanges 14, 15 of the housing.
    [0007] 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 material constituting the matrix. The matrix can be obtained in a manner known per se according to the liquid method. The liquid process involves 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. 6, 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.
    [0008] 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 can in particular be obtained from epoxy resins, such as, for example, the high-performance epoxy resin sold, 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 ceramic precursors, especially SIC, may be polycarbosilane 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 RTM ("Resin Transfer Molding") transfer molding process. 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 delimited between the piece of rigid material and the mold and which comprises the fibrous 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 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 has been 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 10 illustrated in Figures 1 and 2.
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. Composite material gas turbine casing (10) comprising a matrix-densified reinforcement, said casing having a shape of revolution, characterized in that it comprises at least one stiffening portion (17) extending at a greater radius the radius of the upstream and downstream portions (18, 19) of the housing adjacent to said stiffening portion (17) so as to form an annular recess (171) on the inner surface (11) of the housing (10).
    [0002]
    2. Housing according to claim 1, characterized in that each stiffening portion (17) has in axial section an omega type shape.
    [0003]
    3. Carter according to claim 1 or 2, characterized in that the annular recess (271) formed by each stiffening portion (27) is filled with a material or a filling structure (275) so as to ensure continuity on the inner surface (21) of the housing (20) between the upstream and downstream portions (28, 29) of the housing (20) adjacent to each stiffening portion (27).
    [0004]
    4. The housing of claim 1 or 2, characterized in that the annular recess (271) formed by each stiffening portion (27) is filled with a material or acoustic attenuation structure (275).
    [0005]
    5. Housing according to any one of claims 1 to 4, characterized in that it comprises a retention zone (16) having a greater thickness than the rest of the housing (10), or said stiffening portions ( 17) being located outside the retention zone (16).
    [0006]
    An aircraft gas turbine engine having a fan retention housing (10) according to any one of claims 1 to 5. 3031469 11
    [0007]
    An aircraft comprising one or more engines according to claim 6.
    [0008]
    8. A method of manufacturing a casing (10) of composite material for a gas turbine, comprising weaving in one piece by three-dimensional or multi-layer weaving of a fibrous texture (100) in the form of a strip, the implementation of forming said texture by winding on a support tooling (200) and densifying the fibrous reinforcement (300) with a matrix, characterized in that, during shaping, the fibrous texture (100) is shaped so obtaining a fibrous preform (300) comprising at least one recess portion (310) extending along a radius greater than the radius of the upstream and downstream portions (311, 312) of the preform adjacent said recess portion, said portion of recess forming an annular recess (171) on the inner surface (11) of the housing (10) after densification.
    [0009]
    9. The method of claim 8, characterized in that each stiffening portion (17) has in axial section an omega-type shape. 20
    [0010]
    Method according to claim 8 or 9, characterized in that the annular recess formed by each stiffening portion (17) is filled with a filling material or structure (275) so as to ensure continuity on the internal surface ( 21) of the housing (20) between the upstream and downstream portions (28, 29) of the housing (20) adjacent to each stiffening portion (27).
    [0011]
    11. The method of claim 8 or 9, characterized in that the annular recess (271) formed by each stiffening portion (27) is filled with a material or acoustic attenuation structure (275).
    [0012]
    12. Method according to any one of claims 8 to 11, characterized in that the fibrous preform (300) comprises a zone of greater thickness (320) than the rest of the fibrous preform 35 intended to form a retention zone (16) in the housing (10), wherein said recess portions (310) are located outside the thicker portion (320).
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    同族专利:
    公开号 | 公开日
    EP3183111B1|2021-12-15|
    RU2017109261A3|2019-02-25|
    RU2017109261A|2018-09-24|
    JP2017533369A|2017-11-09|
    JP6734261B2|2020-08-05|
    CN106794639A|2017-05-31|
    CA2957608A1|2016-02-25|
    US20170266893A1|2017-09-21|
    RU2703206C2|2019-10-15|
    WO2016027030A1|2016-02-25|
    BR112017003515A2|2017-12-05|
    EP3183111A1|2017-06-28|
    FR3031469B1|2017-09-22|
    引用文献:
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    FR3070624B1|2017-09-06|2019-09-13|Safran Aircraft Engines|CARRIER IN COMPOSITE MATERIAL WITH A STRINGING GEOMETRY|
    FR3085299B1|2018-09-05|2021-04-16|Safran Aircraft Engines|COMPOSITE MATERIAL HOUSING WITH INTEGRATED STRENGTHENING|
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    法律状态:
    2016-01-11| PLFP| Fee payment|Year of fee payment: 2 |
    2016-07-15| PLSC| Publication of the preliminary search report|Effective date: 20160715 |
    2017-01-05| PLFP| Fee payment|Year of fee payment: 3 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 7 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1550278A|FR3031469B1|2015-01-14|2015-01-14|CARRIER IN MATERIAL COMPOSITE WITH ORGANIC MATRIX AUTO-RAIDI|FR1550278A| FR3031469B1|2015-01-14|2015-01-14|CARRIER IN MATERIAL COMPOSITE WITH ORGANIC MATRIX AUTO-RAIDI|
    RU2017109261A| RU2703206C2|2014-08-22|2015-08-17|Self-reinforced housing consisting of composite material with organic matrix|
    CA2957608A| CA2957608A1|2014-08-22|2015-08-17|Casing consisting of a composite material with a self-stiffened organic matrix|
    JP2017510520A| JP6734261B2|2014-08-22|2015-08-17|Self-stiffening casing made of composite material with organic matrix|
    EP15760216.0A| EP3183111B1|2014-08-22|2015-08-17|Casing consisting of a composite material with a self-stiffened organic matrix and method of producing the same|
    BR112017003515-4A| BR112017003515B1|2014-08-22|2015-08-17|COMPOSITE MATERIAL GAS TURBINE CASING, GAS TURBINE AIRCRAFT ENGINE, AIRCRAFT, AND MANUFACTURING METHOD OF A COMPOSITE MATERIAL CASING|
    CN201580044579.4A| CN106794639A|2014-08-22|2015-08-17|The self-reinforcing housing being made up of the composite with organic matrix|
    US15/505,437| US20170266893A1|2014-08-22|2015-08-17|Self-stiffened casing consisting of a composite material with an organic matrix|
    PCT/FR2015/052213| WO2016027030A1|2014-08-22|2015-08-17|Casing consisting of a composite material with a self-stiffened organic matrix|
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