• 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 turbine stator sector (100) includes a plurality of composite material blades (110) each having a blade body (111) extending between first and second ends (112, 113). The sector further comprises first and second platforms (120, 130) of composite material, the first platform (120) comprising openings (121) in which are engaged the first ends (112) of blades (110) and the second platform (130) comprising openings (131) in which are engaged the second ends (113) of blades (110). The openings (121) of the first platform (120) have dimensions greater than the dimensions of the first ends (112) of the blades (110) engaged in said openings (121) so as to provide a clearance (J) between the first end ( 112) of each blade (110) and the opening (121). Each first blade end (112) engaged in the opening (121) has dimensions smaller than the dimensions of the blade body (111) so as to define a shoulder (1121) extending around said first end (112). The shoulder has dimensions greater than the dimensions of the openings (121) of the first platform (120).
    公开号:FR3018308A1
    申请号:FR1451824
    申请日:2014-03-06
    公开日:2015-09-11
    发明作者:Elric Fremont
    申请人:SNECMA SAS；Herakles SA；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The invention relates to turbomachine stators. The targeted field is that of compressors or rectifiers of gas turbines for aeronautical engines or industrial turbines The improvement of the performance of turbomachines and the reduction of their polluting emissions lead to consider operating temperatures of higher and higher. For elements of hot parts of turbomachines, it has therefore been proposed to use ceramic matrix composite materials (CMC). Indeed, these materials have remarkable thermostructural properties, that is to say mechanical properties that make them able to constitute structural elements and the ability to retain these properties at high temperatures. In addition, the CMC materials have a much lower density than metal materials traditionally used for elements of hot parts of turbomachines. Thus, the documents WO 2010/061140, WO 2010/116066 and WO 2011/080443 describe the production of mobile wheel blades of turbomachines in CMC with integrated platform and heel. The use of CMC materials for turbine distributors has also been proposed, in particular in the document WO 2010/146288. A conventional metal compressor turbine or rectifier is formed of a plurality of assembled sectors, each sector comprising an internal platform, an external platform and a plurality of blades extending between the inner and outer platforms and integral with each other. them. The inner and outer platforms delimit the flow of gas or air flow in the distributor or rectifier. On the external side, the outer platforms of the sectors are secured to legs for mounting the turbine distributor or compressor rectifier in a housing.
    [0002] The document EP 1 213 484 describes a compressor rectifier stage made of metallic material made by assembling blades between an inner ferrule and an outer ferrule, the inner and outer ends of the blades being secured respectively to the inner ferrule and to the outer ferrule by a single blade. In this case, the locking of the blades vis-à-vis the inner and outer platforms by means of a continuous blade poses problems of alignment between the blades. Indeed, such a locking solution requires to provide a large clearance between the blades to allow their alignment vis-à-vis the blade. Such a game is unacceptable in the case of a rectifier or low pressure distributor because it causes excessive leaks and pressure drops in the engine.
    [0003] The document EP 1 626 163 describes a compressor rectifier made of metallic material comprising blades assembled between an inner ferrule and an outer ferrule, a large clearance being formed in particular between the lumens of the inner ferrule and the inner ends of the blades. As for EP 1 213 484, such a game can not be tolerated at the level of the definition of the internal vein because it causes too great leaks in the engine. OBJECT AND SUMMARY OF THE INVENTION An object of the invention is to propose a method making it possible to manufacture a stator sector, in particular a turbine distributor or a compressor rectifier, made of a composite material incorporating the various functions of a metallic sector, in particular the functions of gas or air flow vein delimitation by internal and external platforms and hooking in a crankcase. The invention also aims to allow a simplified embodiment of such a stator sector by assembling elementary elements, without generating leakage at the assembly portions between the blades and the platforms. This object is achieved by a method of manufacturing a turbomachine stator sector comprising: - producing a plurality of fibrous blade blanks in one piece, - shaping the fibrous blanks to obtain fiber preforms in one piece, - densification of the blade preforms by a matrix to obtain composite material blades each having a fiber reinforcement constituted by the preform and densified by the matrix, - machining each blade to form a first end and a second end defining between them a blade body, each first end having dimensions smaller than those of the blade body so as to define a shoulder extending around the first end, - the realization of a light or notch in the first and second ends of the blades, - the production of a fibrous blank of a first platform and a a fibrous blank of a second platform; - shaping fibrous blanks to obtain a fibrous preform of a first one-piece arcuate shaped platform and a fibrous preform of a second one-piece shaped platform. of circular arc, - the densification of the preforms of the first and second platforms by a matrix to obtain first and second platforms of composite material in the shape of a circular arc having a fibrous reinforcement constituted by the preform and densified by the matrix - Making openings in the first and second platforms, the openings of the first platform having dimensions greater than the dimensions of the first ends of the blades, the shoulder extending around the first end having dimensions greater than the dimensions. openings of the first platform, - engagement of the second ends of the blades in the openings of the second platform, - placement of a locking element in each slot 30 or notch of the second ends of the blades, - engagement of the first ends of the blades in the openings of the first platform, - placement of a locking element in each light or notch the first ends of the blades. Thus by making openings in the first platform having dimensions greater than the dimensions of the first ends of the blades and realizing a shoulder extending around the first end having dimensions greater than the dimensions of the openings of the first platform, it is possible to provide a clearance between the inner ends of the blades and the openings of the inner platform to facilitate their assembly. Indeed, the second ends of the blades being already engaged and secured in the openings of the second platform having an arcuate shape, it is therefore not possible to engage the first ends of the blades in the openings of the first platform if the latter do not have dimensions allowing to play a game with the first ends of the blades. On the other hand, since the first ends of the blades are surrounded by a shoulder having dimensions greater than those of the openings of the first preform, the shoulder makes it possible to mask for the vein the clearance present between the first ends and the openings of the first platform and thus ensure a sealing of the stator at the internal definition of the vein. Moreover, the choice of providing a clearance to facilitate the assembly of the blades with the platforms makes it possible to manufacture the blades in series according to the same model and, consequently, to reduce the number of different parts necessary for the production of a blade. stator area. The time and cost of manufacturing such a stator sector are thus reduced. According to a particular characteristic of the method of the invention, the blades, the first platform, the second platform and the locking elements are made of ceramic matrix composite material (CMC). The invention also relates to a turbine stator sector comprising a plurality of composite material blades comprising a matrix-densified fiber reinforcement, each blade comprising a blade body extending between a first end and a second end, said sector further comprising a first platform and a second arcuate platform of composite material comprising matrix-densified fiber reinforcement, the first platform comprising apertures in which the first blade tips are engaged and the second platform comprising openings in which are engaged the second ends of blades, characterized in that the openings of the first platform have dimensions greater than the dimensions of the first ends of the blades engaged in said openings so as to provide a clearance between the first end of each blade and the opening and in that each first blade end engaged in said opening has dimensions smaller than the dimensions of the blade body so as to define a shoulder extending around said first end, the shoulder having greater dimensions to the dimensions of the openings of the first platform and being in contact with the surface of the first platform. According to a first characteristic of the sector of the invention, the part of the second end of each blade extending beyond the second platform comprises at least one slot or notch in which is placed a locking element.
    [0004] According to a second feature of the sector of the invention, the portion of the first end of each blade extending beyond the first platform comprises at least one slot or notch in which is placed a locking element. According to a third characteristic of the sector of the invention, the blades, the first platform and the second platform are made of ceramic matrix composite material (CMC). According to a fourth characteristic of the sector of the invention, the first platform corresponds to the internal platform of the stator sector and in that the first end of the blade body corresponds to the inner end of said blade body, the corresponding second platform at the outer platform of said stator sector and the second end of the blade body corresponding to the outer end of said blade body. The present invention also relates to: a turbomachine stator comprising a plurality of sectors according to the invention, a turbomachine compressor equipped with a stator according to the invention, and a turbomachine equipped with a compressor according to the invention; 'invention. BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood from the description given below, by way of indication but without limitation, with reference to the appended drawings in which: FIGS. 1A and 1B are perspective views of a sector of turbomachine stator according to one embodiment of the invention; FIG. 2 very schematically illustrates the production of a multilayer woven fiber blank intended for producing a blade of the stator sector of FIGS. 1A and 1B; FIG. 3 illustrates the production, from the fiber blank of FIG. 2, of a fibrous preform for a stator sector blade as illustrated in FIGS. 1A and 1B; FIG. 4 is a perspective view of a composite material blade of the stator sector of FIGS. 1A and 1B obtained from the fiber preform of FIG. 3; FIG. 5 very schematically illustrates the production of a multilayer woven fiber blank intended for producing an internal platform of the stator sector of FIGS. 1A and 1B; FIG. 6 illustrates the production, from the fiber blank of FIG. 5, of a fibrous preform for an internal stator sector platform as illustrated in FIGS. 1A and 1B; FIG. 7 is a perspective view of the composite material internal platform of the stator sector of FIGS. 1A and 1B obtained from the fiber preform of FIG. 6; FIG. 8 is a perspective view of the composite material outer platform of the stator sector of FIGS. 1A and 1B; FIG. 9 is a perspective view showing the connection between the external platform and the blades during the production of the stator sector of FIGS. 1A and 1B; - Figure 10 is a perspective view showing the assembly between the inner platform and the blades during the realization of the stator sector of Figures 1A and 1B; FIG. 11 is a view from below showing the clearances present between the inner ends of the blades and the openings of the internal platform; - Figure 12 is a sectional view according to the reference XII-XII of Figure 11 showing the clearances present between the inner ends of the blades and the openings of the inner platform; FIG. 13 is a perspective view of a turbomachine stator formed by the union of a plurality of stator sectors of FIGS. 1A and 1B; DETAILED DESCRIPTION OF EMBODIMENTS The invention is applicable to various types of gas turbine stators, in particular low pressure distributors or turbomachine rectifiers. FIGS. 1A and 1B show a stator sector 100 according to an embodiment and corresponding to a portion 15 of a low-pressure turbomachine distributor. The stator 100 here comprises four blades 110, an inner platform 120 and an outer platform 130, the inner and outer platforms 120, 130 having an arcuate shape. Throughout the text, the term "external platform" or "internal platform" denotes both a bi-functional platform having a part constituting a vein-forming platform and a portion forming hooking lugs or hooks or spoilers, a single-functional platform limited to one of these parts. By "vein constitution platform" is meant an element forming part of an outer or inner wall delimiting the gas flow passage in a turbine at a turbine distributor or the air circulation duct in a compressor at a compressor rectifier. Throughout this text, the terms "internal" and "external" are used with reference to the position or orientation with respect to the axis of the turbine. The outer platform 130 comprises a vein-forming platform 132. On the outer side protrudes from the vein-forming platform 132 an upstream hooking tab 133 and a downstream hooking tab 134 in the form of annular sectors to section substantially S-shaped. The attachment tabs 133, 134 extend on the same angle as the platform 132. The end portions of the tabs 133, 134 are respectively directed upstream and downstream and are intended to be engaged in hooks carried by an aircraft engine casing (not shown in Figures 1A and 1B) similarly to a metal turbine distributor. Throughout the text, the terms "upstream" and "downstream" are used with reference to the flow direction of gas flow in the turbomachine. The outer platform 120 comprises a platform constituting the vein 122. On the inner side, protruding under the inner platform 120 upstream hooks 123 and downstream 124 which are in the form of annular sectors with substantially C-shaped section, and are folded respectively downstream and upstream. The hooks 123 and 124 are intended to support and maintain in axial position a sealing system for the adjacent mobile disk 15 in the engine (not shown in Figures 1A and 1B). Each blade comprises a blade body 111 which extends between an inner end 112 and an outer end 113. The inner platform 120 has openings 121 into which the inner ends 112 of the blades 110 are engaged while the outer platform 130 comprises openings 131 in which are engaged the outer ends 113 of the blades 110. The inner platform 120 is secured to the inner ends 112 of the blades 110 by a connection type mortise / tenon made by elements or locking keys 140 each introduced into a light or notch 1120 formed in the portion of the inner ends 112 located beyond the inner platform 120 (Figure 1B). The outer platform 130 is secured to the outer ends 113 of the blades 110 by a tenon / mortise type connection made by locking elements or keys 150 each introduced into a slot or notch 1130 formed in the portion of the outer ends 113 located on the outside. beyond the inner platform 120 (Figure 1A). According to the invention, the blades 110, the inner platform 120, the outer platform 130 and the locking elements 140 and 150 are each made independently of one another. FIG. 2 very diagrammatically shows a fibrous preform 200 from which a fibrous blade preform can be shaped in order, after densification by a die and machining, to obtain a blade of composite material such as the blades 110 illustrated by FIG. Figures 1A and 1B. The blank 200 is here obtained by three-dimensional weaving or multilayer weaving between a plurality of warp and weft threads.
    [0005] The fibrous blank 200 is intended, after shaping, to form a blade preform. The blank 200 may have a variable thickness determined according to the profile thickness of the blade to be produced. A fiber preform 300 of the blade to be manufactured is then obtained by molding with deformation of the blank 200 to reproduce the curved profile of the blade, as shown in FIG. 3. After a first densification making it possible to obtain a preform suitable for retain its shaping, the preform 300 is machined to form a blade body preform portion, an inner blade tip preform portion having smaller dimensions than the blade body preform portion and having a lumen or notch and an outer blade tip preform portion having dimensions smaller than those of the blade body preform portion and having a lumen or notch. Thus, as illustrated in FIG. 4, a blade 110 having a blade body 111 extending between an inner end 112 and an outer end 113 each comprising a respective lumen 1120, 1130 is obtained. a shape similar to that of the blade body 111, it however has dimensions smaller than those of the blade body 25 so as to define a shoulder 1121 which extends all around the inner end 112. Similarly, if the Although the outer end 113 has a shape similar to that of the blade body 111, it has dimensions smaller than those of the blade body so as to define a shoulder 1131 which extends all the way around the inner end 113. In a embodiment, the son used may be silicon carbide (SiC) son provided under the name "Nicalon" by the Japanese company Nippon Carbon and having a title (number of filaments) d e 0.5K (500 filaments). Of course, depending on the available thread titles, different combinations of number of thread layers and variations of context and title can be adopted for the profile to be obtained.
    [0006] For the weaving of the fibrous blank 200, the weave used may for example be a multilayer weave made with satin or multi-satin weave. Other types of multilayer weaving may be used, for example a multilayer multi-weave weave or interlock weave weave. "Interlock" weaving is here understood to mean a weave in which each layer of weft threads binds several layers of warp yarns with all the threads of the same weft column having the same movement in the plane of the weave. . Various modes of multilayer weaving are described in particular in WO 2006/136755, the contents of which are hereby incorporated by reference. The fibrous blank for forming the fibrous reinforcement of the blade may also be obtained from a stack of several layers of: one-dimensional (UD) fabric, two-dimensional (2D) fabric, braid, knit, felt, unidirectional web (UD) son or cables or multidirectional webs (nD) obtained by superposition of several UD webs in different directions and UD web bonding between them for example by sewing, by chemical bonding agent or by needling. The layers are bonded together, for example by sewing, by the implantation of threads or rigid elements or by needling. FIG. 5 very schematically shows a fibrous preform 400 intended to form the fibrous reinforcement of the inner platform and from which a fibrous preform of internal platform can be shaped so as, after a first densification by a matrix 30 to obtain a preform able to retain its shape, and machining of said densified preform, to obtain an internal platform 120 as illustrated in FIGS. 1A and 1B. In the example described here, the fibrous blank 400 is obtained, as schematically illustrated in FIG. 5, by multilayer weaving between a plurality of warp son layers and a plurality of weft layers. The multilayer weave produced can be in particular an "interlock" weave, that is to say a weave weave in which each layer of weft son binds several layers of warp son with all the son of the same column weft with the same movement in the plane of the armor.
    [0007] The blank 400 includes a first and a second portion 410 and 420 for respectively forming the vein-forming platform 122 and the hooks 123 and 124. In the weaving, a first and a second delimitation 401 and 402 are made at the same time. interior of the fiber blank between two successive layers of warp yarns located at the boundary between the portions 410 and 420 and on respectively two debonding zones 403 and 404. The portions 410 and 420 are interconnected at a zone link 405 between the two debonding zones 403 and 404. The debonding 401 and 402 respectively form two parts 421 and 422 which can be folded during the shaping of the blank to form the final hooks 123 and 124. The fibrous blank intended to form the internal platform may also be obtained by assembling two fibrous textures corresponding respectively to the first and second Ith portions 410 and 420 of the fibrous blank 400 described above. In this case, the two fibrous textures are bonded together, for example by sewing or needling, only at the connecting zone 405 so as to form the two parts 421 and 422 which can be folded during the shaping of the blank in order to finally form the hooks 123 and 124. The two fibrous textures respectively corresponding to the first and second portions 410 and 420 may be in particular each obtained from a layer or a stack of several layers of: one-dimensional fabric (UD), - two-dimensional fabric (2D), - braid, - knitting, - felt, - unidirectional web (UD) of yarns or cables or multidirectional webs (nD) obtained by superposition of several UD webs in different directions and bonding the UD webs together, for example by sewing, by chemical bonding agent or by needling. In the case of a stack of several layers, they are interconnected for example by sewing, by implantation of son or rigid elements or by needling. FIG. 6 very diagrammatically shows a fiber preform 500 of the inner platform to be manufactured then obtained by molding with deformation of the whole of the preform to obtain a general shape in a circular arc, deformation of the portion 410 to reproduce shapes similar to those of the internal vein reconstitution plate and folding portions 421 and 422 of the portion 420 to reproduce shapes similar to those of the fixing portions of the hook. After a first densification, the preform 500 is machined to form an opening having a shape and dimensions equivalent to those of the internal platform to be manufactured. Thus, as illustrated in FIG. 7, an internal platform 120 in the form of a circular arc is obtained comprising a platform for constituting the vein 122, hooks 123, 124 and openings 121 having a shape equivalent to the shape of the internal end 112 of the blades 110 but having dimensions greater than the inner end 112 as explained below. The external platform 130 shown in FIG. 8 is obtained in the same manner as that already described above for producing the internal platform 120. The manufacturing steps of the external platform 25 will therefore not be described again for the sake of simplification. The outer platform 130 thus obtained has a shape of a circular arc and comprises a platform constituting the vein 132, hooking tabs 133, 134 and openings 131 having a shape equivalent to the shape of the outer end 113 of the blades 110 but 30 having dimensions greater than the outer end 113 as explained hereinafter. In order to prevent the introduction of differential thermal expansion coefficients between the blades and the platforms, these elements are preferably made with fibers and a matrix of the same nature. The construction of a stator sector by assembling previously manufactured parts is now described. As illustrated in FIG. 9, the blades 110 are first assembled with the external platform 130. For this purpose, the outer ends 113 of the blades 110 are engaged in the openings 131 of the external platform 130. A locking element 150 is made preferably in the same composite material as the blade and the platform, is introduced and adhered in each outer end light 1130 113 present above the outer platform 130 so as to secure the assembly between the external platform 130 and the 110. The inner platform 120 is then assembled with the blades 110 by engaging the inner ends 112 of the latter in the openings 121 of the inner platform 120 as illustrated in FIG. 10. A locking element 140, preferably made in the same composite material as the blade and the platform, is introduced and glued into each external end light 1120 112 present on essus the inner platform 120 so as to secure the assembly between the inner platform 120 and the blades 110. The assembly is then subjected to a second densification to create links between the parts at the assembly interfaces by co -densification.
    [0008] The assembly between the blades 110 and the inner platform 120 is only possible thanks to the presence of a clearance between the inner ends 112 of the blades 110 and the openings 121 of the inner platform. Indeed, in order to respect the circular shape of the final stator, the stator sector to achieve must correspond to a portion of a circle whose radius of curvature is defined by the inner and outer platforms. In this case, the blades 110 are arranged radially between the inner and outer platforms and the docking of one of the two platforms with the blades can not be done as normal to the axis of the blades. In the embodiment described here, it is the outer platform 130 which is approached first with the blades 110. The docking can therefore be performed according to the normal to the axis of the blades so that it is not necessary to have a clearance between the outer ends 113 of the blades and the openings 131 of the outer platform 130. However, once the blades 110 assembled and secured to the outer platform 130 having a circular arc shape, it It is not possible to engage the inner ends 112 of the blades in the openings 121 of the inner platform 120 if no play is provided in the direction of docking between these openings and the inner ends of the blades. As illustrated in Figures 11 and 12, since the openings 121 have dimensions greater than those of the openings 121, a clearance J is present between the inner ends 112 and the openings 121 in the direction of docking between these elements. This game J is divided according to the position of the blade to dock with the internal platform. The clearance J is distributed on both sides of the inner end 112 of the blades 110 located in the center of the inner platform 120 while it is mainly located on one side of the inner end 112 of the blades located at the ends of the blade. internal platform 120. The clearance J thus present between the inner ends 112 of the blades 110 and the openings 121 of the inner platform 120 allows to assemble the latter with all the blades already assembled and secured to the external platform. In addition, in order to maintain a seal between the blades and the inner platform in the presence of such a game and avoid a loss of load, the blades 110 each comprise a shoulder 1121 which extends all around the inner end 112 and which has dimensions greater than those of the openings 121 of the inner platform 120. Thus, after docking and securing the inner platform 112 with the blades 110, the shoulder 1121 is in contact with the upper surface 112a of the platform 112, which which makes it possible to isolate from the vein the spaces present between the inner ends 112 and the openings 121 (FIGS. 11 and 12). The stator sector 100 is preferably made of ceramic matrix composite material (CMC), that is to say parts formed of a reinforcement of refractory fibers (carbon or ceramic) densified by an at least partially ceramic matrix. Examples of CMC materials are C / SiC composites (carbon fiber reinforcement and silicon carbide matrix), C / C-SiC composites (carbon fiber reinforcement and matrix comprising a carbon phase, generally closer to fibers, and a silicon carbide phase), SiC / SiC composites (reinforcing fibers and silicon carbide matrix) and oxide / oxide composites (reinforcing fibers and alumina matrix). An interphase layer may be interposed between the reinforcing fibers and the matrix to improve the mechanical strength of the material. The densification of the fibrous preform intended to form the fibrous reinforcement of each part to be manufactured consists in filling the porosity of the preform, in all or part of the volume thereof, with the material constituting the matrix. This densification can be carried out in a manner known per se according to the liquid method (CVL) or the gaseous process (CVI), or alternatively in a sequence of these two processes.
    [0009] The liquid process consists of impregnating the preform with a liquid composition containing a precursor of the matrix material. The precursor is usually in the form of a polymer, such as a high performance epoxy resin, optionally diluted in a solvent. The preform is placed in a mold that can be sealed with a housing having the shape of the final piece. Then, the mold is closed and the liquid matrix precursor (for example a resin) is injected throughout the housing to impregnate the entire fibrous portion of the preform. The conversion of the precursor into a 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. In the case of the formation of a ceramic matrix, the heat treatment consists in pyrolyzing the precursor to transform the matrix into a carbon or ceramic matrix according to the precursor used and the pyrolysis conditions. By way of example, liquid precursors of ceramics, in particular of SiC, may be polycarbosilane (PCS) or polytitanocarbosilane (PTCS) or polysilazane (PSZ) type resins. Several consecutive cycles, from impregnation to heat treatment, can be performed to achieve the desired degree of densification. The densification of the fiber preform can also be carried out, in a known manner, by gaseous method by chemical vapor infiltration of the matrix (CVI). The fibrous preform corresponding to the fibrous reinforcement of the part to be produced is placed in an oven in which a gaseous reaction phase is admitted. The pressure and the temperature prevailing in the furnace and the composition of the gas phase are chosen so as to allow the diffusion of the gas phase within the porosity of the preform to form the matrix by deposition, in the heart of the material in contact with it. fibers, of a solid material resulting from a decomposition of a constituent of the gas phase or a reaction between several constituents, unlike the pressure conditions and temperatures specific to the CVD ("Chemical Vapor Deposition") processes which lead to exclusively to a deposit on the surface of the material.
    [0010] The formation of an SiC matrix can be obtained with methyltrichlorosilane (MTS) giving SiC by decomposition of the MTS. A densification combining liquid route and gaseous route can also be used to facilitate implementation, limit costs and production cycles while obtaining satisfactory characteristics for the intended use. The first densification performed individually on each fiber preform of blade, internal platform, external platform and locking elements can be performed by liquid route, gaseous route, or a combination of these two routes.
    [0011] FIG. 13 shows a stator 600 produced by the union of a plurality of stator sectors 100 previously described, the stator 600 being able to constitute a low pressure distributor for an aeronautical engine turbine. In the stator sector 100 described above, a clearance has been provided between the inner ends and the openings of the internal platform so as to allow, when the stator sector is being produced, the blade assembly with the internal platform. following the assembly of the latter with the external platform. However, the invention is not limited to this assembly order. The stator sector of the invention can be achieved by first assembling the blades with the inner platform and then with the external platform. In this case, the openings of the outer platform intended to receive the outer ends of the blades have larger dimensions to the outer ends of the blades so as to provide a clearance between the openings and the outer ends and thus allow the assembly between the platform
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A method of manufacturing a turbomachine stator (600) sector (100) comprising: - producing a plurality of fibrous blade blanks (200) in one piece, - shaping fibrous blanks (200) ) to obtain fiber preforms of blade (300) in one piece, - the densification of the blade preforms (300) by a matrix to obtain blades (110) of composite material each having a fiber reinforcement consisting of the preform and densified by the die, - machining each blade (110) to form a first end (112) and a second end (113) delimiting between them a blade body (111), each first end (112) having dimensions less than those of the blade body (11) so as to define a shoulder (1121) extending around the first end (112), - producing a lumen or notch (1120; 1130) in the first and second ends ends (112, 113) of the palms (110), - producing a fibrous blank of a first platform (400) and a fibrous blank of a second platform, - shaping the fibrous blanks to obtain a first platform fibrous preform (500) in one piece in the shape of an arc of a circle and a fibrous preform of second platform in one piece in the shape of an arc of a circle, - the densification of the preforms of the first and second platforms by a matrix to obtain first and second platforms (120, 130) made of arcuate composite material having a fiber reinforcement constituted by the preform and densified by the matrix; - making openings (121, 131) in the first and second platforms (120, 130), the openings (121) of the first platform (120) having dimensions greater than the dimensions of the first ends (112) of the blades (110), the shoulder (1121) 35 extending around the first ex tremité (112) havingdesdimensions greater than the dimensions of the openings (121) of the first platform (120), - engagement of the second ends (113) of the blades (110) in the openings (131) of the second platform (130), - placing a locking member (150) in each slot or notch (1130) of the second ends (113) of the blades (110); - engaging the first ends (112) of the blades (110) in the openings (121) of the first platform (120); - placing a locking element (140) in each slot or notch (1120) of the first ends (112) of the blades (110).
    [0002]
    2. Method according to claim 1, characterized in that the blades (110), the first platform (120), the second platform (130) and the locking elements (140, 150) are made of ceramic matrix composite material ( CMC).
    [0003]
    A turbine stator (600) sector (100) comprising a plurality of composite material blades (110) comprising a matrix-densified fiber reinforcement, each blade (110) comprising a blade body (111) extending between a first end (112) and a second end (113), said sector further comprising a first platform (120) and a second arcuate platform (130) of a composite material comprising a fiber reinforcement densified by a matrix , the first platform (120) comprising openings (121) in which are engaged the first ends (112) of blades (110) and the second platform (130) comprising openings (131) in which are engaged the second ends (113). ) of blades (110), characterized in that the openings (121) of the first platform (120) have dimensions greater than the dimensions of the first ends (112) of the blades (110) engaged in the said s openings (121) so as to provide a clearance (J) between the first end (112) of each blade (110) and the opening (121) and in that each first end (112) of blade engaged in said opening (121) has dimensions smaller than the dimensions of the blade body (111) so as to define a shoulder (1121) extending around said first end (112), the shoulder having dimensions greater than the dimensions of the openings (121). ) of the first platform (120) and being in contact with the surface of the first platform (120).
    [0004]
    4. Sector according to claim 3, characterized in that the portion of the second end (113) of each blade (110) extending beyond the second platform (130) comprises at least one light or notch (1130) in which is placed a locking element (150).
    [0005]
    5. Sector according to claim 3 or 4, characterized in that the portion of the first end (112) of each blade (110) extending beyond the first platform (120) comprises at least one light or notch ( 1120) in which is placed a locking element (140).
    [0006]
    6. Sector according to any one of claims 1 to 5, characterized in that the blades (110), the first platform (120) and the second platform (130) are made of ceramic matrix composite material (CMC).
    [0007]
    7. Sector according to any one of claims 1 to 6, characterized in that the first platform (120) corresponds to the inner platform of the sector (100) of the stator and in that the first end (112) of the blade body (111) corresponds to the inner end of said blade body, the second platform (130) corresponding to the outer platform of said stator sector (100) and the second end (113) of the blade body (111) corresponding to the outer end of said blade body.
    [0008]
    A turbomachine stator (600) comprising a plurality of sectors (100) according to any one of claims 1 to 7.
    [0009]
    9. A turbomachine compressor equipped with a stator according to claim 8.
    [0010]
    10. Turbomachine equipped with a compressor according to claim 9.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3114324B1|2018-05-02|Stator section for a turbomachine and method for producing the same
    EP2771547B1|2017-04-12|Method for manufacturing a turbine nozzle guide vanes sector or a compressor guide vanes sector from composite material for a turbomachine
    EP2707577B1|2018-03-21|Turbine engine rotor including blades made of a composite material and having an added shroud
    EP2118448B1|2010-08-18|Turbine ring assembly for gas turbine
    CA2847239C|2018-11-06|Assembly consisting of a turbine nozzle or a compressor stator vane made of cmc for a turbine engine and an abradable support ring, and turbine or compressor including such an assembly
    EP2831382B1|2016-05-25|Afterbody assembly of an aircraft engine, corresponding aircraft engine and aircraft
    EP2118474B1|2010-08-18|Method of manufacturing a cmc flow mixer lobed structure for a gas turbine aeroengine
    EP2785980B1|2018-10-24|Hollow-blade turbine vane made from composite material, turbine or compressor including a nozzle or guide vane assembly formed by such blades, and turbomachine comprising same
    EP3259123B1|2018-12-12|Method for manufacturing a turbomachine blade made of composite material
    EP3183111B1|2021-12-15|Casing consisting of a composite material with a self-stiffened organic matrix and method of producing the same
    CA2848018C|2019-12-31|Fabrication process for distributor sector in a turbine or compressor stator vane of a composite material for a turbine engine and turbine or a compressor incorporating a distributor or a stator vane made from such sectors
    FR2979661A1|2013-03-08|Element for e.g. distributor of multistage low pressure turbine of aircraft turboshaft engine, has blade extending beyond external platform to form external extension of another blade, where grooves are formed on extension sides
    FR3084445A1|2020-01-31|MANUFACTURE OF A COMBUSTION CHAMBER OF COMPOSITE MATERIAL
    同族专利:
    公开号 | 公开日
    EP3114324A2|2017-01-11|
    WO2015132523A2|2015-09-11|
    US10190426B2|2019-01-29|
    FR3018308B1|2016-04-08|
    RU2684075C2|2019-04-03|
    US20170074110A1|2017-03-16|
    RU2016139110A|2018-04-06|
    CA2940565A1|2015-09-11|
    EP3114324B1|2018-05-02|
    RU2016139110A3|2018-09-14|
    JP2017517663A|2017-06-29|
    WO2015132523A3|2016-06-02|
    JP6649264B2|2020-02-19|
    CN106103904B|2020-05-12|
    CN106103904A|2016-11-09|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1626163A2|1999-08-09|2006-02-15|United Technologies Corporation|Clip member for a stator assembly|
    EP1905956A2|2006-09-25|2008-04-02|General Electric Company|Ceramic matrix composite vane insulator|
    WO2010061140A1|2008-11-28|2010-06-03|Snecma Propulsion Solide|Composite material turbine engine vane, and method for manufacturing same|
    WO2010116066A1|2009-04-06|2010-10-14|Snecma|Method for producing a turbomachine blade made from a composite material|
    GB695724A|1950-08-01|1953-08-19|Rolls Royce|Improvements in or relating to structural elements for axial-flow turbo-machines such as compressors or turbines of gas-turbine engines|
    GB865544A|1958-04-14|1961-04-19|Napier & Son Ltd|Turbines|
    EP1213484B1|2000-12-06|2006-03-15|Techspace Aero S.A.|Compressor stator stage|
    US6648597B1|2002-05-31|2003-11-18|Siemens Westinghouse Power Corporation|Ceramic matrix composite turbine vane|
    US9068464B2|2002-09-17|2015-06-30|Siemens Energy, Inc.|Method of joining ceramic parts and articles so formed|
    JP2005194903A|2004-01-05|2005-07-21|Mitsubishi Heavy Ind Ltd|Compressor stationary blade ring|
    FR2887601B1|2005-06-24|2007-10-05|Snecma Moteurs Sa|MECHANICAL PIECE AND METHOD FOR MANUFACTURING SUCH A PART|
    FR2899270A1|2006-03-30|2007-10-05|Snecma Sa|LOCALLY-SHAPED RECTIFIER RAM, RECTIFIER AREA, COMPRESSION STAGE, COMPRESSOR AND TURBOMACHINE COMPRISING SUCH A BLADE|
    EP2072760B1|2007-12-21|2012-03-21|Techspace Aero|Device for attaching vanes to a stage collar of a turbomachine stator and associated attachment method|
    FR2946999B1|2009-06-18|2019-08-09|Safran Aircraft Engines|CMC TURBINE DISPENSER ELEMENT, PROCESS FOR MANUFACTURING SAME, AND DISPENSER AND GAS TURBINE INCORPORATING SAME.|
    FR2953885B1|2009-12-14|2012-02-10|Snecma|TURBOMACHINE DRAFT IN COMPOSITE MATERIAL AND METHOD FOR MANUFACTURING THE SAME|
    FR2979573B1|2011-09-07|2017-04-21|Snecma|PROCESS FOR MANUFACTURING TURBINE DISPENSER SECTOR OR COMPRESSOR RECTIFIER OF COMPOSITE MATERIAL FOR TURBOMACHINE AND TURBINE OR COMPRESSOR INCORPORATING A DISPENSER OR RECTIFIER FORMED OF SUCH SECTORS|US10538013B2|2014-05-08|2020-01-21|United Technologies Corporation|Integral ceramic matrix composite fastener with non-polymer rigidization|
    WO2016030608A1|2014-08-26|2016-03-03|Snecma|Guide vane made from composite material, comprising staggered attachment flanges for a gas turbine engine|
    FR3041374B1|2015-09-17|2020-05-22|Safran Aircraft Engines|DISTRIBUTOR SECTOR FOR A TURBOMACHINE WITH DIFFERENTIALLY COOLED VANES|
    FR3065024B1|2017-04-10|2021-01-22|Safran Aircraft Engines|TURBOMACHINE TURBINE RING AND PROCESS FOR MANUFACTURING SUCH RING|
    US10724389B2|2017-07-10|2020-07-28|Raytheon Technologies Corporation|Stator vane assembly for a gas turbine engine|
    US10619498B2|2017-09-06|2020-04-14|United Technologies Corporation|Fan exit stator assembly|
    US10808559B2|2018-06-01|2020-10-20|Raytheon Technologies Corporation|Guide vane retention assembly for gas turbine engine|
    US10724387B2|2018-11-08|2020-07-28|Raytheon Technologies Corporation|Continuation of a shear tube through a vane platform for structural support|
    法律状态:
    2015-03-16| PLFP| Fee payment|Year of fee payment: 2 |
    2016-02-24| PLFP| Fee payment|Year of fee payment: 3 |
    2017-02-10| PLFP| Fee payment|Year of fee payment: 4 |
    2017-08-25| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170725 Owner name: HERAKLES, FR Effective date: 20170725 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 5 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN CERAMICS, FR Effective date: 20170719 Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 8 |
    2022-02-18| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1451824A|FR3018308B1|2014-03-06|2014-03-06|STATOR SECTOR FOR TURBOMACHINE AND METHOD FOR MANUFACTURING THE SAME|FR1451824A| FR3018308B1|2014-03-06|2014-03-06|STATOR SECTOR FOR TURBOMACHINE AND METHOD FOR MANUFACTURING THE SAME|
    RU2016139110A| RU2684075C2|2014-03-06|2015-03-03|Stator section for a turbine engine and method for producing a stator section, turbine engine stator, turbine engine compressor and turbine engine|
    US15/123,499| US10190426B2|2014-03-06|2015-03-03|Stator sector for a turbine engine, and a method of fabricating it|
    CA2940565A| CA2940565A1|2014-03-06|2015-03-03|Stator section for a turbomachine and method for producing the same|
    JP2016554663A| JP6649264B2|2014-03-06|2015-03-03|Stator sector for turbine engine and method of manufacturing the same|
    EP15714556.6A| EP3114324B1|2014-03-06|2015-03-03|Stator section for a turbomachine and method for producing the same|
    PCT/FR2015/050512| WO2015132523A2|2014-03-06|2015-03-03|Stator section for a turbomachine and method for producing the same|
    CN201580012167.2A| CN106103904B|2014-03-06|2015-03-03|Stator sector of a turbine engine, and method for manufacturing same|
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