(19)
(11)EP 2 767 698 B1

(12)EUROPEAN PATENT SPECIFICATION

(45)Mention of the grant of the patent:
03.08.2022 Bulletin 2022/31

(21)Application number: 12840521.4

(22)Date of filing:  10.10.2012
(51)International Patent Classification (IPC): 
B32B 18/00(2006.01)
F01D 5/30(2006.01)
B29C 70/24(2006.01)
F01D 5/28(2006.01)
F02C 7/00(2006.01)
B29C 70/22(2006.01)
F01D 25/00(2006.01)
C04B 35/80(2006.01)
(52)Cooperative Patent Classification (CPC):
C04B 35/80; F01D 5/3084; F05D 2300/6033; C04B 2235/5224; C04B 2235/524; C04B 2235/5244; C04B 2235/5248; C04B 2235/5252; C04B 2235/5256; C04B 2235/5268; C04B 2235/614; C04B 2235/616; C04B 2237/38; C04B 2237/60; C04B 2237/61; F01D 5/282; F01D 5/284; Y02T 50/60; B32B 18/00
(86)International application number:
PCT/JP2012/076160
(87)International publication number:
WO 2013/054798 (18.04.2013 Gazette  2013/16)

(54)

CERAMIC MATRIX COMPOSITE MEMBER

KERAMIKMATRIX-VERBUNDWERKSTOFF

ÉLÉMENT COMPOSITE À MATRICE CÉRAMIQUE


(84)Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

(30)Priority: 14.10.2011 JP 2011227221

(43)Date of publication of application:
20.08.2014 Bulletin 2014/34

(73)Proprietor: IHI Corporation
Tokyo 135-8710 (JP)

(72)Inventor:
  • WATANABE, Fumiaki
    Tokyo 135-8710 (JP)

(74)Representative: Carpmael, Robert Maurice Charles et al
Marks & Clerk LLP 15 Fetter Lane
London EC4A 1BW
London EC4A 1BW (GB)


(56)References cited: : 
WO-A1-91/15357
FR-A1- 2 939 130
FR-A1- 2 943 942
JP-A- 2005 133 717
JP-A- 2007 205 350
FR-A1- 2 939 129
FR-A1- 2 943 942
JP-A- H07 180 503
JP-A- 2005 240 797
US-A1- 2008 132 398
  
      
    Note: Within nine months from the publication of the mention of the grant of the European patent, any person may give notice to the European Patent Office of opposition to the European patent granted. Notice of opposition shall be filed in a written reasoned statement. It shall not be deemed to have been filed until the opposition fee has been paid. (Art. 99(1) European Patent Convention).


    Description

    [Technical Field]



    [0001] The present invention relates to a ceramic matrix composite member.

    [Background Art]



    [0002] Jet engines and the like include components which are subjected to large stress applied in a particular direction, such as centrifugal force, while in use. Requirements for such components include particularly high strength as well as heat resistance. For this reason, the components are usually made from metallic materials. Fig. 7(a) is a schematic cross-sectional view of a generally-used aircraft turbo-fan engine. Fig. 7(b) is a schematic view magnifying one of turbine blades of the turbo-fan engine shown in Fig. 7(a). While the engine is in operation, large centrifugal force is applied to the turbine blade in a longitudinal direction (radial direction) of a blade part. For this reason, the turbine blades are usually made from a Ni-based alloy or the like. As shown in Fig. 7(b), a turbine blade 100 includes: a blade part 102; a platform part 104 extending in a direction vertical to a principal surface of the blade part 102; and a dovetail part 106 placed at one end portion of the blade part 102. In this manner, the turbine blade 100 has a relatively complicated shape. Nevertheless, turbine blades can be manufactured with relative ease by casting a metallic material such as a Ni-based alloy.

    [0003] Ceramic matrix composite members are formed from ceramic matrix composites (CMCs) each containing ceramic fibers and a ceramic matrix. In recent years, there are growing expectations that ceramic matrix composite members will be applied to jet engine components. Ceramic matrix composite members are light in weight and excellent in heat resistance. For this reason, if ceramic matrix composite members can be used as jet engine components, it is expected that the weight and fuel consumption rate of an engine will be reduced.

    [0004] Patent Documents 1 to 3 have proposed a jet engine component to which ceramic matrix composites are applied, and a method of manufacturing the component. To put it specifically, these patent documents describe turbine blades formed from ceramic matrix composite members. In these turbine blades, the blade part is joined to the platform part by use of a matrix, a brazing material or the like. Patent Document 4 describes a ceramic matrix composite turbine blade made by matrix impregnation of a shaped preform, said preform comprising a 3D-woven airfoil and root part as well as a platform part, the latter being inserted, folded and stitched to the former.

    [Citation List]


    [Patent Literature]



    [0005] 

    [PTL1] US Patent 7510379

    [PTL2] US Patent 7094021

    [PTL3] US Patent 4650399

    [PTL 4] FR Patent application 2943942


    [Summary of Invention]


    [Technical Problem]



    [0006] The conventional turbine blade using the ceramic matrix composite member break down in some cases, because the turbine blade cannot withstand large stress (centrifugal force or the like) applied in a particular direction. The breakdown tends to start, particularly, at a portion where the parts are joined.

    [0007] An object of the present invention is to solve the foregoing problem. To put it specifically, an object of the present invention is to provide a ceramic matrix composite member, which withstands large stress (centrifugal force or the like) applied in a particular direction and is accordingly less likely to break down when used as a turbine blade.

    [Solution to Problem]



    [0008] A first aspect of the present invention provides a ceramic matrix composite member as defined in claim 1. It is to be used as a turbine blade and it includes: a principal part forming a blade part and a dovetail part; and a subordinate part forming a platform part. Here, a principal fiber in a ceramic fiber fabric forming the principal part is a continuous fiber. A direction of the principal fiber is in parallel with a direction in which stress is applied. The ceramic fiber fabric forming the principal part and a ceramic fiber fabric forming the subordinate part are joined together to form an integrated three-pronged fiber fabric. The ceramic fiber fabric forming the principal part and the ceramic fiber fabric forming the subordinate part are integrated together by being set into a mold with the ceramic fiber fabric forming the subordinate part folded at a desired angle to the ceramic fiber fabric forming the principal part. Then, a ceramic matrix is formed in the obtained molded body.

    [0009] A second aspect of the present invention provides a ceramic matrix composite member as defined in claim 2 as appended hereto. It is to be used as a turbine blade and it includes: a principal part forming a blade part and a dovetail part; and a subordinate part forming a platform part. Here, a principal fiber in a ceramic fiber fabric forming the principal part is a continuous fiber. A direction of the principal fiber is in parallel with a direction in which stress is applied. The ceramic fiber fabric forming the principal part and a ceramic fiber fabric forming the subordinate part are joined together by stitching. Thereafter, the joined ceramic fiber fabrics are integrated together by being set into a mold with the ceramic fiber fabric forming the subordinate part folded at a desired angle to the ceramic fiber fabric forming the principal part. Then, a ceramic matrix is formed in the obtained molded body.

    [Advantageous Effects of Invention]



    [0010] The present invention can provide a ceramic matrix composite member, which withstands large stress (centrifugal force or the like) applied in a particular direction and is accordingly less likely to break down when used as a turbine blade.

    [Brief Description of Drawings]



    [0011] 

    [Fig. 1] Fig. 1(a) is a schematic perspective view of a turbine blade of first and second embodiments of the present invention, and Fig. 1(b) is a schematic perspective view showing an example of a structure of a ceramic fiber fabric forming the turbine blade.

    [Fig. 2] Figs. 2(a) and 2(b) show an integrated three-pronged fiber fabric of the first embodiment of the present invention, in which Fig. 2(a) is a schematic side view of the integrated three-pronged fiber fabric and Fig. 2(b) is a cross-sectional view taken along the A-A line of Fig. 2(a).

    [Fig. 3] Figs. 3(a) and 3(b) are schematic perspective views for explaining how the integrated three-pronged fiber fabric of the first embodiment of the present invention is deformed.

    [Fig. 4] Fig. 4 (a) is a schematic side view of a fiber fabric in a principal part of a second embodiment of the present invention, Fig. 4(b) is a cross-sectional view taken along the B-B line of Fig. 4 (a), and Fig. 4(c) is a schematic front view of two platform parts.

    [Fig. 5] Fig. 5(a) is a schematic side view of the fiber fabric in the principal part of the second embodiment of the present invention, and Fig. 5(b) is a cross-sectional view taken along the C-C line of Fig. 5(a).

    [Fig. 6] Figs. 6(a) and 6(b) are schematic perspective views for explaining how the fiber fabric of the second embodiment of the present invention is deformed.

    [Fig. 7] Fig. 7 (a) is a schematic perspective view of a generally-used aircraft turbo-fan engine, and Fig. 7(b) is a schematic diagram magnifying one of turbine blades of the turbo-fan engine.


    [Description of Embodiments]



    [0012]  The present invention has been accomplished based on the following findings. A ceramic matrix composite member includes a ceramic fiber fabric forming a principal part of the ceramic matrix composite member. A principal fiber in the ceramic fiber fabric extends in a predetermined direction (the direction will be referred to as an extension direction for the sake of explanatory convenience). When the ceramic matrix composite member is used as a turbine blade, the ceramic matrix composite member is subjected to stress, such as centrifugal force associated with its rotation. In this regard, it has been found that even if the stress is large, the ceramic matrix composite member is less likely to break down when the extension direction of the principal fiber is in parallel with the direction of the stress. Furthermore, in a case where multiple parts, which will later form the ceramic matrix composite member as the turbine blade, are molded individually and joined together after a matrix is formed with the multiple parts, the ceramic matrix composite member is more likely to break down from joining portions thus formed. In contrast, it has been found that: when the multiple parts are formed integrally and the matrix is formed in the integrally molded body, bonds among fibers of the parts become stronger and the strength becomes larger as a whole; and accordingly, the ceramic matrix composite member becomes less likely to break down.

    [0013] Descriptions will be hereinbelow provided for embodiments of the present invention. Each embodiment represents a ceramic matrix composite member to be used as a turbine blade. Fig. 1(a) is a schematic perspective view of a turbine blade 1 of the embodiments of the present invention. Fig. 1(b) is a schematic perspective view showing an example of a structure of a ceramic fiber fabric forming the turbine blade. As shown in Fig. 1(a), the external shape of the turbine blade 1 may be the same as that of a generally-used turbine blade (shown in Fig. 7, for example).

    [0014]  The turbine blade 1 includes: a blade part 2 and a dovetail part 6 collectively forming a principal part; and platform parts 4 forming a subordinate part to the principal part. Each platform part 4 extends in a direction perpendicular to a principal surface of the blade part 2. The dovetail part 6 is placed at one of two end portions of the blade part 2. As shown in Fig. 1(a), the dovetail part 6 is placed in an end portion closer to the center of rotation of the turbine blade 1, for example. In this case, as shown in Fig. 1(a), the dovetail part 6 is fitted in a disk part 8. While the turbine blade 1 is in use, the disk part 8 rotates. This rotation applies strong centrifugal force to the turbine blade 1 in a longitudinal direction (radial direction) of the blade part 2.

    [0015] As shown in Fig. 1(b), a ceramic fiber fabric forming the turbine blade 1 has a three-dimensional structure. The fiber fabric having the three-dimensional structure can be obtained by: tying hundreds to thousands of ceramic fibers into a fiber bundle; and then weaving such fiber bundles in the X-, Y-, and Z-directions. To put it specifically, the fiber fabric having the three-dimensional structure can be obtained by: stacking multiple layers each obtained by arranging fiber bundles in the X-direction and in the Y-direction perpendicular to the X-direction; and stitching the multiple layers with other fiber bundles in the thickness direction of the multiple layers (in the Z-direction). It should be noted that the ceramic fiber fabric of the embodiments does not have to adopt the three-dimensional structure, or may partially adopt the three-dimensional structure.

    [0016] The ceramic fiber fabric forming the principal part (i.e., the blade part 2 and the dovetail part 6) includes a principal fiber. In the embodiments, the extension direction of the principal fiber is almost in parallel with the direction of application of the centrifugal force. In this respect, the principal fiber in the ceramic fiber fabric means a group of fibers extending in a particular direction which are among the fibers included in the fiber fabric. In addition, the particular direction means the X-direction, the Y-direction or the Z-direction, for example, if the ceramic fiber fabric has the three-dimensional structure. For this reason, in this case, the principal fiber is any one of the fiber bundles in the X-direction, the fiber bundles in the Y-direction and the bundles in the Z-direction. As described above, when the direction of the centrifugal force applied to the turbine blade is almost in parallel with the direction of the principal fiber (the X-direction, the Y-direction or the Z-direction), the turbine blade is less likely to break down even if the turbine blade is subjected to large centrifugal force.

    [0017] Furthermore, the principal fiber in the ceramic fiber fabric forming the principal part may be formed from a continuous fiber. In other words, the principal fiber is not cut out from one end portion to another end portion of the principal part. In this case, the principal fiber may be a monofilament formed only from one continuous fiber, or a multifilament formed from a bundle of continuous fibers. When the principal fiber extends in the direction almost in parallel with that of the centrifugal force, and concurrently when the principal fiber is formed from the continuous fiber, the principal fiber is less likely to break down even if the principal fiber is subjected to large centrifugal force. As a consequence, the principal part as a whole becomes less likely to break down and durable for use.

    [0018] A first embodiment of the present invention provides a ceramic matrix composite member to be used as a turbine blade, which includes: a principal part forming a blade part and a dovetail part; and a subordinate part forming platform parts. A principal fiber in a ceramic fiber fabric forming the principal part is a continuous fiber. The direction of the principal fiber is in parallel with a direction in which centrifugal force is applied. The ceramic fiber fabric forming the principal part and the ceramic fiber fabric forming the subordinate part are unified into an integrated three-pronged fiber fabric. The ceramic matrix composite member is manufactured by: integrating the two ceramic fiber fabrics together by setting the ceramic fiber fabric forming the principal part and the ceramic fiber fabric forming the subordinate part into a mold with the ceramic fiber fabric forming the subordinate part folded at a desired angle to the ceramic fiber fabric forming the principal part; and forming a ceramic matrix in the obtained molded body.

    [0019] In addition, a second embodiment of the present invention is a ceramic matrix composite member to be used as a turbine blade, which includes: a principal part forming a blade part and a dovetail part; and a subordinate part forming platform parts. A principal fiber in a ceramic fiber fabric forming the principal part is a continuous fiber. The direction of the principal fiber is in parallel with a direction in which centrifugal force is applied. The ceramic matrix composite member is manufactured by: joining the ceramic fiber fabric forming the principal part and the ceramic fiber fabric forming the subordinate part by stitching; then integrating the joined ceramic fiber fabrics together by setting the joined ceramic fiber fabrics into a mold with the ceramic fiber fabric forming the subordinate part folded at a desired angle to the ceramic fiber fabric forming the principal part; and forming a ceramic matrix in the obtained molded body.

    [0020] Descriptions will be provided for the first embodiment by use of Fig. 2 and Fig. 3. Figs. 2(a) and 2(b) are diagrams illustrating an integrated three-pronged fiber fabric 11 in which a ceramic fiber fabric 13 forming the blade part and the dovetail part (the principal part), and ceramic fiber fabrics 15 forming the platform parts (the subordinate part) are joined together. Fig. 2(a) is a schematic side view of the integrated three-pronged fiber fabric 11 and Fig. 2(b) is a cross-sectional view taken along the A-A line of Fig. 2(a).

    [0021] In the first embodiment, after the integrated three-pronged fiber fabric 11 is obtained, as shown in Fig. 3(a), the ceramic fiber fabrics 15 forming platform parts 4 (see Fig. 1) are folded at a desired angle to the ceramic fiber fabric 13 forming a blade part 2 (see Fig. 1) and a dovetail part 6 (see Fig. 1) (at almost 90 degrees in the case of the turbine blade) . Thus, the fiber fabric in the aspect shown in Fig. 3 (b) is obtained. Thereafter, overlapping portions 151 of the two fiber fabrics 15 each forming the platform part 4 are stitched together by use of other fiber bundles. This stitching makes it possible to further increase strength of the ceramic fiber fabric.

    [0022] Here, the integrated three-pronged fiber fabric 11 can be manufactured by a conventional publicly-known method, for example. For instance, the integrated three-pronged fiber fabric in a desired shape can be obtained by: tying hundreds to thousands of ceramic fibers into a fiber bundle; and then weaving such fiber bundles in the X-, Y-, and Z-directions.

    [0023] Furthermore, no specific restriction is imposed on the material quality, thickness or the like of the ceramic fibers. For example, ceramic fibers made of SiC, C, Si3N4, Al2O3, BN and the like may be used. Moreover, the thickness of the ceramic fibers may be the same as that of conventional publicly-known fibers. The thickness may be in a range from several micrometers to several tens of micrometers, for example.

    [0024] After the fiber fabric in the aspect shown in Fig. 3(b) is obtained, the obtained fiber fabric is set into a mold (not illustrated) and integrated together. The mold has an internal shape corresponding to the shape of the desired molded body, and is dividable into an appropriate number (6, for example) of pieces. The fiber fabric is set into the mold while changing its shape to the mold. Thus, the fiber fabric can be integrated together in the mold. Thereafter, the ceramic matrix is formed in the obtained molded body. The forming of the ceramic matrix can be achieved, for example, by a method using a chemical reaction of a gas, a method using sintering of solid power, and the like. For example, the matrix is precipitated in a surface of the molded body through a chemical reaction by exposing the molded body, integrated in the mold, to a material gas in a chamber. Alternatively, the integrated molded body is dipped into slurry of material power solids, and is then subjected to sintering. Other methods are also applicable.

    [0025] Next, descriptions will be provided for the second embodiment by use of Fig. 4, Fig. 5 and Fig. 6.

    [0026] Figs. 4(a), 4(b) and 4(c) are diagrams illustrating a fiber fabric 23 forming the blade part and the dovetail part (the principal part), as well as fiber fabrics 25 forming the platform parts (the subordinate part) . Fig. 4(a) is a schematic side view of the fiber fabrics 23, 25. Fig. 4(b) is a cross-sectional view taken along the B-B line of Fig. 4(a). Fig. 4(c) is a schematic front view of two platform parts.

    [0027] In the second embodiment, after the fiber fabric 23 and the fiber fabrics 25 as shown in Fig. 4 are obtained, the fiber fabric 21 in a shape shown in Fig. 5 is obtained by joining the fiber fabric 23 and the fiber fabrics 25 together by stitching. Fig. 5 (a) is a schematic side view of the fiber fabric 21 obtained by stitching. Fig. 5(b) is a cross-sectional view taken along the C-C line of Fig. 5(a). In the aspect shown in Fig. 5, the fiber fabric 23 and the fiber fabrics 25 are joined together by being stitched in the vicinity of the dovetail part, as shown in Fig. 5(b).

    [0028] Subsequently, as shown in Fig. 6(a), the fiber fabrics 25 forming the platform parts are folded at the desired angle to the fiber fabric 23 forming the blade part and the dovetail part (at 90 degrees in the case of the turbine blade). Thus, the fiber fabric in the aspect shown in Fig. 6(a) is obtained.

    [0029] After the fiber fabric in the aspect shown in Fig. 6(b) is obtained, it is desirable that overlapping portions 251 of the two fiber fabrics 25 each forming the platform part be stitched together by use of other fiber bundles, because the strength of the obtained turbine blade of the present invention is further increased.

    [0030] Here, no specific restriction is imposed on the method of manufacturing the fiber fabric 23 and the fiber fabrics 25. The fiber fabric 23 and the fiber fabrics 25 may be manufactured by use of a conventional, publicly-known method, for example. For instance, each fiber fabric in the desired shape can be obtained by: tying hundreds to thousands of ceramic fibers into a fiber bundle; and then weaving such fiber bundles in the X-, Y-, and Z-directions.

    [0031] Furthermore, no specific restriction is imposed on the material quality, thickness or the like of the ceramic fibers. For example, ceramic fibers made of SiC, C, Si3N4, Al2O3, BN and the like may be used. Moreover, the thickness of the ceramic fibers may be the same as that of conventional publicly-known fibers. The thickness may be in a range from several micrometers to several tens of micrometers, for example.

    [0032] After the fiber fabric in the aspect shown in Fig. 6(b) is obtained as described above, the obtained fiber fabric is set into the mold and integrated together. The shaping and the subsequent forming of the ceramic matrix are the same as the process for forming the ceramic matrix composite member of the first embodiment. To put it specifically, the ceramic matrix composite member is similarly manufactured by: setting the fiber fabrics into the divided mold integrating the fiber fabrics together; and then forming the ceramic matrix in the surface of the molded body by use of the foregoing method.

    [0033] It should be noted that: the present invention is not limited to the above-described embodiments; the present invention is specified by the scope of claims; and the present invention further includes all modifications which fall within the range and meanings equivalent to the scope of claims.

    [Industrial Applicability]



    [0034] The present invention provides a ceramic matrix composite member, which withstands large stress (centrifugal force or the like) applied in a particular direction and is accordingly less likely to break down when used as a turbine blade.


    Claims

    1. A ceramic matrix composite member for a turbine blade (1), comprising:

    a principal part forming a blade part (2) and a dovetail part (6); and

    a subordinate part forming a platform part (4), wherein

    a principal fiber in a ceramic fiber fabric forming the principal part is a continuous fiber,

    a direction of the principal fiber is in parallel with a direction in which stress is applied,

    characterised in that

    the ceramic fiber fabric (13) forming the principal part and a ceramic fiber fabric (15) forming the subordinate part are formed into form an integrated three pronged ceramic fiber fabric (11) obtained by weaving ceramic fibers bundles in the X-, Y- and Z-directions,

    the ceramic fiber fabric (13) forming the principal part and the ceramic fiber fabric (15) forming the subordinate part are integrated together by being set into a mold with the ceramic fiber fabric (15) forming the subordinate part folded at a desired angle to the ceramic fiber fabric (13) forming the principal part,

    a ceramic matrix is formed in the obtained molded body, and

    the ceramic fiber fabric (15) of the subordinate part is formed of two ceramic fiber fabrics provided with overlapping portions (151) stitched together.


     
    2. A ceramic matrix composite member for a turbine blade (1), comprising:

    a principal part forming a blade part (2) and a dovetail part (6); and

    a subordinate part forming a platform part (4), wherein

    a principal fiber in a ceramic fiber fabric forming the principal part is a continuous fiber,

    a direction of the principal fiber is in parallel with a direction in which stress is applied,

    characterised in that

    the ceramic fiber fabric (23) forming the principal part and a ceramic fiber fabric (25) forming the subordinate part are joined together by stitching, thereafter, the joined ceramic fiber fabrics (23, 25) are integrated together by being set into a mold with the ceramic fiber fabric (25) forming the subordinate part folded at a desired angle to the ceramic fiber fabric (23) forming the principal part,

    a ceramic matrix is formed in the obtained molded body, and

    the ceramic fiber fabric (25) of the subordinate part is formed of two ceramic fiber fabrics provided with overlapping portions ( 251)

    stitched together.


     


    Ansprüche

    1. Keramikmatrixverbundstoffelement für eine Turbinenschaufel (1), Folgendes umfassend:

    ein Hauptteil, welches ein Schaufelteil (2) und ein Schwalbenschwanzteil (6) bildet; und

    ein untergeordnetes Teil, welches ein Plattformteil (4) bildet, wobei

    eine Hauptfaser in einem Keramikfaserstoff, welcher das Hauptteil bildet, eine durchgängige Faser ist,

    eine Richtung der Hauptfaser parallel zu einer Richtung liegt, in welcher Belastung aufgebracht wird,

    dadurch gekennzeichnet, dass:

    der Keramikfaserstoff (13), welcher das Hauptteil bildet und ein Keramikfaserstoff (15), welcher das untergeordnete Teil bildet, gebildet sind, um einen integrierten dreigezackten Keramikfaserstoff (11) zu bilden, welcher durch Weben von Keramikfaserbündeln in den Richtungen X, Y und Z erhalten wird,

    der Keramikfaserstoff (13), welcher das Hauptteil bildet und der Keramikfaserstoff (15), welcher das untergeordnete Teil bildet, miteinander integriert werden, indem sie in eine Form eingesetzt werden, wobei der das untergeordnete Teil bildende Keramikfaserstoff (15) in einem gewünschten Winkel gegenüber dem das Hauptteil bildenden Keramikfaserstoff (13) gefaltet ist,

    eine Keramikmatrix in dem erhaltenen geformten Körper gebildet wird, und der Keramikfaserstoff (15) des untergeordneten Teils aus zwei Keramikfaserstoffen gebildet wird, welche mit miteinander vernadelten, überlappenden Abschnitten (151) versehen sind.


     
    2. Keramikmatrixverbundstoffelement für eine Turbinenschaufel (1), Folgendes umfassend:

    ein Hauptteil, welches ein Schaufelteil (2) und ein Schwalbenschwanzteil (6) bildet; und

    ein untergeordnetes Teil, welches ein Plattformteil (4) bildet, wobei

    eine Hauptfaser in einem Keramikfaserstoff, welcher das Hauptteil bildet, eine durchgängige Faser ist,

    eine Richtung der Hauptfaser parallel zu einer Richtung liegt, in welcher Belastung aufgebracht wird,

    dadurch gekennzeichnet, dass:

    der Keramikfaserstoff (23), welcher das Hauptteil bildet und ein Keramikfaserstoff (25), welcher das untergeordnete Teil bildet, miteinander durch Vernadeln verbunden sind, wonach die verbundenen Keramikfaserstoffe (23, 25) miteinander integriert werden, indem sie in eine Form eingesetzt werden, wobei der das untergeordnete Teil bildende Keramikfaserstoff (25) in einem gewünschten Winkel gegenüber dem das Hauptteil bildenden Keramikfaserstoff (23) gefaltet ist,

    eine Keramikmatrix in dem erhaltenen geformten Körper gebildet wird, und der Keramikfaserstoff (25) des untergeordneten Teils aus zwei Keramikfaserstoffen gebildet wird, welche mit miteinander vernadelten, überlappenden Abschnitten (251) versehen sind.


     


    Revendications

    1. Élément composite à matrice céramique pour une aube de turbine (1), comprenant :

    une pièce principale formant une pièce aube (2) et une pièce de queue d'aronde (6), et

    une pièce secondaire formant une pièce de plate-forme (4), dans lequel

    une fibre principale dans un tissu de fibre céramique formant la pièce principale est une fibre continue,

    une direction de la fibre principale est parallèle à une direction dans laquelle une tension est appliquée,

    caractérisé en ce que

    le tissu de fibre céramique (13) formant la pièce principale et un tissu de fibre céramique (15) formant la pièce secondaire sont façonnés pour former un tissu intégré de fibres de céramique à trois axes (11) obtenu en entrelaçant des faisceaux de fibres céramiques dans les directions X, Y et Z,

    le tissu de fibre céramique (13) formant la pièce principale et le tissu de fibre céramique (15) formant la pièce secondaire sont intégrés ensemble en les déposant dans un moule, de façon à ce que le tissu de fibre céramique (15) formant la pièce secondaire soit plié selon un angle souhaité par rapport au tissu de fibre céramique (13) formant la pièce principale, et

    une matrice céramique est formée dans le corps moulé obtenu, et le tissu de fibre céramique (15) de la pièce secondaire est constitué de deux tissus de fibre céramique pourvus de pièces chevauchantes (151) cousues ensemble.


     
    2. Élément composite à matrice céramique pour une aube de turbine (1), comprenant :

    une pièce principale formant une pièce aube (2) et une pièce de queue d'aronde (6), et

    une pièce secondaire formant une pièce de plate-forme (4), dans lequel

    une fibre principale dans un tissu de fibre céramique formant la pièce principale est une fibre continue,

    une direction de la fibre principale est parallèle à une direction dans laquelle une tension est appliquée,

    caractérisé en ce que

    le tissu de fibre céramique (23) formant la pièce principale et un tissu de fibre céramique (25) formant la pièce secondaire sont reliés ensemble par couture, puis les tissus de fibre de céramique (23, 25) assemblés sont intégrés ensemble en les déposant dans un moule, de façon à ce que le tissu de fibre céramique (25) formant la pièce secondaire soit plié selon un angle souhaité par rapport au tissu de fibre céramique (23) formant la pièce principale, et

    une matrice céramique est formée dans le corps moulé obtenu, et le tissu de fibre céramique (25) de la pièce secondaire est constitué de deux tissus de fibre céramique pourvus de pièces chevauchantes (251) cousues ensemble.


     




    Drawing

















    Cited references

    REFERENCES CITED IN THE DESCRIPTION



    This list of references cited by the applicant is for the reader's convenience only. It does not form part of the European patent document. Even though great care has been taken in compiling the references, errors or omissions cannot be excluded and the EPO disclaims all liability in this regard.

    Patent documents cited in the description