Connection between a ceramic matrix composite stator sector and a metallic support of a turbomachine turbine

Patent metadata

Field	Value
Publication number	US-11208906-B2
Application number	US-201816769498-A
Country	US
Kind code	B2
Filing date	Dec 3, 2018
Priority date	Dec 5, 2017
Publication date	Dec 28, 2021
Grant date	Dec 28, 2021

Abstract

A turbine of a turbomachine includes a ceramic matrix composite sector of a stator includes an outer platform and an inner platform connected via at least one vane. The outer platform has means for attaching to a sector of a metallic support, the attachment means having at least one central rim and two lateral rims. The central rim is radially offset with respect to said lateral rims along a directrix line such that the central rim is radially on one side of said directrix line and the lateral rims on the other. The central rim and said central hook bear radially against one another and are located radially on either side of said directrix line. The lateral rim and said corresponding lateral hook bear radially against one another and are located radially on either side of said directrix line.

First claim

The invention claimed is:

1. A sector of an annular sectorized turbine stator made of ceramic matrix composite for a turbine of a turbomachine, said sector of the turbine stator comprising an outer platform and an inner platform coaxial with said outer platform, said outer platform being connected to said inner platform via at least one fixed straightening vane extending in a radial direction, said outer platform comprising attachment means for attaching to a sector of an annular sectorized metallic support,
wherein the attachment means comprise a central rim and first and second lateral rims located circumferentially on either side of the central rim, the central rim and the lateral rims extending in an axial direction perpendicular to the radial direction, said central rim being radially offset with respect to said lateral rims along a guiding line (L) coinciding with a face of each of said central rim and the lateral rims such that the central rim is radially on one side of said guiding line (L) and the lateral rims on the other, said central rim being configured to cooperate with a central hook of said sector of the support so that said central rim and said central hook are bearing radially against one another and are located radially on either side of said guiding line (L), the first and second lateral rims being configured to cooperate with corresponding first and second lateral hooks, respectively, of said sector of the support so that each lateral rim and said corresponding lateral hook are bearing radially against one another and are located radially on either side of said guiding line (L).

2. The sector of the turbine stator according to claim 1 , wherein each lateral rim is circumferentially offset from said central rim by a predetermined distance (E).

3. The sector of the turbine stator according to claim 2 , wherein the predetermined distance (E) is less than 0.5 mm.

4. The sector of the turbine stator according to claim 1 , wherein the guiding line (L) is rectilinear or curvilinear.

5. The sector of the turbine stator according to claim 1 , wherein each of said rims has a rectangular cross-section.

6. An annular sectorized turbine stator of a turbine of a turbomachine comprising a plurality of sectors of the turbine stator according to claim 1 , said sectors of the turbine stator being arranged circumferentially end to end.

7. An assembly of a turbine of a turbomachine comprising the annular sectorized turbine stator and the annular sectorized metallic support according to claim 1 .

8. A turbine of a turbomachine comprising the assembly according to claim 7 .

9. A turbomachine comprising the turbine according to claim 8 .

10. A sector of an annular sectorized support of a turbine of a turbomachine, said sector of the support being metallic and comprising an outer shell comprising reception means for receiving a ceramic matrix composite sector of a turbine stator, wherein the reception means comprise a central hook and first and second lateral hooks located circumferentially on either side of the central hook, the central hook and lateral hooks extending in an axial direction, said central hook being radially offset with respect to said lateral hooks along a guiding line (L) coinciding with one face of each of said central hook and lateral hooks so that the central hook is radially on one side of said guiding line (L) and the lateral hooks on the other, said central hook being configured to cooperate with a central rim of said sector of the turbine stator so that said central hook and said central rim are bearing radially against one another and are located radially on either side of said guiding line (L), the first and second lateral hooks being configured to cooperate with corresponding first and second lateral rims, respectively, of said sector of the turbine stator so that each lateral hook and said corresponding lateral rim are bearing radially against one another and are located radially on either side of said guiding line (L).

11. The sector of the support according to claim 10 , wherein each lateral hook is circumferentially offset from said central hook by a predetermined distance (E).

12. The sector of the support according to claim 11 , wherein the predetermined distance (E) is less than 0.5 mm.

13. The sector of the support according to claim 10 , wherein the guiding line (L) is rectilinear or curvilinear.

14. The sector of the support according to claim 10 , wherein each of said hooks has a rectangular cross-section.

15. An annular sectorized support for a turbine stator of a turbine of a turbomachine comprising a plurality of sectors of the support according to claim 10 , said sectors of the support being arranged circumferentially end to end.

Assignees

• Safran Aircraft Engines
• Safran Helicopter Engines

Inventors

• Tableau Nicolas Paul
• Congratel Sébastien Serge Francis
• Quennehen Lucien Henri Jacques
• Lepretre Gilles Gérard Claude
• Boisseleau Denis Daniel Jean

Classifications

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title