Turbine vane assembly with ceramic matrix composite airfoil and friction fit metallic attachment features

Patent metadata

Field	Value
Publication number	US-10260362-B2
Application number	US-201715607744-A
Country	US
Kind code	B2
Filing date	May 30, 2017
Priority date	May 30, 2017
Publication date	Apr 16, 2019
Grant date	Apr 16, 2019

Abstract

A turbine vane for a gas turbine engine incorporating a ceramic matrix composite airfoil is disclosed in this paper. The turbine vane includes an attachment unit configured to mount the ceramic matrix composite airfoil to other metallic components of the turbine vane.

First claim

What is claimed is:

1. A turbine vane comprising:
an end wall comprising metallic materials and adapted to bound a primary gas path,
an airfoil comprising ceramic matrix composite materials and aerodynamically shaped to redirect gasses that move along the primary gas path, the airfoil formed to include an external surface exposed to the primary gas path and an internal surface, opposite the external surface, that is shielded from the primary gas path, and
an attachment unit configured to couple the airfoil to the end wall, the attachment unit shaped to include an airfoil-receiving channel that receives the airfoil and such that the attachment unit engages the external and internal surfaces of the airfoil with a friction fit so that the attachment unit is coupled via friction with the airfoil.

2. The turbine vane of claim 1 , wherein the attachment unit includes an outer collar engaged with the exterior surface of the airfoil and an inner collar engaged with an interior surface of the airfoil.

3. The turbine vane of claim 2 , wherein the outer collar includes a band that engages a portion of the exterior surface of the airfoil and a lip that engages along a radial end of the airfoil to radially locate the outer collar relative to the airfoil.

4. The turbine vane of claim 3 , wherein the band and the lip of the outer collar form surfaces defining the airfoil receiving channel, wherein the outer collar is coupled to the inner collar by a bond formed between the lip of the outer collar and the inner collar, and wherein the bond is one of a diffusion weld bond and a braze bond.

5. The turbine vane of claim 3 , wherein the inner collar includes a band that extends along a portion of the interior surface of the airfoil and a lip that engages the radial end of the airfoil to radially locate the inner collar relative to the airfoil.

6. The turbine vane of claim 5 , wherein the outer collar is coupled to the inner collar by a bond formed between the lip of the outer collar and the lip of the inner collar.

7. The turbine vane of claim 6 , wherein the bond is one of a diffusion weld bond and a braze bond.

8. The turbine vane of claim 1 , wherein the attachment unit comprises metallic materials and is coupled to the end wall by a braze bond.

9. The turbine vane of claim 1 , wherein the attachment unit comprises metallic materials and is couple to the end wall by a mechanical bi-cast joint.

10. The turbine vane of claim 1 , wherein the outer collar of the first attachment unit is integrally formed with the first end wall.

11. The turbine vane of claim 1 , wherein the airfoil is hollow such that a passageway extends from an outer radial end to an inner radial end of the airfoil.

12. A turbine vane comprising:
a first end wall comprising metallic materials and adapted to bound a primary gas path,
an airfoil comprising ceramic matrix composite materials and aerodynamically shaped to redirect gasses that move along the primary gas path, the airfoil formed to include an external surface exposed to the primary gas path and an internal surface, opposite the external surface, that is shielded from the primary gas path, and
a first attachment unit configured to couple the airfoil to the first end wall, the first attachment unit including an outer collar comprising metallic materials and an inner collar comprising metallic materials, wherein the outer collar is engaged with the exterior surface of the airfoil and the inner collar engaged with an interior surface of the airfoil such that a friction fit is established between the first attachment unit and the airfoil.

13. The turbine vane of claim 12 , wherein the outer collar of the first attachment unit is bonded to the first end wall by a braze bond.

14. The turbine vane of claim 13 , wherein the outer collar of the first attachment unit includes a gas path facing surface that is flush with a gas path facing surface of the first end wall.

15. The turbine vane of claim 12 , wherein the attachment unit comprises metallic materials and is coupled to the end wall by a mechanical bi-cast joint.

16. The turbine vane of claim 15 , wherein the outer collar of the first attachment unit includes a gas path facing surface that is flush with a gas path facing surface of the first end wall.

17. The turbine vane of claim 12 , wherein the outer collar of the first attachment unit is integrally formed with the first end wall.

18. The turbine vane of claim 12 , wherein the inner collar of the first attachment unit includes a band that extends along a portion of the interior surface of the airfoil and a lip that engages a radial end of the airfoil to radially locate the inner collar relative to the airfoil.

19. The turbine shroud of claim 18 , wherein the outer collar of the first attachment unit includes a band that engages a portion of the exterior surface of the airfoil and a lip that engages the radial end of the airfoil to radially locate the outer collar relative to the airfoil.

20. The turbine vane of claim 19 , wherein the outer collar is coupled to the inner collar by a bond formed between the lip of the outer collar and the lip of the inner collar.

21. The turbine vane of claim 12 , further comprising a second end wall comprising metallic materials and adapted to bound the primary gas path, and a second attachment unit configured to couple the airfoil to the second end wall, the second attachment unit including an outer collar comprising metallic materials and an inner collar comprising metallic materials, wherein the outer collar is engaged with the exterior surface of the airfoil and the inner collar engaged with an interior surface of the airfoil such that a friction fit is established between the second attachment unit and the airfoil.

22. The turbine vane of claim 21 , wherein the inner collar of each attachment unit includes a band that extends a portion of the interior surface of the airfoil and a lip that engages a radial end of the airfoil to radially locate the inner collar relative to the airfoil, and wherein the outer collar of each attachment unit includes a band that engages a portion of the exterior surface of the airfoil and a lip that engages the radial end of the airfoil to radially locate the outer collar relative to the airfoil.

23. A method of assembling a turbine vane, the method comprising:
slipping an inner collar comprising metallic materials into a radial end of an airfoil comprising ceramic matrix composite materials so that a band of the inner collar engages an interior surface of the airfoil and a lip of the inner collar engages a radial end of the airfoil to radially locate the inner collar relative to the airfoil,
slipping an outer collar comprising metallic materials onto the radial end of the airfoil so that a band of the outer collar engages an exterior surface of the airfoil and a lip of the outer collar engages the radial end of the airfoil to radially locate the outer collar relative to the airfoil, and
diffusion bonding the inner collar to the outer collar along a gap formed between the lip of the inner collar and the lip of the outer collar while the inner collar and the outer collar are positioned to create a friction fit with the airfoil so that an attachment unit including the inner collar, the outer collar, and the diffusion bond is established for interfacing the ceramic matrix composite materials of the airfoil with other metallic components.

24. The method of claim 23 , further

Assignees

• Rolls Royce Corp

Inventors

• Varney Bruce E

Classifications

• F05D2230/237

  Brazing · CPC title

• F01D9/044 Primary

  permanently, e.g. by welding, brazing, casting or the like · CPC title

• F01D5/141

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• C04B37/02

  with metallic articles · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title