Ceramic matrix composite vane with added platform

Patent metadata

Field	Value
Publication number	US-11261747-B2
Application number	US-201916415172-A
Country	US
Kind code	B2
Filing date	May 17, 2019
Priority date	May 17, 2019
Publication date	Mar 1, 2022
Grant date	Mar 1, 2022

Abstract

A turbine vane assembly adapted for use in a gas turbine engine includes an aerofoil configured to interact with gases flowing through the gas turbine engine along a gas path, an outer platform that defines an outer boundary of a gas path, and an inner platform that defines an inner boundary of the gas path.

First claim

What is claimed is:

1. A turbine vane assembly for a gas turbine engine, the turbine vane assembly comprising
a ceramic matrix composite vane adapted to conduct hot gases flowing through a gas path of the gas turbine engine around the turbine vane assembly during use of the turbine vane assembly, the ceramic matrix composite vane includes an outer platform that defines an outer boundary of the gas path, an inner platform spaced apart radially from the outer platform relative to an axis to define an inner boundary of the gas path, and an aerofoil that extends radially between and interconnects the outer platform and the inner platform, and the aerofoil is formed to define an interior cavity that extends radially through the aerofoil,
a metallic support strut located in the interior cavity formed in the aerofoil and configured to receive force loads applied to the ceramic matrix composite vane by the hot gases during use of the turbine vane assembly,
a metallic reinforcement platform coupled with the metallic support strut to locate the metallic reinforcement platform radially between the inner platform of the ceramic matrix composite vane and the axis, wherein a portion of the force loads are applied to the metallic reinforcement platform instead of the inner platform during use of the turbine vane assembly and the portion of the force loads are transferred from the metallic reinforcement platform to the metallic support strut so that a total amount of the force loads applied to the ceramic matrix composite vane is reduced,
an inner seal configured to block gas from passing between the inner seal and a rotor located adjacent the inner seal and wherein the inner seal is coupled with the metallic support strut to locate the metallic reinforcement platform radially between the inner platform and the inner seal, and
a buffer seal coupled with the metallic support strut to locate the metallic reinforcement platform radially between the buffer seal and the inner platform and the buffer seal includes an axial wall and a seal flange that extends radially outward away from the axial wall and toward the metallic reinforcement platform to block axial fluid flow between the buffer seal and the metallic reinforcement platform,
wherein the metallic reinforcement platform includes a wall and a lip, the wall extends axially and circumferentially and the lip extends radially away from the wall toward the axis and circumferentially and engages the inner seal to block axial fluid flow between the inner seal and the metallic reinforcement platform.

2. The turbine vane assembly of claim 1 , wherein the metallic reinforcement platform is spaced apart radially from the inner platform to define a first chamber radially between the metallic reinforcement platform and the inner platform and the inner seal is spaced apart radially from the metallic reinforcement platform to define a second chamber radially between the metallic reinforcement platform and the inner seal.

3. The turbine vane assembly of claim 1 , wherein the metallic reinforcement platform includes a wall and a lip, the wall extends axially and circumferentially and the lip extends radially away from the wall toward the axis and circumferentially relative to the axis.

4. The turbine vane assembly of claim 1 , wherein the metallic reinforcement platform axially and circumferentially surrounds the metallic support strut.

5. The turbine vane assembly of claim 1 , wherein the entire metallic reinforcement platform is spaced apart from the inner platform.

6. The turbine vane assembly of claim 1 , wherein the metallic reinforcement platform is cantilevered from the metallic support strut in an axial fore direction and in an axial aft direction.

7. A turbine vane assembly comprising
a vane that includes an outer platform, an inner platform spaced apart radially from the outer platform relative to an axis, and an aerofoil that extends radially between the outer platform and the inner platform,
a support strut that extends radially through the aerofoil,
a reinforcement platform coupled with the support strut to locate the inner platform of the vane radially between the reinforcement platform and the outer platform of the vane,
an inner seal coupled with the support strut to locate the reinforcement platform radially between the inner platform and the inner seal, and
a buffer seal coupled with the support strut to locate the reinforcement platform radially between the buffer seal and the inner platform and the buffer seal includes an axial wall and a seal flange that extends radially outward away from the axial wall and toward the reinforcement platform.

8. The turbine vane assembly of claim 7 , wherein the reinforcement platform includes a wall and a lip, the wall extends axially and circumferentially, and the lip extends radially away from the wall toward the axis and circumferentially relative to the axis.

9. The turbine vane assembly of claim 7 , wherein the reinforcement platform is cantilevered from the support strut.

10. The turbine vane assembly of claim 7 , wherein the vane comprises ceramic materials and the reinforcement platform comprises metallic materials.

11. The turbine vane assembly of claim 7 , wherein a first chamber is defined radially between the inner platform and the reinforcement platform.

12. The turbine vane assembly of claim 7 , wherein the entire reinforcement platform is radially spaced apart from the inner platform.

13. The turbine vane assembly of claim 7 , wherein the reinforcement platform is spaced apart radially from the inner platform to define a first chamber radially between the reinforcement platform and the inner platform and the inner seal is spaced apart radially from the reinforcement platform to define a second chamber radially between the reinforcement platform and the inner seal.

Assignees

• Rolls Royce Plc

Inventors

• Steedman Emma C
• Whittle Michael J
• Jones Edward M
• Smith James C

Classifications

• F01D5/284 Primary

  Selection of ceramic materials · 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

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title