Vane assembly for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10094239-B2
Application number	US-201514869559-A
Country	US
Kind code	B2
Filing date	Sep 29, 2015
Priority date	Oct 31, 2014
Publication date	Oct 9, 2018
Grant date	Oct 9, 2018

Abstract

A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A reinforcement spar made from a metallic material extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil.

First claim

What is claimed is:

1. A vane assembly for a gas turbine engine, the assembly comprising
an inner platform made from a metallic material,
an outer platform made from a metallic material,
a ceramic-containing airfoil that extends from the inner platform to the outer platform and engaged with at least one of the inner platform and the outer platform so that some aerodynamic loads applied to the ceramic-containing airfoil are transferred directly to at least one of the inner platform and the outer platform, and
a reinforcement spar made from a metallic material that extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil and engages an interior surface of the ceramic-containing airfoil so that some aerodynamic loads applied to the ceramic-containing airfoil are transferred to at least one of the inner platform and the outer platform,
wherein the ceramic-containing airfoil includes a first end and a second end and the interior surface of the ceramic-containing airfoil engages the reinforcement spar adjacent to the second end of the ceramic-containing airfoil,
wherein the first end of the ceramic-containing airfoil is received in one of the inner platform and the outer platform to transfer load,
wherein the ceramic-containing airfoil is disengaged from the inner platform adjacent to the second end of the ceramic-containing airfoil.

2. The vane assembly of claim 1 , wherein the reinforcement spar engages the interior surface of the ceramic-containing airfoil along half or less of the distance between the inner platform and the outer platform.

3. The vane assembly of claim 1 , wherein the reinforcement spar is formed to include an attachment flange adapted to be coupled to a turbine case and the attachment flange extends beyond the outer platform.

4. The vane assembly of claim 1 , wherein the second end of the ceramic-containing airfoil receives a portion of the inner platform.

5. The vane assembly of claim 4 , wherein the interior surface of the ceramic-containing airfoil is engaged by the reinforcement spar about midway between the first end and the second end.

6. The vane assembly of claim 4 , wherein the reinforcement spar engages the interior surface of the ceramic-containing airfoil along half or less of the distance between the inner platform and the outer platform.

7. The vane assembly of claim 4 , wherein the reinforcement spar is formed to include an attachment flange adapted to be coupled to a turbine case and the attachment flange is extends beyond the outer platform.

8. A vane assembly for a gas turbine engine, the assembly comprising
an inner platform made from a metallic material and arranged to extend at least partway around an axis of the vane assembly,
an outer platform made from a metallic material,
a ceramic-containing airfoil that extends from the inner platform to the outer platform and engaged with at least one of the inner platform and the outer platform, and
a reinforcement spar made from a metallic material coupled to at least one of the inner platform and the outer platform that extends through a hollow core of the ceramic-containing airfoil and engages an interior surface of the ceramic-containing airfoil,
wherein the reinforcement spar is formed to include an attachment flange adapted to be coupled to a turbine case and the attachment flange extends radially outward away from the inner platform and beyond the outer platform.

9. The vane assembly of claim 8 , wherein the reinforcement spar is coupled to both the inner platform and the outer platform by bicast joints.

10. The vane assembly of claim 8 , wherein the reinforcement spar engages the interior surface of the ceramic-containing airfoil along half or less of the distance between the inner platform and the outer platform.

11. The vane assembly of claim 10 , wherein the interior surface of the ceramic-containing airfoil engages the reinforcement spar adjacent to a second end of the ceramic-containing airfoil.

12. The vane assembly of claim 11 , wherein an opposing end of the ceramic-containing airfoil is engaged with the other of the inner platform and the outer platform adjacent to the opposing end to transfer load.

13. The vane assembly of claim 10 , wherein the reinforcement spar engages the interior surface of the ceramic-containing airfoil along less than half of the distance between the inner platform and the outer platform.

14. The vane assembly of claim 13 , wherein the ceramic-containing airfoil is engaged with both the inner platform and the outer platform to transfer load to both the inner platform and the outer platform.

15. A method of making a vane assembly, the method comprising
positioning a ceramic-containing airfoil between an inner platform made from a metallic material and an outer platform made from a metallic material so that the ceramic-containing airfoil extends from the inner platform to the outer platform,
engaging at least one end of the ceramic-containing airfoil with at least one of the inner platform and the outer platform to transfer load,
inserting a reinforcement spar made from a metallic material through an aperture formed in the inner platform, a hollow core of the ceramic-containing airfoil, and an aperture formed in the outer platform so that the reinforcement spar extends from the inner platform to the outer platform, and
forming bicast joints between the inner platform and the reinforcement spar as well as between the outer platform and the reinforcement spar,
wherein the reinforcement spar engages an interior surface of the ceramic-containing airfoil adjacent to an end of the ceramic-containing airfoil to transfer aerodynamic load applied to the ceramic-containing airfoil to the inner platform and the outer platform through the bicast joints,
wherein the ceramic-containing airfoil includes a first end and a second end and the interior surface of the ceramic-containing airfoil engages the reinforcement spar adjacent to the second end of the ceramic-containing airfoil,
wherein the first end of the ceramic-containing airfoil is received in the outer platform to transfer load,
wherein the ceramic-containing airfoil is disengaged from the inner platform adjacent to the second end of the ceramic-containing airfoil.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Freeman Ted J
• Varney Bruce E
• Thomas David J
• Walston Jeffrey A

Classifications

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F01D25/005 Primary

  Selecting particular materials · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic