Gas turbine engine CMC airfoil assembly

Patent metadata

Field	Value
Publication number	US-10125620-B2
Application number	US-201414906618-A
Country	US
Kind code	B2
Filing date	Jun 19, 2014
Priority date	Jul 29, 2013
Publication date	Nov 13, 2018
Grant date	Nov 13, 2018

Abstract

A gas turbine engine airfoil assembly includes an airfoil and an attachment structure respectively bonded to opposing sides of a platform. At least one of the airfoil, the platform and the attachment structure are constructed from a ceramic matrix composite.

First claim

What is claimed is:

1. A gas turbine engine airfoil assembly comprising:
an airfoil and an attachment structure respectively bonded to opposing sides of a platform, at least one of the airfoil, the platform and the attachment structure are constructed from a ceramic matrix composite, and wherein at least one of the airfoil, the attachment structure and the platform is constructed from a metal alloy.

2. The gas turbine engine airfoil assembly according to claim 1 , wherein at least one of the airfoil and the attachment structure is bonded to the platform using at least one of a transient liquid phase bonding material and a partial transient liquid phase bonding material.

3. The gas turbine engine airfoil assembly according to claim 1 , wherein at least one of the airfoil, the attachment structure and the platform is a hybrid component including ceramic matrix composite and a metallic member.

4. The gas turbine engine airfoil assembly according to claim 1 , wherein the airfoil is constructed from the ceramic matrix composite.

5. The gas turbine engine airfoil assembly according to claim 1 , wherein the platform is constructed from the ceramic matrix composite.

6. The gas turbine engine airfoil assembly according to claim 1 , wherein the attachment structure is constructed from the ceramic matrix composite.

7. The gas turbine engine airfoil assembly according to claim 1 , wherein the airfoil assembly is a blade, and the attachment structure is a root.

8. The gas turbine engine airfoil assembly according to claim 1 , wherein the airfoil assembly is a vane, and the attachment structure is a tab or a hook.

9. The gas turbine engine airfoil assembly according to claim 1 , wherein at least two of the airfoil, the platform and the attachment structure are constructed from a ceramic matrix composite.

10. The gas turbine engine airfoil assembly according to claim 1 , wherein the at least one ceramic matrix composite-constructed airfoil, platform and attachment structure includes fibers having an orientation, the fibers generally parallel to an adjacent surface to which the at least one ceramic matrix composite-constructed airfoil, platform and attachment structure is bonded.

11. The gas turbine engine airfoil assembly according to claim 10 , wherein the at least one ceramic matrix composite-constructed airfoil, platform and attachment structure includes multiply layers, each layer having fibers, the fibers between layers oriented transversely to one another.

12. The gas turbine engine airfoil assembly according to claim 1 , wherein the airfoil provides an internal cavity.

13. The gas turbine engine airfoil assembly according to claim 12 , wherein the airfoil has a variable wall thickness.

14. The gas turbine engine airfoil assembly according to claim 1 , wherein multiple airfoils are secured to common platforms to provide a vane cluster.

15. A method of manufacturing an airfoil assembly comprising:
bonding a platform to an airfoil and an attachment structure, wherein at least one of the airfoil, the platform and the attachment structure are constructed from a ceramic matrix composite, and wherein at least one of the airfoil, the attachment structure and the platform is constructed from a metal alloy.

16. The method according to claim 15 , wherein the bonding step includes melting at least one of a transient liquid phase bonding material and a partial transient liquid phase bonding material.

17. The method according to claim 15 , wherein the airfoil is constructed from a ceramic matrix composite, the method further comprising the step of wrapping the ceramic matrix composite about a die to provide the airfoil with an internal cavity.

18. The method according to claim 17 , wherein the airfoil includes a variable wall thickness.

Assignees

• United Technologies Corp

Inventors

• Alvanos Ioannis

Classifications

• C04B2237/127

  The active component for bonding being a refractory metal · CPC title

• F01D9/041

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

• C04B37/006

  consisting of metals or metal salts · CPC title

• C04B2237/80

  Joining the largest surface of one substrate with a smaller surface of the other substrate, e.g. butt joining or forming a T-joint · CPC title

• C04B37/026

  consisting of metals or metal salts · CPC title