Gas turbine engine cmc airfoil assembly

Patent metadata

Field	Value
Publication number	US-2016186583-A1
Application number	US-201414906618-A
Country	US
Kind code	A1
Filing date	Jun 19, 2014
Priority date	Jul 29, 2013
Publication date	Jun 30, 2016
Grant date	—

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.

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 at least one of the airfoil, the attachment structure and the platform is constructed from a metal alloy.

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

9 . 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.

10 . 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.

11 . The gas turbine engine airfoil assembly according to claim 10 , wherein each of the airfoil, the platform and the attachment structure are constructed from a ceramic matrix composite.

12 . 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.

13 . The gas turbine engine airfoil assembly according to claim 12 , 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.

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

15 . The gas turbine engine airfoil assembly according to claim 14 , wherein the airfoil has a variable wall thickness.

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

17 . 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.

18 . The method according to claim 17 , wherein the bonding step includes melting at least one of a transient liquid phase bonding material and a partial transient liquid phase bonding material.

19 . The method according to claim 17 , comprising the step of wrapping the ceramic matrix composite about a die to provide the airfoil with an internal cavity.

20 . The method according to claim 19 , wherein the airfoil includes a variable wall thickness.

Assignees

• United Technologies Corp

Inventors

• Alvanos Ioannis

Classifications

• F01D5/3084 Primary

  the blades being made of ceramics · CPC title

• F01D5/3007

  of axial insertion type · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• C04B37/026

  consisting of metals or metal salts · CPC title

• C04B2237/122

  based on refractory metals · CPC title