High durability turbine exhaust case

Patent metadata

Field	Value
Publication number	US-10294816-B2
Application number	US-201414540253-A
Country	US
Kind code	B2
Filing date	Nov 13, 2014
Priority date	Jun 15, 2012
Publication date	May 21, 2019
Grant date	May 21, 2019

Abstract

A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a fan delivering air into a core engine, and into a bypass duct as bypass air, said core engine including a compressor fluidly connected to a combustor, said combustor fluidly connected to a turbine section, with a turbine exhaust case downstream of said turbine section, said turbine exhaust case including:
a central hub including a support surface; and
an outer housing secured within the gas turbine engine;
said turbine section including at least one turbine rotor, with the turbine rotor including a shaft supported at least, in part, by the support surface in the turbine exhaust case;

wherein the turbine exhaust case is constructed of at least a first material and a second material; and
said central hub having a plurality of radially outwardly extending stubs and struts extending between the outer housing and said central hub, and said plurality of radially outwardly extending stubs being welded to said struts, such that radially inner portions of an airfoil are formed by the stubs of the second material, and radially outward portions of said airfoil are formed by the struts of the first material.

2. The gas turbine engine of claim 1 , wherein said stub being formed as an integral part of said central hub by being cast, forged or wrought.

3. A gas turbine engine comprising:
a fan delivering air into a core engine, and into a bypass duct as bypass air, said core engine including a compressor fluidly connected to a combustor, said combustor fluidly connected to a turbine section, with a turbine exhaust case downstream of said turbine section;
the turbine exhaust case downstream of and in fluid communication with the core engine, the turbine exhaust case having:
a central hub including a support surface; and
an outer housing secured within the gas turbine engine;
a turbine section including at least a turbine rotor, with the turbine rotor including a shaft supported at least, in part, by the support surface in the turbine exhaust case;

wherein the turbine exhaust case is constructed of at least a first material and a second; material; and
said central hub having a plurality of radially outwardly extending stubs and struts extending between the outer housing and said central hub, and said plurality of radially outwardly extending stubs being welded to said struts, such that radially inner portions of an airfoil are formed by the stubs of the second material, and radially outward portions are formed by the struts of the first material.

4. The gas turbine engine of claim 3 , wherein said stub being formed as an integral part of said central hub by being cast, forged or wrought.

Assignees

• United Technologies Corp
• Gkn Aerospace Sweden Ab

Inventors

• Mountz Daryl B
• Kapustka Theodore W
• Levasseur Glenn
• Borg Marcus
• Berglund Joakim
• Svahn Anders
• Ockborn Johan
• Pettersson Bengt

Classifications

• F05D2300/176

  Heat-stable alloys · CPC title

• F05D2230/54

  by sheet metal manufacturing · CPC title

• F05D2230/25

  by forging · CPC title

• F01D25/30

  Exhaust heads, chambers, or the like · CPC title

• F01D25/162

  Bearing supports · CPC title