High durability turbine exhaust case

Patent metadata

Field	Value
Publication number	US-10280790-B2
Application number	US-201414540276-A
Country	US
Kind code	B2
Filing date	Nov 13, 2014
Priority date	Jun 15, 2012
Publication date	May 7, 2019
Grant date	May 7, 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;
the turbine section comprising:
at least a turbine rotor, with the turbine rotor include a shaft supported at least, in part, by the support surface in the turbine exhaust case;
at least one rotating blade driven by the turbine rotor, and

wherein the turbine exhaust case is constructed of at least a first material and a second material such that the turbine exhaust case captures the at least one blade should the blade become separated from the rotor at temperatures of greater than about 1200° F.; and
wherein the turbine exhaust case captures the at least one blade should the blade become separated from the rotor during conditions in which greater than about 15% of airflow through a core of the engine, which is upstream of the turbine exhaust case, is continuously bled from the core.

2. The gas turbine engine of claim 1 , wherein the turbine exhaust case captures the at least one blade should the blade become separated from the rotor during engine idle conditions.

3. A gas turbine engine comprising:
at least one fan blade driven to rotate on a fan rotor, said 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 core;
a turbine exhaust case downstream of and in fluid communication with the core, the turbine exhaust case comprising:
a central hub including a support surface; and
an outer housing secured within the gas turbine engine;

the 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; and
wherein the turbine exhaust case is constructed of at least a first material and a second material such that the turbine exhaust case continues to support an aft end of the engine should the at least one blade become separated from the fan rotor during conditions in which greater than about 15% of the airflow through the core engine is continuously bled from the core engine.

4. The gas turbine engine of claim 3 , wherein the turbine exhaust case continues to support said aft end of the engine should the fan blade become separated from the fan rotor at temperatures of greater than about 1200° F.

5. The gas turbine engine of claim 3 , wherein an engine idle condition is the condition in which greater than about 15% of the airflow through the core of the engine is continuously bled from the core.

6. A gas turbine engine comprising:
at least one fan blade driven to rotate on a fan rotor;
a turbine exhaust case comprising:
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 such that the turbine exhaust case continues to support an aft end of the engine should the at least one blade become separated from the fan rotor at temperatures of greater than about 1200° F.; and
wherein the turbine exhaust case continues to support said aft end of the engine should the at least one blade become separated from the fan rotor during conditions in which greater than about 15% of airflow through a core of the engine, which is upstream of the turbine exhaust case, is continuously bled from the core.

7. The gas turbine engine of claim 6 , wherein the turbine exhaust case continues to support said aft end of the engine should the at least one blade become separated from the fan rotor during engine idle conditions.

8. The gas turbine engine of claim 6 , further comprising a duplex bearing mounted to the shaft and configured to stabilize the turbine section for rotor dynamic stability throughout the operating range of speeds, pressures and temperatures of the turbine section.

9. The gas turbine engine of claim 8 , wherein the turbine exhaust case comprises at least one flange that is configured to enable disassembly and replacement of the duplex bearing from an aft position of the engine.

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

• F05D2230/21

  by casting · CPC title

• F01D25/005 Primary

  Selecting particular materials · CPC title

• F05D2230/25

  by forging · CPC title

• F05D2230/54

  by sheet metal manufacturing · CPC title

• F05D2300/176

  Heat-stable alloys · CPC title