Diffuser case mixing chamber for a turbine engine

Patent metadata

Field	Value
Publication number	US-10612469-B2
Application number	US-201414910283-A
Country	US
Kind code	B2
Filing date	Aug 1, 2014
Priority date	Aug 5, 2013
Publication date	Apr 7, 2020
Grant date	Apr 7, 2020

Abstract

A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. Also included in the turbine engine is a mixing chamber. The mixing chamber is located between the compressor section and the combustor section and the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and the turbine section.

First claim

The invention claimed is:

1. A turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section;
a turbine section in fluid communication with the combustor; and
a mixing chamber defined by an inner diffuser case wall, an outer diffuser case wall, and a mixing chamber wall,
wherein the mixing chamber is located between the compressor section and the combustor section,
wherein the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and the turbine section,
wherein said outer diffuser case wall includes an opening for connecting to a bypass airflow passage such that bypass air enters the mixing chamber through the opening, and
wherein said mixing chamber wall isolates said mixing chamber from a diffuser chamber, and wherein said mixing chamber wall includes a seal having local penetrations such that diffuser air can travel from said diffuser chamber into said mixing chamber.

2. The turbine engine of claim 1 , wherein said seal is a finger seal.

3. The turbine engine of claim 1 , wherein said seal is a sheet metal seal.

4. The turbine engine of claim 1 , wherein an inner diffuser case strut includes at least one passage directing mixed air from said mixing chamber to a secondary flow passage.

5. The turbine engine of claim 4 , wherein said secondary flow passage directs the mix air from the mixing chamber to at least one turbine engine component.

6. The turbine engine of claim 5 , wherein said turbine engine component is one of a tangential on board injection system and a compressor on board injection system.

7. The turbine engine of claim 1 , wherein the bypass air entering the mixing chamber from the bypass airflow passage is overcooled air.

8. A method for cooling air comprising the steps of; receiving overcooled air in a mixing chamber, wherein said mixing chamber is defined by an inner diffuser case wall, an outer diffuser case wall, and a mixing chamber wall and is located between a compressor section and a combustor section, wherein the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and a turbine section of a turbine engine, and wherein said mixing chamber wall isolates said mixing chamber from a diffuser chamber, and wherein said mixing chamber wall includes a seal having local penetrations such that ambient air can travel from said diffuser chamber into said mixing chamber;
receiving said ambient air in the mixing chamber, wherein said ambient air is warm relative to said overcooled air;
mixing said overcooled air and said ambient air in said mixing chamber such that a desired air temperature is achieved; and
distributing mixed air to a turbine engine cooling system.

9. The method of claim 8 , wherein the step of distributing the mixed air to a turbine engine cooling system comprises distributing air to at least one of a tangential on board injection system, a compressor on board injection system, and an exit rim of the compressor section.

Assignees

• United Technologies Corp

Inventors

• Guardi Vito
• Lyons Christopher B
• Snape Nathan

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F02C9/18

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F01D5/18

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title