Diffuser case strut for a turbine engine

Patent metadata

Field	Value
Publication number	US-10247098-B2
Application number	US-201414890188-A
Country	US
Kind code	B2
Filing date	May 8, 2014
Priority date	May 10, 2013
Publication date	Apr 2, 2019
Grant date	Apr 2, 2019

Abstract

An inner diffuser case for a turbine engine includes a fore gas path edge and an aft gas path edge defining a strut, wherein each of the fore gas path edge and the aft gas path edge include a gas path opening, a support cone structure extending radially outward from the strut, wherein the support cone structure is operable to structurally connect the strut to a turbine engine case, a diffuser case skirt structure extending radially inward from the strut, wherein the diffuser case skirt structure is operable to structurally connect the diffuser case strut to an inner support structure of the turbine engine, and at least one direct feed air passage passing radially through the strut including a radially outward upper mixing chamber opening and a radially inward direct air feed opening, the direct air feed opening is connected to a direct air feed.

First claim

The invention claimed is:

1. A turbine engine comprising:
a compressor section having a first compressor portion and a second compressor portion, wherein the second compressor portion is a high pressure compressor relative to the first compressor portion;
a combustor in fluid communication with the compressor section;
a turbine section in fluid communication with the combustor;
a gas path passing through each of said compressor section, said combustor, and said turbine section;
the second compressor portion further including an exit guide vane at an aftmost edge, relative to gas flow through the gas path, of the second compressor portion; and an inner diffuser case including a diffuser case strut positioned in said gas path aft of said exit guide vane and fore of said combustor, wherein said diffuser case strut includes at least a first direct feed passage connected on a first end to a cooled air system and on a second end to a direct air feed, wherein said direct air feed delivers air to at least one of a compressor rim and an aftmost compressor stage of said second compressor portion and a second direct feed passage including a first end opening to the cooled air system and a second end opening to a tangential onboard injection (TOBI) system.

2. The turbine engine of claim 1 , wherein said diffuser case strut further comprises a cavity intersecting with said direct feed air passage, such that airflow through said direct feed air passage passes through said cavity.

3. The turbine engine of claim 2 , wherein said cavity is arranged such that air flowing through said cavity is conditioned within said cavity and prior to exiting said direct feed air passage.

4. The turbine engine of claim 1 , wherein said direct air feed delivers air to at least one of a compressor hub, spacer arm and an aftmost compressor stage of said second compressor portion via a compressor on board injection (COBI) system.

5. The turbine engine of claim 1 , wherein said direct air feed delivers air directly to at least one of a compressor hub, spacer arm and an aftmost compressor stage of said second compressor portion.

6. The turbine engine of claim 1 , wherein said diffuser case strut is integral to said diffuser case and wherein said diffuser case strut is connected to said high pressure compressor via a support cone and to said turbine section via an inner case skirt.

7. The turbine engine of claim 6 , further comprising an air space fore of said inner diffuser case, said air space connected to said direct feed air passage via an opening in said direct feed air passage, and wherein said air space receives air from a heat exchanger.

8. The turbine engine of claim 1 , wherein said diffuser case strut is immediately aft of the exit guide vane in said gas path.

9. A method for providing cooling air to at least an aftmost stage of a high pressure compressor in a turbine engine comprising the step of:
passing cooling air from an upper mixing chamber to an air feed through a direct feed passage in a diffuser strut and passing cooling air through a second direct feed passage in the diffuser strut, the second direct feed passage including a first end opening to the cooled air system and a second end opening to a tangential onboard injection (TOBI) system.

10. The method of claim 9 , wherein said step of passing cooling air from an upper mixing chamber to a direct air feed through a direct feed passage in a diffuser strut further comprises passing the cooling air to a compressor on board injection (COBI), thereby allowing the COBI system to cool the aftmost compressor stage.

11. An inner diffuser case for a turbine engine comprising:
a fore gas path edge and an aft gas path edge defining a strut, wherein each of said fore gas path edge and said aft gas path edge include a gas path opening;
a support cone structure extending radially outward from said strut, wherein said support cone structure is operable to structurally connect the strut to a turbine engine case;
a diffuser case skirt structure extending radially inward from said strut, wherein said diffuser case skirt structure is operable to structurally connect the diffuser case strut to an inner support structure of said turbine engine; and
at least one direct feed air passage passing radially through said strut including a radially outward upper mixing chamber opening and a radially inward direct air feed opening, said direct air feed opening is connected to a direct air feed, wherein said upper mixing chamber opening is aft of said diffuser case skirt structure, relative to said gas path, and wherein the direct feed air passage includes an air opening fore of said diffuser case skirt on a radially outward edge of said strut, such that said direct feed air passage can receive air from a hot air injection system.

12. An inner diffuser case for a turbine engine comprising:
a fore gas path edge and an aft gas path edge defining a strut, wherein each of said fore gas path edge and said aft gas path edge include a gas path opening;
a support cone structure extending radially outward from said strut, wherein said support cone structure is operable to structurally connect the strut to a turbine engine case;
a diffuser case skirt structure extending radially inward from said strut, wherein said diffuser case skirt structure is operable to structurally connect the diffuser case strut to an inner support structure of said turbine engine; and
at least one direct feed air passage passing radially through said strut including a radially outward upper mixing chamber opening and a radially inward direct air feed opening, said direct air feed opening is connected to a direct air feed and a second direct feed air passage passing radially through said strut, wherein said second direct feed air passage includes a radially outward upper mixing chamber opening and a radially inward tangential on-board injection (TOBI) passage opening.

13. The inner diffuser case of claim 12 , wherein said direct air feed is a direct air feed passage for a compressor on-board injection (COBI) system.

14. The inner diffuser case of claim 12 , further comprising a cavity defined in said strut, said cavity intersecting said direct feed air passage thereby causing a flow path through said direct feed air passage to pass through said cavity.

Assignees

• United Technologies Corp

Inventors

• Lyons Christopher B

Classifications

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title

• F05D2210/12

  gaseous, i.e. compressible · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title