Gas turbine engine diffuser cooling and mixing arrangement

Patent metadata

Field	Value
Publication number	US-2016201688-A1
Application number	US-201414913922-A
Country	US
Kind code	A1
Filing date	Jul 18, 2014
Priority date	Aug 28, 2013
Publication date	Jul 14, 2016
Grant date	—

Abstract

A diffuser for a gas turbine engine includes a diffuser housing that has a circumferential array of hollow struts that provide a cavity. The diffuser housing includes inlet and outlet apertures that are in fluid communication with the cavity. An opening on a trailing end of the struts is in fluid communication with the cavity. The diffuser housing is configured to introduce a fluid through the inlet aperture and receive a core flow through the opening. The fluid and core flow exit through the outlet aperture.

First claim

What is claimed is:

1 . A diffuser for a gas turbine engine comprising:
a diffuser housing having a circumferential array of hollow struts providing a cavity, the diffuser housing including inlet and outlet apertures in fluid communication with the cavity, and an opening on a trailing end of the struts in fluid communication with the cavity, the diffuser housing configured to introduce a fluid through the inlet aperture and receive a core flow through the opening, the fluid and core flow exiting through the outlet aperture.

2 . The diffuser according to claim 1 , wherein the diffuser housing includes inner and outer flow path surfaces joined by the struts and configured to provide a core flow path for the core flow.

3 . The diffuser according to claim 2 , wherein the diffuser housing includes an inner diffuser case and an outer diffuser case, and comprising a combustor secured to the diffuser housing between the inner and outer diffuser case and downstream from the struts.

4 . The diffuser according to claim 3 , wherein the opening faces the combustor.

5 . The diffuser according to claim 2 , comprising a tube extending through the diffuser housing into the strut cavity through the inlet aperture, the tube configured to provide the fluid.

6 . The diffuser according to claim 4 , comprising a seal provided between the tube and the diffuser.

7 . The diffuser according to claim 1 , wherein the outlet aperture is arranged radially inward of the inlet aperture.

8 . The diffuser according to claim 1 , wherein the trailing end has a generally flat face, and the opening is provided in the face.

9 . A gas turbine engine comprising:
a compressor section and a turbine section configured to receive a core flow; a combustor section fluidly arranged between the compressor and turbine sections; and a diffuser arranged fluidly between the compressor section and the combustor section, the diffuser having a circumferential array of hollow struts providing a cavity, the diffuser including inlet and outlet apertures in fluid communication with the cavity, and an opening on a trailing end of the struts in fluid communication with the cavity, the diffuser configured to introduce a fluid through the inlet aperture and receive the core flow through the opening, the fluid and core flow exiting through the outlet aperture.

10 . The gas turbine engine according to claim 9 , wherein the diffuser includes a diffuser housing secured to a combustor, and a mixture of the fluid and the core flow is configured to be provided to an exterior of the combustor.

11 . The gas turbine engine according to claim 9 , comprising a TOBI module arranged downstream from the strut, the TOBI module configured to receive a mixture of the fluid and the core flow.

12 . The gas turbine engine according to claim 9 , comprising a bearing compartment, the bearing compartment configured to receive a mixture of the fluid and the core flow.

13 . The gas turbine engine according to claim 9 , comprising a tube extending through the diffuser into the strut cavity through the inlet aperture, the tube configured to provide the fluid.

14 . The gas turbine engine according to claim 9 , wherein the opening faces the combustor.

15 . The gas turbine engine according to claim 9 , wherein the outlet aperture is arranged radially inward of the inlet aperture.

16 . The gas turbine engine according to claim 9 , wherein the trailing end has a generally flat face, and the opening is provided in the face.

17 . A method of supplying fluid to a gas turbine engine diffuser, comprising the steps of:
introducing a fluid to a strut cavity; introducing a core flow to the strut cavity; and mixing the fluid and the core flow to provide mixed fluid to at least one of a bearing and an inner diffuser case.

18 . The method according to claim 17 , wherein the fluid introducing step includes providing a compressor bleed air to the strut cavity.

19 . The method according to claim 17 , wherein the core flow introducing step includes flowing fluid through a trailing end of a strut providing the strut cavity that faces a combustor.

20 . The method according to claim 17 , comprising the step of providing a mixture of the fluid and the core flow to a TOBI module.

Assignees

• United Technologies Corp

Inventors

• Lyons Christopher B
• Cheung Albert K

Classifications

• F04D29/542 Primary

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F01D25/125

  of bearings · CPC title

• F01D5/082

  on the side of the rotor disc · CPC title

• F02C6/08 Primary

  the gas being bled from the gas-turbine compressor · CPC title

• F01D5/081

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title