Method and apparatus for handling pre-diffuser airflow for cooling high pressure turbine components

Patent metadata

Field	Value
Publication number	US-2016003149-A1
Application number	US-201414771069-A
Country	US
Kind code	A1
Filing date	Feb 28, 2014
Priority date	Feb 28, 2013
Publication date	Jan 7, 2016
Grant date	—

Abstract

A gas turbine engine is provided comprising a compressor section, a combustor section, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said compressor section.

First claim

What is claimed is:

1 . A gas turbine engine comprising:
a compressor section; a combustor section; a diffuser case module with a multiple of struts within an annular flow path from said compressor section to said combustor section, at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path; and a manifold in communication with said mid-span pre-diffuser inlet and said compressor section.

2 . The gas turbine engine as recited in claim 1 , wherein said manifold communicates a temperature tailored airflow.

3 . The gas turbine engine as recited in claim 1 , wherein said manifold communicates a temperature tailored airflow thru a heat exchanger.

4 . The gas turbine engine as recited in claim 3 , wherein said manifold communicates said temperature tailored airflow from said heat exchanger as buffer air.

5 . The gas turbine engine as recited in claim 4 , wherein said buffer air is communicated thru a buffer passage to one or more bearing compartments.

6 . The gas turbine engine as recited in claim 1 , wherein said mid-span pre-diffuser inlet supplies a temperature tailored airflow into said manifold.

7 . The gas turbine engine as recited in claim 1 , wherein said manifold communicates with a high pressure turbine of said compressor section.

8 . The gas turbine engine as recited in claim 1 , wherein said manifold is generally annular.

9 . The gas turbine engine as recited in claim 1 , wherein said manifold communicates with a row of rotor blade attachments in said compressor section.

10 . The gas turbine engine as recited in claim 9 , wherein said manifold is at least partially defined by a rotor hub.

11 . A method of communicating an airflow within a gas turbine engine, comprising:
tapping a pre-diffuser airflow as a temperature tailored airflow; and communicating the temperature tailored airflow to a compressor section.

12 . The method as recited in claim 11 , further compromising communicating the pre-diffuser airflow thru at least one of a multiple of struts.

13 . The method as recited in claim 11 , further compromising communicating the temperature tailored airflow to a high pressure compressor section of said compressor section.

14 . The method as recited in claim 11 , further compromising communicating the temperature tailored airflow to a row of guide vanes in said compressor section.

15 . The method as recited in claim 11 , further compromising communicating the temperature tailored airflow thru a manifold.

16 . The method as recited in claim 15 , further compromising communicating the temperature tailored airflow thru a heat exchanger prior to communication thru the manifold.

17 . The method as recited in claim 16 , further compromising communicating the temperature tailored airflow from the heat exchanger as buffer air.

18 . The method as recited in claim 17 , further compromising communicating the buffer air to a bearing compartment.

19 . The method as recited in claim 11 , further compromising recirculating the temperature tailored airflow thru a manifold into the compressor section.

20 . The method as recited in claim 19 , further compromising directing the manifold at least partially through a rotor hub.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Ackermann William K

Classifications

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F02C7/04

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

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title