Diversion Of Fan Air To Provide Cooling Air For Gas Turbine Engine

Patent metadata

Field	Value
Publication number	US-2016258359-A1
Application number	US-201514635366-A
Country	US
Kind code	A1
Filing date	Mar 2, 2015
Priority date	Mar 2, 2015
Publication date	Sep 8, 2016
Grant date	—

Abstract

A gas turbine engine section includes a plurality of spaced rotor stages, with a static guide vane intermediate the spaced rotor stages. The static guide vane provides swirl into air passing toward a downstream one of the spaced rotor stages, and an outer housing surrounding the spaced rotor stages. A diverter diverts a portion of air radially outwardly through the outer housing, and across at least one heat exchanger. The diverted air passes back into a duct radially inwardly through the outer housing, and is exhausted toward the downstream one of the spaced rotor stages.

First claim

1 . A gas turbine engine section comprising:
a plurality of spaced rotor stages, with a static guide vane intermediate said spaced rotor stages, said static guide vane providing swirl into air passing toward a downstream one of said spaced rotor stages, and an outer housing surrounding said spaced rotor stages, a diverter diverting a portion of air radially outwardly through said outer housing, and across at least one heat exchanger, with the diverted air passing back into a duct radially inwardly through said outer housing, and being exhausted toward said downstream one of said spaced rotor stages.

2 . The gas turbine engine as set forth in claim 1 , wherein said exhausted air passing through an injector.

3 . The gas turbine engine as set forth in claim 2 , wherein said injector imparting swirl into the air exhausting toward the downstream one of the two spaced turbine rotors.

4 . The gas turbine engine as set forth in claim 3 , wherein a swirl angle imparted by said injector is greater than a swirl angle imparted by said static guide vane.

5 . The gas turbine engine as set forth in claim 4 , wherein a swirl angle imparted by said static guide vane is greater than 40 degrees.

6 . The gas turbine engine as set forth in claim 5 , wherein said swirl angle is greater than 55 degrees.

7 . The gas turbine engine as set forth in claim 1 , wherein said at least one heat exchanger cooling an electronic component.

8 . The gas turbine engine as set forth in claim 1 , wherein said at least one heat exchanger cooling air from a compressor rotor.

9 . The gas turbine engine as set forth in claim 1 , wherein said spaced rotor stages are fan rotors.

10 . The gas turbine engine as set forth in claim 9 , wherein a swirl angle imparted by said static guide vane is greater than 40 degrees.

11 . The gas turbine engine as set forth in claim 10 , wherein said swirl angle is greater than 55 degrees.

12 . The gas turbine engine as set forth in claim 1 , wherein said spaced rotor stages are compressor rotors.

13 . The gas turbine engine as set forth in claim 12 , wherein a swirl angle imparted by said static guide vane is greater than 40 degrees.

14 . The gas turbine engine as set forth in claim 1 , wherein a bypass housing surrounds said outer housing and said at least one heat exchanger being positioned within a flow path in said bypass housing.

15 . The gas turbine engine as set forth in claim 14 , wherein air in said flow path cools said at least one heat exchanger.

16 . The gas turbine engine as set forth in claim 1 , wherein there are a plurality of heat exchangers.

17 . The gas turbine engine as set forth in claim 1 , wherein a swirl angle imparted by said static guide vane is greater than 40 degrees.

18 . The gas turbine engine as set forth in claim 17 , wherein said swirl angle is greater than 55 degrees.

19 . The gas turbine engine as set forth in claim 1 , wherein said portion of air diverted radially outwardly passes through a duct, and said duct extending generally axially in one direction, then being turned back in an opposed direction before passing radially inwardly and being exhausted.

20 . The gas turbine engine as set forth in claim 1 , wherein said portion of air diverted radially outwardly passes into a duct which extends circumferentially around a center axis of said engine before being directed radially inwardly and being exhausted.

Assignees

• United Technologies Corp

Inventors

• Kupratis Daniel Bernard
• Bifulco Anthony R

Classifications

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2260/601

  using an ejector or a jet pump · CPC title

• F02C7/18

  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

• F05D2260/205

  Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes · CPC title