Staged heat exchangers for multi-bypass stream gas turbine engines

Patent metadata

Field	Value
Publication number	US-2016177828-A1
Application number	US-201514606076-A
Country	US
Kind code	A1
Filing date	Jan 27, 2015
Priority date	Feb 26, 2014
Publication date	Jun 23, 2016
Grant date	—

Abstract

A gas turbine bypass flow arrangement comprises an outer housing and an inner housing, an outer bypass duct defined between the outer housing and the inner housing and an inner bypass duct defined inwardly of the inner housing. A first heat exchanger is positioned at an upstream location within the outer bypass duct and a second heat exchanger is positioned within the inner bypass duct at an upstream location. A downstream heat exchanger is positioned to be in the path of air downstream of the second heat exchanger in the inner bypass duct. Air flowing across the downstream heat exchanger passes from the inner bypass duct into the outer bypass duct. A gas turbine engine is also disclosed.

First claim

1 . A gas turbine bypass flow arrangement comprising:
an outer housing and an inner housing, an outer bypass duct defined between said outer housing and said inner housing, and an inner bypass duct defined inwardly of said inner housing; a first heat exchanger positioned at an upstream location within said outer bypass duct and a second heat exchanger positioned within said inner bypass duct at an upstream location; and a downstream heat exchanger positioned to be in the path of air downstream of said second heat exchanger in said inner bypass duct, and air flowing across said downstream heat exchanger passing from said inner bypass duct into said outer bypass duct.

2 . The gas turbine bypass flow arrangement as set forth in claim 1 , wherein a first stage fan delivers air inwardly of said outer housing and inwardly of said inner housing, and a second stage fan delivers air inwardly of said inner housing, but does not deliver air inwardly of said outer housing.

3 . The gas turbine bypass flow arrangement as set forth in claim 2 , wherein at least one of said first and second upstream heat exchangers being utilized to cool electrical components.

4 . The gas turbine bypass flow arrangement as set forth in claim 2 , wherein at least one of said first and second upstream heat exchangers being utilized to provide air for use on an associated aircraft.

5 . The gas turbine bypass flow arrangement as set forth in claim 2 , wherein said downstream heat exchanger being utilized to cool cooling air to be used on an associated engine.

6 . The gas turbine bypass flow arrangement as set forth in claim 2 , wherein a core housing defines a radially inner extent of said inner bypass duct.

7 . The gas turbine bypass flow arrangement as set forth in claim 1 , wherein air passing through said downstream heat exchanger enters said outer bypass duct at a location downstream of said first heat exchanger.

8 . The gas turbine bypass flow arrangement as set forth in claim 2 , wherein at least one of said first and second upstream heat exchangers being utilized to cool electrical components.

9 . The gas turbine bypass flow arrangement as set forth in claim 8 , wherein at least one of said first and second upstream heat exchangers being utilized to provide air for use on an associated aircraft.

10 . The gas turbine bypass flow arrangement as set forth in claim 1 , wherein at least one of said first and second upstream heat exchangers being utilized to provide air for use on an associated aircraft.

11 . The gas turbine bypass flow arrangement as set forth in claim 1 , wherein said downstream heat exchanger being utilized to cool cooling air to be used on an associated engine.

12 . The gas turbine bypass flow arrangement as set forth in claim 1 , wherein a core housing defines a radially inner extent of said inner bypass duct.

13 . A gas turbine comprising:
a first stage fan and a second stage fan, said first stage fan delivering air inwardly of an outer housing, and into a second stage fan, said second stage fan further delivering air inwardly of an inner housing, and into a core engine including at least a compressor and a turbine , an outer bypass duct defined between said outer housing and said inner housing and an inner bypass duct defined inwardly of said inner housing; a first heat exchanger positioned at an upstream location within said outer bypass duct and a second heat exchanger positioned within said inner bypass duct at an upstream location; and a downstream heat exchanger positioned to be in the path of air downstream of said second heat exchanger in said inner bypass duct, and air flowing across said downstream heat exchanger passing from said inner bypass duct into said outer bypass duct.

14 . The gas turbine as set forth in claim 7 , wherein a first stage fan delivers air inwardly of said outer housing and inwardly of said inner housing, and a second stage fan delivers air inwardly of said inner housing, but does not deliver air inwardly of said outer housing.

15 . The gas turbine as set forth in claim 13 , wherein said at least one of said first and second upstream heat exchangers being utilized to cool electrical components.

16 . The gas turbine as set forth in claim 15 , wherein at least one of said first and second upstream heat exchangers being utilized to provide air for use on an associated aircraft.

17 . The gas turbine as set forth in claim 13 , wherein at least one of said first and second upstream heat exchangers being utilized to provide air for use on an associated aircraft.

18 . The gas turbine as set forth in claim 17 , wherein said downstream heat exchanger being utilized to cool cooling air to be used on an associated engine.

19 . The gas turbine as set forth in claim 13 , wherein said downstream heat exchanger being utilized to cool cooling air to be used on an associated engine.

20 . The gas turbine as set forth in claim 13 , wherein air passing through said downstream heat exchanger enters said outer bypass duct at a location downstream of said first heat exchanger.

Assignees

• United Technologies Corp

Inventors

• Snyder Ryan K
• Thomas Michael R

Classifications

• F02K3/06

  with front fan · 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

• F05D2260/213

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

• F05D2260/232

  characterized by the cooling medium · CPC title