Heat exchanger mounted at rear of gas turbine engine for challenging temperature applications

Patent metadata

Field	Value
Publication number	US-11149643-B2
Application number	US-201615369189-A
Country	US
Kind code	B2
Filing date	Dec 5, 2016
Priority date	Dec 5, 2016
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

A gas turbine engine has a fan rotor delivering air into a bypass duct defined between an outer fan case and an outer interior housing. The fan rotor also delivers air into a compressor section, a combustor, a turbine section. A chamber is defined between the outer interior housing and an inner housing. The inner housing contains the compressor section, the combustor and the turbine section. A first conduit taps hot compressed air to be cooled and passes the air to at least one heat exchanger. The air is cooled in the heat exchanger and returned to a return conduit. The return conduit passes the cooled air to at least one of the turbine section and the compressor section. The heat exchanger has a core exhaust plane. The turbine section has at least a first and a downstream second rotor blade row, with the core exhaust plane located downstream of a center plane of the second blade row.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a fan rotor delivering air into a bypass duct defined between an outer fan case and an outer interior housing, said fan rotor also delivering air into a compressor section, a combustor, a turbine section;
a chamber defined between said outer interior housing and an inner housing;
said inner housing containing said compressor section, said combustor and said turbine section;
a first conduit for tapping hot compressed air to be cooled and passing said air to at least one heat exchanger, said air being cooled in said heat exchanger and returned to a return conduit, said return conduit passing the cooled air to at least one of said turbine section and said compressor section;
said heat exchanger having a core exhaust plane, and said turbine section having at least a first and a downstream second rotor blade row, with said core exhaust plane located downstream of a center plane of said second blade row;
wherein said turbine section includes at least a high pressure turbine and a low pressure turbine, and said heat exchanger core exhaust plane is positioned downstream of an axially downstream most end of said high pressure turbine; and
wherein said heat exchanger core exhaust plane is positioned downstream of an axially downstream most end of said low pressure turbine.

2. The gas turbine engine as set forth in claim 1 , wherein a turbine exhaust case is positioned downstream of said low pressure turbine and said heat exchanger core exhaust plane is positioned downstream of an axially downstream most end of said turbine exhaust case.

3. The gas turbine engine as set forth in claim 1 , wherein said outer interior housing includes a pivoting cowl door.

4. The gas turbine engine as set forth in claim 3 , wherein said first conduit and said return conduit stay fixed to the engine when said outer cowl door is pivoted open.

5. The gas turbine engine as set forth in claim 1 , wherein there is a shut-off valve on said first conduit for controlling the flow of hot compressed air to said heat exchanger.

6. The gas turbine engine as set forth in claim 5 , wherein a flow valve selectively allows air to flow from said bypass duct into said chamber and over said heat exchanger.

7. The gas turbine engine as set forth in claim 6 , wherein a control for said shut off valve limits the flow of hot compressed air to said heat exchanger under low power conditions and allows the flow of air to said heat exchanger under higher power conditions.

8. The gas turbine engine as set forth in claim 7 , wherein said low power conditions include at least idle and cruise conditions.

9. The gas turbine engine as set forth in claim 8 , wherein said higher power conditions include at least take-off.

10. The gas turbine engine as set forth in claim 5 , wherein a control for said shut-off valve limits the flow of hot compressed air to said heat exchanger under low power conditions and allows the flow of air to said heat exchanger under higher power conditions.

11. The gas turbine engine as set forth in claim 10 , wherein said low power conditions include at least idle and cruise conditions.

12. The gas turbine engine as set forth in claim 1 , wherein a flow valve is mounted on said outer interior housing, and selectively allows air to flow from said bypass duct into said chamber and over said heat exchanger.

13. The gas turbine engine as set forth in claim 1 , wherein said heat exchanger is formed of elongated members having fins on an outer surface.

14. The gas turbine engine as set forth in claim 13 , wherein said elongated members are tubes.

15. The gas turbine engine as set forth in claim 13 , wherein said elongated members include a first elongated member that extends radially outwardly to an elbow, and a second elongated member that returns air radially inwardly from said elbow into a housing for said engine.

16. The gas turbine engine as set forth in claim 15 , wherein said elongated members are formed of a cast nickel alloy.

17. The gas turbine engine as set forth in claim 1 , wherein said return conduit passes into a strut and radially inwardly to pass to the turbine section.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Schwarz Frederick M
• Snape Nathan

Classifications

• F02K3/115 Primary

  by means of indirect heat exchange · CPC title

• F02C7/141

  of working fluid · CPC title

• F02C3/04

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

• F05D2260/232

  characterized by the cooling medium · CPC title

• F05D2260/213

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