Low profile compressor bleed air-oil coolers

Patent metadata

Field	Value
Publication number	US-9714610-B2
Application number	US-201213645067-A
Country	US
Kind code	B2
Filing date	Oct 4, 2012
Priority date	Oct 4, 2012
Publication date	Jul 25, 2017
Grant date	Jul 25, 2017

Abstract

An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed.

First claim

What is claimed is:

1. An air-oil cooler for a gas turbine engine which includes a fan, a low pressure compressor downstream of the fan, a low pressure compressor panel which is radially outwardly from the low pressure compressor, and a V-groove downstream of the low pressure compressor panel, the air-oil cooler comprising:
an oil inlet receiving a hot oil from a component of the gas turbine engine;
an oil outlet; and
a plurality of heat exchange elements between the oil inlet and the oil outlet, wherein the air-oil cooler has a curved geometry and extends circumferentially about the low pressure compressor, wherein the air-oil cooler is longitudinally located between the fan and the V-groove and radially spaced between the low pressure compressor and the low pressure compressor panel and the air-oil cooler has a low profile such that the air-oil cooler does not protrude outside of the low pressure compressor panel, and wherein the air-oil cooler receives a current of cold air bled from the low pressure compressor and the current of cold air bled exits the air-oil cooler through an overboard exhaust.

2. The air-oil cooler of claim 1 , wherein the air-oil cooler is subjected to the direct action of the current of cold air, and wherein the cold air exits through an overboard exhaust of the engine after flowing over the air-oil cooler.

3. The air-oil cooler of claim 1 , wherein the gas turbine engine further comprises a core nacelle which is circumferentially around the low pressure compressor, and wherein the air-oil cooler is positioned radially inwardly from the core nacelle.

4. The air-oil cooler of claim 1 , wherein the gas turbine engine further comprises a firewall downstream of the low pressure compressor panel, and wherein the air-oil cooler is longitudinally located between the fan and the firewall.

5. The air-oil cooler of claim 1 , wherein the heat exchange elements have a one-pass configuration.

6. The air-oil cooler of claim 1 , wherein the heat exchange elements have a two-pass configuration.

7. The air-oil cooler of claim 1 , wherein the air-oil cooler is positioned in a cavity between the low pressure compressor and the low pressure compressor panel.

8. A gas turbine engine which includes a fan, a low pressure compressor downstream of the fan, a low pressure compressor panel which is radially outwardly from the low pressure compressor, and a V-groove downstream of the low pressure compressor panel, the gas turbine engine comprising:
an air-oil cooler, the air oil cooler comprising:
an oil inlet receiving a hot oil from a component of the gas turbine engine;
an oil outlet; and
a plurality of heat exchange elements between the oil inlet and the oil outlet,
wherein the air-oil cooler has a curved geometry and extends circumferentially about the low pressure compressor, wherein the air-oil cooler is longitudinally located between the fan and the V-groove and radially spaced between the low pressure compressor and the low pressure compressor panel and the air-oil cooler has a low profile such that the air-oil cooler does not protrude outside of the low pressure compressor panel, and wherein the air oil cooler receives a current of cold air bled from the low pressure compressor and the current of cold air bled exits the air-oil cooler through an overboard exhaust.

9. The gas turbine engine of claim 8 , wherein the air-oil cooler is subjected to the direct action of the current of cold air, and wherein the cold air exits through an overboard exhaust of the engine after flowing over the air-oil cooler.

10. The gas turbine engine of claim 8 , wherein the gas turbine engine further comprises a core nacelle which is circumferentially around the low pressure compressor, and wherein the air-oil cooler is positioned radially inwardly from the core nacelle.

11. The gas turbine engine of claim 8 , wherein the gas turbine engine further comprises a firewall downstream of the low pressure compressor panel, and wherein the air-oil cooler is longitudinally located between the fan and the firewall.

12. The gas turbine engine of claim 8 , wherein the heat exchange elements have a one-pass configuration.

13. The gas turbine engine of claim 8 , wherein the heat exchange elements have a two-pass configuration.

14. The gas turbine engine of claim 8 , wherein the air-oil cooler is positioned in a cavity between the low pressure compressor and the low pressure compressor panel.

15. A method of operating an air-oil cooler for use on a gas turbine engine which includes a fan, a low pressure compressor downstream of the fan, a low pressure compressor panel which is radially outwardly from the low pressure compressor, and a V-groove downstream of the low pressure compressor panel, the method comprising the steps of:
providing the air-oil cooler with a curved geometry extending circumferentially about the low pressure compressor and an oil inlet receiving a hot oil from a first component of the gas turbine engine, an oil outlet, and a plurality of heat exchange elements between the oil inlet and oil outlet;
placing the air-oil cooler longitudinally between the fan and the V-groove and radially between the low pressure compressor and the low pressure compressor panel, the air-oil cooler having a low profile such that the air-oil cooler does not protrude outside of the low pressure compressor panel;
extending the air-oil cooler circumferentially about the low pressure compressor;
flowing a current of cold air bled from the low pressure compressor over the air-oil cooler;
cooling the hot oil via the air-oil cooler; and
exiting the current of cold air bled from the air-oil cooler into a core nacelle of the gas turbine engine.

16. The method of claim 15 , further comprising the steps of:
flowing the hot oil from the first component of the gas turbine engine to the air-oil cooler; and
flowing a cooled oil from the air-oil cooler to a second component of the gas turbine engine.

17. The method of claim 15 , further comprising the step of:
providing an overboard exhaust for the cold air to exit after blowing the cold air over the air-oil cooler.

18. The method of claim 15 , further comprising the steps of:
providing the gas turbine engine with the core nacelle circumferentially around the low pressure compressor; and
placing the air-oil cooler radially inwardly from the core nacelle.

19. The method of claim 15 , further comprising the steps of:
providing a firewall in the gas turbine engine, the firewall being positioned longitudinally downstream of the low pressure compressor panel and radially outwardly from the low pressure compressor; and
placing the air-oil cooler longitudinally between the fan and the firewall.

20. The method of claim 15 , further comprising the step of:
placing the air-oil cooler in a cavity between the low pressure compressor and the low pressure compressor panel.

Assignees

• United Technologies Corp

Inventors

• Snape Nathan
• Suciu Gabriel L
• Pickford Simon
• Penda Allan R

Classifications

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F02C7/14

  of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} · CPC title

• F02C6/08 Primary

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

• F05D2260/213

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