Turbine engine thermal management

Patent metadata

Field	Value
Publication number	US-10107200-B2
Application number	US-201514700172-A
Country	US
Kind code	B2
Filing date	Apr 30, 2015
Priority date	Apr 30, 2015
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

A gas turbine engine including core engine is provided. Air may enter the core engine through an inlet and travel through and engine air flowpath extending through the core engine, e.g., generally along an axial direction of the gas turbine engine. The gas turbine engine additionally includes a cooling air flowpath extending outwardly generally along the radial direction of the gas turbine engine. The cooling air flowpath extends between an inlet in flow communication with engine air flowpath and an outlet defined by an opening in an outer casing of the core engine. Moreover, the gas turbine engine includes a heat exchanger positioned at least partially within the outer casing the core engine with the cooling air flowpath extending over or through the heat exchanger.

First claim

What is claimed is:

1. A gas turbine engine defining a radial direction, the gas turbine engine comprising:
a core engine including an outer casing;
an engine air flowpath extending through the core engine;
a cooling air flowpath extending outwardly generally along the radial direction between an inlet in flow communication with the engine air flowpath and an outlet defined by an opening in the outer casing of the core engine; and
a heat exchanger positioned at least partially within the outer casing of the core engine, the cooling air flowpath extending over or through the heat exchanger.

2. The gas turbine of claim 1 , wherein the core engine includes a vent over the opening in the outer casing, the vent configured to adjust an amount of airflow allowable through the cooling air flowpath.

3. The gas turbine of claim 1 , wherein the heat exchanger is rigidly attached to the outer casing.

4. The gas turbine of claim 3 , wherein the core engine includes an annular compressor frame positioned within the outer casing, and wherein the heat exchanger is also rigidly attached to the annular compressor frame such that the heat exchanger provides structural support between the outer casing and the annular compressor frame.

5. The gas turbine of claim 1 , wherein the core engine includes a compressor section, wherein the engine air flowpath extends through the compressor section, and wherein the inlet of the cooling air flowpath is in flow communication with the engine air flowpath in the compressor section of the core engine.

6. The gas turbine of claim 1 , wherein the core engine defines a plurality of bleed air flowpaths extending outwardly generally along the radial direction from the engine air flowpath through the outer casing, wherein the gas turbine engine further defines a circumferential direction, and wherein the bleed air flowpaths and the cooling air flowpath are spaced along the circumferential direction.

7. The gas turbine of claim 6 , wherein the core engine includes an inner liner and an outer liner spaced from one another along the radial direction and at least partially defining the engine air flowpath, wherein the core engine also includes a pair of sidewalls extending outwardly along the radial direction from the outer liner at least partially defining the cooling air flowpath, wherein each of the sidewalls defines an opening allowing for air to flow between the cooling air flowpath and one or more of the bleed air flowpaths.

8. The gas turbine of claim 1 , wherein the core engine includes an inner liner and an outer liner spaced from one another along the radial direction and at least partially defining the engine air flowpath, wherein the inlet of the cooling air flowpath is defined by an opening in the outer liner, wherein the core engine further includes a variable bleed valve door positioned over the opening in the outer liner configured to vary an amount of airflow that passes therethrough and into the cooling air flowpath.

9. The gas turbine of claim 1 , wherein the heat exchanger is an air cooled oil cooler.

10. The gas turbine of claim 1 , further comprising
a fan positioned in flow communication with the core engine; and
an annular fan casing surrounding the fan and at least a portion of the core engine, the annular fan casing defining a bypass passage with the outer casing of the core engine, wherein the outlet of the cooling air flowpath defined by the opening in the outer casing of the core engine opens into the bypass passage.

11. A gas turbine engine defining a radial direction and a circumferential direction, the gas turbine engine comprising:
a core engine including an outer casing and a compressor section;
an engine air flowpath extending through the compressor section of the core engine;
a plurality of bleed air flowpaths extending outwardly generally along the radial direction from the engine air flowpath;
a cooling air flowpath extending outwardly generally along the radial direction from the engine air flowpath, the cooling air flowpath and the plurality of bleed air flowpaths spaced along the circumferential direction of the gas turbine engine; and
a heat exchanger positioned at least partially within the outer casing of the core engine, the cooling air flowpath extending over or through the heat exchanger.

12. The gas turbine of claim 11 , wherein the cooling air flowpath extends from an inlet in flow communication with the cooling air flowpath to an outlet defined by an opening in the outer casing of the core engine.

13. The gas turbine of claim 12 , wherein the core engine includes a vent over the opening in the outer casing, the vent configured to adjust an amount of airflow allowable through the cooling air flowpath.

14. The gas turbine of claim 11 , wherein the heat exchanger is rigidly attached to the outer casing.

15. The gas turbine of claim 14 , wherein the core engine includes an annular compressor frame positioned within the outer casing, and wherein the heat exchanger is also rigidly attached to the annular compressor frame such that the heat exchanger provides structural support between the outer casing and the annular compressor frame.

16. The gas turbine of claim 11 , wherein the compressor section of the core engine includes a low pressure compressor and a high pressure compressor, wherein the cooling air flowpath and the plurality of bleed air flowpaths extend outwardly generally along the radial direction from the engine air flowpath between the low pressure compressor and the high pressure compressor.

17. The gas turbine of claim 11 , wherein the core engine includes an inner liner and an outer liner spaced from one another along the radial direction and at least partially defining the engine air flowpath, wherein the core engine also includes a pair of sidewalls extending outwardly along the radial direction from the outer liner at least partially defining the cooling air flowpath, wherein each of the sidewalls defines an opening allowing for air to flow between the cooling air flowpath and one or more of the bleed air flowpaths.

18. The gas turbine of claim 11 , wherein the core engine includes an inner liner and an outer liner spaced from one another along the radial direction and at least partially defining the engine air flowpath, wherein an inlet of the cooling air flowpath is defined by an opening in the outer liner, wherein the core engine further includes a variable bleed valve door positioned over the opening in the outer liner configured to vary an amount of airflow that passes therethrough and into the cooling air flowpath.

19. The gas turbine of claim 11 , wherein the heat exchanger is an air cooled oil cooler.

20. The gas turbine of claim 11 , wherein the cooling air flowpath is a first cooling air flowpath, and wherein the gas turbine further comprises
a second cooling air flowpath extending outwardly generally along the radial direction from the engine air flowpath, the first and second cooling air flowpaths and the plurality of bleed air flowpaths spaced along the circumferential direction of the gas turbine engine; and
a second heat exchanger positioned at least partially within the outer casing of the core engine, the second cooling air flowpath extending over or through the second heat exchanger.

Assignees

• Gen Electric

Inventors

• Miller Brandon Wayne
• Glover Jeffrey

Classifications

• F28D2021/0021

  for aircrafts or cosmonautics · 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

• F02K3/075 Primary

  controlling flow ratio between flows · CPC title

• F02C7/185

  Cooling means for reducing the temperature of the cooling air or gas · CPC title

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title