EFFUSION COOLING TECHNIQUES FOR COMBUSTORS IN ENGINE ASSEMBLIES

• US 20100071379A1
• Filed: 09/25/2008
• Published: 03/25/2010
• Est. Priority Date: 09/25/2008
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Ertz, Timothy, Koch, Brian, Woodcock, Gregory O.
• Granted Patent: US 8,104,288 B2
• Time in Patent Office: Days
• US Class Current: 60/752
• CPC Class Codes: F05B 2260/201 by impingement of a fluid
• CPC Class Codes: F05B 2260/202 by film cooling
• CPC Class Codes: F05B 2260/203 by transpiration cooling
• CPC Class Codes: F23R 2900/03041 Effusion cooled combustion chamber walls or domes
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A combustor for an engine assembly includes a cylindrical wall forming a combustion chamber in which an air and fuel mixture is combusted; and a plurality of effusion cooling holes formed in the cylindrical wall, the plurality of effusion cooling holes oriented such that cooling air flowing therethrough cools the cylindrical wall with effusion cooling, convection cooling, and impingement cooling.

Claims

1. A combustor for an engine assembly, comprising:

a cylindrical wall forming a combustion chamber in which an air and fuel mixture is combusted; and

a plurality of effusion cooling holes formed in the cylindrical wall, the plurality of effusion cooling holes oriented such that cooling air flowing therethrough cools the cylindrical wall with effusion cooling, convection cooling, and impingement cooling.

2. The combustor of claim 1, wherein each of the plurality effusion cooling holes is oriented at an angle of about 60°

to about 120°

relative a meridinal line of a surface of the combustion chamber.

3. The combustor of claim 1, wherein each of the plurality effusion cooling holes is oriented at an angle of about 90°

relative a centerline of the combustion chamber.

4. The combustor of claim 1, wherein each of the plurality of effusion cooling holes is oriented at an angle of about 10°

to about 30°

relative to the cylindrical wall.

5. The combustor of claim 1, wherein each of the plurality of effusion cooling holes is oriented at an angle of about 20°

relative to the cylindrical wall.

6. The combustor of claim 1, wherein each of the plurality of effusion cooling holes is oriented such that the cooling air flowing therethough strikes an inner portion of the cylindrical wall.

7. The combustor of claim 1, wherein the combustion chamber is a can combustion chamber.

10. The combustor of claim 1, wherein each of the plurality effusion cooling holes is oriented at an angle of about 90°

relative a centerline of the combustion chamber.

11. The combustor of claim 1, wherein each of the plurality of effusion cooling holes is oriented at an angle of about 20°

relative to the cylindrical wall.

12. The combustor of claim 1, wherein each of the plurality of effusion cooling holes is oriented such that the cooling air flowing therethough strikes an inner portion of the cylindrical wall.

13. The combustor of claim 1, wherein the combustion chamber is a can combustion chamber.

8. A combustor for an engine assembly, comprising:

a cylindrical wall forming a combustion chamber in which an air and fuel mixture is combusted; and

a plurality of effusion cooling holes formed in the cylindrical wall, wherein each of the plurality effusion cooling holes is oriented at an angle of about 60°

to about 120°

relative a meridinal line of the combustion chamber and at an angle of about 10°

to about 30°

relative to the cylindrical wall.

9. The combustor of claim 8, wherein the plurality of effusion cooling holes is oriented such that cooling air flowing therethrough cools the cylindrical wall with effusion cooling, convection cooling, and impingement cooling.

14. An engine assembly, comprising:

a compressor section configured to supply compressed air;

a combustor section configured to received the compressed air, to mix the compressed air with fuel, and to ignite the air-fuel mixture to produce combustion gases, the combustor section comprising a combustor with a cylindrical wall and a plurality of effusion cooling holes formed in the cylindrical wall, the plurality of effusion cooling holes oriented such that cooling air flowing therethrough cools the cylindrical wall with effusion cooling, convection cooling, and impingement cooling;

a scroll assembly coupled to the combustor section and configured to receive the combustion gases; and

a turbine section coupled to the scroll assembly and configured to receive the combustion gases from the scroll assembly and to extract energy from the combustion gases.

15. The engine assembly of claim 14, wherein each of the plurality effusion cooling holes is oriented at an angle of about 60°

to about 120°

relative a meridinal of the combustion chamber.

16. The engine assembly of claim 14, wherein each of the plurality effusion cooling holes is oriented at an angle of about 90°

relative a centerline of the combustion chamber.

17. The engine assembly of claim 14, wherein each of the plurality of effusion cooling holes is oriented at an angle of about 10°

to about 30°

relative to the cylindrical wall.

18. The engine assembly of claim 14, wherein each of the plurality of effusion cooling holes is oriented at an angle of about 30°

relative to the cylindrical wall.

19. The engine assembly of claim 14, wherein each of the plurality of effusion cooling holes is oriented such that the cooling air flowing therethough strikes an inner portion of the cylindrical wall.

20. The engine assembly of claim 14, wherein the combustion is can combustor.