Gas turbine engine combustor liner

Patent metadata

Field	Value
Publication number	US-10107497-B2
Application number	US-201213644634-A
Country	US
Kind code	B2
Filing date	Oct 4, 2012
Priority date	Oct 4, 2012
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

A liner for a combustor of a turbine engine includes a cooling feature which projects from a backside and one or more effusion holes that communicate(s) through the liner. The effusion hole(s) surround an opening through said liner. The cooling feature may include a trip strip or a pyramid pin fin (e.g., a three-side pyramid pin fin, a conical pyramid pin fin). The effusion hole(s) may penetrate said cooling feature. The effusion hole(s) may define an angle less than or equal to ninety (90) degrees with respect to a face of said liner. The effusion hole(s) may be proximate an opening through said liner.

First claim

What is claimed is:

1. A liner of a combustor for a turbine engine, the liner comprising:
a backside;
a plurality of cooling features projecting from said backside, wherein said plurality of cooling features includes at least one of:
a pyramid pin fin,
a three-sided pyramid pin fin, or
a conical pyramid pin fin; and

a plurality of effusion holes that communicate through said liner,
wherein each of the effusion holes are aligned with a row of the at least one of the pyramid pin fin, the three-sided pyramid pin fin, or the conical pyramid pin fin.

2. The liner as recited in claim 1 , wherein said cooling features include the pyramid pin fin.

3. The liner as recited in claim 1 , wherein said cooling features include the three-sided pyramid pin fin.

4. The liner as recited in claim 1 , wherein said cooling features include the conical pyramid pin fin.

5. The liner as recited in claim 1 , wherein at least one of said effusion holes defines an angle less than or equal to ninety degrees with respect to a face of said liner.

6. The liner as recited in claim 1 , wherein at least one of said effusion holes is proximate an opening through said liner.

7. A combustor of a turbine engine comprising:
a liner with a plurality of cooling features on a backside thereof and a multiple of effusion holes therethrough,
wherein said cooling features include at least a non-linear trip strip and at least one of:
a pyramid pin fin,
a three-sided pyramid pin fin, or
a conical pyramid pin fin,

wherein each of the effusion holes are aligned with a row of the at least one of the pyramid pin fin, the three-sided pyramid pin fin, or the conical pyramid pin fin.

8. The combustor as recited in claim 7 , wherein said cooling features include the pyramid pin fin.

9. The combustor as recited in claim 7 , wherein said cooling features include the three-sided pyramid pin fin.

10. The combustor as recited in claim 7 , wherein said cooling features include the conical pyramid pin fin.

11. The combustor as recited in claim 7 , wherein at least one of said multiple of effusion holes defines an angle with respect to a face of said liner.

12. The combustor as recited in claim 7 , wherein at least one of said effusion holes is defined adjacent to an opening through said liner.

13. A combustor of a turbine engine comprising:
a bulkhead liner with a plurality of cooling features on a backside thereof and a multiple of effusion holes therethrough, said multiple of effusion holes surround an opening through said bulkhead liner,
wherein said cooling features include at least a non-linear trip strip and at least one of:
a pyramid pin fin,
a three-sided pyramid pin fin, or
a conical pyramid pin fin,

wherein each of the effusion holes are aligned with a row of the at least one of the pyramid pin fin, the three-sided pyramid pin fin, or the conical pyramid pin fin.

14. The combustor as recited in claim 13 , wherein an axis defined by a fuel injector passes through said opening.

15. The liner as recited in claim 1 , wherein at least one of said effusion holes defines an angle of approximately thirty degrees with respect to a face of said liner.

16. The combustor as recited in claim 7 , wherein at least one of said multiple of effusion holes defines an angle of approximately thirty degrees with respect to a face of said liner and is oriented along a flow of combustion gases.

17. The combustor as recited in claim 13 , wherein at least one of said multiple of effusion holes defines an angle of approximately thirty degrees with respect to a face of said bulkhead liner.

Assignees

• Bangerter James P
• Williams Alexander W
• Mule Nicholas
• Pacheco Tougas Monica
• United Technologies Corp

Inventors

• Bangerter James P
• Williams Alexander W
• Mule Nicholas
• Pacheco-Tougas Monica

Classifications

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R3/04

  Air inlet arrangements · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title