Combustion liner for use in a combustor assembly and method of manufacturing

Patent metadata

Field	Value
Publication number	US-10041677-B2
Application number	US-201514972281-A
Country	US
Kind code	B2
Filing date	Dec 17, 2015
Priority date	Dec 17, 2015
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

Abstract

A combustion liner for use in a combustor assembly is provided. The combustion liner includes a side wall that defines a combustion chamber having a main flow axis extending therethrough. The combustion chamber channels a flow of combustion gas therethrough along a mixer swirl flow axis oriented obliquely relative to the main flow axis. The combustion liner also includes film cooling holes defined within the side wall. The film cooling holes are configured to discharge a pressurized fluid jet into the combustion chamber, and arranged in at least a first row and a second row positioned a first distance from the first row. The film cooling holes are arranged such that, when mixed with the flow of combustion gas, the pressurized fluid jet discharged from film cooling holes in the first row is directed along a discharge flow axis misaligned from film cooling holes in the second row.

First claim

What is claimed is:

1. A combustion liner for use in a combustor assembly, said combustion liner comprising:
a side wall that defines a combustion chamber having a main flow axis extending therethrough, wherein said combustion chamber is configured to channel a flow of combustion gas therethrough along a mixer swirl flow axis oriented obliquely relative to the main flow axis;
a plurality of film cooling holes defined within said side wall, said plurality of film cooling holes configured to discharge a pressurized fluid jet into said combustion chamber, said plurality of film cooling holes arranged in at least a first row of film cooling holes, a second row of film cooling holes positioned a first distance from said first row, and a third row of film cooling holes positioned a second distance, greater than the first distance, from said first row;
said plurality of film cooling holes arranged such that, when mixed with the flow of combustion gas, the pressurized fluid jet discharged from film cooling holes in said first row is directed along a discharge flow axis misaligned from film cooling holes in said second row and said film cooling holes in said third row are offset from said film cooling holes in said first row relative to the main flow axis such that said film cooling holes in said third row are aligned with the discharge flow axis; and
wherein said film cooling holes in said first row discharge the pressurized fluid jet at velocity such that the discharge flow axis is angled relative to the main flow axis by half an angle defined between the main flow axis and the mixer swirl flow axis.

2. The combustion liner in accordance with claim 1 , wherein said first row and said second row extend transversely relative to the main flow axis.

3. The combustion liner in accordance with claim 1 , wherein said plurality of film cooling holes arranged in each of said first row and said second row are spaced an equal distance from each other.

4. The combustion liner in accordance with claim 3 , wherein said film cooling holes in said second row are offset from said film cooling holes in said first row relative to the main flow axis by less than half a length of the equal distance.

5. The combustion liner in accordance with claim 1 , wherein the discharge flow axis is oriented obliquely relative to the main flow axis.

6. A combustor assembly comprising:
a combustion liner comprising:
a side wall that defines a combustion chamber having a main flow axis extending therethrough;
a plurality of film cooling holes defined within said side wall, said plurality of film cooling holes configured to discharge a pressurized fluid jet into said combustion chamber, said plurality of film cooling holes arranged in at least a first row of film cooling holes, a second row of film cooling holes positioned a first distance from said first row, and a third row of film cooling holes positioned a second distance, greater than the first distance, from said first row, wherein film cooling holes in said third row are offset from said film cooling holes in said first row relative to the main flow axis such that said film cooling holes in said third row are aligned with a discharge flow axis; and
a mixer positioned at an upstream end of said combustion liner, said mixer configured to channel a flow of combustion gas into said combustion chamber along a mixer swirl flow axis oriented obliquely relative to the main flow axis, wherein said plurality of film cooling holes are arranged such that, when mixed with the flow of combustion gas, the pressurized fluid jet discharged from film cooling holes in said first row is directed along the discharge flow axis misaligned from film cooling holes in said second row and wherein said film cooling holes in said first row discharge the pressurized fluid jet at a velocity such that the discharge flow axis is angled relative to the main flow axis by half an angle defined between the main flow axis and the mixer swirl flow axis.

7. The combustor assembly in accordance with claim 6 , wherein said first row and said second row extend transversely relative to the main flow axis.

8. The combustor assembly in accordance with claim 6 , wherein said plurality of film cooling holes arranged in each of said first row and said second row are spaced an equal distance from each other.

9. The combustor assembly in accordance with claim 8 , wherein said film cooling holes in said second row are offset from said film cooling holes in said first row relative to the main flow axis by less than half a length of the equal distance.

10. The combustor assembly in accordance with claim 6 , wherein the discharge flow axis is oriented obliquely relative to the main flow axis.

11. A method of manufacturing a combustion liner for use in a combustor assembly, said method comprising:
defining a plurality of film cooling holes within a side wall of the combustor assembly, the side wall defining a combustion chamber having a main flow axis extending therethrough, the plurality of film cooling holes configured to discharge a pressurized fluid jet into the combustion chamber, the combustion chamber configured to channel a flow of combustion gas therethrough along a mixer swirl flow axis angled obliquely relative to the main flow axis; and
arranging the plurality of film cooling holes in at least a first row of film cooling holes, a second row of film cooling holes positioned a first distance from the first row, and a third row of film cooling holes positioned a second distance, greater than the first distance, from the first row, the plurality of film cooling holes arranged such that, when mixed with the flow of combustion gas, the pressurized fluid jet discharged from film cooling holes in the first row is directed along a discharge flow axis misaligned from film cooling holes in the second row, comprising:
offsetting film cooling holes in the third row from film cooling holes in the first row relative to the main flow axis such that the film cooling holes in the third row are aligned with the discharge flow axis;
wherein offsetting film cooling holes in the third row comprises defining the discharge flow axis as angled obliquely relative to the main flow axis by half an angle defined between the main flow axis and the mixer swirl flow axis.

12. The method in accordance with claim 11 , wherein arranging the plurality of film cooling holes comprises extending the first row and the second row transversely relative to the main flow axis.

13. The method in accordance with claim 11 , wherein arranging the plurality of film cooling holes comprises arranging the plurality of film cooling holes such that the film cooling holes in each of the first row and the second row are spaced an equal distance from each other.

14. The method in accordance with claim 13 , wherein arranging the plurality of film cooling holes comprises offsetting the film cooling holes in the second row from the film cooling holes in the first row relative to the main flow axis by less than half a length of the equal distance.

Assignees

• Gen Electric

Inventors

• Fitzpatrick Erich Robert
• Stieg Michael Alan
• Kenoyer Kimberly Lynne Christman

Classifications

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title