Combustion liner having improved cooling and sealing
View Patent ↗A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness along the aft end of the combustion liner is improved, resulting in extended component life, while utilizing a simpler combustion liner geometry. The region of the combustion liner proximate its second end comprises a plurality of spring seals that seal against a transition duct while admitting a cooling fluid to pass into a passage, formed between the combustion liner and spring seals, that feeds a plurality of cooling holes located in the combustion liner proximate the liner second end. Depending on the cooling requirements, the cooling holes can be angled both axially and circumferentially to maximize the cooling effectiveness.
1. A combustion liner for a gas turbine engine, said combustion liner comprising:
a centerline;
a first end;
a second end;
a first cylindrical portion proximate said first end;
a second portion fixed to said first portion and extending towards said second end;
a third cylindrical portion fixed to said second portion proximate said second end, said third portion comprising:
an inner liner wall;
an outer liner wall;
a first spring seal adjacent to said outer liner wall and having a first length and a plurality of first axial slots, with each of said first axial slots having a first width;
a second spring seal adjacent to said first spring seal and having a second length and a plurality of second axial slots, with each of said second axial slots having a second width; and,
a plurality of cooling holes extending from said outer liner wall to said inner liner wall.
2. The combustion liner of claim 1 wherein said second portion is generally conical.
3. The combustion liner of claim 1 wherein said second portion is generally cylindrical.
4. The combustion liner of claim 1 wherein said first length is greater than said second length.
5. The combustion liner of claim 1 wherein said first width is greater than said second width.
6. The combustion liner of claim 1 wherein said cooling holes have a hole diameter between 0.015 and 0.125 inches.
7. The combustion liner of claim 1 wherein said cooling holes are oriented generally towards said second end at a first angle α relative to said outer wall.
8. The combustion liner of claim 7 wherein said first angle α is between 10 and 75 degrees.
9. The combustion liner of claim 7 wherein said cooling holes are further oriented in a generally circumferential direction at a second angle β relative to said centerline.
10. The combustion liner of claim 9 wherein said second angle β is up to 80 degrees.
11. The combustion liner of claim 1 wherein said first and second spring seals are fixed to said combustion liner proximate said second end of said combustion liner.
12. The combustion liner of claim 1 wherein a cooling fluid passes through said first axial slots, into an annular plenum formed between said outer liner wall of said combustion liner and said first spring seal, and through said cooling holes.
13. A combustion liner for a gas turbine engine, said combustion liner comprising:
a centerline;
a first end;
a second end;
a first cylindrical portion proximate said first end;
a second generally conical portion fixed to said first portion and extending towards said second end;
a third cylindrical portion fixed to said second portion proximate said second end, said third portion comprising:
an inner liner wall;
an outer liner wall;
a first spring seal adjacent to said outer liner wall and having a first length and a plurality of first axial slots, with each of said first axial slots having a first width;
a second spring seal adjacent to said first spring seal and having a second length and a plurality of second axial slots, with each of said second axial slots having a second width; and,
a plurality of cooling holes extending from said outer liner wall to said inner liner wall, said cooling holes oriented generally towards said second end at a first angle α relative to said outer wall and in a generally circumferential direction at a second angle β relative to said centerline.
14. The combustion liner of claim 13 wherein said first length is greater than said second length.
15. The combustion liner of claim 13 wherein said first width is greater than said second width.
16. The combustion liner of claim 13 wherein said cooling holes have a hole diameter between 0.015 and 0.125 inches.
17. The combustion liner of claim 13 wherein said first angle α is between 10 and 75 degrees.
18. The combustion liner of claim 17 wherein said second angle β is up to 80 degrees.
19. The combustion liner of claim 13 wherein said first and second spring seals are fixed to said combustion liner proximate said second end of said combustion liner.
20. The combustion liner of claim 13 wherein a cooling fluid passes through said first axial slots, into an annular plenum formed between said outer liner wall of said combustion liner and said first spring seal, and through said cooling holes.