Combustor liner helical cooling apparatus
A combustor liner is provided. The combustor liner may include an upstream portion and a downstream end portion. The upstream portion may have a radius and a length along a generally longitudinal axis. The downstream end portion may have a radius and a length along the generally longitudinal axis. The downstream end portion may define a plurality of channels. Each of the plurality of channels may extend helically through the length of the downstream end portion. Each of the plurality of channels may be configured to flow an air flow therethrough, cooling the downstream end portion.
1. A combustor liner comprising:
an upstream portion having a radius and a length along a generally longitudinal axis, the upstream portion defining a plurality of bypass holes; and
a downstream end portion having a radius and a length along the generally longitudinal axis, the downstream portion extending downstream from the plurality of bypass holes in an air flow direction, an outer surface of the downstream end portion defining a plurality of channels, each of the plurality of channels defined only in the downstream end portion and extending helically through the length of the downstream end portion,
wherein each of the plurality of channels is configured to flow an air flow therethrough, cooling the downstream end portion,
and wherein the radius of at least a portion of the downstream end portion is less than the radius of the upstream portion.
2. The combustor liner of claim 1 , wherein each of the plurality of channels extends helically through approximately the entire length of the downstream end portion.
3. The combustor liner of claim 1 , wherein each of the plurality of channels extends helically through only a portion of the length of the downstream end portion.
4. The combustor liner of claim 1 , wherein each of the plurality of channels has a length greater than the length of the downstream end portion.
5. The combustor liner of claim 1 , wherein each of the plurality of channels has a width, and wherein the width of each of the plurality of channels is substantially constant throughout the length of the channel.
6. The combustor liner of claim 5 , wherein the width of each of the channels is in the range from approximately 0.25 inches to approximately 1 inch.
7. The combustor liner of claim 1 , wherein each of the plurality of channels has a width, and wherein the width of each of the plurality of channels is reduced through the length of the channel in the direction of the air flow through the channel.
8. The combustor liner of claim 1 , wherein each of the plurality of channels has a substantially smooth surface.
9. The combustor liner of claim 1 , wherein each of the plurality of channels has a surface that includes a plurality of surface features.
10. The combustor liner of claim 1 , wherein each of the plurality of channels has a depth, and wherein the depth of each of the plurality of channels is substantially constant throughout the length of the channel.
11. The combustor liner of claim 10 , wherein the depth is in the range from approximately 0.05 inches to approximately 0.3 inches.
12. The combustor liner of claim 1 , wherein each of the plurality of channels has a depth, and wherein the depth of each of the plurality of channels is reduced through the length of the channel in the direction of the air flow through the channel.
13. The combustor liner of claim 1 , wherein the length of each of the plurality of channels is in the range from approximately 4 inches to approximately 16 inches.
14. The combustor liner of claim 1 , wherein the length of the downstream end portion is in the range from approximately 3 inches to approximately 12 inches.
15. The combustor liner of claim 1 , wherein the length of the downstream end portion is less than the length of the upstream portion.
16. The combustor liner of claim 1 , wherein the radius of the downstream end portion is generally less than the radius of the upstream portion.
17. The combustor liner of claim 1 , wherein the radius of the downstream end portion is reduced throughout the length of the downstream end portion in the direction of the air flow through the plurality of channels.
18. The combustor liner of claim 1 , wherein the radius of the upstream portion is reduced throughout a portion of the length of the upstream portion in the direction of the air flow through the plurality of channels.
19. A combustor comprising:
a combustor liner at least partially defining a hot gas path, the combustor liner including an upstream portion and a downstream end portion, the upstream portion defining a plurality of bypass holes, the upstream portion and the downstream end portion each having a radius and a length along a generally longitudinal axis, the downstream portion extending downstream from the plurality of bypass holes in an air flow direction, and wherein the radius of at least a portion of the downstream end portion is less than the radius of the upstream portion;
a transition piece coupled to the combustor liner and further defining the hot gas path; and
an annular wrapper disposed between the combustor liner and the transition piece, the annular wrapper defining a plurality of inlet passages, the plurality of inlet passages configured to provide an air flow to the downstream end portion of the combustor liner,
wherein an outer surface of the downstream end portion of the combustor liner defines a plurality of channels, each of the plurality of channels defined only in the downstream end portion and extending helically through the length of the downstream end portion, and wherein the air flow is directed from the inlet passages through the plurality of channels, cooling the downstream end portion.
20. The combustor of claim 19 , wherein each of the plurality of channels has a length greater than the length of the downstream end portion.