| CPC F23R 3/002 (2013.01) [F02C 7/18 (2013.01); F23R 3/06 (2013.01); F05D 2220/32 (2013.01); F05D 2240/35 (2013.01); F05D 2260/202 (2013.01); F05D 2260/22141 (2013.01)] | 20 Claims |
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1. A combustor for a gas turbine engine, comprising:
a combustor liner having a wall defining a combustion chamber, the wall having an inner surface facing the combustion chamber and an outer surface across the wall from the inner surface; and
fins disposed on the outer surface,
wherein the wall defines air admission holes that extend through the wall from the outer surface to the inner surface, the air admission holes configured to admit combustion air into the combustion chamber,
wherein the wall defines film cooling holes that extend through the wall from the outer surface to the inner surface, the film cooling holes configured to admit cooling air through the wall of the combustor liner,
wherein the fins are spaced away from the film cooling holes and comprise solid structures without openings,
wherein the fins are disposed in areas of the outer surface between the film cooling holes and the air admission holes,
wherein the film cooling holes are in-part each defined by a raised structure of the wall that extends from the outer surface and that is spaced away from the air admission holes, wherein the raised structure matches the air flowing through the air passage to maximize air entry and to avoid flow disturbances, wherein the air flowing through the air passage creates wake areas downstream of the air admission holes in a direction of the air flowing through the air passage, wherein at least some of the fins are disposed in the wake areas, wherein the at least some of the fins are configured to align with an airflow around the combustor liner, including in the wake areas.
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20. A gas turbine engine comprising:
a compressor configured to compress air;
a combustor, configured to receive the compressed air from the compressor, the combustor including a combustor liner having a wall defining a combustion chamber and an air passage defined around the combustor liner, the wall having an inner surface facing the combustion chamber and an outer surface disposed across the wall from the inner surface and facing the air passage; and
fins disposed on the outer surface and projecting into the air passage,
wherein the wall defines air admission holes that extend through the wall from the outer surface to the inner surface to admit the air from the air passage into the combustion chamber,
wherein the wall defines film cooling holes that extend through the wall from the outer surface to the inner surface to cool the inner surface,
wherein the air admission holes are configured to allow air to move into the combustion chamber for combustion,
wherein the film cooling holes are configured to generate a film layer of cool air inside the combustor liner and are disposed at an angle through the wall,
wherein the air admission holes are substantially larger than the film cooling holes,
wherein the fins are disposed in areas of the outer surface between the film cooling holes and the air admission holes,
wherein the fins are formed as solid structures integral with the wall with no through holes through the wall at the fins,
wherein the fins each have an airfoil shape with a leading end, a trailing end, and a main body between the leading end and the trailing end, with a profile of the fins projecting from the outer surface and being contoured to match an airflow along the outer surface of the wall, the fins spaced apart from the film cooling holes and configured to avoid disturbing a part of the air which moves into the air admission holes, and
wherein each fin has an opening forming a cavity, wherein the cavity is a blind cavity with an end so that the cavity is open to the air passage and is closed to the combustion chamber.
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