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A gas turbine combustor structure having improved cooling effectiveness and increased life as well as a method for improving the cooling effectiveness is disclosed. The gas turbine combustor incorporates a unique flow sleeve configuration for directing air to more effectively cool a combustion liner

A gas turbine combustor structure having improved cooling effectiveness and increased life as well as a method for improving the cooling effectiveness is disclosed. The gas turbine combustor incorporates a unique flow sleeve configuration for directing air to more effectively cool a combustion liner. The flow sleeve geometry is configured to incorporate a conical aft portion having a plurality of air feed holes that reduce pressure loss to the incoming air and flow separation effects from the surrounding combustor hardware, thereby resulting in improved combustor performance.

대표청구항 ▼

We claim: 1. A gas turbine combustor having improved cooling effectiveness and increased life, said gas turbine combustor comprising: a generally cylindrical case having a center axis, a first case flange, and a second case flange; a generally cylindrical end cover fixed to said first case flange,

We claim: 1. A gas turbine combustor having improved cooling effectiveness and increased life, said gas turbine combustor comprising: a generally cylindrical case having a center axis, a first case flange, and a second case flange; a generally cylindrical end cover fixed to said first case flange, said end cover having a plurality of first fuel nozzles arranged in an annular array about said center axis; a flow sleeve located radially within said case and coaxial with said center axis, said flow sleeve comprising: a first portion generally cylindrical in shape, having a first end, a second end, and a mounting flange, said first end proximate said first case flange, said mounting flange extending radially outward and located proximate said second case flange, and said second end proximate said mounting flange; a second portion generally conical in shape having a first end, a second end, and a plurality of feed holes, said first end of said second portion fixed to said second end of said first portion and said second end of said second portion having an inlet ring; wherein said mounting flange fixes said flow sleeve to said case at said second case flange; a combustion liner located radially within said flow sleeve, coaxial with said center axis, and in fluid communication with said plurality of first fuel nozzles, said combustion liner comprising: an inner wall, an outer wall, a first liner end, a second liner end, and a plurality of receptacles for receiving said plurality of first fuel nozzles; and, a seal fixed to said outer wall proximate said second liner end, said seal having a means for passing cooling air through said seal. 2. The gas turbine combustor of claim 1 wherein said means for passing cooling air comprises a plurality of openings. 3. The gas turbine combustor of claim 2 wherein a first supply of cooling air is directed through said plurality of openings in said seal to cool said outer wall of said liner proximate said second end. 4. The gas turbine combustor of claim 3 wherein a second supply of cooling air is directed along said inner wall of said liner to cool said inner wall proximate said second end. 5. The gas turbine combustor of claim 1 wherein said plurality of feed holes are arranged in at least one row about said second portion of said flow sleeve. 6. The gas turbine combustor of claim 1 wherein said feed holes are located forward of said combustion liner seal. 7. The gas turbine combustor of claim 1 wherein said seal is in contact with a transition duct. 8. The gas turbine combustor of claim 4 wherein a third supply of cooling air is directed along said outer wall of said liner towards said first liner end.