Patent ID: 7082770

Claim:
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.