Patent ID: 8051663

Claim:
A gas turbine engine comprising: a compressor; a turbine operative to rotate the compressor; and a combustion section operative to provide thermal energy for rotating the turbine; the combustion section comprising: a transition piece having an open, upstream end; a liner having an outer side, an inner side, an upstream end and a downstream end, the outer side being configured to face away from a combustion reaction of the combustion section, the inner side being configured to face the combustion reaction, and the downstream end being received within the open, upstream end of the transition piece such that gas associated with the combustion reaction is directed from the liner, through the transition piece and to the turbine; a barrier wall attached to the outer side of the liner; a cooling air channel located between the outer side of the liner and the barrier wall, and in fluid communication with an aperture in the barrier wall; a plurality of cooling holes extending between the cooling air channel and the inner side of the liner; and a seal positioned between downstream end of the liner and the transition piece; the combustion section being operative to direct cooling air from the outer side of the liner, through the aperture, the cooling air channel and the cooling holes, to the inner side of the liner to cool a portion of the downstream end of the liner obstructed by the transition piece.