liner a first flow sleeve surrounding the combustor liner forming a first substantially axially extending flow annulus radially therebetween the first flow sleeve has a first plurality of apertures formed about a circumference thereof for directing compressor discharge air as cooling air radially into said first flow annulus a transition piece is connected to the combustor liner the transition piece adapted to carry hot combustion gases to the turbine and a second flow sleeve surrounds the transition piece forming a second substantially axially extending flow annulus radially therebetween the second flow sleeve has a second plurality of apertures for directing compressor discharge air as cooling air radially into the second flow annulus the first substantially axially extending flow annulus connecting with the second substantially axially extending flow annulus a resilient annular seal structure is disposed radially between an aft end portion of the combustor liner and a forward end portion of said transition piece the resilient annular seal structure configured to form a first annular cavity radially between the forward end portion of the transition piece and the aft end portion of said combustor liner at least one transfer tube radially extends from the second flow sleeve through the second flow annulus to the transition piece.