Patent ID: 7712314

Claim:
A combustor for a gas turbine comprising: a nozzle assembly located at a first end of the combustor; a combustion chamber defined within the combustor, downstream of the nozzle; a venturi positioned within the combustor and defining a transition between the first end and the combustion chamber, the venturi having a venturi wall and a radially outer wall adjacent to and running along an interior of the combustor and an internal passageway therebetween, the internal passageway having first and second passageway portions and a radial plenum extending radially inward towards the wall of the venturi and defined by sidewalls that extend in a generally radial direction, with the radial plenum being in direct fluid communication with the first and second passageway portions, wherein the first passageway portion extends along the venturi wall towards the first end of the combustor and the second passageways portion extends along the venturi wall towards the second end of the combustor, and wherein the radial plenum engages the first and second passageway portions adjacent the wall of the venturi; and a compressed air source directing cooling air into the first and second passageway portions via the radial plenum, the first and second passageway portions directing the compressed air from the source in opposite directions within the venturi.