Patent ID: 7712314
Filing Date: 2010-05-11
Classification: F23R,Y02T

Abstract:
1. 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, 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.