Patent ID: 8438856
Filing Date: 2013-05-14
Classification: F23R

Abstract:
1. A combustor for an industrial turbine including: a single transition piece transitioning directly from a combustor head-end to a turbine inlet and configured to direct combusted gas flow in a stream from the combustor head to the turbine inlet without reversal of direction of the transition piece, the transition piece including an inner surface and an outer surface, the inner surface bounding an interior space for the combusted gas flow from the combustor head-end to the turbine inlet, the outer surface at least partially defining an area for compressor discharge air flow, the transition piece including a plurality of apertures configured to allow compressor discharge air flow, approaching the transition piece from a relatively downstream area of the turbine with respect to the combusted gas flow, into the interior space, each of the plurality of apertures extending from an entry portion on the outer surface to an exit portion on the inner surface, with the exit portion of each aperture being located further downstream, with respect to the combusted gas flow, than the respective entry portion to cause a reversal of direction of the compressor discharge air as the compressor discharge air proceeds into the interior space.