Patent ID: 8695322

Claim:
A turbomachine comprising: a combustor assembly including a combustor liner bounding a flow of combustion gases and having a plurality of injection nozzles arranged in a can-annular array; a transition piece including at least one wall defining a combustion flow passage and bounding the flow of combustion gases; at least one dilution orifice formed in the at least one wall of the transition piece, the at least one dilution orifice guiding dilution gases to the combustion flow passage; a heat shield member mounted to the at least one wall of the transition piece in the combustion flow passage and positioned radially inside of the combustor liner such that a leading edge of the heat shield member is in contact with the flow of combustion gases, the heat shield member including a body having a first surface and an opposing second surface through which extends at least one dilution passage, the at least one dilution passage being off-set from the at least one dilution orifice, the heat shield member being spaced from the at least one wall of the transition piece so as to define a flow region between the at least one wall and the second surface, the flow region thermally decoupling the transition piece from combustion gases produced by the can-annular array of injection nozzles; and at least one mounting member provided on the transition piece; and at least one mounting element provided in the second surface of the heat shield member, the at least one mounting member being adapted to interact with the at least one mounting element to detachably mount the heat shield member to the transition piece.