Patent ID: 7260935

Claim:
A reverse flow combustor for a gas turbine, comprising: a combustor casing comprising an elongated cylindrical combustor liner interiorly defining a combustion chamber and a reverse flow fluid passageway between the liner and the casing, wherein the combustor liner comprises a plurality of openings about a primary combustion zone, and a plurality of openings radially disposed in the liner about a dilution zone of the combustion chamber; a plurality of swirler and mixer assemblies upstream from the combustion chamber; and a generally planar domeplate intermediate the combustion chamber and the plurality of swirler and mixer assemblies comprising a heat shield attached thereto having an annular end body, wherein the domeplate further comprises a plurality of fluid openings to provide a plurality of airflow passages that impinge upon an outer surface of the heat shield during operation of the gas turbine, and wherein the plurality of openings radially disposed in the liner about the primary combustion zone provide airflow passages that impinge on the outer surface of the heat shield during operation of the gas turbine.