FILM COOLING STRIP FOR GAS TURBINE ENGINE COMBUSTION CHAMBER

摘要

The invention provides in a gas turbine engine combustion chamber, an array of elongate louver strips between fuel nozzles of a combustion chamber dome wall, to cool the dome wall and contain combustion gases in the area between nozzles. The elongate louver strips are each disposed symmetrically along the median line on the inner surface dome wall and extend between each nozzle cup of the annular array. Each strip includes an elongate flange extending into the combustion chamber from the inner dome wall. The flange has an inner surface, and lateral side walls, with the inner surface generally parallel to the inner surface of the dome wall. Compressed air outlets are disposed along each flange lateral side wall, for directing a compressed air film along the inner surface of the dome wall in a direction away from the median line. A compressed air inlet extends from the outer surface of the dome wall to the outlets. The air inlet has a series of inlet orifices extending between each accumulation chamber and the outer surface of the dome wall. Flange cooling jets are disposed along the inner surface of the flange, for directing a flow of cooling air over the flange inner surface. The air jets are also provided compressed cooling air by the compressed air inlet.