TURBINE COOLING SYSTEM

摘要

2098741 9214918 PCTABS00015 A first flow of cooling air (65) is directed to the nozzle and shroud assembly (38) wherein the first flow (65) is used to cool the nozzle vane portion (150) and is exited through a plurality of first exit passages (157) in a trailing edge (152) of the nozzle vane (150). Another portion of the first flow (65) is exited from the nozzle plenum (153) into an annular reservoir (166) and is further used to cool a rotor assembly (110) and to reduce ingestion of hot power gases into the internal portion of the engine (10). The system (12) further includes a second flow of cooling air (66) which is directed through internal passages (100, 106) of the engine (10) and into the annular reservoir (166) and is used to cool the rotor assembly (110) and to reduce ingestion of hot power gases into the internal portion of the gas turbine engine (10). A radial blade flange arrangement (144) and a radial shroud flange arrangement (172) axially overlap each other in a preestablished radially spaced proximity forming a buffering zone (174) therebetween into which the mixed cooling air in the annular reservoir is directed.