| 摘要 |
<P>PROBLEM TO BE SOLVED: To cool a gas turbine fixed component. <P>SOLUTION: A combustor 14 delivers hot combustion gas 20 through an outlet to a turbine 16. The turbine 16 includes a nozzle assembly 33, downstream turbine rotor blades 24, and shroud assemblies 35 adjacent to radially distal ends of turbine rotor blades 24. The nozzle assembly 33 and the shroud assemblies 35 include internal cooling passages for receiving compressed air from the compressor, and cooling air apertures opening through outer walls of stator vanes 22 and the shroud assemblies 35 into the hot gas path to release film cooling air 19. The number of the cooling air apertures, the aperture area, and the aperture pattern are varied in relation to the circumferential temperature profile of the combustion gas 20 with a higher aperture area and/or higher number of apertures in high temperature regions and a lower aperture area and/or lower number of apertures in low temperature regions. <P>COPYRIGHT: (C)2010,JPO&INPIT |
