| 摘要 |
A turbine engine has a compressor for delivery of compressed air to a combustor. The combustor delivers hot combustion gas through an outlet to a turbine. The turbine includes a nozzle assembly, downstream turbine blades, and shroud assemblies adjacent radially distal ends of turbine rotor blades. The nozzle and shroud assemblies include internal cooling passages for receiving compressed air from the compressor and, cooling air apertures opening through walls of the vanes and shrouds into the hot gas path to release film cooling air. The number of apertures, the aperture area, and the aperture pattern are varied in relation to the circumferential temperature profile of the combustion gas 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.
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