| 摘要 |
A turbine engine (10) has a compressor (12) for delivery of compressed air (18) to a combustor (14). The combustor (14) delivers hot combustion gas (20) through an outlet to a turbine (16). The turbine (16) includes a nozzle assembly (33), downstream turbine blades (24), and shroud assemblies (35) adjacent radially distal ends of turbine rotor blades (35). The nozzle (33) and shroud assemblies (45) include internal cooling passages for receiving compressed air (18) from the compressor (12) and, cooling air apertures (42, 46, 48) opening through walls of the vanes (22) and shrouds (35) into the hot gas path to release film cooling air (19). The number of apertures (42), 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 (42) in high temperature regions and a lower aperture area and/or lower number of apertures (42) in low temperature regions. |
