Patent ID: 8677763
Filing Date: 2014-03-25
Classification: F01D,F05D

Abstract:
1. A turbine engine comprising; a turbine; a combustor creating a combustion gas temperature profile, the combustion gas temperature profile having a high temperature region, an intermediate temperature region, and a low temperature region where the high temperature region is greater than the intermediate temperature region, and the intermediate temperature region is greater than the low temperature region; a compressor for delivery of compressed air to the combustor wherein the combustor combusts fuel with the compressed air to deliver hot combustion gas through an outlet to the turbine; stationary components including a nozzle assembly disposed in the turbine having vanes supported by sidewalls, for directing the hot combustion gas to downstream turbine blades; cooling passages in the vanes and sidewalls configured to receive compressed air from the compressor; and cooling air apertures opening through outer walls of the vanes and sidewalls to release the cooling air, the apertures having an aperture distribution in the vanes and sidewalls related to the combustion gas temperature profile, with a larger aperture area placed in the high temperature region and a lower aperture area placed in the low temperature region such that the aperture distribution varies circumferentially between adjacent nozzle vanes across the nozzle assembly, the aperture distribution corresponding to the high temperature region, the intermediate temperature region and the low temperature region.