Patent ID: 9003807
Filing Date: 2015-04-14
Classification: F01D,F05D

Abstract:
1. A gas turbine engine comprising: a compressor for generating compressed air, wherein the compressed air increases in temperature from ambient when the gas turbine engine begins operation to an elevated temperature; a turbine comprising: said blade ring including upstream and downstream ends defining respective vertical blade ring surfaces, said vertical blade ring surfaces extending radially outward to an engagement of said blade ring with an inner surface of a turbine casing surrounding said blade ring; and fluid structure for receiving compressed air from the compressor and extending toward said one stationary blade ring for discharging the compressed air directly against at least one of said vertical blade ring surfaces of said blade ring at least during an initial startup period of said gas turbine engine such that the compressed air impinges on said at least one vertical blade ring surface, said fluid structure comprising at least one impingement pipe located adjacent said at least one vertical blade ring surface and including a plurality of openings positioned so as to discharge the compressed air toward said at least one vertical blade ring surface.