Patent ID: 7665953
Filing Date: 2010-02-23
Classification: F01D,F05D,Y02T

Abstract:
1. A method for cooling a shroud segment of a gas turbine engine, said method comprising: providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface; coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge; metering a flow of cooling air into the gap through at least one forwardly directed cooling opening defined in the leading edge and positioned radially outward from the at least one cooling hole extending between the leading edge and the inner surface; and directing the cooling air in the gap through at least one cooling hole formed between the leading edge and the inner surface.