Patent Number: 7,785,067

Title: Method and system to facilitate cooling turbine engines

Abstract: A method of assembling a gas turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the gas turbine engine. The at least one turbine nozzle segment includes at least one airfoil vane extending between an inner band and an outer band that includes an aft flange and a radial inner surface. The method also includes coupling at least one turbine shroud segment downstream from the at least one turbine nozzle segment, wherein the at least one turbine shroud segment includes a leading edge and a radial inner surface, and coupling a cooling fluid source in flow communication with the at least one turbine nozzle segment such that cooling fluid channeled to each turbine nozzle outer band aft flange is directed at an oblique discharge angle towards the leading edge of the at least one turbine shroud segment.

Inventors: Lee; Ching-Pang (Cincinnati, OH), Estill; Eric Alan (Morrow, OH), Laflen; James Harvey (Loveland, OH), Vitt; Paul Hadley (Hamilton, OH), Wymore; Michael Elliot (Madison, AL)

Assignee: General Electric Company

International Classification: F01D 25/12 (20060101)

Expiration Date: 8/31/12018