Methods and system for cooling integral turbine nozzle and...

Details Methods and system for cooling integral turbine nozzle and... Methods and system for cooling integral turbine nozzle and...

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 25/14 (2006.01) F02C 7/18 (2006.01) F02K 1/38 (2006.01)

Patent

CA 2603174

A turbine nozzle and shroud assembly (300) for a gas turbine engine is provided. The turbine nozzle and shroud assembly (300) includes a shroud segment (130) including a leading edge (133) defining a forward face (304) of the shroud segment, and a turbine nozzle (302) including an outer band (183) having a trailing edge (137) defining an aft face (312) of the outer band, the turbine nozzle upstream from the shroud segment and coupled with the shroud segment such that a gap (182) is defined between the aft face and the forward face, the gap is configured to direct cooling air towards a hot gas flow path (325) flowing through the gas turbine engine, the aft face includes a lip (350) formed thereon radially inward with respect to the gap and extending axially downstream of the gap.

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