Methods and system for recuperated cooling of integral...

Details Methods and system for recuperated cooling of integral... Methods and system for recuperated cooling of integral...

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 25/14 (2006.01) F01D 9/02 (2006.01) F02C 7/18 (2006.01) F02K 1/38 (2006.01)

Patent

CA 2603636

A turbine nozzle and shroud assembly (110) for a gas turbine engine (108) is provided. The turbine nozzle and shroud assembly (110) include a shroud segment including a leading edge (133) and an inner surface that is substantially perpendicular to the leading edge, and a turbine nozzle including an outer band (183) including an aft edge (150), the turbine nozzle is upstream from the shroud segment and is coupled with the shroud segment such that a gap (182) is defined between the aft edge and the leading edge, the shroud segment includes at least one cooling hole formed between the leading edge and the inner surface, the at least one cooling hole (181) is configured to direct cooling air in the gap toward the hot gas flow path (320).

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