Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies

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...

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Bibliographische Detailangaben
Hauptverfasser:	ESTILL, ERIC ALAN, LEE, CHING-PANG, LAFLEN, JAMES HARVEY, ANDERSEN, KATHERINE JAYNETORRENCE
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	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).