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

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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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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creator ESTILL, ERIC ALAN
LEE, CHING-PANG
LAFLEN, JAMES HARVEY
ANDERSEN, KATHERINE JAYNETORRENCE
description 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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subjects 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
title Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies
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