INTEGRAL TURBINE NOZZLE AND SHROUD ASSEMBLY AND SYSTEM FOR RECOVERING COOLING OF THESE COMBINATIONS

PROBLEM TO BE SOLVED: To provide a turbine nozzle and a shroud assembly for a gas turbine engine. SOLUTION: This turbine nozzle and the shroud assembly 110 include a shroud segment having a leading edge and an inner surface substantially perpendicular to the leading edge and the turbine nozzle inclu...

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Hauptverfasser:	ANDERSEN KATHERINE JAYNETORRENCE, LAFLEN JAMES HARVEY, ESTILL ERIC ALAN, LEE CHING-PANG
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To provide a turbine nozzle and a shroud assembly for a gas turbine engine. SOLUTION: This turbine nozzle and the shroud assembly 110 include a shroud segment having a leading edge and an inner surface substantially perpendicular to the leading edge and the turbine nozzle including an outer band 183 having an aft edge. 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. At least the one cooling hole is configured to direct cooling air in the gap toward a hot gas flow path 320. COPYRIGHT: (C)2008,JPO&INPIT