GAS TURBINE STATOR BLADE

PROBLEM TO BE SOLVED: To simply repair, while maintaining a cooling performance, on the occurrence of damage in the trailing edge of a gas turbine stator blade having a cooling structure inside an airfoil.SOLUTION: The gas turbine stator blade comprises: an outer peripheral side end wall 9, the airf...

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Bibliographische Detailangaben
1. Verfasser:	SEKIHARA TAKASHI
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS 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:	PROBLEM TO BE SOLVED: To simply repair, while maintaining a cooling performance, on the occurrence of damage in the trailing edge of a gas turbine stator blade having a cooling structure inside an airfoil.SOLUTION: The gas turbine stator blade comprises: an outer peripheral side end wall 9, the airfoil 7 and an inner peripheral side end wall 10, which are integrally molded by casting; and a trailing edge component 15 with a pin fin cooling structure 14 formed thereon. On the outer peripheral side end wall 9, a notched portion 11 corresponding to a cross-sectional shape of the trailing edge component 15 is formed, and the trailing edge component 15 is inserted from the outer peripheral side end wall 9 and fixed to the outer peripheral side end wall.