GAS TURBINE BLADE AND GAS TURBINE EQUIPPED THEREWITH

PROBLEM TO BE SOLVED: To provide a gas turbine blade capable of improving the heat transfer performance of a serpentine flow path.SOLUTION: The serpentine flow path is formed of second-fourth cooling flow paths 12B, 12C, 12D so that the second cooling flow path 12B is situated at the most downstream...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	YURI MASANORI, HANEDA SATORU
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 provide a gas turbine blade capable of improving the heat transfer performance of a serpentine flow path.SOLUTION: The serpentine flow path is formed of second-fourth cooling flow paths 12B, 12C, 12D so that the second cooling flow path 12B is situated at the most downstream side. A first wall 22A and a third wall 22C are disposed so that a space therebetween is gradually wider from the belly side toward the back side of the blade. A second wall 24B extends approximately parallel to the first wall 22A. A second flow path 12B having an approximately square cross section is formed of the first wall 22A, a back sidewall 4B of the blade, the second wall 24B and a belly sidewall 4A of the blade. A third flow path 12C having an approximately triangular cross section is formed of the second wall 24B, the belly sidewall 4A of the blade and the third wall 22C.