Gas turbine blade cooling

Holes (38 and 39) formed at a top portion (TP) of a turbine blade have upstream opening portions (38b and 39b) and downstream opening portions (38a and 39a) which have a larger cross-sectional area than upstream opening portions (38b and 39b). Holes (38 and 39) have tapered shapes (T1 and T2) or ste...

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Bibliographische Detailangaben
Hauptverfasser:	SOECHTING, FRIEDRICH, TORII, SHUNSUKE, TOMITA, YASUOKI
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:	Holes (38 and 39) formed at a top portion (TP) of a turbine blade have upstream opening portions (38b and 39b) and downstream opening portions (38a and 39a) which have a larger cross-sectional area than upstream opening portions (38b and 39b). Holes (38 and 39) have tapered shapes (T1 and T2) or step portions, and preferably, downstream opening portions (38a and 39a) are eccentrically formed toward the moving direction. When tip squealer (37) is formed, hole (38) is formed so that its opening portion is provided at the side surface of tip squealer (37). Without covering the holes for cooling which are formed at the top portion of the turbine blade due to rubbing or the like, the turbine blade is accurately cooled and stably driven.