COOLING CIRCUIT FOR A MULTI-WALL BLADE

A turbine blade cooling system according to an embodiment includes: a first arcuate turn for redirecting a first flow of gas flowing through a first channel of a turbine blade (6) into a central plenum (44) of the turbine blade (6); and a second arcuate turn (70) for redirecting a second flow of gas...

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Bibliographische Detailangaben
Hauptverfasser:	WEBER, David Wayne, WILLETT, Fred Thomas Jr
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING 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 WEAPONS
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Beschreibung
Zusammenfassung:	A turbine blade cooling system according to an embodiment includes: a first arcuate turn for redirecting a first flow of gas flowing through a first channel of a turbine blade (6) into a central plenum (44) of the turbine blade (6); and a second arcuate turn (70) for redirecting a second flow of gas flowing through a second channel of the turbine blade (6) into the central plenum (44) of the turbine blade (6), wherein the first and second arcuate turns (60, 70) reduce impingement of the first flow of gas and the second flow of gas in the central plenum (44) of the turbine blade (6).