COOLING CIRCUIT FOR A MULTI-WALL BLADE

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

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Bibliographische Detailangaben
Hauptverfasser: Ciray Mehmet Suleyman, Perry, II Jacob Charles, Weber David Wayne
Format: Patent
Sprache:eng
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Beschreibung
Zusammenfassung:A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum; wherein the first turn is offset from the second turn to reduce impingement of the first flow of gas and the second flow of gas in the central plenum.