TURBINE ROTOR AIRFOIL AND CORRESPONDING METHOD FOR REDUCING PRESSURE LOSS IN A CAVITY WITHIN A BLADE

TURBINE ROTOR AIRFOIL AND CORRESPONDING METHOD FOR REDUCING PRESSURE LOSS IN A CAVITY WITHIN A BLADE

A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consisten...

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Bibliographische Detailangaben
Hauptverfasser: SIW, Sin Chien, LEE, Ching-Pang, HOLLOMAN, Harry, KOESTER, Steven, UM, Jae Y
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:A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consistent cavity width similar to the cavity width of the rest of the leading edge circuit.