Turbine blade with triple pass serpentine flow cooling circuit

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

Reexamination Certificate

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Reexamination Certificate

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07611330

ABSTRACT:
A turbine blade used in a gas turbine engine, the blade having a dual triple pass serpentine flow cooling circuit to provide cooling to the blade. A first triple pass serpentine flow circuit includes a first leg located on the pressure side, a second leg located on the suction side and directly opposed to the first leg, and a third leg located aft of the first and second leg and between the pressure side and suction side walls. A showerhead cooling arrangement is supplied cooling air through metering holes connected to the third leg. A second triple pass serpentine flow circuit is located downstream from the first serpentine flow circuit and includes a first leg on the pressure side of the blade, a second leg on the suction side and directly opposed to the first leg, and a third leg downstream from the first and second leg and between the pressure side and suction side walls, the third leg including trailing edge exit cooling holes.

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patent: 6916155 (2005-07-01), Eneau et al.
patent: 2007/0128034 (2007-06-01), Lee et al.

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