Method and apparatus for cooling gas turbine rotor blades

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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C416S09700R

Reexamination Certificate

active

07431561

ABSTRACT:
Methods and apparatus for cooling gas turbine rotor blades is provided. The blade includes an airfoil having an internal three pass serpentine cooling circuit having radially extending first, second, and third serpentine cooling cavities partially separated by, in axially aft succession, a first radially extending internal rib and a second radially extending internal rib. The serpentine cooling circuit includes a first inlet in flow communication with the first cavity and a second inlet in flow communication with at least one of the second and third cavities wherein the first and second inlets are formed during casting of the airfoil.

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patent: 6981742 (2006-01-01), Hsiao

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