Method and apparatus for cooling air flow at gas turbine bucket

Details Method and apparatus for cooling air flow at gas turbine bucket Method and apparatus for cooling air flow at gas turbine bucket

1990-04-13

1992-06-30

Look, Edward K.

Fluid reaction surfaces (i.e., impellers)

With fluid passage in working member communicating with...

Discharge solely at periphery normal to rotation axis

416 97R, 415115, F01D 518

Patent

active

051257980

ABSTRACT:
An apparatus and method for varying the cooling air flow within a gas turbine bucket tip. Each turbomachinery blade contains at least one radial cooling passage located between a hollow interior and an outside of the blade. A transversely-oriented elongate channel connects at least one of the cooling passages with the trailing edge of the blade. Secured within the transversely-oriented channel is a pin which extends into at least one of the radial cooling passages to partially obstruct the cooling fluid flow depending on the needs of the design.

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