Rotor blade for a gas turbine engine

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

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F01D 508, F01D 518

Patent

active

043021530

ABSTRACT:
A rotor blade for a gas turbine engine comprises an aerofoil, shank portion and a root by which the remainder of the blade may be supported from a rotor disc. Cooling for the aerofoil is provided by passages in the leading portion of the aerofoil which are fed with cooling air from an entry aperture and a sealed liquid cooling circuit which contains a cooling liquid. This circuit comprises a liquid feed passage adjacent the trailing edge of the aerofoil and connected adjacent the tip of the aerofoil with a vapor return passage, both passages communicating with a sealed cavity within the shank of the blade. In operation the cooling fluid (e.g. metallic sodium) flows under the influence of centrifugal and other forces along the feed passage, is vaporized and returns to the cavity via the return passage. The cavity acts as a condenser for the fluid.

REFERENCES:
patent: 2708564 (1955-05-01), Erickson
patent: 3314650 (1967-04-01), McCormick
patent: 3334685 (1967-08-01), Burggraf et al.
patent: 4073599 (1978-02-01), Allen et al.
patent: 4134709 (1979-01-01), Eskesen

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