Tip cooling for turbine blades

Details Tip cooling for turbine blades Tip cooling for turbine blades

1977-09-02

1979-03-06

Casaregola, Louis J.

Rotary kinetic fluid motors or pumps

With passage in blade, vane, shaft or rotary distributor...

416 97R, F01D 518, F02C 718

Patent

active

041428242

ABSTRACT:
A turbomachinery rotor blade includes an internal coolant cavity between a pair of radially extending side walls which combine to form an airfoil having an open end between the radial extremities of the side walls. A tip cap recessed within the open end partially seals the internal coolant cavity from the blade environment. The radial extremities of the side walls extending beyond the tip cap into proximity with a circumscribing shroud form a labyrinth seal for inhibiting leakage of the operating gas across the blade tip. A portion of the cooling air is routed from the internal coolant cavity, around the tip cap and through a multiplicity of generally radial channels formed within the radial extremities of the side walls to provide cooling thereof, and is thereafter discharged out of the open end of each channel at the tip of the side walls.

REFERENCES:
patent: 3533712 (1970-10-01), Kercher
patent: 3628885 (1971-12-01), Sidenstick et al.
patent: 3810711 (1974-05-01), Emmerson et al.
patent: 4040767 (1977-08-01), Dierberger et al.

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