F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
170/71
F01D 5/18 (2006.01)
Patent
CA 1113010
TIP COOLING FOR TURBINE BLADES Abstract A turbomachinery rotor blade includes an internal coolant cavity between a pair of radially extending side walls which combine to form an air- foil 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 dis- charged out of the open end of each channel at the tip of the side walls.
319578
Company General Electric
Eckersley Raymond A.
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