Cooled 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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416192, F01D 518

Patent

active

042240115

ABSTRACT:
A cooled rotor blade for a gas turbine has an aerofoil in which there are longitudinally extending cooling fluid passages. At the tip of the aerofoil is located a separate, chordwise extending tube. The tube has apertures in its wall which correspond with at least some of the cooling fluid passages, whereby the spent cooling fluid from these passages may pass through the tube to rejoin the gas flow of the engine.

REFERENCES:
patent: 3816022 (1974-06-01), Day
patent: 3876330 (1975-04-01), Pearson et al.
patent: 3989412 (1976-11-01), Mukherjee
patent: 4017209 (1977-04-01), Bodman
patent: 4127358 (1978-11-01), Parkes

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