Cooled blade for a gas turbine engine

Details Cooled blade for a gas turbine engine Cooled blade for a gas turbine engine

1975-04-01

1979-07-24

Pendegrass, Verlin R.

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

Changing state mass within or fluid flow through working...

416 96A, 415115, F01D 518

Patent

active

041621360

ABSTRACT:
A cooled blade for a gas turbine engine comprises an aerofoil portion having a longitudinally extending hollow. An air entry tube is mounted within the hollow and is pressed against a locating surface within the hollow by a resilient member such as a spring tube.

REFERENCES:
patent: 2912223 (1959-11-01), Hull
patent: 3628885 (1971-12-01), Sidenstick et al.
patent: 3691822 (1972-09-01), Deckard
patent: 3806275 (1974-04-01), Aspinwall
patent: 3930748 (1976-01-01), Redman et al.

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