Aerofoil member for a gas turbine engine

Details Aerofoil member for a gas turbine engine Aerofoil member for a gas turbine engine

1979-07-31

1982-03-23

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

With fluid passage in working member communicating with...

Discharge solely at periphery normal to rotation axis

416 96A, F01D 518

Patent

active

043210104

ABSTRACT:
A blade or vane structure for a gas turbine engine comprises a hollow aerofoil member and a cooling air entry tube within the hollow aerofoil member, the aerofoil member and the tube comprising a unitary cast structure. To make this structure it is proposed that a lost wax casting process should be utilized, with the internal cavities formed using ceramic cores formed with the aid of temporary, disposable pieces which define the space eventually occupied by the tube.

REFERENCES:
patent: 3056014 (1962-09-01), Hulley et al.
patent: 3094310 (1963-06-01), Bowmer
patent: 3697192 (1972-10-01), Hayes
patent: 3742706 (1973-07-01), Klompas
patent: 3867068 (1975-02-01), Corsmeier et al.
patent: 3902820 (1975-09-01), Amos

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