Method of making a blade aerofoil for a gas turbine engine

Details Method of making a blade aerofoil for a gas turbine engine Method of making a blade aerofoil for a gas turbine engine

1982-03-09

1984-03-06

Lin, Kuang Y.

Metal founding

Process

Shaping a forming surface

164 35, 164 36, 164516, 164 45, B22C 702, B22C 904

Patent

active

044348355

ABSTRACT:
A method of making at least the aerofoil of a blade for a gas turbine engine in which the cooling air exit passages, whether at the trailing edge or in other parts of the aerofoil, are cast rather than machined subsequently. In the method a disposable piece is formed with holes of the shape of the holes eventually required in the blade aerofoil. The piece is placed in a die and used to define part of the ceramic core required in the casting process, the die being arranged to produce a channel portion interconnecting the otherwise free ends of the parts of the core which will form the passages. The ceramic core thus formed in a lost-wax casting process to form the blade aerofoil, the channel portion being embedded in the shell mould to support the parts which define the passages.

REFERENCES:
patent: 4384607 (1983-05-01), Wood et al.

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