Core for fabrication of gas turbine engine airfoils

Details Core for fabrication of gas turbine engine airfoils Core for fabrication of gas turbine engine airfoils

1994-11-01

1997-02-04

Look, Edward K.

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

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

164369, F01D 518

Patent

active

055991661

ABSTRACT:
An airfoil (20) for a gas turbine engine (10) includes cooling passages (40), (50) extending radially within the airfoil to circulate cooling air therethrough. Pluralities of small crossover holes (48), (66), (72) are formed within the walls (50), (68), (74), respectively, to allow cooling air to flow between the cooling passages. Optimum stiffness parameters are provided to improve producability of the airfoils with small geometric features, such as the crossover holes, as well as to improve the overall cooling scheme without jeopardizing manufacturability of airfoils.

REFERENCES:
patent: 3965963 (1976-06-01), Phipps et al.
patent: 4148350 (1979-04-01), Rossmann
patent: 4596281 (1986-06-01), Bishop
patent: 4627480 (1986-12-01), Lee
patent: 5050665 (1991-09-01), Judd
patent: 5337805 (1994-08-01), Green et al.
patent: 5403159 (1995-04-01), Green et al.

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