Coolable turbine airfoil

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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Details

415115, F01D 518

Patent

active

040638510

ABSTRACT:
An airfoil cooling system for use in a gas turbine engine having high turbine inlet temperatures is disclosed. Various construction details designed to prevent thermal deterioration are developed. The system is built around impingement, film, and convective cooling techniques which are combined to limit the temperature of the airfoil material and to reduce thermal gradients within the component.

REFERENCES:
patent: 3369792 (1968-02-01), Kraimer et al.
patent: 3388888 (1968-06-01), Kercher et al.
patent: 3628880 (1971-12-01), Smuland et al.
patent: 3799696 (1974-03-01), Redman
patent: 3930748 (1976-01-01), Redman et al.
patent: 3994622 (1976-11-01), Schultz et al.

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