Leading edge cooling of turbine airfoils

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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B63H 114

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active

054860938

ABSTRACT:
The leading edge of the turbine airfoil of a turbine blade for a gas turbine engine is cooled by utilizing helix shaped holes that are rectangular in cross-section and curved to produce film holes egressing at low angles adjacent the outer surface of the leading edge. The helix holes extend from the root to the tip of the blade and are parallelly and longitudinally spaced.

REFERENCES:
patent: 4384823 (1983-05-01), Graham et al.

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