Turbine airfoil suction aided film cooling means

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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415115, F01D 518

Patent

active

061295159

ABSTRACT:
Film cooling effectiveness for internally air cooled turbine blades of gas turbine engines is enhanced by including an interconnecting passage to the film cooling hole that is in communication with a lower internal pressure in the blade to create a suction at the exit end of the film hole to limit penetration into the gas stream.

REFERENCES:
patent: 4753575 (1988-06-01), Levengood et al.
patent: 4897020 (1990-01-01), Tonks

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