Coolable air foil for a gas turbine engine

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

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active

058578374

ABSTRACT:
A coolable airfoil (25) for a gas turbine engine includes a leading edge portion (52) cooled by a combination of radial and impingement flows through internal passages (80) and (90) separated by an internal wall (95) which is imperforate along a radially inner portion (100) thereof and apertured along a radially outer portion (105) thereof

REFERENCES:
patent: 4775296 (1988-10-01), Schwarzmann et al.
patent: 4820123 (1989-04-01), Hall
patent: 5122033 (1992-06-01), Paul
patent: 5403159 (1995-04-01), Green et al.
patent: 5488825 (1996-02-01), Davis et al.
International Search Report of International Application No. PCT/US97/11565, 3 pgs., dated Nov. 5, 1997.

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