Airfoil with dual source cooling

Details Airfoil with dual source cooling Airfoil with dual source cooling

1994-04-28

1996-03-12

Kwon, John T.

Rotary kinetic fluid motors or pumps

With passage in blade, vane, shaft or rotary distributor...

415116, F01D 906

Patent

active

054981263

ABSTRACT:
An airfoil for a gas turbine engine, having an airfoil portion with a leading and a trailing edge, includes dual pressure source cooling. The trailing edge of the airfoil includes an internal trailing edge passage and the leading edge includes an internal leading edge passage. Compressor bleed air at higher pressure is channeled through the leading edge passage whereas compressor bleed air at lower pressure is channeled through the trailing edge passage. The higher internal pressure in the leading edge ensures that the inward flow of products of combustion does not occur.

REFERENCES:
patent: 5134844 (1992-08-01), Lee et al.
patent: 5252026 (1993-10-01), Shepherd
patent: 5320483 (1994-06-01), Cunha et al.
patent: 5403157 (1995-04-01), Moore

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