Method and apparatus for cooling an airfoil

Details Method and apparatus for cooling an airfoil Method and apparatus for cooling an airfoil

2005-10-18

2005-10-18

Lopez, F. Daniel (Department: 3745)

Rotary kinetic fluid motors or pumps

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

C416S09700R

Reexamination Certificate

active

06955522

ABSTRACT:
An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes a plenum longitudinally located within the leading edge of the airfoils. Within the plenum are positioned a plurality of turbulence promoters to provide enhance heat transfer within the leading edge. Also, the cooling design includes a plurality of inlets to receive cooling air from an internal cavity of the airfoil as well as a plurality of outlets located within a trench on the exterior surface of the leading edge through which the cooling air exits to film cool leading edge.

REFERENCES:
patent: 5779437 (1998-07-01), Abdel-Messeh et al.
patent: 6050777 (2000-04-01), Tabbita et al.
patent: 6210112 (2001-04-01), Tabbita et al.
patent: 6247896 (2001-06-01), Auxier et al.
patent: 6280140 (2001-08-01), Soechting et al.
patent: 6402470 (2002-06-01), Kvasnak et al.
patent: 6514042 (2003-02-01), Kvasnak et al.

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