Trailing edge cooling apparatus for a gas turbine airfoil

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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416 97A, F01D 518

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active

061026581

ABSTRACT:
A coolable airfoil is provided which includes an internal cavity, an external wall, a plurality of first cooling apertures, and a plurality of second cooling apertures. The external wall includes a suction side portion and a pressure side portion. The wall portions extend chordwise between a leading edge and a trailing edge and spanwise between an inner radial surface and an outer radial surface. The first cooling apertures are disposed in the external wall adjacent the trailing edge, exiting the airfoil through the pressure side portion. The second cooling apertures are disposed in the external wall adjacent the trailing edge, exiting the airfoil through the suction side portion.

REFERENCES:
patent: 3560107 (1971-02-01), Helms
patent: 4025226 (1977-05-01), Hovan
patent: 4153386 (1979-05-01), Leogrande
patent: 5342172 (1994-08-01), Coudray et al.
patent: 5403159 (1995-04-01), Green et al.
patent: 5486093 (1996-01-01), Auxier et al.
patent: 5498133 (1996-03-01), Lee
U.S. Patent Application Serial No. 08/969,670--Soechting et al. (Our Docket No.: F-7753).

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