Shaped film cooling hole for turbine airfoil

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

Reexamination Certificate

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Reexamination Certificate

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08057180

ABSTRACT:
A film cooling hole for a turbine airfoil used in a gas turbine engine, where the film cooling hole includes a metering inlet section of constant diameter cross section and a diffusion section having side walls with multiple expansion. The two side walls have an expansion of around 10 degrees and also slant inwards or toward the downstream side wall of from 10 to 45 degrees to provide the addition expansion. The downstream wall also expands at around 10 degrees. For a compound shaped film hole, the multiple expansions are 10 degrees in the downstream direction and 0 to 5 degrees in the radial outward direction. The side wall in the radial expansion direction will at a convergent angle of 10 to 45 degrees. In the radial inward direction, the expansion angle is from 10 to 20 degrees with a convergent side wall angle of from 10 to 45 degrees.

REFERENCES:
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patent: 4738588 (1988-04-01), Field
patent: 5382133 (1995-01-01), Moore et al.
patent: 6183199 (2001-02-01), Beeck et al.
patent: 6869268 (2005-03-01), Liang
patent: 6918742 (2005-07-01), Liang

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