Turbine vane with end-wall leading edge cooling

Details Turbine vane with end-wall leading edge cooling Turbine vane with end-wall leading edge cooling

2006-09-15

2010-12-28

Verdier, Christopher (Department: 3745)

Rotary kinetic fluid motors or pumps

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

Reexamination Certificate

active

07857580

ABSTRACT:
A first stage guide vane used in a gas turbine engine, the guide vane including an airfoil portion extending between an inner shroud and an outer shroud, each shroud having an extension to form a flow transition for the hot gas flow from the combustor to the guide vane, and where the leading edge of the shroud extensions include a plurality of diffusion cooling holes opening onto the surface of the shroud extension to provide film cooling. Each diffusion cooling hole is in fluid communication with a cooling supply channel that runs along the shroud extension to provide convective cooling of the shroud extension; the cooling supply channel includes a metering hole to regulate the flow of cooling air into the channel. In the preferred embodiment, each diffusion cooling hole includes a separate cooling supply channel and a metering hole in order to regulate the individual cooling diffusion hole cooling air flow to provide specific cooling requirements for the specific location of the diffusion hole.

REFERENCES:
patent: 4187054 (1980-02-01), Landis et al.
patent: 5417545 (1995-05-01), Harrogate
patent: 5470198 (1995-11-01), Harrogate et al.
patent: 6082961 (2000-07-01), Anderson et al.
patent: 6402463 (2002-06-01), Jang et al.
patent: 7004720 (2006-02-01), Synnott et al.
patent: 2004/0161336 (2004-08-01), Imbourg et al.

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