Turbine nozzle trailing edge cooling configuration

Details Turbine nozzle trailing edge cooling configuration Turbine nozzle trailing edge cooling configuration

2006-10-17

2006-10-17

Edgar, Richard A. (Department: 3745)

Rotary kinetic fluid motors or pumps

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

C416S09700R

Reexamination Certificate

active

07121787

ABSTRACT:
The trailing edge region of a nozzle airfoil is provided with a cooling configuration wherein post-impingement cooling air flows between radially spaced ribs defining convective cooling channels into a generally radially extending plenum. Cooling air in the plenum is split between film cooling holes for film cooling the pressure side of the trailing edge region and for flow about downstream pins for pin cooling the downstream regions of the opposite sides of the airfoil. The cooling air exiting the pins is directed through convective channels defined by a second set of radially spaced ribs and through exit apertures on the pressure side of the trailing edge.

REFERENCES:
patent: 5288207 (1994-02-01), Linask
patent: 6099251 (2000-08-01), LaFleur
patent: 6607355 (2003-08-01), Cunha et al.

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