Method for cooling a gas turbine stator vane

Sheet metal container making – Apparatus to form container closure – Having means to apply seal or liner

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416 97R, F01D 518

Patent

active

057411174

ABSTRACT:
A method for cooling a stator vane is provided, comprising the steps of: (a) providing a hollow stator vane having a high pressure and a standard pressure chamber disposed within the hollow stator vane, adjacent the leading edge of the airfoil, and a supply chamber, disposed within the hollow stator vane, aft of the high and standard pressure chambers, and forward of the trailing edge; the stator vane further includes first and second inlet apertures, and first and second exit apertures; the first inlet apertures extend between the high pressure chamber and the supply chamber, and the second inlet apertures extend between the standard pressure chamber and the supply chamber; the first exit apertures extend between the high pressure chamber and the exterior of the stator vane, and the second exit apertures extend between the standard pressure chamber and the exterior of the stator vane; (b) determining the magnitudes of the gas flow pressure gradient facing the stator vane, and the position of the gradient relative to the stator vane; (c) manipulating the inlet apertures or both the inlet and exit apertures such that the pressure in the high chamber is greater than the pressure in the standard pressure chamber for a given pressure in the supply chamber; and (d) positioning the high pressure chamber along the leading edge to oppose an external high pressure region acting on the stator vane.

REFERENCES:
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T. Auxier, G. A. Bonner, D. Clevenger, S. N. Finger, AIAA-85-1221 "Military Engine Durability Improvements through Innovative Advancements in Turbine Design and Materials", AIAA/SAE/ASME/ASEE 21st Joint Propulsion Conference, Jul. 8-10, 1985, Monterey, California, copyright 1985 by the American Institute of Aeronautics and Astronautics, Inc.

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