United Technologies Corporation

Kenneth B Hall

Friedrich O Soechting

William L Plank

A vane assembly for a gas turbine engine is provided, which includes a plurality of vanes, an inner vane support, a casing, and apparatus for maintaining a pressure difference. Each vane has a leading edge, a trailing edge, an outer radial end, an inner radial end, and an internal cavity. The internal cavity includes a forward compartment adjacent the leading edge and an aft compartment adjacent the trailing edge. The casing, which includes an annulus, is positioned radially outside of the vanes. The vanes extend between the inner vane support and the casing. The apparatus for maintaining a pressure difference maintains a difference in the cooling air pressure within the forward and aft compartments of the vane cavity under operating conditions.

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Klingnau, Switzerland

Kenneth B Hall