United Technologies Corporation

Henry Bispham Brown

Francis L DeTolla

Gary J Vollinger

Eugene Cantor

Apparatus for cooling the nozzle guide vanes in the turbine section of a gas turbine engine is disclosed. A plurality of guide vanes is cantilevered from the turbine case and extends radially inward across the path of working medium gases flowing through the turbine. A ring which is deformable in response to pressure forces is disposed between the vanes and the turbine case forming an annular chamber from which air is metered to the vanes during operation of the engine for cooling. In one embodiment platform cavities and airfoil cavities are alternately disposed between the vanes and the ring to isolate airfoil cooling air from platform cooling air.

Turbine cooling

Apparatus forming a portion of the outer wall of the flow path for working medium gases in the turbine section of a gas turbine engine is disclosed. The vanes of each turbine stage are grouped into a plurality of vane clusters which are circumferentially disposed in adjacent relationship about the flow path. A shroud which surrounds the tips of the rotor blades immediately upstream of the vane clusters is segmented in integral ratio to the number of vane clusters. The gap between each pair of adjacent vane clusters is circumferentially positioned in axial alignment with one of the gaps between adjacent shroud segments.

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Manchester, CT, United States of America

Henry Bispham Brown