General Electric Company

United States of America As Represented by the Secretary of the Air Force

Edward S Hsia

John Howard Starkweather

Raghuram J Emani

William K Koffel

The cooling insert for a movable vane in a jet engine is divided into plural overlapping forward and aft segregated members, each member being coolant fed through separate vane trunnion areas and each insert is of successively decreasing cross-sectional area. Problems of locally inadequate vane cooling, coolant match point movement, and unequal coolant supply pressures are addressed by the disclosed apparatus. Reuse of the trunnion supplied impingement cooling air for additional cooling functions is also disclosed.

Variable nozzle area turbine vane cooling

A multiple-impingement cooled structure, such as for use as a turbine shroud assembly. The structure includes a plurality of baffles which define with an element to be cooled, such as a shroud, a plurality of cavities. Impingement cooling air is directed through holes in one of the baffles to impinge upon only the portion of the shroud in a first cavity. That cooling air is then directed to impinge again upon the portion of the shroud in a second cavity.

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Cincinnati, OH, United States of America

Edward S Hsia