United Technologies Corporation

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

Stephen N Finger

Johnny B Davis

Gerald Bracci

Walter A Ledwith, Jr

Mark A Strange

A control system for controlling the margin of temperature between the turbine's operating temperature and temperature limit throughout the engine operating range is manifested by utilizing a trim logic schedule that provides a constant margin value for each operating condition of the gas turbine engine. The system allows the engine to achieve the requisite performance while maintaining durability requirements.

Constant thrust retention turbine temperature limit system

A turbine stator vane assembly for gas turbine or turbojet engines has an improved structure for retention of a cooling impingement plate. Two inwardly directed flanges are added to the wall-like extensions extending from the bottom of the platform upon which the vane is mounted. The cooling impingment plate is resiliently snapped into place between pin fins on the bottom of the platform and the flanges.

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Jupiter, FL, United States of America

Stephen N Finger