United Technologies Corporation

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

United Technologies Corporaton

Kenneth E Harmon

Dale William Petty

John L Mayers

Peter B DeGress

The horsepower requirements for the actuation system for a convergent/divergent exhaust nozzle for a gas turbine engine is reduced by the judicious selection of the crank arms and their location on a torque shaft that rotates to move a connecting link attached to the convergent flap of the nozzle. A pressure balancing hood is attached to the top surface on the forward end of the convergent flap to augment the lowering of the horsepower requirements. In another embodiment a tie rod/end cup arrangement and two piece torque shaft are utilized for ease of removal of the actuation system from the exhaust nozzle assembly.

Actuation system for convergent/divergent nozzle

The invention discloses a liner hanger assembly which is mechanically attached to the component to which the liner is secured, thereby allowing hanger materials to be selected based on other than weldability considerations, and allowing the hanger to be removed and repaired when worn or damaged.

Mechanically attached liner hanger assembly

A paired vane structure for the first stator stage of a gas turbine, having the vane structure of each vane pair cast in two matching parts which are then assembled and held together by means of bolts passing through flanges on the vane inner and outer platforms. The paired vanes are assembled into the gas turbine structure in the same manner as the prior art paired vane sections.

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North Palm Beach, FL, United States of America

Kenneth E Harmon