United Technologies Corporation

John H Young

Gerald F Goetz

Loren Hawdon White

Charles Edward Salisbury

Anthony R De Cosmo

A shroud ring (22) for a gas turbine engine having a stator structure (14) and an array of inwardly extending stator vanes (20) is disclosed. The shroud ring is circumferentially segmented to accommodate inward and outward movement of the vanes and the stator structure. The shroud ring has a segmented outer ring (28) and a segmented inner ring (30). The outer ring engages the vanes to support the vanes and to position the inner ring and an integral seal member (24) about a rotor structure. In one embodiment the vanes (20) are rotatable about a spanwise axis S. In a second embodiment, the vanes (120) are integrally attached to the shroud ring (122).

Shroud ring for use in a gas turbine engine

The fore end (nose) of the centerbody of a two-dimensional nozzle located in the direct path of the exhaust from the tail pipe or afterburner of a jet engine includes an aerodynamic shaped sheath and slip joint means are disclosed which serve to support the sheath to a structural member such that the thermal stress problems at the attachment points occasioned by the hostile environment are obviated and means for cooling the joint are also disclosed.

Attachment for a nozzle centerbody

This invention relates to sealing means for a movable centerbody having collapsible panels located in the two-dimensional exhaust nozzle of a jet engine so that movement of the centerbody and collapsing its walls serves to provide thrust vectoring, variable geometry and internal nozzle expansion. Cooling air supplied internally of said centerbody is utilized to pressurize the seal to assure that the jet exhaust does not ingress into the centerbody cavity or cooling air does not indiscriminately egress therefrom.

Seal means for a movable centerbody in a two dimensional nozzle

This invention relates to a cooling air management system for a movable centerbody having articulating panels located in the two-dimensional exhaust nozzle of a jet engine so that movement of the centerbody and articulating its panels can provide thrust vectoring, variable geometry internal nozzle expansion or other flight control functions. Cooling air supplied from a fan discharge and/or ram air is fed internally of the centerbody to enhance its operation in a hostile environment while assuring sufficient pressure to effectuate cooling throughout the flight envelope of the aircraft, which during different regimes requires different cooling loads.

Cooling air management system for a two-dimensional aircraft engine

In adjusting turbine vanes to control the nozzle area, the unison ring actuates a lever that has one end fixed to the vane casing ring and the vane actuating arm is connected to the lever at a point between the ends to reduce actuating forces required by the unison ring and to permit close tolerance control on the vane angle position.

High ratio actuation linkage

Apparatus for varying the nozzle area in the turbine section of a gas turbine engine is disclosed. Nozzle guide vanes extend across the flow path for the working medium gases and are rotatable to alter the area of the nozzle. In one embodiment the rotatable vanes are cantilevered from the outer engine case and are opposed at their radially inner ends by a shroud which is affixed to the inner engine case. The outer engine case has a double wall type construction including a plurality of bearing cartridges disposed between the walls.

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South Windsor, CT, United States of America

John H Young