General Electric Company

Robert M Ausdenmoore

William C Lippmeier

Thomas G Wakeman

Bernard James Renggli

David J Markstein

Martin A Clements

Wilbert B Freid

Todd T Wilkinson

An aircraft gas turbine axisymmetric vectoring nozzle has an interface ring centered about a nozzle, a vectoring ring disposed radially inwardly of and apart from the interface ring, and a bearing radially disposed between the vectoring ring and the interface ring. The bearing may be a sliding bearing having a sliding interface between the vectoring ring and the interface ring and the sliding interface is spherical. The bearing may be constructed of sliding bearing segments having sliding interfaces between the vectoring ring and the interface ring and the sliding interfaces are spherical. Each of the bearing segments includes an outer sliding element attached to the interface ring, an inner sliding element attached to the vectoring ring, and spherically curved outer and inner sliding surfaces on the outer and inner sliding elements respectively wherein the spherically curved outer and inner sliding surfaces define the sliding interfaces between the vectoring ring and the interface ring. At least one of the outer sliding elements is circumferentially disposed and trapped between circumferentially spaced apart rails disposed on a corresponding one of the inner sliding elements. A plurality of interface ring support guides are disposed radially inwardly of and in sliding support relationship with the interface ring and located axially forward of the vectoring ring.

Engine interface for axisymmetric vectoring nozzle

A nozzle failsafe nozzle actuating system for an aircraft gas turbine engine variable exhaust nozzle having a plurality of pivotal flaps circumferentially disposed about a nozzle centerline and bounding an exhaust gas flowpath in the nozzle is provided with a number of primary actuators which are operably connected to nozzle flaps for pivoting and setting an attitude of the flaps relative to the centerline and wherein each of the primary actuators is extendable between a fully extended position and a fully retracted position, and a failsafe nozzle actuating actuator for setting the attitude of each of the flaps to a failsafe attitude during a failsafe mode of the nozzle actuating system wherein the failsafe attitude is such that each of the primary actuators is at a partially retracted position between the fully extended and the fully retracted positions. A particular embodiment provides actuator assembly wherein a failsafe piston rod of the failsafe actuator is disposed concentrically about a primary rod of the primary actuator and a stop element is provided for the failsafe rod to engage the primary rod when the primary rod is being retracted and the failsafe rod is extended.

Hydraulic failsafe system and method for an axisymmetric vectoring nozzle

A hollow actuating ring and apparatus for actuating and/or vectoring the flaps of an aircraft gas turbine engine nozzle by transferring actuation loads from a small number of actuators to a greater number of pivotal divergent flap members of the nozzle. The actuating ring has a generally hollow annular structure including axially spaced apart coaxial forward and aft walls, struts axially extending between and structurally joining together the forward and aft walls, and a ring stiffening for decreasing the effective ring bending and torsional length of at least one of the forward and aft walls between the struts. Stiffening structure is provided for spreading out loads transferred from the struts to one of the forward and aft walls using structural braces extending diagonally between the struts and one of the forward and aft walls.

Hollow nozzle actuating ring

A failsafe nozzle actuating system for an aircraft gas turbine engine axisymmetric vectoring exhaust nozzle has a vectoring ring operably linked to a plurality of pivotal flaps which are circumferentially disposed about a nozzle centerline and bounding an exhaust gas flowpath in the nozzle. The failsafe nozzle actuating system has at least two independently operable first and second vectoring actuating systems including first and second groups of actuators operably connected to the vectoring ring and first and second failsafe control means to control power to the first and second groups of actuators, respectively. The first group of vectoring actuators is interdigitated with the second group of second vectoring actuators around the nozzle. Either of the two groups of actuators are operable to actuate the nozzle when the other group is failsafed.

Axisymmetric vectoring nozzle actuating system having multiple power

A nozzle cooling system having apparatus to overexpand the exhaust flow in a divergent section of an aircraft gas turbine engine nozzle, relative to the air in the engine nozzle's bay and a valve to allow ambient air from the bay to flow over divergent flaps and seals of the divergent section, and rapidly cool the divergent section of the nozzle for IR suppression. An area ratio control apparatus may be used to change a ratio of the nozzle exit area to the nozzle throat area to an overexpanded level that reduces static pressures along at least a longitudinally extending portion of the surfaces to below the ambient pressure of air outside the nozzle to draw the ambient air into the exhaust gas flowpath, and a valve apparatus to controllably flow the ambient air into the exhaust gas flowpath when the static pressures are below the ambient pressure. Further embodiments of the present invention provide alternative area ratio control apparatus, such as a variable exit area control apparatus to vary the exit area or a variable throat area control apparatus to vary the throat area, or both. Valve apparatus with a gap apparatus to controllably open gaps between the circumferentially adjacent divergent flaps and seals are provided such as spring loaded divergent seal retainers and flapper valves sealingly disposed over corresponding cooling apertures through the divergent seals.

Cooling system for a divergent section of a nozzle

The present invention provides support for a vectoring ring used to pivot flaps in a gas turbine engine thrust vectoring nozzle. The ring support transfers at least a portion of the side loads acting generated by a gas turbine engine thrust vectoring nozzle to a relatively stationary portion of the engine. The support includes apparatus that provides for allowing two degree of freedom (2 DOF) pivoting or gimballing motion and axial translation of the vectoring ring.

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West Chester, OH, United States of America

Robert M Ausdenmoore