Gulfstream Aerospace Corporation

Derek Muzychka

Donald Freund

John Louis

Joseph Gavin

Till Gerhardt

Benjamin Walke

William Mcfarland

Andrew Clemens

Joe Gavin

Douglas Klutzke

Nicholas Powell

Shawn Bennett

Various non-limiting embodiments of a nozzle assembly for use with a propulsion system and a sleeve assembly for use with the nozzle assembly are disclosed herein. In a non-limiting embodiment, the nozzle assembly includes, but is not limited to, a nacelle. The nozzle assembly further includes, but is not limited to, a sleeve assembly mounted within the nacelle downstream of the engine. The sleeve assembly is configured to receive the mass flow from the engine and to guide the mass flow to an exit of the propulsion system. The sleeve assembly is comprised of a plurality of sleeve segments arranged in a circumferential configuration. Each sleeve segment of the plurality of sleeve segments has an elongate body that is longitudinally aligned with a longitudinal axis of the sleeve assembly.

Nozzle assembly for use with a propulsion system and sleeve assembly for use with the nozzle assembly

An exhaust nozzle assembly includes, but is not limited to, a nozzle body configured to be fluidly coupled with an engine and to receive a jet produced by the engine. An outer cover covers the nozzle body. A movable component is disposed and configured to have an effect on either the jet or an exhaust plume when the movable component moves. A linkage is coupled to the movable component and adapted for coupling to an actuator. The linkage transmits the force to the moveable component from the actuator. There is a gap between an inner surface of the outer cover and an outer surface of the nozzle body. The linkage is smaller than the actuator. The gap is smaller than a smallest dimension of the actuator and larger than the linkage. The linkage is partially disposed within the gap, and the exhaust nozzle assembly is free of the actuator.

Exhaust nozzle assembly, propulsion system employing the exhaust nozzle assembly, and aircraft employing the propulsion system

A nozzle assembly includes a sleeve defining a pathway, the sleeve disposed within a nacelle. The pathway and an internal surface of the nacelle guides a mass flow from an engine to an exit of the propulsion system. The sleeve is configured to move between a forward position an aft position within the nacelle aft of the engine. The sleeve has a protruding portion that extends towards a center of the pathway and that defines a smallest internal diameter of the sleeve. The sleeve includes a plurality of sleeve segments that are longitudinally aligned and circumferentially arranged to form the sleeve. The sleeve segments are configured to move circumferentially closer as the sleeve moves in a first direction within the nacelle and to move circumferentially further apart as the sleeve moves in a second direction within the nacelle. An actuator is coupled with, and is configured to move the sleeve.

Nozzle assembly for use with a propulsion system

An aircraft propulsion system includes an engine. The propulsion system further includes an inlet having a forward cowl lip and an aft cowl lip. The forward cowl lip moves between retracted and deployed positions. The forward cowl lip is adjacent to the aft cowl lip when retracted. The forward cowl lip is spaced apart from the aft cowl lip when deployed. The forward cowl lip has a smaller radius of curvature than the aft cowl lip. The propulsion system further includes a controller coupled with the engine and inlet. The controller restricts the maximum thrust commanded position of the engine when the aircraft is on the ground and moving below a predetermined speed. The controller lifts the restriction when the aircraft is moving at at least the predetermined speed. The controller controls the inlet to deploy the cowl lip when the aircraft is on the ground.

Propulsion system for an aircraft

Growing community of inventors

Savannah, GA, United States of America

Derek Muzychka