Nozzle assembly for use with propulsion system

By designing a nozzle assembly with a variable geometry and using the longitudinal movement of the sleeve in the nacelle to change the nozzle configuration, the problem of low nozzle efficiency in different flight states of supersonic aircraft is solved, and fuel consumption is reduced and the range is increased.

CN119212921BActive Publication Date: 2025-09-19GULFSTREAM AEROSPACE CORP
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Patent Information

Application Number
CN202380036853.8
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Priority Date
2022-04-29
Filing Date
2023-04-26
Publication Date
2025-09-19
Estimated Expiration
2043-04-26

AI Technical Summary

Technical Problem

It is difficult for existing technologies to maintain high efficiency of the nozzle assembly under different flight conditions of a supersonic aircraft, resulting in increased fuel consumption and reduced range.

Method used

A variable-geometry nozzle assembly was designed. This nozzle configuration is modified to accommodate different flight conditions by moving a sleeve longitudinally within the nacelle. The sleeve, comprised of multiple segments, is able to move forward and backward within the nacelle through the coordination of guides and actuators, changing the nozzle's cross-sectional area and shape.

Benefits of technology

The high efficiency of the nozzle assembly is achieved under different flight conditions, fuel consumption is reduced, and the range of the aircraft and the efficiency of the propulsion system are improved.

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Abstract

A nozzle assembly (100, 108, 40, 60, 68) includes a sleeve (106, 108, 44, 66, 68) defining a path (52). The sleeve (106, 108, 44, 66, 68) is disposed within a nacelle (102, 104, 36, 62, 64). The path (52) and an inner surface of the nacelle (102, 104, 36, 62, 64) direct mass flow from an engine (38) to an outlet (102, 42, 62) of a propulsion system. The sleeve (106, 108, 44, 66, 68) is configured to move between a forward position and an aft position within the nacelle (102, 104, 36, 62, 64) at the rear of the engine (38). The sleeve (106, 108, 44, 66, 68) has a protruding portion extending toward the center of the path (52) and defining a minimum inner diameter of the sleeve (106, 108, 44, 66, 68). The sleeve (106, 108, 44, 66, 68) includes a plurality of sleeve segments (68) that are longitudinally aligned and circumferentially arranged to form the sleeve (106, 108, 44, 66, 68). The sleeve segments (68) are configured to move circumferentially closer together when the sleeve (106, 108, 44, 66, 68) moves in a first direction within the nacelle (102, 104, 36, 62, 64) and to move circumferentially farther apart when the sleeve (106, 108, 44, 66, 68) moves in a second direction within the nacelle (102, 104, 36, 62, 64). An actuator (130, 46) is coupled to the sleeve (106, 108, 44, 66, 68) and is configured to move the sleeve (106, 108, 44, 66, 68).
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