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

Patent metadata

Field	Value
Publication number	US-11834189-B2
Application number	US-202117301239-A
Country	US
Kind code	B2
Filing date	Mar 30, 2021
Priority date	Apr 9, 2020
Publication date	Dec 5, 2023
Grant date	Dec 5, 2023

Abstract

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.

First claim

What is claimed is:

1. An exhaust nozzle assembly for use with a propulsion system for an aircraft, the propulsion system including an engine configured to produce a jet, the exhaust nozzle assembly comprising:
a nozzle body configured to be fluidly coupled with the engine and to receive the jet;
an outer cover at least partially covering the nozzle body;
a movable component configured to move between a first position and a second position when a force is applied to the movable component, the movable component disposed and configured to have an effect on one of the jet and an exhaust plume produced by the propulsion system when the movable component moves between the first position and the second position; and
a linkage coupled to the movable component and adapted for coupling to an actuator configured to generate the force, the linkage transmitting the force to the moveable component when the linkage is coupled with the actuator and when the actuator is actuated,
wherein a gap exists between an inner surface of the outer cover and an outer surface of the nozzle body,
wherein the linkage is partially disposed within the gap,
wherein the exhaust nozzle assembly is free of the actuator, and
wherein a cross-sectional dimension of the linkage is smaller than a smallest dimension of the actuator, and wherein a dimension of the gap is smaller than the smallest dimension of the actuator and greater than the cross-sectional dimension of the linkage.

2. The exhaust nozzle assembly of claim 1 , wherein the movable component comprises a thrust reverser.

3. The exhaust nozzle assembly of claim 1 , wherein the moveable component comprises a variable A8.

4. The exhaust nozzle assembly of claim 1 , wherein the moveable component comprises a variable A9.

5. A propulsion system for an aircraft, the propulsion system comprising:
an engine configured to produce a jet; and
an exhaust nozzle assembly disposed downstream of the engine, the exhaust nozzle assembly including:
a nozzle body fluidly coupled with the engine and configured to receive the jet;
an outer cover at least partially covering the nozzle body;
a movable component configured to move between a first position and a second position when a force is applied to the movable component, the movable component disposed and configured to have an effect on one of the jet and an exhaust plume produced by the propulsion system when the movable component moves between the first position and the second position; and
a linkage coupled to the movable component and adapted for coupling to an actuator, the actuator configured to generate the force, the linkage transmitting the force to the moveable component when the linkage is coupled with the actuator and when the actuator is actuated,

wherein a gap exists between an inner surface of the outer cover and an outer surface of the nozzle body,
wherein the linkage is partially disposed within the gap,
wherein the exhaust nozzle assembly is free of the actuator, and
wherein a cross-sectional dimension of the linkage is smaller than a smallest dimension of the actuator, and wherein a dimension of the gap is smaller than the smallest dimension of the actuator and greater than the cross-sectional dimension of the linkage.

6. The propulsion system for an aircraft of claim 5 , wherein the movable component comprises a thrust reverser.

7. The propulsion system for an aircraft of claim 5 , wherein the moveable component comprises a variable A8.

8. The propulsion system for an aircraft of claim 5 , wherein the moveable component comprises a variable A9.

9. An aircraft comprising:
a fuselage;
a wing coupled with the fuselage;
an actuator; and
a propulsion system mounted to one of the fuselage and the wing, the propulsion system including:
an engine configured to produce a jet, and
an exhaust nozzle assembly disposed downstream of the engine, the exhaust nozzle assembly including:
a nozzle body fluidly coupled with the engine and configured to receive the jet,
an outer cover at least partially covering the nozzle body,
a movable component configured to move between a first position and a second position when a force is applied to the movable component, the movable component disposed and configured to have an effect on one of the jet and an exhaust plume produced by the propulsion system when the movable component moves between the first position and the second position, and
a linkage coupled to the movable component and further coupled to the actuator, the actuator configured to generate the force, the linkage transmitting the force to the moveable component when the actuator is actuated,
wherein a gap exists between an inner surface of the outer cover and an outer surface of the nozzle body,

wherein the linkage is partially disposed within the gap,
wherein the exhaust nozzle assembly is free of the actuator, and
wherein a cross-sectional dimension of the linkage is smaller than a smallest dimension of the actuator, and wherein a dimension of the gap is smaller than the smallest dimension of the actuator and greater than the cross-sectional dimension of the linkage.

10. The aircraft of claim 9 , further comprising a pylon coupling the propulsion system to the wing.

11. The aircraft of claim 9 further comprising a pylon coupling the propulsion system to the fuselage.

12. The aircraft of claim 9 , wherein the movable component is one of a thrust reverser, a variable A8, and a variable A9.

13. An aircraft comprising:
a fuselage;
a wing coupled with the fuselage;
an actuator; and
a propulsion system mounted to one of the fuselage and the wing, the propulsion system including:
an engine configured to produce a jet, and
an exhaust nozzle assembly disposed downstream of the engine, the exhaust nozzle assembly including:
a nozzle body fluidly coupled with the engine and configured to receive the jet,
an outer cover at least partially covering the nozzle body,
a movable component configured to move between a first position and a second position when a force is applied to the movable component, the movable component disposed and configured to have an effect on one of the jet and an exhaust plume produced by the propulsion system when the movable component moves between the first position and the second position, and
a linkage coupled to the movable component and further coupled to the actuator, the actuator configured to generate the force, the linkage transmitting the force to the moveable component when the actuator is actuated,
wherein a gap exists between an inner surface of the outer cover and an outer surface of the nozzle body,
wherein the linkage is partially disposed within the gap, and
wherein the actuator is mounted to an external surface of the nozzle body proximate a mounting location,
wherein the mounting location comprises a location on the external surface of the nozzle body where the propulsion system is mounted to the one of the fuselage and the wing,
wherein the propulsion system is mounted to the one of the fuselage and the wing by a mounting structure, and
wherein the mounting structure is enclosed within a mounting-structure fairing, and
wherein the actuator is enclosed within the mounting-structure fairing.

14. The aircraft of claim 13 , wherein a cross-sectional dimension of the linkage is smaller than a smallest dimension of the actuator, and wherein a dimension of the gap is greater than the cross-sectional dimension of the linkage.

15. The aircraft of claim 13 , wherein the mounting structure comprises a pylon.

16. The aircraft of claim 13 , w

Assignees

• Gulfstream Aerospace Corp

Inventors

• Freund Donald
• Muzychka Derek

Classifications

• B64D33/04 Primary

  of exhaust outlets or jet pipes · CPC title

• B64D27/16

  of jet type · CPC title

• B64D29/02

  associated with wings · CPC title

• B64D29/04

  associated with fuselages · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title