Passively actuated variable area nozzle for an aircraft propulsion system

Patent metadata

Field	Value
Publication number	US-11725608-B2
Application number	US-202217734723-A
Country	US
Kind code	B2
Filing date	May 2, 2022
Priority date	May 15, 2020
Publication date	Aug 15, 2023
Grant date	Aug 15, 2023

Abstract

An aircraft system includes a propulsion system structure, a variable area nozzle and a linkage system. The propulsion system structure is moveable between a first position and a second position. The variable area nozzle is fluidly coupled with a duct in the propulsion system structure. The variable area nozzle is moveable between a first configuration and a second configuration. An exit area of the variable area nozzle has a first value when the variable area nozzle is in the first configuration and a second value when the variable area nozzle is in the second configuration. The variable area nozzle includes a flap moveably connected to the propulsion system structure. The linkage system mechanically links the variable area nozzle with the propulsion system structure. The linkage system includes a driver linkage, a first bell crank, a bridge linkage, a second bell crank, a follower linkage and a crank arm.

First claim

What is claimed is:

1. An aircraft system, comprising:
a propulsion system structure comprising a duct, the propulsion system structure adapted to move between a first position and a second position;
a variable area nozzle fluidly coupled with the duct, the variable area nozzle adapted to move between a first configuration and a second configuration, an exit area of the variable area nozzle having a first value when the variable area nozzle is in the first configuration, the exit area of the variable area nozzle having a second value when the variable area nozzle is in the second configuration, and the variable area nozzle comprising a flap moveably connected to the propulsion system structure; and
a linkage system configured to mechanically link movement of the variable area nozzle between the first configuration and the second configuration with movement of the propulsion system structure between the first position and the second position, the linkage system comprising a driver linkage, a first bell crank, a bridge linkage, a second bell crank, a follower linkage and a crank arm, the first bell crank coupling the driver linkage to the bridge linkage, the second bell crank coupling the bridge linkage to the follower linkage, and the crank arm coupling the follower linkage to the flap.

2. The aircraft system of claim 1 , wherein
the variable area nozzle further comprises a second flap moveably connected to the propulsion system structure;
the linkage system further comprises a second follower linkage and a second crank arm;
the first bell crank further couples the driver linkage to the second follower linkage; and
the second crank arm couples the second follower linkage to the second flap.

3. The aircraft system of claim 1 , wherein
the linkage system further comprises an aircraft structure crank arm; and
the driver linkage couples the aircraft structure crank arm to the first bell crank.

4. The aircraft system of claim 3 , further comprising:
a stationary structure;
the propulsion system structure movably connected to the stationary structure; and
the aircraft structure crank arm fixedly attached to the stationary structure.

5. The aircraft system of claim 1 , wherein the movement of the propulsion system structure between the first position and the second position drives the movement of the variable area nozzle between the first configuration and the second configuration.

6. The aircraft system of claim 1 , wherein movement of the variable area nozzle from the first configuration towards the second configuration begins when the propulsion system structure moves from the first position towards the second position.

7. The aircraft system of claim 1 , wherein movement of the variable area nozzle from the first configuration towards the second configuration begins when the propulsion system structure moves from an intermediate position towards the second position, and the intermediate position is between the first position and the second position.

8. The aircraft system of claim 1 , further comprising:
a stationary structure;
the linkage system coupled to the stationary structure, the propulsion system structure and the variable area nozzle; and
the linkage system adapted to move the variable area nozzle between the first configuration and the second configuration as the propulsion system structure moves relative to the stationary structure between the first position and the second position.

9. The aircraft system of claim 8 , wherein the propulsion system structure is movably connected to the stationary structure.

10. The aircraft system of claim 1 , wherein the linkage system further comprises a track and a slider mated with and slidable along the track.

11. The aircraft system of claim 1 , further comprising:
a fixed structure;
the propulsion system structure pivotally coupled to the fixed structure such that the propulsion system structure pivots between the first position and the second position.

12. The aircraft system of claim 1 , wherein
the variable area nozzle further comprises a second flap;
the first flap is pivotally coupled to the propulsion system structure at a first side of the propulsion system structure; and
the second flap is pivotally coupled to the propulsion system structure at a second side of the propulsion system structure that is opposite the first side of the propulsion system structure.

13. The aircraft system of claim 1 , further comprising:
a propulsor of an aircraft propulsion system;
the propulsor housed within the propulsion system structure.

14. The aircraft system of claim 1 , wherein a centerline of the duct when the propulsion system structure is in the first position is angularly offset from the centerline of the duct when the propulsion system structure is in the second position.

Assignees

• Rohr Inc

Inventors

• Wylie Steve A

Classifications

• F02K1/1207 Primary

  of one series of flaps hinged at their upstream ends on a fixed structure (F02K1/1215 - F02K1/1292 take precedence) · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• B64D33/04 Primary

  of exhaust outlets or jet pipes · CPC title

• F02K1/12

  by means of pivoted flaps · CPC title

• F05D2220/90

  in vehicles adapted for vertical or short take off and landing (v/stol vehicles) · CPC title