PASSIVELY ACTUATED VARIABLE AREA NOZZLE FOR AN AIRCRAFT PROPULSION SYSTEM
An aircraft system is provided that includes a propulsion system structure and a variable area nozzle. The propulsion system structure includes a duct, and is adapted to move between a first position and a second position. The variable area nozzle is fluidly coupled with the duct. The variable area nozzle is adapted to move 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. The exit area of the variable area nozzle has a second value when the variable area nozzle is in the second configuration. Movement of the variable area nozzle between the first configuration and the second configuration is mechanically linked with movement of the propulsion system structure between the first position and the second position.
This application claims priority to U.S. Patent Appln. No. 63/025,346 filed May 15, 2020 where in hereby incorporated herein by reference in its entirety.
BACKGROUND 1. Technical FieldThis disclosure relates generally to an aircraft and, more particularly, to a variable area nozzle for an aircraft propulsion system.
2. Background InformationAn aircraft propulsion system may include a variable area nozzle. Various types and configurations of variable area nozzles are known in the art. While these known variable area nozzles have various benefits, there is still room in the art for improvement. In particular, there is a need in the art for an improved system for actuating movement of a variable area nozzle that may simplify design, reduce costs, reduce maintenance, etc.
SUMMARY OF THE DISCLOSUREAccording to an aspect of the present disclosure, an aircraft system is provided that includes a propulsion system structure and a variable area nozzle. The propulsion system structure includes a duct. The propulsion system structure is adapted to move between a first position and a second position. The variable area nozzle is fluidly coupled with the duct. The variable area nozzle is adapted to move 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. The exit area of the variable area nozzle has a second value when the variable area nozzle is in the second configuration. Movement of the variable area nozzle between the first configuration and the second configuration is mechanically linked with movement of the propulsion system structure between the first position and the second position.
According to another aspect of the present disclosure, another aircraft system is provided that includes a propulsion system structure, a variable area nozzle and a linkage system. The propulsion system structure includes a duct. The propulsion system structure is adapted to move between a first disposition and a second disposition that is angularly offset from the first disposition. The variable area nozzle is fluidly coupled with and downstream of the duct. The linkage system is adapted such that movement of the propulsion system structure between the first disposition and the second disposition drives actuation of the variable area nozzle through the linkage system.
According to still another aspect of the present disclosure, another aircraft system is provided that includes an aircraft effector, a variable area nozzle and a linkage system. The aircraft effector is adapted to move between a first position and a second position. The linkage system is adapted such that movement of the aircraft effector between the first position and the second position mechanically drives actuation of the variable area nozzle through the linkage system.
The actuation of the variable area nozzle may include movement of the variable area nozzle between a first configuration and a second configuration. An exit area of the variable area nozzle may have a first value when the variable area nozzle is in the first configuration. The exit area of the variable area nozzle may have a second value when the variable area nozzle is in the second configuration.
The aircraft effector may be configured as or otherwise include a propulsion duct. The variable area nozzle may be fluidly coupled with and downstream of the propulsion duct.
The movement of the propulsion system structure between the first position and the second position may drive the movement of the variable area nozzle between the first configuration and the second configuration.
Movement of the variable area nozzle from the first configuration towards the second configuration may begin when the propulsion system structure moves from the first position towards the second position.
Movement of the variable area nozzle from the first configuration towards the second configuration may begin when the propulsion system structure moves from an intermediate position towards the second position. The intermediate position may be between the first position and the second position.
The aircraft system may also include a stationary structure and a linkage system. The linkage system may be coupled to the stationary structure, the propulsion system structure and the variable area nozzle. The linkage system may be 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.
The propulsion system structure may be movably connected to the stationary structure. A flap of the variable area nozzle may be movably connected to the propulsion system structure.
The linkage system may include one or more bell cranks.
The linkage system may include one or more cam elements.
The linkage system may include a first pulley, a second pulley and a tension member engaged with and spanning between the first pulley and the second pulley.
The linkage system may include a track and a slider mated with and slidable along the track.
The linkage system may include one or more linkages.
The aircraft system may also include a fixed structure. The propulsion system structure may be pivotally coupled to the fixed structure such that the propulsion system structure pivots between the first position and the second position.
The variable area nozzle may include a first flap and a second flap. The first flap may be pivotally coupled to the propulsion system structure at a first side of the propulsion system structure. The second flap may be pivotally coupled to the propulsion system structure at a second side of the propulsion system structure that may be opposite the first side of the propulsion system structure.
The aircraft system may include a propulsor of an aircraft propulsion system. The propulsor may be housed within the propulsion system structure.
The duct may be or otherwise include a first duct. The propulsion system structure may also include a second duct in parallel with the first duct. The variable area nozzle may also be fluidly coupled with the second duct.
A centerline of the duct when the propulsion system structure is in the first position may be angularly offset from the centerline of the duct when the propulsion system structure is in the second position.
The present disclosure may include any one or more of the individual features disclosed above and/or below alone or in any combination thereof.
The foregoing features and the operation of the invention will become more apparent in light of the following description and the accompanying drawings.
The aircraft system 20 of
The aircraft structure 22 of
The propulsor 26 of
The propulsion system structure 28 is configured as a structural housing, casing and/or nacelle for one or more components of the aircraft propulsion system 24. The propulsion system structure 28 of
The passage 40 extends longitudinally along a longitudinal centerline 42 through the propulsion system structure 28 between and to a passage first (e.g., forward/upstream) end 44 and a passage second (e.g., aft/downstream) end 46. The passage 40 of
Referring to
When the propulsion system structure 28 is in the first position of
When the propulsion system structure 28 is in the second position of
The variable area nozzle 30 of
Referring to
The variable area nozzle 30 of
In the first configuration of
Where each of the variable area nozzle flaps 60 is pivotally coupled (e.g., hinged) to the propulsion system structure 28, each flap 60 may pivot an actuation angle 72 between the first disposition of
Each variable area nozzle flap 60 of
Referring to
The linkage system 32 of
The linkage system 32 of the present disclosure includes an assembly of linkage components that operatively couple various aircraft system components together. Examples of linkage components include, but are now limited to, a bell crank, a crank arm, a cam element, a pulley, a tension member (e.g., a belt, a cable, a rope, etc.), a track, a slider, a linkage (e.g., a fixed length arm, an adjustable length arm, a tie rod, a push rod, etc.), a pushrod, a gear, etc. Such linkage components operatively connect the variable area nozzle 30 and its flaps 60 to (a) the aircraft propulsion system 24 and its propulsion system structure 28 and to (b) the aircraft structure 22. The linkage system 32 may thereby move the variable area nozzle 30 and its flaps 60 between its first and second configurations as the propulsion system structure 28 moves (e.g., pivots) relative to the aircraft structure 22 between its first and second positions.
The linkage components of
With the foregoing assembly of linkage components, the linkage system 32 is configured to translate relative motion between the propulsion system structure 28 and the aircraft structure 22 into motion of the variable area nozzle flaps 60 as shown in
The linkage system 32 of
The linkage system 32 of
The linkage system 32 of
While various embodiments of the linkage system 32 are described above, the present disclosure is not limited to any particular configurations thereof. Rather, the linkage system 32 may have any configuration which enables, for example, passive actuation/movement of the variable area nozzle 30 and its flaps 60 through motion of the propulsion system structure 28 or any other aircraft effector configured with the aircraft.
In some embodiments, the aircraft propulsion system 24 may be configured with a single propulsor 26 and a single passage 40 as generally described above. However, in other embodiments, the aircraft propulsion system 24 may include more than one propulsor 26 and more than one passage 40; e.g., a dedicated passage 40 for each propulsor 26. For example, referring to
While various embodiments of the present invention have been disclosed, it will be apparent to those of ordinary skill in the art that many more embodiments and implementations are possible within the scope of the invention. For example, the present invention as described herein includes several aspects and embodiments that include particular features. Although these features may be described individually, it is within the scope of the present invention that some or all of these features may be combined with any one of the aspects and remain within the scope of the invention. Accordingly, the present invention is not to be restricted except in light of the attached claims and their equivalents.
Claims
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; and
- 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, and the exit area of the variable area nozzle having a second value when the variable area nozzle is in the second configuration;
- wherein movement of the variable area nozzle between the first configuration and the second configuration is mechanically linked with movement of the propulsion system structure between the first position and the second position.
2. 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.
3. 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.
4. 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.
5. The aircraft system of claim 1, further comprising:
- a stationary structure; and
- a linkage system coupled to the stationary structure, the propulsion system structure and the variable area nozzle;
- 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.
6. The aircraft system of claim 5, wherein
- the propulsion system structure is movably connected to the stationary structure; and
- a flap of the variable area nozzle is movably connected to the propulsion system structure.
7. The aircraft system of claim 5, wherein the linkage system comprises a bell crank.
8. The aircraft system of claim 5, wherein the linkage system comprises a cam element.
9. The aircraft system of claim 5, wherein the linkage system comprises a first pulley, a second pulley and a tension member engaged with and spanning between the first pulley and the second pulley.
10. The aircraft system of claim 5, wherein the linkage system comprises a track and a slider mated with and slidable along the track.
11. The aircraft system of claim 5, wherein the linkage system comprises one or more linkages.
12. 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.
13. The aircraft system of claim 1, wherein
- the variable area nozzle comprises a first flap and 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.
14. The aircraft system of claim 1, further comprising:
- a propulsor of an aircraft propulsion system;
- the propulsor housed within the propulsion system structure.
15. The aircraft system of claim 1, wherein
- the duct comprises a first duct, and the propulsion system structure further comprises a second duct in parallel with the first duct; and
- the variable area nozzle is further fluidly coupled with the second duct.
16. 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.
17. An aircraft system, comprising:
- a propulsion system structure comprising a duct, the propulsion system structure adapted to move between a first disposition and a second disposition that is angularly offset from the first disposition;
- a variable area nozzle fluidly coupled with and downstream of the duct; and
- a linkage system adapted such that movement of the propulsion system structure between the first disposition and the second disposition drives actuation of the variable area nozzle through the linkage system.
18. The aircraft system of claim 17, wherein
- the actuation of the variable area nozzle comprises movement of the variable area nozzle 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
- the exit area of the variable area nozzle has a second value when the variable area nozzle is in the second configuration.
19. An aircraft system, comprising:
- an aircraft effector adapted to move between a first position and a second position;
- a variable area nozzle; and
- a linkage system adapted such that movement of the aircraft effector between the first position and the second position mechanically drives actuation of the variable area nozzle through the linkage system.
20. The aircraft system of claim 19, wherein
- the aircraft effector comprises a propulsion duct; and
- the variable area nozzle is fluidly coupled with and downstream of the propulsion duct.
Type: Application
Filed: May 11, 2021
Publication Date: Jan 20, 2022
Inventor: Steve A. Wylie (San Diego, CA)
Application Number: 17/317,380