JP2003056405A - Exhaust nozzle for jet engine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an exhaust nozzle for a jet engine capable of positively operating a plurality of flaps in desired directions and further simply constituting a guide mechanism that guides a ring used for the operation of the flaps. SOLUTION: The guide mechanism 30 is provided, which guides the movement of an annular ring 24 connected to a plurality of the flaps 21. The guide mechanism 30 guides the ring 24 in several directions of a central axis direction of the ring 24, a diameter direction of the ring 24, and a rotational direction centering the diameter direction of the ring 24.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an exhaust nozzle for a jet engine, which has a plurality of flaps that form a flow path of exhaust gas from the engine.

[0002]

2. Description of the Related Art In an exhaust nozzle for a jet engine used in a supersonic aircraft or the like, generally, the speed of the exhaust gas is controlled by operating a plurality of flaps to change a flow path of the exhaust gas to a desired state. There is.

An example of an exhaust nozzle that operates a plurality of flaps to change the flow path of exhaust gas is, for example, Japanese Patent Laid-Open No.
275,050, US Pat. No. 5,437,4111
The technology described in the issue is known.

In the above-mentioned exhaust nozzle, a plurality of flaps arranged side by side in the circumferential direction are tilted in the axial direction (the rear end side in the exhaust gas flow direction is inclined radially inward).
A convergent is formed in the exhaust gas flow path. Further, by inclining the other flaps connected to the rear ends of the plurality of flaps so that the rear end side in the axial direction is the outer side in the radial direction, a diffusion portion (divergen) is formed in the exhaust gas flow path.
t) is formed. Thereby, the flow passage cross-sectional area of the exhaust gas is changed, the speed of the exhaust gas is controlled, and a desired thrust is obtained.

Further, in the above exhaust nozzle, the direction of the opening of the exhaust nozzle can be changed by changing the plurality of flaps arranged side by side in the circumferential direction from the axially symmetrical arrangement state to the asymmetrical arrangement state. Has become. For example, with the front ends of the flaps arranged in axial symmetry,
By arranging the rear end in an asymmetrical arrangement state, that is, arranging the opening center of the rear end off the axis, the direction of the opening can be inclined from the axial direction. Thus, by changing the direction of the opening of the exhaust nozzle, the thrust direction of the engine can be changed to an arbitrary direction.

[0006]

By the way, in the exhaust nozzle having a plurality of flaps as described above, in order to operate the plurality of flaps, the plurality of flaps are connected to an annular ring and the annular ring is used for operation. Often connected to the actuator. In this case, a guide mechanism that guides the movement of the ring in a predetermined direction is required.

However, in the conventional exhaust nozzle, the guide mechanism does not have a sufficient degree of freedom or has a complicated mechanism. For example, the above-mentioned Japanese Patent Laid-Open No. 2-275
In the exhaust nozzle described in Japanese Patent No. 050, the guide mechanism is 1
It has only freedom. That is, the guide mechanism is configured to guide the ring only in the central axis direction of the ring. In this case, although the plurality of flaps can be changed axially symmetrically via the ring, it is difficult to change the plurality of flaps from the axially symmetrical arrangement state to the asymmetrical arrangement state via the ring.

Further, conventionally, in the ring guide mechanism, another actuator is arranged as a dummy in addition to the actuator for moving the ring, whereby 2
A structure that secures the degree of freedom is often used. However, in this case, the configuration is likely to be complicated and the cost is likely to be increased. In addition, in order to change the plurality of flaps from the axially symmetric arrangement state to the asymmetrical arrangement state,
Freedom is often not enough.

The present invention has been made in view of the above-mentioned circumstances, and a guide mechanism that can reliably operate a plurality of flaps in a desired direction and that guides a ring used for the operation is simply described. An object is to provide an exhaust nozzle for a jet engine that can be configured.

[0010]

In order to solve the above problems, the present invention relates to an exhaust nozzle for a jet engine, which is provided with a plurality of flaps that form a flow path of exhaust gas from an engine, wherein the plurality of flaps are provided. An annular ring to be connected, and a plurality of actuators connected to the ring and actuating the plurality of flaps via the ring,
A guide mechanism that guides the movement of the ring, wherein the guide mechanism has a center axis direction of the ring, a radial direction of the ring, and a rotation direction centered on the radial direction of the ring. , Guiding the ring. In this jet engine exhaust nozzle, the guide mechanism guides the ring in each of the central axis direction of the ring, the radial direction of the ring, and the rotation direction centered on the radial direction of the ring. 3 degrees of freedom are secured as the moving direction of the. Therefore, it is possible to reliably change the plurality of flaps from the axially symmetric arrangement state to the asymmetrical arrangement state via the ring.

In this case, the guide mechanism has a member in which a groove extending in the central axis direction of the ring is formed, at least a part of which is accommodated in the groove, and the groove extends inside the groove. A guide pin slidably and rotatably in a direction, a member having a curved surface whose height changes in the radial direction of the ring, and a guide roller abutting the curved surface. . In this case, the guide pin slides in the extending direction of the groove inside the groove, so that the ring is guided in the central axis direction of the ring. Further, when the guide pin rotates inside the groove, the ring is guided in the rotation direction centered on the radial direction of the ring. Further, by moving the guide roller along the curved surface, the ring is guided in the radial direction of the ring. Therefore, even though the guide mechanism is simple, the ring moving direction is 3
The degree of freedom is secured.

Further, the guide mechanism has a link mechanism for guiding the ring in the central axis direction of the ring and the radial direction of the ring, and the link mechanism is rotatable in the radial direction of the ring. A connecting portion may be provided. In this case, the link mechanism guides the ring in the central axis direction of the ring and the radial direction of the ring. Also,
The ring is guided in the rotational direction centered on the radial direction of the ring by the rotational movement of the connecting portion. Therefore, although the guide mechanism is simple, three degrees of freedom are secured as the moving direction of the ring.

[0013]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of an exhaust nozzle for a jet engine according to the present invention will be described below with reference to the drawings. FIG. 1 is a diagram schematically showing an overall configuration of an embodiment of an exhaust nozzle for a jet engine used in an aircraft such as a supersonic aircraft. An exhaust nozzle 10 is installed at a rear end portion of an engine (not shown). To be done. Exhaust gas (mainstream) from the engine passes through an introduction duct 11 of the exhaust nozzle 10, is accelerated by a convergent-divergent section 12, and is discharged to the outside of the engine.

The throttle / divergence section 12 includes a plurality of convergent flaps 20 which mainly form a throttle section (flow passage whose cross-sectional area decreases in the flow direction) and a divergent section (having a cross-sectional area in the flow direction). And a plurality of divergent flaps 21 which mainly form an enlarged channel. Convergent flap 20 and divergent flap 21
A plurality of each is arranged side by side in the circumferential direction. Further, the convergent flap 20 and the divergent flap 21 are arranged side by side in the axial direction of the exhaust duct. The convergent flap 20 has one end in the axial direction connected to the introduction duct 11 and the other end connected to one end of the divergent flap 21.

A link member 22 is connected to the other end of the divergent flap 21, and the link member 22 has an annular first ring to which a plurality of (here, three) actuators (first actuators 23) are connected. It is connected to 24. On the other hand, a track rail 25 having a predetermined curved surface is provided on the back surface of the convergent flap 20, and a plurality of (here, three) actuators (second actuators 26) are provided so as to contact the curved surface of the track rail 25. ) -Connected second ring 2 having an annular shape
7 is arranged so as to be movable in the axial direction and the like. The plurality of first actuators 23 and the plurality of second actuators 26 are arranged at equal intervals in the circumferential direction.

FIG. 2 is a schematic sectional view in which the diaphragm / divergent portion 12 is partially enlarged. In FIG. 2, the plurality of second actuators 26 connected to the second ring 27 actuate the convergent flaps 20 via the track rails 25, and the cross-sectional area of the throttle-type flow path (the cross-sectional area of the nozzle throat NS). ) Is changed. Also, the first ring 24
The plurality of first actuators 23, which are connected to each other, actuate the divergent flap 21 via the first ring 24 and the link member 22, and the cross-sectional area of the divergence-type flow path (the opening of the rear end portion of the exhaust nozzle 10). Area). 2A shows a state in which the opening of the exhaust nozzle 10 is narrowed, and FIG. 2B shows a state in which the opening is in a diffusion state. Further, the flow passage cross-sectional area of the exhaust nozzle 10 is controlled according to the fuel flow rate of the engine so that an appropriate thrust can be obtained.

Further, in the exhaust nozzle 10, the first ring 24 is tilted by providing a difference in the working distance of the plurality of first actuators 23 connected to the first ring 24, and as shown in FIG. Gent flap 21
Can be changed from an axisymmetric arrangement state to an asymmetric arrangement state. In this case, the plurality of first actuators 2
By periodically changing the respective working distances of No. 3, it is possible to turn the direction of the opening of the exhaust nozzle 10. As described above, in the exhaust nozzle 10, the thrust direction of the engine can be controlled in any direction by changing the direction of the opening. In addition, divergent flap 2
Reference numeral 1 denotes a plurality of master flaps 21a connected to the first ring 24 (see FIG. 2) and a master flap 21.
a and a plurality of seal flaps 21b arranged so as to cover the gaps between the two a's, and both are connected by a positioning mechanism 29. The positioning mechanism 29 is configured to position the relative position of the seal flap 21b with respect to the master flap 21a such that the seal flap 21b is positioned substantially in the middle of the adjacent master flaps 21a.

FIG. 4 is a perspective view showing an example of the guide mechanism 30 for guiding the movement of the first ring 24 described above. As shown by the arrow in FIG. 4, the guide mechanism 30 is centered on the central axis direction of the first ring 24 (arrow a), the radial direction of the first ring 24 (arrow b), and the radial direction of the first ring 24. The first ring 24 is movably guided in each of the rotation directions (arrow c).

Specifically, as shown in FIGS. 5 and 6, the guide mechanism 30 includes a groove 31 extending in the central axis direction (direction of arrow a) of the first ring 24, and at least the groove 31. A part of the guide pin 33, which is housed in the groove 31 and is slidable and rotatable in the extending direction of the groove 31 (direction of arrow a), and the radial direction of the first ring 24 (direction of arrow b).
It has a curved surface 34 whose height changes, and a guide roller 36 which comes into contact with the curved surface 34. In addition, the groove 31
The curved surface 34 and the curved surface 34 are provided on the peripheral surface of the introduction duct 11 or the second ring 27 described above or a member attached to them. In the present embodiment, the groove 31 and the curved surface 3
4 is provided on the outer peripheral surface of the introduction duct 11 described above.

In the structure shown in FIGS. 5 and 6, in the guide mechanism 30, the guide pin 33 slides inside the groove 31 in the extending direction of the groove 31 to move in the central axis direction of the first ring 24. The first ring 24 is guided. Also, the groove 3
By rotating the guide pin 33 inside the first
The first ring 24 is guided in a rotation direction around the radial direction of the ring 24. Further, the guide roller 36 moves along the curved surface 34, so that the first ring 24 is guided in the radial direction of the first ring 24. Accordingly, in the guide mechanism 30, the moving direction of the first ring 24 is 3
The degree of freedom is secured. In particular, with this guide mechanism 30,
While guiding the axial movement of the first ring 24 by the groove 31 and the guide pin 33, the first ring 24 is also guided in the radial rotation direction, so that a plurality of degrees of freedom are provided with a simple configuration. Can be secured.

Thus, in the exhaust nozzle 10 of this example,
First used to operate the divergent flap 21
A guide mechanism 30 that guides the ring 24 ensures three degrees of freedom. Therefore, it is possible to change the divergent flaps 21 so as to be axially symmetric and surely to change from the axially symmetric arrangement state to the asymmetrical arrangement state.

In the example shown in FIGS. 5 and 6, the introduction duct 11 on the fixed side is provided with the groove 31 and the curved surface 34, and the first ring 24 on the moving side is provided with the guide pin 33 and the guide roller 36. However, a guide pin or a guide roller may be provided on the fixed side and a groove or a curved surface may be provided on the moving side. Also,
As a material for the above-mentioned constituent members, a ceramic composite material or A
Weight reduction can be achieved by using a lightweight material such as an l-based intermetallic compound. Further, the guide mechanism may have three degrees of freedom as the moving direction of the first ring,
The structure of the guide mechanism is not limited to that described above.

7 and 8 are views showing another example (guide mechanism 40) of the guide mechanism for guiding the movement of the first ring 24. As shown in FIG. In this configuration as well, the guide mechanism 40 is configured such that the guide ring 40 moves in the central axis direction (arrow a) of the first ring 24 and the first ring 2
The first ring 24 is movably guided in each of the four radial directions (arrow b) and the rotational direction (arrow c) about the radial direction of the first ring 24.

Specifically, the guide mechanism 40 includes the first ring 24 and the central axis direction (arrow a direction) of the first ring 24.
It has a link mechanism 41 for guiding the first ring 24 in the radial direction of 4 (direction of arrow b). Then, the link mechanism 41
Includes a connecting portion 42 that is rotatable in the radial direction of the first ring 24.
Is provided. As the rotatable connecting portion 42, for example, a mechanism using a spherical bearing having a spherical seat can be used.

In the case of the structure shown in FIGS. 7 and 8, in the guide mechanism 40, the first ring 2 is moved by the link mechanism 41.
The first ring 24 is guided in the central axis direction of 4 and in the radial direction of the first ring 24. Further, the rotational movement of the connecting portion 42 guides the first ring 24 in a rotational direction around the radial direction of the first ring 24. Thereby, also in this guide mechanism 40, three degrees of freedom are secured as the moving direction of the first ring 24. Particularly, in the guide mechanism 40, the link mechanism 41 provided with the rotatable connecting portion 42 is provided.
By using, it is possible to secure a plurality of degrees of freedom with a simple configuration.

The preferred embodiment of the present invention has been described above with reference to the accompanying drawings, but it goes without saying that the present invention is not limited to the example. The shapes, combinations, and the like of the respective constituent members shown in the above-described examples are merely examples, and various changes can be made based on design requirements and the like without departing from the spirit of the present invention.

[0027]

As described above, according to the exhaust nozzle for a jet engine of the present invention, the guide mechanism for guiding the ring used for the operation of the plurality of flappers secures three degrees of freedom. The flapper can be reliably operated in the desired direction. Further, the guide mechanism can be simply constructed without using a dummy actuator, and the cost can be reduced.

[Brief description of drawings]

FIG. 1 is a diagram schematically showing an overall configuration of an embodiment of an exhaust nozzle for a jet engine according to the present invention.

FIG. 2 is a schematic sectional view in which a throttle / divergent portion of the exhaust nozzle of FIG. 1 is partially enlarged.

FIG. 3 is a diagram schematically showing a state in which divergent flaps are changed from an axially symmetric arrangement state to an asymmetrical arrangement state.

FIG. 4 is a perspective view showing an example of a guide mechanism.

5 is a view of the guide mechanism of FIG. 4 viewed in the axial direction of the ring.

6 is a view of the guide mechanism of FIG. 4 viewed in the radial direction of the ring.

FIG. 7 is a view showing another example of the guide mechanism and is a view seen in the axial direction of the ring.

8A and 8B are enlarged views showing a part of the guide mechanism of FIG. 7, in which FIG. 8A is a view seen in a radial direction of the ring, and FIG.
FIG. 3 is a sectional view taken along line AA shown in FIG.

[Explanation of symbols]

10 exhaust nozzle 11 Introduction duct 12 Aperture / divergence section 20 Convergent flap 21 Divergent flap 22 Link members 24 First Ring 23 First Actuator 25 track rails 26 Second Actuator 27 Second Ring 30, 40 guide mechanism 31 groove 33 guide pin 34 curved surface 36 Guide roller 41 Link mechanism 42 Connection

Claims (3)

[Claims] 1. An exhaust nozzle for a jet engine, comprising: a plurality of flaps that form a flow path of exhaust gas from an engine; an annular ring connected to the plurality of flaps; A plurality of actuators that actuate the plurality of flaps via a ring; and a guide mechanism that guides the movement of the ring, wherein the guide mechanism has a central axis direction of the ring, a radial direction of the ring, and An exhaust nozzle for a jet engine, characterized in that the ring is guided in respective directions with respect to a rotational direction around the radial direction of the ring. 2. The guide mechanism includes a member having a groove extending in the central axis direction of the ring, at least a part of which is accommodated in the groove, and the guide mechanism extends in the extending direction of the groove inside the groove. It has a guide pin which is arranged slidably and rotatably, a member having a curved surface whose height changes in the radial direction of the ring, and a guide roller which abuts on the curved surface. The exhaust nozzle for a jet engine according to Item 1. 3. The guide mechanism has a link mechanism that guides the ring in a central axis direction of the ring and a radial direction of the ring, and the link mechanism is rotatable in the radial direction of the ring. The exhaust nozzle for a jet engine according to claim 1, wherein a connecting portion is provided.