JP4736271B2 - Exhaust nozzle for jet engine - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to an exhaust nozzle for a jet engine including a plurality of flaps that form a flow path for exhaust gas from an engine.
[0002]
[Prior art]
In an exhaust nozzle for a jet engine used for a supersonic aircraft or the like, the exhaust gas speed is generally controlled by operating a plurality of flaps to change the flow path of the exhaust gas to a desired state.
[0003]
The exhaust nozzle for operating a plurality of flaps to change the flow path of the exhaust gas, for example, JP-A 2-275050 and JP-known to the technique described in U.S. Patent No. 5,437,41 1 No. Yes.
[0004]
In the exhaust nozzle, a plurality of flaps arranged side by side in the circumferential direction are inclined in the exhaust gas flow path by inclining the axial direction (the rear end side in the exhaust gas flow direction is radially inward). In addition, the plurality of other flaps connected to the rear ends of the plurality of flaps are diffused into the exhaust gas flow path by inclining the rear end in the axial direction radially outward. A divergent is formed, whereby 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.
[0005]
In the 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 an axially symmetric arrangement state to an asymmetric arrangement state. . For example, when the front ends of a plurality of flaps are arranged axially symmetrically, the rear ends are arranged in an asymmetrical manner, that is, the opening center of the rear end is shifted from the axis, whereby the direction of the opening can be inclined from the axial direction. it can. Thus, the thrust direction of the engine can be changed to an arbitrary direction by changing the direction of the opening of the exhaust nozzle.
[0006]
[Problems to be solved by the invention]
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 may be connected to an annular ring and an actuator for operation may be connected to the annular ring. Many. In this case, a guide mechanism for guiding the movement of the ring in a predetermined direction is required.
[0007]
However, in the conventional exhaust nozzle, the guide mechanism does not have a sufficient degree of freedom or is a complicated mechanism.
For example, in the exhaust nozzle described in JP-A-2-275050 described above, the guide mechanism has only one degree of 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 it is possible to change a plurality of flaps axially symmetrically through the ring, it is difficult to change the plurality of flaps from the axially symmetric arrangement state to the asymmetric arrangement state via the ring.
[0008]
Conventionally, in a ring guide mechanism, another actuator is often used as a dummy in addition to an actuator for moving the ring, thereby ensuring two degrees of freedom. However, in this case, the configuration tends to be complicated, and the cost is likely to increase. Also, two degrees of freedom are often insufficient to change the plurality of flaps from the axially symmetric arrangement state to the asymmetric arrangement state.
[0009]
The present invention has been made in view of the above-described circumstances, and can jet a plurality of flaps in a desired direction with certainty and a simple guide mechanism for guiding a ring used for the operation. An object is to provide an exhaust nozzle for an engine.
[0010]
[Means for Solving the Problems]
In order to solve the above-mentioned problem, the present invention is an exhaust nozzle for a jet engine comprising a plurality of flaps that form a flow path for exhaust gas from the engine, and an annular ring connected to the plurality of flaps, A plurality of actuators coupled to the ring and operating the plurality of flaps via the ring; and a guide mechanism for guiding the movement of the ring, wherein the guide mechanism includes a central axis direction of the ring, and the ring The ring is guided in each of a radial direction of the ring and a rotational direction centered on the radial direction of the ring.
In this jet engine exhaust nozzle, the guide mechanism guides the ring in each of the center axis direction of the ring, the radial direction of the ring, and the rotational direction centered on the radial direction of the ring. As a moving direction, three degrees of freedom are secured. Therefore, the plurality of flaps can be reliably changed from the axially symmetric arrangement state to the asymmetric arrangement state via the ring.
[0011]
In this case, the guide mechanism includes a member in which a groove extending in the central axis direction of the ring is formed, and at least a part of the guide mechanism is accommodated in the groove, and slides in the groove extending direction inside the groove. You may have the guide pin arrange | positioned so that movement and rotation are possible, the member in which the curved surface from which the height changes to the radial direction of the said ring was formed, and the guide roller contact | abutted to the said curved surface.
In this case, the guide pin slides in the groove extending direction inside the groove, whereby 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 centering on the radial direction of the ring. Further, the guide roller moves along the curved surface, whereby the ring is guided in the radial direction of the ring. Therefore, although it is a simple guide mechanism, three degrees of freedom are secured as the moving direction of the ring.
[0012]
The guide mechanism includes 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 includes a connecting portion that is rotatable in the radial direction of the ring. It may be provided.
In this case, the ring is guided by the link mechanism in the center axis direction of the ring and in the radial direction of the ring. Further, the ring is guided in the rotational direction centering on the radial direction of the ring by the rotational movement at the connecting portion. Therefore, although it is a simple guide mechanism, three degrees of freedom are secured as the moving direction of the ring.
[0013]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, embodiments of an exhaust nozzle for a jet engine according to the present invention will be described with reference to the drawings.
FIG. 1 is a diagram schematically showing the overall configuration of an embodiment of an exhaust nozzle for a jet engine used in an aircraft such as a supersonic aircraft. The exhaust nozzle 10 is installed at the rear end of an engine (not shown). Is done. Exhaust gas (mainstream) from the engine passes through the introduction duct 11 of the exhaust nozzle 10 and is then accelerated by a constrictive-divergent 12 to be discharged outside the engine.
[0014]
The throttle / diverging unit 12 includes a plurality of convergent flaps 20 mainly forming a throttle unit (a flow path whose cross-sectional area decreases in the flow direction) and a diverging unit (a flow in which the cross-sectional area increases in the flow direction). And a plurality of divergent flaps 21 mainly forming a road). A plurality of the convergent flaps 20 and the divergent flaps 21 are arranged in the circumferential direction. 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 axial end connected to the introduction duct 11 and the other end connected to one end of the divergent flap 21.
[0015]
A link member 22 is connected to the other end of the divergent flap 21, and this link member 22 is connected to an annular first ring 24 to which a plurality of (here, three) actuators (first actuators 23) are connected. Has been. 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 in contact with the curved surface of the track rail 25. ) Are connected to each other so as to be movable in the axial direction or the like. The plurality of first actuators 23 and the plurality of second actuators 26 are arranged at equal intervals in the circumferential direction.
[0016]
FIG. 2 is a schematic cross-sectional view in which the aperture / diverging unit 12 is partially enlarged.
In FIG. 2, the plurality of second actuators 26 connected to the second ring 27 actuate the convergent flap 20 via the track rail 25, so that the sectional area of the throttle-type channel (the sectional area of the nozzle throat NS) is obtained. ). The plurality of first actuators 23 connected to the first ring 24 actuate the divergent flap 21 via the first ring 24 and the link member 22, and the cross-sectional area of the divergent flow path (the exhaust nozzle 10). The opening area at the rear end of the head is changed. 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. 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.
[0017]
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. Can be changed from an axially symmetric arrangement state to an asymmetric arrangement state. In this case, the direction of the opening of the exhaust nozzle 10 can be turned by periodically changing the working distances of the plurality of first actuators 23. As described above, in the exhaust nozzle 10, the thrust direction of the engine can be controlled in an arbitrary direction by changing the direction of the opening. The divergent flap 21 includes a plurality of master flaps 21a connected to the first ring 24 (see FIG. 2) and a plurality of seal flaps 21b arranged to cover the gaps between the master flaps 21a. 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 so that the seal flap 21b is positioned approximately in the middle of the adjacent master flaps 21a.
[0018]
FIG. 4 is a perspective view illustrating an example of the guide mechanism 30 that guides the movement of the first ring 24 described above. The guide mechanism 30 is centered on the central axis direction (arrow a) of the first ring 24, the radial direction of the first ring 24 (arrow b), and the radial direction of the first ring 24, as indicated by arrows in FIG. The first ring 24 is movably guided in each of the rotational directions (arrow c).
[0019]
Specifically, as shown in FIGS. 5 and 6, the guide mechanism 30 includes a groove 31 extending in the central axis direction (arrow a direction) of the first ring 24, and at least a part of the groove 31. A guide pin 33 that is housed and is slidably and rotatably arranged in the extending direction of the groove 31 (arrow a direction) inside the groove 31, and the height of the first ring 24 in the radial direction (arrow b direction). And a guide roller 36 that comes into contact with the curved surface 34. In addition, the said groove | channel 31 and the curved surface 34 are provided in the surrounding surface of the introduction duct 11 or the 2nd ring 27 mentioned above, or the member attached to them. In the present embodiment, the groove 31 and the curved surface 34 are provided on the outer peripheral surface of the introduction duct 11 described above.
[0020]
In the case of the configuration shown in FIGS. 5 and 6, in the guide mechanism 30, the guide pin 33 slides in the extending direction of the groove 31 inside the groove 31, whereby the first ring in the central axis direction of the first ring 24. 24 is guided. Further, when the guide pin 33 rotates inside the groove 31, the first ring 24 is guided in the rotation direction around the radial direction of the first ring 24. Further, the guide roller 36 moves along the curved surface 34, whereby the first ring 24 is guided in the radial direction of the first ring 24. Thereby, in this guide mechanism 30, three degrees of freedom are secured as the moving direction of the first ring 24. In particular, the guide mechanism 30 guides the first ring 24 in the radial direction while guiding the axial movement of the first ring 24 by the groove 31 and the guide pin 33. Multiple configurations can be secured with a simple configuration.
[0021]
Thus, in the exhaust nozzle 10 of this example, the guide mechanism 30 that guides the first ring 24 used for the operation of the divergent flap 21 ensures three degrees of freedom. Therefore, the divergent flap 21 can be changed axially symmetrically and reliably changed from the axially symmetric arrangement state to the asymmetric arrangement state.
[0022]
5 and 6, the groove 31 and the curved surface 34 are provided in the introduction duct 11 on the fixed side, and the guide pin 33 and the guide roller 36 are provided on the first ring 24 on the moving side. A guide pin or a guide roller may be provided on the side, and a groove or a curved surface may be provided on the moving side. Moreover, it becomes possible to achieve weight reduction by using lightweight materials, such as a ceramic type composite material and Al type intermetallic compound, as a material of the said structural member. Furthermore, the guide mechanism only needs to ensure three degrees of freedom as the moving direction of the first ring, and the configuration of the guide mechanism is not limited to the above.
[0023]
7 and 8 are diagrams showing another example (guide mechanism 40) of the guide mechanism for guiding the movement of the first ring 24. FIG.
Also in this configuration, the guide mechanism 40 is configured to rotate in the direction of the central axis 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 direction (arrow c).
[0024]
Specifically, the guide mechanism 40 has a link mechanism 41 that guides the first ring 24 in the central axis direction (arrow a direction) of the first ring 24 and in the radial direction of the first ring 24 (arrow b direction). is doing. The link mechanism 41 is provided with a connecting portion 42 that is rotatable in the radial direction of the first ring 24. As the rotatable connecting portion 42, for example, a mechanism using a spherical bearing having a spherical seat can be used.
[0025]
In the case of the configuration shown in FIGS. 7 and 8, in the guide mechanism 40, the link mechanism 41 guides the first ring 24 in the central axis direction of the first ring 24 and the radial direction of the first ring 24. Further, the first ring 24 is guided in the rotational direction centered on the radial direction of the first ring 24 by the rotational movement at the connecting portion 42. As a result, also in this guide mechanism 40, three degrees of freedom are secured as the moving direction of the first ring 24. In particular, in the guide mechanism 40, a plurality of degrees of freedom can be secured with a simple configuration by using the link mechanism 41 provided with the rotatable connecting portion 42.
[0026]
As described above, the preferred embodiments according to the present invention have been described with reference to the accompanying drawings, but the present invention is not limited to the examples. Various shapes, combinations, and the like of the constituent members shown in the above-described examples are examples, and various modifications can be made based on design requirements and the like without departing from the gist of the present invention.
[0027]
【The invention's effect】
As described above, according to the exhaust nozzle for a jet engine according to the present invention, the guide mechanism that guides the ring used for the operation of the plurality of flappers secures three degrees of freedom. Can be operated reliably. Further, the guide mechanism can be simply configured without using a dummy actuator, and the cost can be reduced.
[Brief description of the drawings]
FIG. 1 is a diagram schematically showing the overall configuration of an embodiment of an exhaust nozzle for a jet engine according to the present invention.
FIG. 2 is a schematic cross-sectional view in which an aperture / diverging portion of the exhaust nozzle of FIG. 1 is partially enlarged.
FIG. 3 is a diagram schematically showing a state in which a divergent flap is changed from an axially symmetric arrangement state to an asymmetric 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 as viewed in the axial direction of the ring.
6 is a view of the guide mechanism of FIG. 4 as viewed in the radial direction of the ring.
FIG. 7 is a view showing another example of the guide mechanism, as viewed in the axial direction of the ring.
8 is an enlarged view of a part of the guide mechanism of FIG. 7, where (a) is a view seen in the radial direction of the ring, and (b) is a cross-sectional view taken along line AA shown in FIG.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 10 Exhaust nozzle 11 Introduction duct 12 Restriction | divergence / divergence part 20 Convergent flap 21 Divergent flap 22 Link member 24 1st ring 23 1st actuator 25 Track rail 26 2nd actuator 27 2nd ring 30, 40 Guide mechanism 31 Groove 33 Guide Pin 34 Curved surface 36 Guide roller 41 Link mechanism 42 Connecting portion

Claims (1)

An exhaust nozzle for a jet engine comprising a plurality of flaps forming exhaust gas flow paths from the engine,
An annular ring connected to the plurality of flaps;
A plurality of actuators coupled to the ring and actuating the plurality of flaps through the ring;
A guide mechanism for guiding the movement of the ring,
The guide mechanism guides the ring in each of a central axis direction of the ring, a radial direction of the ring, and a rotation direction centered on the radial direction of the ring ,
The guide mechanism includes a member formed with a groove extending in the central axis direction of the ring, and at least a part of the guide mechanism is slidable in the groove extending direction inside the groove. An exhaust for a jet engine , comprising: a guide pin that is rotatably arranged; a member formed with a curved surface whose height changes in a radial direction of the ring; and a guide roller that contacts the curved surface. nozzle.

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