JP3074982B2 - Jet engine exhaust nozzle - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an exhaust nozzle of a jet engine.

[0002]

2. Description of the Related Art In recent years, a turbofan engine has been used for an aircraft cruising at a navigation speed of Mach number 2.5 to 5 from a stationary state on the ground to a low Mach number, and a flight speed of Mach number 3 or more. In Japan, a combined cycle engine using a ramjet engine is being studied.

In the operation of such a jet engine, not only the combustion efficiency in the combustor is improved, but also the thrust efficiency is improved by utilizing the combustion airflow (jet flow) in the exhaust nozzle disposed downstream of the combustor. It is known that can be improved. As an exhaust nozzle for utilizing the combustion airflow, a convergent / divergent (CD) nozzle having a structure shown in FIG. 7 is employed.

The exhaust nozzle 1 is formed in a duct shape having a rectangular cross section by a pair of fixed walls 2 facing each other at an interval, and a pair of movable flaps 3 arranged between them. The movable flap 3 is configured by connecting two flat convergent flaps 3a and a divergent flap 3b arranged along the flow direction of the combustion gas C so that the relative angle can be changed. Then, a driving means (not shown) such as a cylinder attached to each of the flaps 3a and 3b is operated, and the connecting portion 3c of the flaps 3a and 3b is used as a joint to change the relative angle to bend the combustion gas C.
The cross-sectional area can be changed along the flow direction.

When the exhaust nozzle 1 is configured as described above, the combustion gas C flowing through the exhaust nozzle 1 is accelerated to about the Mach number 1 by being once throttled by the throat portion S, and further diverged thereafter. As a result, the speed is increased to supersonic speed, and the thrust efficiency is improved. In addition, since the nozzle opening ratio that achieves the optimum thrust efficiency according to each navigation speed is realized, there is an advantage that high thrust efficiency can be obtained over a wide navigation speed range.

[0006]

When the body X equipped with the exhaust nozzle 1 configured as described above performs takeoff and landing, the discharge speed of the combustion gas C flowing through the exhaust nozzle is low. As shown by a solid line, the divergent flap 3b has a small inclination angle, and the opposing divergent flaps 3b are in a substantially parallel state to maintain the discharge speed of the combustion gas C, thereby maintaining the thrust of the body X. Done.

However, in the case of the exhaust nozzle 1, the thrust of the body X is maintained only by increasing the discharge speed of the combustion gas C flowing through the exhaust nozzle 1. There is a problem that the noise generated by the exhaust nozzle 1 increases when the body X is close to the ground.

Further, when taking off and landing of the airframe in a limited space, there is a demand for reducing the gliding distance at takeoff and the braking distance at landing, and it is conceivable to use the energy of the combustion gas discharged from the exhaust nozzle. ing.

The present invention has been made in view of the above circumstances, and can reduce noise while maintaining the thrust of the aircraft X during takeoff and landing, and can reduce the sliding distance and braking distance of the aircraft. It is intended to provide an exhaust nozzle for a jet engine.

[0010]

In order to achieve the above object, the present invention proposes the following four means. The first means includes an inner nozzle formed in a duct shape having a rectangular cross section by a pair of fixed walls arranged at intervals and a pair of movable flaps arranged between the fixed walls, and the inner nozzle. And an external nozzle which is disposed around and is moved in a longitudinal direction of the internal nozzle by a moving means,
The movable flap is composed of a convergent flap and a divergent flap that are connected to the flow direction of the combustion gas and change the inclination angle by the swinging means to change the flow area along the longitudinal direction of the internal nozzle. A duct having a rectangular cross-section formed by a pair of external walls in which an external nozzle is disposed outside the fixed wall, and a pair of external flaps attached to the external walls and disposed at intervals outside the movable flap. At the front end of the external nozzle, an external air intake which is opened / closed by the movement of the external nozzle and takes in external air into a gap with the internal nozzle is disposed, and an outer surface of the divergent flap is provided with the external flap. Mixing the outside air taken in from the outside air inlet located in the gap position with the combustion gas in the internal nozzle That the mixer is arranged, the mixer
Slides along the length of the divergent flap
And the external nozzle is moved backwards
The divergent flap
An exhaust nozzle is proposed for a jet engine in which sliding means are arranged at the ends . A second means proposes an exhaust nozzle of a jet engine in which a mixer is formed in a corrugated shape whose wave height increases rearward in a flow direction of combustion gas. The third means is that an external nozzle is
Part flap parallel to the axis of the divergent flap
Oscillating around the axis, while the external nozzle is
When positioned behind the internal nozzle,
External flap that swings the external flap to the position to close
Exhaust noise of jet engine provided with oscillating means
I suggest. The fourth means is to attach the rear of the internal nozzle
Slide the external nozzle in the direction of combustion gas flow.
An external nozzle swinging means for swinging in the direction of insertion is provided.
And it has proposed the exhaust nozzle of Jefferies Ttoenjin.

[0011]

According to the exhaust nozzle of a jet engine according to the first aspect of the present invention, the swing means is operated in the internal nozzle formed into a duct shape having a rectangular cross section by the fixed wall and the movable flap, and the converter is operated. By changing the swing angle of the gentle flap and the divergent flap, the internal nozzle is formed in a form suitable for each traveling speed. In supersonic cruising conditions, a large thrust can be obtained by narrowing the flow of combustion gas with a convergent flap and increasing the inclination angle of the divergent flap to diverge the flow of combustion gas and improve the flow velocity. become. At the time of takeoff and landing, the inclination angle of the divergent flap is reduced to increase the flow velocity of the combustion gas discharged from the internal nozzle as much as possible, and the moving means is operated to move the external nozzle behind the internal nozzle. Thus, the outer nozzle surrounded by the outer wall and the outer flap is disposed behind the inner nozzle, the outer air intake is opened, and the outer air flows into the exhaust nozzle from between the outer flap and the divergent flap. Will be incorporated. And
The introduced outside air is stirred and mixed with the combustion gas discharged from the internal nozzle by a mixer arranged between the external flap and the divergent flap, and the flow rate of the gas discharged from the external flap is increased. , The flow rate of which is reduced. During takeoff and landing, the outer nozzle is positioned behind the inner nozzle.
The sliding means is activated and the mixer
It is located at the rear end of the gentle flap. This allows fuel
The combustion gas and the outside air are agitated, and the
Is sucked and the flow rate of the gas mixture in the external nozzle is increased.
It becomes possible. According to the jet engine exhaust nozzle according to the second means, at the time of takeoff and landing, when the external nozzle is disposed behind the internal nozzle, the sliding means is operated and the mixer is disposed at the rear end of the divergent flap. You. Since the mixer is formed in a corrugated plate shape whose wave height increases toward the downstream in the flow direction of the combustion gas, the combustion gas circulated on the inner surface and the external air circulated on the outer surface are formed in adjacent irregularities. The combustion gas and the outside air are mixed alternately at the rear end. Thus, the combustion gas and the outside air are efficiently stirred, and the outside air is sucked into the combustion gas having a high flow velocity, so that the flow rate of the mixed gas in the external nozzle can be efficiently increased. According to the exhaust nozzle of a jet engine according to the third means, the outer
With the outer nozzle positioned behind the inner nozzle,
Activating the external flap swinging means allows the external
Is the axis parallel to the axis of the divergent flap
Swung around, the back of the internal nozzle is closed,
The combustion gas discharged from the internal nozzle is blocked
And The rearward movement of the external nozzle causes
Since the outside air intake is open at the front end of the nozzle,
The stopped combustion gas is deflected by the external flap and
It is jetted forward from the air intake. This allows the reverse
A thrust in the direction can be obtained. According to the jet engine exhaust nozzle according to the fourth means, at the time of takeoff and landing, etc.
The outer nozzle is located behind the inner nozzle
When the external nozzle swinging means is operated,
Nozzle oscillates in a direction that intersects the combustion gas flow direction
As a result, a bent exhaust nozzle is formed. This allows fuel
Deflection of the thrust direction by changing the direction of firing gas
Becomes possible.

[0012]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of an exhaust nozzle of a jet engine according to the present invention will be described below with reference to FIGS. In these figures, reference numeral 10 denotes an exhaust nozzle, 11 denotes a movable flap, 12 denotes an internal nozzle, 13 denotes an external nozzle, 14 denotes a convergent flap, 15 denotes a divergent flap, 16 denotes a first cylinder (oscillating means), 17 is a second cylinder (oscillation means), 18 is a mixer, 19 is a guide rail, 20 is sliding means, 21 is an external wall, 22 is an external flap, 22b is a motor (external flap oscillation means), and 23 is Moving means, 24 is an outside air intake, 25 is a guide rail, A is outside air, C is combustion gas, S
Is a throat part.

The exhaust nozzle 10 of the present embodiment is formed in a duct shape having a rectangular cross section by the fixed wall 2 arranged in a facing state at a parallel interval and a pair of movable flaps 11 arranged therebetween. Internal nozzle 12 and internal nozzle 1
And an external nozzle 13 arranged to surround the periphery of the second nozzle.

Each of the movable flaps 11 comprises a convergent flap 14 and a divergent flap 15 which is swingably connected to a rear end of the convergent flap 14.

The convergent flap 14 is provided at the front end thereof by a bracket 14a formed on the outer surface of the convergent flap 14 and a first cylinder 16 which is swingably connected to an engine body Y. It can be swung around the driving shaft 14b. On the other hand, the divergent flap 15 is provided at its front end by a second cylinder 17 which is swingably mounted between a bracket 15a formed on an outer surface thereof and a bracket 14c formed on an outer surface of the convergent flap 14. The swing shaft 15b is arranged to swing around the swing shaft 15b.

A mixer 18 is provided on the outer surface of the divergent flap 15. The mixer 18
Is a divergent flap 15 as shown in FIG.
Is formed in a flat shape along the outer surface of the divergent flap 15 on the front end side, and is formed in a corrugated plate shape in which the wave height increases from the front end side to the rear end side. The divergent flap 15 is slid in the longitudinal direction along a guide rail 19 formed on the outer surface of the divergent flap 15. The sliding means 20 for sliding the mixer 18 is, for example, a linear moving means comprising a motor 20a, a ball screw 20b and the like disposed in the divergent flap 15, and
The divergent flap 15 can be arranged at any position in the longitudinal direction of the divergent flap 15.

The external nozzle 13 is connected to the internal nozzle 1
An outer wall 21 slidably mounted on the outer surface of the second fixed wall 2 and an outer flap 22 mounted between the outer walls 21 and forming the outer nozzle 13 in a rectangular cross-sectional duct shape together with the outer wall 21. doing.

The outer wall 21 is slid along the longitudinal direction of the inner nozzle 12 by the moving means 23. The moving means 23 is provided with a cylindrical projection 23a provided on the outer surface of the fixed wall 2 of the inner nozzle 12 and a projection 23a provided on the inner surface of the outer wall 21 in a retracted state, and the sliding operation of the outer nozzle 13 is performed. Guide groove 23b for guiding
And a movable cylinder 23c swingably mounted between a front end of the outer wall 21 and a body X disposed in front of the outer wall 21. The moving cylinder 23c is arranged outside the pair of movable flaps 11, respectively, and by simultaneously extending, slides the projection 23a in the guide groove 23b to move the outer nozzle 13 behind the inner nozzle 12. The external nozzle 13 can be swung around the protrusion 23a by making the two movable cylinders 23c different in the amount of extension while being able to move.

The outer flap 22 is disposed outside the movable flap 11 of the inner nozzle 12 with a gap therebetween, and is disposed so as to close the gap of the outer wall 21. An outer nozzle 13 is formed around the outer nozzle 13 in a duct shape having a rectangular cross section larger than the inner nozzle 12. When the movable cylinder 23c is in a contracted state and the external nozzle 13 is disposed forward, the front end of the external flap 22 is disposed in close contact with the body X, and the movable cylinder 23c is extended to move the external nozzle 13 rearward. , An outside air intake 24 for taking in outside air A is opened between itself and the body X.

The outer flap 22 is attached to the outer wall 21 so as to be able to swing around a swing shaft 22a provided at the front end thereof. And the outer wall 21
Motor 2 incorporated inside and directly connected to swing shaft 22a
It can be swung by an actuator such as 2b. Further, the outer flap 22 is connected to an arc-shaped guide rail 25 provided on the inner surface of the outer wall 21.
The rear end is supported, and is held so that the swinging operation of the external flap 22 is not unstable due to the pressure of the combustion gas C. Also, the guide rail 2
5 is formed to the center position of the outer wall 21 so that the opposing outer flap 22 can contact the rear end at the center position.

The operation of the exhaust nozzle 10 configured as described above will be described below. First, when the airframe X is in a supersonic cruise state, the exhaust nozzle 10 has the form shown in FIG. That is, by extending the first cylinder 16, the convergent flap 14 is
Is inclined in such a manner as to reduce the flow path area of the internal nozzle 12 toward the rear in the flow direction, and a throat portion S is formed at the rear end. The divergent flap 15 connected to the rear end of the convergent flap 14 has an inclination angle for gradually expanding the flow area of the internal nozzle 12 rearward from the throat S by contraction of the second cylinder 17. Is set to As a result, the internal nozzle 12 having a large nozzle opening ratio is formed, and the thrust efficiency of the exhaust nozzle 10 in the supersonic cruising state is improved.

At this time, the mixer 18 is stored in the front of the divergent flap 15. In addition, the external flap 22 is
c are all in a contracted state, brought into contact with the body X disposed in front thereof, and the outside air intake 24 is closed,
By the operation of the motor 22b, the rear end of the divergent flap 15 is swung so as to be in contact with the rear end of the divergent flap 15. As a result, the turbulence of the airflow downstream of the exhaust nozzle 10 is reduced to a minimum, and the air resistance acting on the body X is reduced.

When the navigation speed is reduced from this state, the second cylinder 17 is extended, and the inclination angle of the divergent flap 15 is reduced so as to obtain an optimum nozzle opening ratio according to the navigation speed. With this,
The outer flap 22 is swung so that its rear end is in contact with the divergent flap 15. Then, when the cruising speed is further reduced and the body X is in the subsonic cruising state, as shown in FIG.
Is extended, and the inclination angle of the divergent flap 15 is set to 0 °. Thereby, the flow area of the internal nozzle 12 from the rear end of the convergent flap 14 to the rear end of the divergent flap 15 is kept constant,
The nozzle opening ratio becomes 1, the flow rate of the combustion gas C is maintained at a high value, and the thrust is maintained.

Next, when the aircraft X enters the landing position,
The inclination angle of the convergent flap 14 is reduced by contracting the first cylinder 16. Then, the second nozzle 17 is extended to form the internal nozzle 12 so that the divergent flap 15 is arranged in the same plane as the convergent flap 14. Thus, a form of the internal nozzle 12 is formed in which the flow area is slightly reduced toward the rear along the flow direction of the combustion gas C.

In addition to the above operation, the external flap 2
2, the external nozzle 13 is fully opened, and the movable cylinder 23c is fully extended to dispose the external nozzle 13 behind the internal nozzle 12. As a result, an outside air inlet 24 is opened between the front end of the outer flap 22 and the body X, and outside air A is passed from the outside air inlet 24 to the rear of the inner nozzle 12 through a gap between the inner nozzle 12 and the outer nozzle 13. Will be incorporated.

At this time, by simultaneously operating the sliding means 20, the mixer 18 housed in the front part of the divergent flap 15 is arranged so as to protrude from the rear end of the divergent flap 15. . As a result, the landing position of the exhaust nozzle 10 as shown in FIG.
A form will be formed. With the exhaust nozzle 10 formed in this manner, the combustion gas C flows through the inner surface of the mixer 18 protruding from the rear end of the divergent flap 15, while the outside air flows through the outer surface of the mixer 18. The outside air A introduced from the intake 24 is circulated.

Here, since the mixer 18 is formed in a corrugated plate shape whose wave height increases rearward, the combustion gas C flowing through the inner surface of the mixer 18 and the outside air A flowing through the outer surface are mixed. Are alternately circulated in adjacent wavy irregularities, and are mixed and stirred at the rear end of the mixer 18. In this case, since the flow rate of the combustion gas C is higher than the flow rate of the outside air A, the outside air A is sucked by the circulation of the combustion gas C,
The intake of the outside air A from the outside air inlet 24 is promoted, and the flow rate of the mixed gas of the combustion gas C and the outside air A in the outside nozzle 13 is efficiently increased.

By forming the exhaust nozzle 10 in such a form, the high-speed combustion gas C flowing through the internal nozzle 12 is supplied to the external nozzle 13 behind the internal nozzle 12.
Is released to the wide flow path area formed by the above, the flow velocity is reduced. As a result, noise that increases in proportion to the eighth power of the flow velocity is suppressed. Further, since the gas flowing out of the external nozzle 13 becomes a mixed gas of the outside air A and the combustion gas C introduced from the outside air inlet 24, the flow rate thereof can be increased, so that the gas is proportional to the product of the flow rate and the flow velocity. The increased thrust is offset by the increase in the flow rate and the decrease in the flow velocity, and is maintained at a constant level.

Such a configuration of the landing nozzle 10 in the landing position is also applied at the time of takeoff, so that noise can be reduced and thrust can be increased. In particular, during takeoff and landing, since the body X is close to the ground, the damage caused by the noise is large, and in this regard, the exhaust nozzle of the present embodiment can effectively solve the problem.

Further, when the airframe X using the exhaust nozzle 10 of the present embodiment takes off, the external nozzle 13
The movable cylinder 23c attached to the front end of the is extended and contracted as shown in FIG. That is, the moving cylinder 23c located above the internal nozzle 12 is further extended from the above-described takeoff posture of the exhaust nozzle 10, and conversely, the moving cylinder 23c located below the internal nozzle 12 is reduced. The outer nozzle 13 is supported by the fixed wall 2 of the inner nozzle 12 by storing a cylindrical projection 23a in a guide groove 23b formed on the inner surface of the outer wall 21. The rear opening is directed obliquely downward by the expansion and contraction.

By forming the form of the exhaust nozzle 10 in this manner, the mixed gas discharged from the external nozzle 13 is deflected obliquely downward, and a thrust is applied to the body X obliquely upward. Therefore, the fuselage X to which such a thrust is given can be quickly levitated, and the sliding distance can be reduced.

Further, when the body X has landed, the form of the exhaust nozzle 10 is configured as shown in FIG. In other words, by swinging the outer flap 22 from the landing attitude of the exhaust nozzle 10, the exhaust nozzle 10 is closed behind the internal nozzle 12, and the sliding means 20 is operated to move the mixer 18 to the divergent flap. Move to the front of 15. As a result, the combustion gas C discharged from the internal nozzle 12 is
2 and the outer flap 2
It is deflected in the direction of the outside air inlet 24 along 2 and is jetted forward from the outside air inlet 24. As a result, the outer flap 22 is pushed backward by the combustion gas C, and a reverse thrust acts on the body X via the moving cylinder 23c to which the outer flap 22 is attached.
The body X can be stopped at a short braking distance.

With the exhaust nozzle 10 of the jet engine configured as described above, the thrust efficiency in a wide speed range from subsonic cruise to supersonic cruise can be changed to an optimum form. Further, the outside air A can be efficiently taken into the combustion gas C during takeoff and landing, so that both noise prevention and thrust maintenance can be achieved. Further, the fuselage X equipped with the exhaust nozzle 10 has an effect that the sliding distance at takeoff and the braking distance at landing can be shortened.

<Other Embodiments> The following technology can be adopted for the exhaust nozzle 10 of the jet engine according to the present invention. The guide groove 23b is provided on the inner surface of the outer wall 21 of the outer nozzle 13, and the protrusion 23a is provided on the outer surface of the fixed wall 2 of the inner nozzle 12. Instead, the protrusion 23a is provided on the inner surface of the outer wall 21 and the outer surface of the fixed wall 2. The guide groove 23b. Although the motor 22b is used as the external flap swinging means, another arbitrary actuator may be used instead. The sliding means 20 for sliding the mixer 18 is connected to the motor 2
Although the linear moving mechanism includes the linear motion mechanism composed of the ball screw 20a and the ball screw 20b, another linear moving mechanism such as a cylinder or a linear motor may be used instead. Cylinders 16 and 17 are used as swing means for the convergent flap 14 and the divergent flap 15.
However, instead of this, an arbitrary actuator should be adopted.

[0035]

As described in detail above, the exhaust nozzle of the jet engine according to the first means of the present invention has a structure in which a fixed wall and a movable flap surround an internal nozzle formed in a duct shape having a rectangular cross section. In addition, an external nozzle that is moved in the longitudinal direction of the internal nozzle by the moving means is provided, and the movable flap includes a convergent flap and a divergent flap that changes a flow path area along the longitudinal direction of the internal nozzle. It is formed in a duct shape having a rectangular cross section by the outer wall and the outer flap,
At the front end, an outside air intake which is opened and closed by the movement and takes in outside air into the gap with the internal nozzle is provided, and a mixer for mixing the introduced outside air with the combustion gas in the internal nozzle is provided on the outer surface of the divergent flap. And the mixer is positioned such that the divergent flaps
Slidably mounted along the direction
When the mixer is moved to
A sliding means is provided at the rear end of the toflap.
Since that, the following effects. Since the movable flap can be swung in accordance with the navigation speed to achieve an optimal nozzle opening ratio, good thrust efficiency can be achieved over a wide navigation speed range. The external nozzle is located behind the internal nozzle, and the external air taken in from the external air intake is mixed with the combustion gas from the internal nozzle via a mixer, reducing the flow velocity of the gas discharged from the exhaust nozzle and reducing noise. In addition, it is possible to avoid a decrease in thrust by increasing the flow rate. Die the mixer as needed
Slide along the longitudinal direction of the bargent flap.
Can be. According to the exhaust nozzle of a jet engine according to the second aspect, the mixer, in <br/> of being formed on the corrugated shape to increase the wave height toward the flow direction behind the combustion gases, first means In addition to the effects described above, the outside air can be efficiently taken in by using the mixer to suck the outside air into the combustion gas, and the thrust during takeoff and landing can be improved. According to the exhaust nozzle of a jet engine according to the third means, the external nozzle to close the rear of the internal nozzle
External flap swing means for swinging the external flap to the position
Is provided, so that the external flap swing means during landing
Activate and place the outer flap behind the inner nozzle
Reverse thrust is generated by blocking the flow of combustion gas
As a result, the braking distance can be shortened. According to the exhaust nozzle of the jet engine according to the fourth means, the internal nozzle
The external nozzle, which is slid to the rear of the
External nozzle oscillating means for oscillating in the direction intersecting the through direction
, The external nozzle swinging means is activated.
The rear end opening of the external nozzle
The flow direction of the burning gas is deflected downward, and the
The running distance can be reduced.

[Brief description of the drawings]

FIG. 1 is a longitudinal sectional view showing one embodiment of an exhaust nozzle of a jet engine according to the present invention and showing a supersonic cruising state of an airframe.

FIG. 2 is a longitudinal sectional view showing a subsonic cruise state of the exhaust nozzle of FIG. 1;

FIG. 3 is a longitudinal sectional view showing a state of the exhaust nozzle of FIG. 1 at the time of takeoff and landing.

FIG. 4 is a perspective view showing a mixer mounted on a divergent flap of the exhaust nozzle of FIG. 1;

FIG. 5 is a longitudinal sectional view showing a state in which an external nozzle of the exhaust nozzle of FIG. 1 is swung.

FIG. 6 is a longitudinal sectional view showing a state in which an outer flap of the exhaust nozzle of FIG. 1 closes a rear side of an inner nozzle.

FIG. 7 is a schematic view showing a conventional example of an exhaust nozzle of a jet engine.

[Explanation of symbols]

 2 Fixed Wall 10 Exhaust Nozzle 11 Movable Flap 12 Internal Nozzle 13 External Nozzle 14 Convergent Flap 15 Divergent Flap 16 First Cylinder (Swinging Means) 17 Second Cylinder (Swinging Means) 18 Mixer 20 Sliding Means 21 External wall 22 External flap 23 Moving means 22b Motor (external flap swinging means) 24 External air intake A External air C Combustion gas X Body Y Engine body

Continuation of the front page (56) References JP-A-59-554 (JP, A) JP-A-63-162955 (JP, A) US Patent 4,502,637 (US, A) (58) Fields investigated (Int. ⁷ , DB name) F02K 1/08-1/12 F02K 1/28 F02K 1/36-1/38 F02K 1/46-1/48

Claims (4)

(57) [Claims] 1. A pair of fixed walls arranged at intervals,
An inner nozzle formed in a duct shape having a rectangular cross section by a pair of movable flaps arranged in a facing state therebetween, and an outer nozzle arranged around the inner nozzle and moved in a longitudinal direction of the inner nozzle by a moving means. A convergent flap and a diver, wherein the movable flap is connected to the flow direction of the combustion gas, and the tilt angle is changed by the swinging means to change the flow path area along the longitudinal direction of the internal nozzle. A pair of external flaps disposed outside the fixed wall, and a pair of external flaps respectively attached to the external wall and disposed at an interval outside the movable flap. The outer nozzle is formed in a duct shape having a rectangular cross-section. An outside air intake is provided which is opened and closed to take in outside air into a gap between the inside nozzle and the outside surface of the divergent flap, and is disposed at a gap position between the outside flap and outside air taken in from the outside air intake. A mixer for mixing the combustion gas in the nozzle is provided , and the mixer is a divergent mixer.
Attached slidably along the length of the wrap,
When the head nozzle is moved backward, the mixer is turned off.
Sliding means arranged at the rear end of the divergent flap
An exhaust nozzle for a jet engine, wherein the nozzle is disposed . 2. A mixer, exhaust nozzle of a jet engine according to claim 1, characterized in that it is formed in the corrugated shape to increase the wave height toward the flow direction behind the combustion gases. 3. A diver with an external flap attached to an external nozzle.
Swing around an axis parallel to the axis of the gentle flap
And the outer nozzle is located behind the inner nozzle.
When the external nozzle is closed,
An external flap swinging means for swinging the wrap is provided.
Exhaust nozzle of claim 1 or jet engine according to claim 2, characterized in that there. 4. An external slide slid behind the internal nozzle.
The nozzle is swung in a direction that intersects the combustion gas flow direction.
The exhaust nozzle of a jet engine according to any one of claims 1 to 3, further comprising an external nozzle swing means for causing the nozzle to swing .