JP3163840B2 - Two-dimensional 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 a two-dimensional exhaust nozzle.

[0002]

2. Description of the Related Art In recent years, it has been proposed to use a two-dimensional exhaust nozzle in order to improve the maneuverability of an aircraft.

FIG. 7 to FIG. 10 show an example of a two-dimensional exhaust nozzle, wherein 1 is a duct, 2 is a nozzle inlet member, and the front A side end of the nozzle inlet member 2 is on the rear B side of the duct 1. The duct 1 is connected to a gas turbine engine (not shown).

The nozzle inlet member 2 has a substantially circular cross section at the front A side end and a substantially rectangular cross section at the rear B side end.

[0005] Reference numeral 3 denotes a pair of left and right nozzle side walls, and the base ends of the nozzle side walls 3 are fixed to the left and right side walls of the nozzle inlet member 2.

Reference numerals 4a and 4b denote a pair of upper and lower support brackets. The support bracket 4a has a space 5a formed between the left and right nozzle side walls 3 and the upper end on the rear B side of the nozzle inlet member 2. And both ends are fixed to the nozzle side wall 3, respectively, and the support bracket 4 b is provided in a space between the left and right nozzle side walls 3 and a lower end on the rear B side of the nozzle inlet member 2. 5b are formed and both ends are fixed to the nozzle side wall 3, respectively.

The left and right nozzle side walls 3a and 6b are arranged so that the front end faces the front A side and the base end faces the rear B side.
It is a pair of upper and lower reverse flaps arranged between them.

The reverse flap 6a is pivotally supported by a portion of the support bracket 4a closer to the front A side via a reverse flap rotating shaft 7a whose base end extends in the left-right direction of the nozzle inlet member 2. The base 6b is pivotally supported by a portion of the support bracket 4b closer to the front A side via a reverse flap rotation shaft 7b substantially parallel to the reverse flap rotation shaft 7a.

The reverse flaps 6a and 6b are fixed to the reverse flap rotation shafts 7a and 7b, respectively. When the reverse flap rotation shafts 7a and 7b are rotated to predetermined positions, the tips of the reverse flaps 6a and 6b are nozzles. The rear end of the inlet member 2 faces the rear B side.

Reference numerals 8a and 8b denote a pair of upper and lower convergent flaps disposed between the left and right nozzle side walls 3 so that the base end faces the front A side and the front end faces the rear B side.

The convergent flap 8a is pivotally supported on a portion near the rear B side of the support bracket 4a via a convergent flap rotation shaft 9a whose base end is substantially parallel to the reverse flap rotation shaft 7a. Also, the convergent flap 8b pivots to a portion closer to the rear B side of the support bracket 4b via a convergent flap rotation shaft 9b whose base end is substantially parallel to the reverse flap rotation shaft 7a. Supported.

The convergent flaps 8a and 8b are fixed to the convergent flap rotation shafts 9a and 9b, respectively.
When the b is rotated, the convergent flaps 8a and 8b
Angle is changed.

Reference numerals 10a and 10b denote a pair of upper and lower divergent flaps disposed between the left and right nozzle side walls 3 such that a base end faces the front A side and a front end faces the rear B side.

The divergent flap 10a is pivotally supported at the distal end of the convergent flap 8a via a divergent flap support shaft 11a whose base end is substantially parallel to the reverse flap rotation shaft 7a.
The divergent flap 10b is pivotally supported at the distal end of the convergent flap 8b via a divergent flap support shaft 11b whose base end is substantially parallel to the reverse flap rotation shaft 7a.

In the two-dimensional exhaust nozzle described above, the left and right nozzle side walls 3, the upper and lower support brackets 4a and 4b, the upper and lower reverse flaps 6a and 6b, the upper and lower convergence flaps 8a and 8b, and the upper and lower divergent An exhaust passage 12 is formed by the flaps 10a and 10b.

In FIGS. 7 to 10, 13a,
13b is a thrust reverser provided in the spaces 5a and 5b, 1
Reference numeral 4 denotes exhaust flowing from a gas turbine engine (not shown) into the two-dimensional exhaust nozzle.

When performing a normal flight on an aircraft having a two-dimensional exhaust nozzle mounted on a gas turbine engine,
As shown in FIG. 7, the reverse flap rotation shafts 7a, 7b
Is rotated so that the distal ends of the reverse flaps 6a and 6b face the rear B-side end of the nozzle inlet member 2, and the reverse flaps 6a and 6b allow the exhaust passage 12 and the two-dimensional exhaust through the spaces 5a and 5b. Block communication with the outside of the nozzle.

Also, the convergent flap rotation shaft 9
a, 9b are rotated to make the convergent flaps 8a,
8b are brought close to each other so as to maintain a predetermined interval, and the left and right nozzle side walls 3 and the convergence flap 8
The cross-sectional area of the exhaust passage 12 formed by a and 8b gradually decreases as it goes toward the rear B side.

Further, the divergent flaps 10a,
10b is positioned to hold it at an angle that results in ideal expansion.

In such a normal flight state, the exhaust gas 14 flowing from the gas turbine engine (not shown) into the exhaust passage 12 of the two-dimensional exhaust nozzle is supplied to the convergent flaps 8a and 8b and the divergent flap 10
After being accelerated between a and 10b, the fuel is injected toward the outside of the rear B side of the two-dimensional exhaust nozzle.

On the other hand, when operating the afterburner of the gas turbine engine, as shown in FIG. 8, the convergent flap rotating shafts 9a and 9b are rotated to make the convergent flaps 8a and 9b as compared with the state shown in FIG. The divergent flaps 10a and 10b are positioned so as to be kept at an angle that allows the divergent flaps 10a and 10b to be ideally expanded, while separating the tip ends of the divergent flaps 8b from each other so as to increase the interval between the distal ends of the fins 8b.

When an afterburner (not shown) of the turbine engine is operated in such an afterburner operating state, a large amount of exhaust gas generated by combustion in the afterburner generates convergent flaps 8a and 8b.
The air flows between the divergent flaps 10a and 10b and is injected toward the outside of the rear B side of the two-dimensional exhaust nozzle.

When deflecting the angle of the exhaust injection direction with respect to the center line of the two-dimensional exhaust nozzle, as shown in FIG. 9, the distal ends of the divergent flaps 10a and 10b face the direction in which the exhaust is to be injected. The divergent flaps 10a and 10b are displaced as described above.

In such an exhaust injection angle deflected state, the exhaust gas 14 flowing from the gas turbine engine into the exhaust passage 12 of the two-dimensional exhaust nozzle is accelerated by the convergent flaps 8a and 8b and then accelerated by the divergent flap 10a. Divergent flaps 10 flowing between the two-dimensional exhaust nozzle and the outside of the rear B side of the two-dimensional exhaust nozzle.
a and 10b are injected in the inclination direction.

Further, when performing the reverse injection operation, FIG.
7, the reverse flap rotating shafts 7 a and 7 b are rotated to displace the distal end of the reverse flap 6 a upward and the distal end of the reverse flap 6 b downward from the state shown in FIGS. 7 to 9. The exhaust passage 12 communicates with the outside of the two-dimensional exhaust nozzle through the spaces 5a and 5b.

At the same time, the convergent flap rotation shafts 9a and 9b are rotated to bring the tip portions of the convergent flaps 8a and 8b into contact with each other, and are formed by the left and right nozzle side walls 3 and the convergent flaps 8a and 8b. The rear B side end of the exhaust passage 12 to be closed is closed.

In such a reverse injection operation state, the exhaust passage 1 of the two-dimensional exhaust nozzle is supplied from the gas turbine engine.
Exhaust 14 flowing into 2 is injected toward the front A side by thrust reversers 13a and 13b via spaces 5a and 5b.

[0028]

In the two-dimensional exhaust nozzle described above, as shown in FIGS. 7 to 10, the reverse flaps 6a and 6b, the convergent flaps 8a and
8b, in order to displace the divergent flaps 10a and 10b, an actuator for simultaneously displacing the upper and lower reverse flaps 6a and 6b, an actuator for simultaneously displacing the upper and lower convergent flaps 8a and 8b, and an upper divergent flap 10a And an actuator that independently displaces the lower divergent flap 10b.

[0029] For this reason, the two-dimensional exhaust nozzle has the characteristic that the maneuverability of the aircraft can be improved, but also requires four sets of actuators, so that the weight increases and time is required for inspection and maintenance. There is a problem.

An object of the present invention is to provide a two-dimensional exhaust nozzle that is lightweight and easy to inspect and maintain.

[0031]

In order to achieve the above object, in a two-dimensional exhaust nozzle according to the present invention, a pair of substantially parallel nozzle side walls whose front A sides are fixed to left and right side walls of a nozzle inlet member 2 are provided. Spaces 5a and 5b are respectively formed between the nozzle side walls 3 and 3 and upper and lower ends between the nozzle side walls 3 and 3 so as to form spaces 5a and 5b. A pair of upper and lower support brackets 4a and 4b fixed to the nozzle side walls 3 and 3 are disposed between the nozzle side walls 3 and 3 so that their base ends face the rear B side, and the base ends are the aforementioned. A pair of upper and lower reverse flaps 6a, 6b pivotally supported on the support brackets 4a, 4b by reverse flap rotation shafts 7a, 7b extending from one nozzle side wall 3 to the other nozzle side wall 3, and the base ends thereof are forward. A side Wherein both the nozzle side wall 3 moves easily,
3 and a base end of each support bracket 4
a pair of upper and lower convergent flaps 8a, 8 pivotally supported by the convergent flap rotation shafts 9a, 9b substantially parallel to the reverse flap rotation shafts 7a, 7b.
b and a divergent flap support which is arranged between the nozzle side walls 3 and 3 so that the base end faces forward A, and whose base end is substantially parallel to the reverse flap rotation shafts 7a and 7b. A pair of upper and lower divergent flaps 10a, 10b pivotally supported at the distal ends of the convergent flaps 8a, 8b via shafts 11a, 11b, and the two nozzle side walls 3, 3 and the support brackets 4a, 4b. And the reverse flaps 6a and 6b, the convergent flaps 8a and 8b, and the divergent flaps 10a and 10b form an exhaust passage 12 extending from the front A side to the rear B side.
6b is rotated about the reverse flap rotation shafts 7a and 7b, so that the exhaust passage 12 and the spaces 5a and 5b
And a connector 17 attached to the nozzle side wall 3 so as to be able to move in the front-rear direction, and one end of the connector 17 is connected to the convergent flaps 8a and 8b. A pair of upper and lower convergent flap links 19a, 19b fixed to each other, and a pair of upper and lower convergent members each having one end pivotally supported by the connector 17 and the other end pivotally supported by the other end of the convergent flap links 19a, 19b. Gent flap drive links 28a, 28b and a pair of upper and lower reverse flap links 18 each having one end fixed to the aforementioned reverse flaps 6a, 6b.
a, 18b, and a pair of upper and lower reverse flap drive links 23a, 23 each having one end pivotally supported by the connector 17.
a pair of upper and lower guide links 25a, 25b each having one end pivotally supported by the other end of the reverse flap drive link 23a, 23b and the other end pivotally supported by the other end of the reverse flap link 18a, 18b. A first actuator 36 for displacing the connector 17 back and forth,
The upper and lower divergent flaps 10a, 10b
And third actuators 39a, 39 for rotating the shafts about the divergent flap support shafts 11a, 11b.
9b and the pivot point between the guide links 25a, 25b and the reverse flap drive links 23a, 23b when the connector 17 is displaced from the front A side to the rear B side from the center side of the exhaust passage 12 to the outside. And a pair of upper and lower guide members 21a and 21b for guiding the convergent flaps 8a and 8b when the connector 17 is displaced from the rear B side to the front A side. The shape of the drive links 28a, 28b is determined, and both the convergent flaps 8a, 8
b at the time when the tip ends of the two reverse flaps 6
The shapes of the guide links 25a, 25b and the guide members 21a, 21b are determined so that the exhaust passage 12 and the spaces 5a, 5b communicate with each other by rotating the a, 6b.

[0032]

The first and second convergent flaps 8a and 8b and the two reverse flaps 6a and 6b are connected to the first actuator 3.
6 and one divergent flap 10
Since a is operated by the second actuator 39a and the other divergent flap 10b is operated by the third actuator 39b, it is possible to reduce the weight of the two-dimensional exhaust nozzle and the time required for inspection and maintenance. .

[0033]

Embodiments of the present invention will be described below with reference to the drawings.

FIGS. 1 to 6 show an embodiment of the two-dimensional exhaust nozzle of the present invention. The basic structure of the two-dimensional exhaust nozzle of this embodiment is substantially the same as that shown in FIGS. 7 to 10. , And portions denoted by the same reference numerals as those in FIGS. 7 to 10 represent the same components.

Reference numeral 15 denotes a guide member.
Reference numeral 5 is fixed to an outer portion of the nozzle side wall 3.

A guide groove 16 provided on the guide member 15 and extending from the front A side to the rear B side is provided with the guide groove 16.
The connector 17 is attached so that it can move along.

Reference numerals 19a and 19b denote a pair of upper and lower convergent flap links. One ends of the convergent flap links 19a and 19b are ends of convergent flap rotation shafts 9a and 9b supporting the convergent flaps 8a and 8b, respectively. It is fixed to the part.

Reference numerals 28a and 28b denote a pair of upper and lower convergent flap drive links. One ends of the convergent flap drive links 28a and 28b are pivotally supported by the connector 17 by pins 29a and 29b, respectively. Link 28a,
The other end of 28b is pivotally supported on the other end of the convergent flap links 19a, 19b by pins 30a, 30b, respectively.

When the connector 17 is displaced toward the front A-side end or the rear B-side end of the guide member 15, the convergent flaps 8a and 8b Is rotated so that the distal ends of the convergent flaps 8a and 8b can be gradually moved toward and away from each other.

That is, as shown in FIG.
Is displaced to the rear B side end of the guide member 15, the convergent flaps 8a and 8b are set to the afterburner operating state (see FIG. 8), and the connector 17 is connected to the guide member 15 as shown in FIG. When the convergent flaps 8a and 8b are located at a substantially middle position in the front-rear direction, the two convergent flaps 8a and 8b are set to a normal flight state (see FIG. 7). Further, as shown in FIG. When displaced, both convergent flaps 8a,
8b is set to the reverse injection operation state (see FIG. 10).

Reference numerals 18a and 18b denote a pair of upper and lower reverse flap links.
One end of 18b is fixed to the end of the reverse flap rotation shafts 7a, 7b that support the reverse flaps 6a, 6b, respectively.

Reference numerals 23a and 23b denote a pair of upper and lower reverse flap drive links. One ends of the reverse flap drive links 23a and 23b are pivotally supported by the connector 17 by pins 24a and 24b, respectively.

Reference numerals 25a and 25b denote a pair of upper and lower guide links. One end of each of the guide links 25a and 25b is pivotally supported by the other ends of the reverse flap drive links 23a and 23b by pins 26a and 26b, respectively. The other end of each of the links 25a and 25b is a pin 27.
a, 27b, the reverse flap link 18
a, 18b pivotally supported at the other end.

Reference numerals 21a and 21b denote a pair of upper and lower guide members. The guide members 21a and 21b are fixed to the nozzle side wall 3 so as to be located above and below the guide member 15, respectively.

The guide members 21a, 21b have guide grooves 22a, 22 which extend in the up-down direction and are bent so that the middle part in the up-down direction projects toward the front A side with respect to the upper and lower ends.
b are provided, and the pins 26a and 26b are fitted into the guide grooves 22a and 22b so as to be movable along the guide grooves 22a and 22b.

As shown in FIG. 6, the shape of the guide groove 22a from the lower end portion to the intermediate portion is such that the reverse flap 6a is in a normal flight state (see FIGS. 1 and 7) and an afterburner operating state (see FIGS. 1 and 7). When the pin 26a moves from the lower end to the middle of the guide groove 22a in the exhaust angle deflected state (see FIGS. 3 and 9), the guide link is set. 25a is formed in a substantially arc shape centering on the pin 27a so that it can rotate about the pin 27a.

Further, the shape of the guide groove 22a from the middle part to the upper end part is such that when the pin 26a moves from the middle part to the upper end part of the guide groove 22a, the guide link is accompanied by the displacement of the pin 26a. 25a is the reverse flap 6a
Is formed substantially linearly so as to be gradually displaced to the reverse injection state (see FIGS. 4 and 10).

Similarly, the shape between the upper end portion and the middle portion of the guide groove 22b is such that when the reverse flap 6b is set to the normal flight state, the afterburner operating state, and the exhaust injection angle deflected state, 26b is the guide groove 2
The guide link 25b is formed in a substantially arc shape centering on the pin 27b so that the guide link 25b can rotate about the pin 27b when moving between the upper end portion and the middle portion of the 2b.

Further, the shape of the guide groove 22b from the intermediate portion to the lower end portion is such that when the pin 26b moves from the intermediate portion to the lower end portion of the guide groove 22b, the guide link is moved in accordance with the displacement of the pin 26b. 25b is reverse flap 6b
Is formed in a substantially straight line so as to be gradually displaced to the reverse injection state.

Reference numerals 20a and 20b denote a pair of upper and lower divergent flap eye plates. The divergent flap eye plate 20a is fixed to the upper surface of the divergent flap 10a. The divergent flap eye plate 20b is connected to the divergent flap 10b. It is fixed to the lower surface.

Reference numerals 31a and 31b denote a pair of upper and lower divergent flap drive links. One end of each of the divergent flap drive links 31a and 31b is pivotally connected to the convergent flap rotation shafts 9a and 9b, respectively. Divergent flap drive link 31
a, 31b and convergent flap rotation shafts 9a, 9
No torque is transmitted to b.

Reference numerals 32a and 32b denote a pair of upper and lower divergent flap support links. One end of each of the divergent flap support links 32a and 32b is a distal end of the divergent flap drive link 31a or 31b by a pin 33a or 33b, respectively. A divergent flap support link 32a,
The other end of the divergent flap eye plate 20a,
20b, divergent flap 1
Parallel link mechanisms 35a and 35b are formed by the reference flaps 0a and 10b, the convergent flaps 8a and 8b, the divergent flap drive links 31a and 31b, and the divergent flap support links 32a and 32b.

Since the divergent flap drive links 31a and 31b are not affected by the rotation of the convergent flap rotation shafts 9a and 9b, the angle of the divergent flap drive links 31a and 31b is increased. As long as the angle does not change, the angles of the convergent flaps 8a and 8b
The angle of the divergent flaps 10a and 10b is maintained at a constant angle even if it changes as shown in FIGS. 7, 8, and 10.

Reference numeral 36 denotes a first actuator. The first actuator 36 has a piston rod 37 projecting backward B.

The cylinder body 38 of the first actuator 36 is fixed to the nozzle side wall 3 and the tip of a piston rod 37 is connected to the connector 17.

Reference numeral 39a denotes a second actuator. The second actuator 39a has a piston rod 40a projecting backward B and the cylinder body 41a is positioned above the first actuator 36. It is fixed to the nozzle side wall 3.

Reference numeral 39b denotes a third actuator. The third actuator 39b has a piston rod 40b protruding backward B and the cylinder body 41b is positioned below the first actuator 36. It is fixed to the nozzle side wall 3.

Reference numerals 42a and 42b denote a pair of upper and lower bell cranks having a substantially L-shape.
The bent portion 2b is pivotally supported on the nozzle side wall 3 by pins 43a and 43b, respectively, so as to be located on the front upper side and the front lower side of the guide member 15, respectively.

Reference numerals 44a and 44b denote a pair of upper and lower first intermediate links. One ends of the first intermediate links 44a and 44b are pivotally supported by the pins 45a and 45b, respectively, at the distal ends of the piston rods 40a and 40b. And the first
The other ends of the intermediate links 44a and 44b are
6a and 46b, the bell cranks 42a and 42
b is pivotally supported at one end.

Numerals 47a and 47b denote a pair of upper and lower second intermediate links. One ends of the second intermediate links 47a and 47b are pivotally connected to the other ends of the bell cranks 42a and 42b by pins 48a and 48b, respectively. The other ends of the second intermediate links 47a and 47b are
The divergent flap drive links 31a and 31b are pivotally supported by the other ends a and 49b.

The guide blocks 50a and 50b are fixed to the nozzle side wall 3 so as to be located above and below the guide member 15, respectively, and are connected to the piston rods 40a and 50b. 40b
Has come to support.

Hereinafter, the operation of this embodiment will be described.

In an aircraft in which the two-dimensional exhaust nozzle shown in FIGS. 1 to 6 is mounted on a gas turbine engine, when performing a normal flight, the first actuator 36 is operated to operate the guide member as shown in FIG. The connector 17 is positioned at the intermediate portion of the front and back 15 in the front-rear direction, and the convergent flaps 8 are connected via the convergent flap drive links 28a and 28b, the convergent flap links 19a and 19b, and the convergent flap rotating shafts 9a and 9b.
a and 8b are set to the normal flight state (see FIG. 7), and the second actuator 39a and the third actuator 39b are operated to operate the first intermediate links 44a and 4b.
4b, the bell cranks 42a and 42b, the second intermediate links 47a and 47b, the parallel link mechanisms 35a and 35b, and the divergent flaps 10a and 10b are set to the normal flight state via the divergent flap eye plates 20a and 20b.

At this time, the pins 26a and 26b are located substantially at the middle of the guide grooves 22a and 22b of the guide members 21a and 21b, and the reverse flaps 6a and 6b are set to the normal flight state.

On the other hand, when operating the afterburner of the gas turbine engine, the first actuator 36 is operated to position the connector 17 at the rear B side end of the guide member 15 as shown in FIG. The two convergent flaps 8 are connected via flap drive links 28a and 28b, convergent flap links 19a and 19b, and convergent flap rotating shafts 9a and 9b.
a, 8b are set to the afterburner operating flight state (see FIG. 8).

At this time, the divergent flap drive links 31a and 31b are not affected by the rotation of the convergent flap rotation shafts 9a and 9b, and the divergent flaps 10a and 10b are set in the afterburner operating flight state.

The reverse flap drive link 23
a, 23b and the pins 26a, 26b connecting the guide links 25a, 25b are connected to the reverse flap drive link 2
The guide grooves 25a and 22b move toward the center of the exhaust passage with the displacement of the guide links 25a and 25b.
Rotates about the pins 27a and 27b without displacing the reverse flap links 18a and 18b.

When deflecting the angle of the exhaust injection direction with respect to the center line of the two-dimensional exhaust nozzle, the state shown in FIG.
Second actuator 39a, third actuator 3
9b to operate the first intermediate link 4 as shown in FIG.
4a, 44b, bell cranks 42a, 42b, second intermediate links 47a, 47b, parallel link mechanisms 35a, 35
b, divergent flap eye plate 20a, 2
0b, both divergent flaps 10a, 10
b, as shown in FIG. 9, the divergent flap 1
It is set so that the tips of 0a and 10b face the direction in which exhaust gas is to be injected.

Further, when performing the reverse injection operation, the first actuator 36 is operated to be positioned at the front A side end of the guide member 15 as shown in FIG. 4, and the convergent flap drive links 28a, 28b The two convergent flaps 8a and 8b are set to the reverse injection operation state (see FIG. 10) via the convergent flap links 19a and 19b and the convergent flap rotation shafts 9a and 9b.

At this time, the reverse flap drive link 2
The pins 26a, 26b connecting the guide flaps 3a, 23b and the guide links 25a, 25b are provided with guide grooves 22a, 22b in accordance with the displacement of the reverse flap drive links 23a, 23b.
Move toward the outside of the exhaust passage of the guide link 25a,
25b, the reverse flap links 18a, 18b are displaced, and the reverse flap links 18a, 18b,
The reverse flaps 6a, 6b are set to the reverse injection operation state via the reverse flap rotation shafts 7a, 7b.

As described above, in this embodiment, the reverse flaps 6a and 6b and the convergent flap 8 are constituted by three sets of the first actuator 36, the second actuator 39a and the third actuator 39b.
By operating the divergent flaps 10a and 10b and the divergent flaps 10a and 10b, the weight of the two-dimensional exhaust nozzle can be reduced and the time required for inspection and maintenance of the two-dimensional exhaust nozzle can be reduced.

Note that the two-dimensional exhaust nozzle of the present invention is not limited to the above-described embodiment, but the shape of each member constituting the two-dimensional exhaust nozzle may be appropriately changed. Of course, various changes can be made without departing from the scope.

[0073]

As described above, in the two-dimensional exhaust nozzle of the present invention, the first actuator 36 operates both the convergent flaps 8a and 8b and the two reverse flaps 6a and 6b, and the second actuator 39
a to operate one divergent flap 10a and the third actuator 39b to operate the other divergent flap 10b, so that the weight of the two-dimensional exhaust nozzle can be reduced and the two-dimensional exhaust nozzle can be inspected and maintained. An excellent effect that the required time can be shortened can be obtained.

[Brief description of the drawings]

FIG. 1 is a side view showing a normal flight state in one embodiment of a two-dimensional exhaust nozzle of the present invention.

FIG. 2 is a side view showing an afterburner operating state in one embodiment of the two-dimensional exhaust nozzle of the present invention.

FIG. 3 is a side view showing an exhaust angle deviation state in one embodiment of the two-dimensional exhaust nozzle of the present invention.

FIG. 4 is a side view showing a reverse injection operation state in one embodiment of the two-dimensional exhaust nozzle of the present invention.

FIG. 5 is a partially cutaway perspective view showing an embodiment of the two-dimensional exhaust nozzle of the present invention.

FIG. 6 is a partial view showing a relationship between a guide member and a guide link shown in FIGS. 1 to 5;

FIG. 7 is a longitudinal sectional view showing a normal flight state in an example of a two-dimensional exhaust nozzle.

FIG. 8 is a longitudinal sectional view showing an afterburner operating state in an example of a two-dimensional exhaust nozzle.

FIG. 9 is a longitudinal sectional view showing an example of a two-dimensional exhaust nozzle in a state where an exhaust angle is deflected.

FIG. 10 is a longitudinal sectional view showing a reverse injection operation state in an example of a two-dimensional exhaust nozzle.

[Explanation of symbols]

2 Nozzle inlet member 3 Nozzle side wall 4a, 4b Support bracket 5a, 5b Space 6a, 6b Reverse flap 7a, 7b Reverse flap rotation axis 8a, 8b Convergent flap 9a, 9b Convergent flap rotation axis 10a, 10b Divergent flap 11a, 11b Divergent flap support shaft 12 Exhaust flow path 18a, 18b Reverse flap link 19a, 19b Convergent flap link 21a, 21b Guide member 23a, 23b Reverse flap drive link 25a, 25b Guide link 28a, 28b Convergent flap drive link 36 first actuator 39a second actuator 39b third actuator A front B rear

──────────────────────────────────────────────────続 き Continued on the front page (58) Field surveyed (Int.Cl. ⁷ , DB name) F02K 1/12 F02K 1/15

Claims (1)

(57) [Claims] 1. A pair of substantially parallel nozzle side walls (3), (3) having front A side portions fixed to left and right side wall portions of a nozzle inlet member (2), and both nozzle side walls (3), (3). Spaces (5a) and (5b) are respectively formed between the upper and lower ends of the nozzle inlet member (2) and the rear B-side end of the nozzle inlet member (2), and both ends are located at the nozzle side wall (3). ,
A pair of upper and lower support brackets (4) fixed to (3)
a) and (4b), the base brackets are disposed between the nozzle side walls (3) and (3) such that the base ends face the rear B side, and the base ends are the support brackets (4a) and (4b). 4b) Reverse flap rotation shafts (7a), (7) extending from one nozzle side wall (3) to the other nozzle side wall (3).
b) a pair of upper and lower reverse flaps (6)
a), (6b), and the nozzles are disposed between the nozzle side walls (3), (3) such that the base ends face the front A side, and the base ends are the support brackets (4a), (4b)
And the convergent flap rotation axes (9a) and (9b) substantially parallel to the reverse flap rotation axes (7a) and (7b).
And a pair of upper and lower convergent flaps (8a) and (8b) pivotally supported by the nozzles, and are disposed between the two nozzle side walls (3) and (3) such that the base ends thereof face forward A. The end is the reverse flap rotation shaft (7
a) A pair of upper and lower divergents pivotally supported by the distal ends of the convergent flaps (8a) and (8b) via divergent flap support shafts (11a) and (11b) substantially parallel to (7b). Flap (10a),
(10b), the nozzle side walls (3),
(3) The front A side by the support brackets (4a) and (4b) and the reverse flaps (6a) and (6b) and the convergent flaps (8a) and (8b) and the divergent flaps (10a) and (10b). And an exhaust passage (12) extending from the rear flap to the rear B side, and the reverse flaps (6a) and (6b) are connected to the reverse flap rotation shaft (7).
a) and a two-dimensional exhaust nozzle configured to be able to close the communication between the exhaust flow path (12) and the spaces (5a) and (5b) by rotating about the (7b). A connector (17) attached to the nozzle side wall (3) so as to be movable in the front-rear direction, and one end of each of the connectors (8a) and (8)
b) a pair of upper and lower convergent flap links (19a) and (19b) fixed to b), one end of which is pivotally supported by the connector (17) and the other end is convergent flap links (19a) and (19b). ), A pair of upper and lower convergent flap drive links (28a) and (28b) pivotally supported at the other end, and a pair of upper and lower reverse flaps each having one end fixed to the reverse flap (6a) or (6b). Flap link (18a),
(18b) and a pair of upper and lower reverse flap drive links (23) each having one end pivotally supported by the connector (17).
a) and (23b), one end of which is pivotally supported by the other end of the reverse flap drive link (23a) or (23b) and the other end is a reverse flap link (18a) or (23b).
A pair of upper and lower guide links (25a) and (25b) pivotally supported at the other end of (18b), a first actuator (36) for displacing the connector (17) back and forth, and the upper and lower divers Gent flap (10a), (1
0b) is a divergent flap support shaft (11a),
Second and third actuators (39a) and (39b) that rotate about (11b), and the connector (1).
7) is displaced from the front A side to the rear B side, a pivot point between the guide links (25a) and (25b) and the reverse flap drive links (23a) and (23b) is connected to the exhaust flow path (12). A pair of upper and lower guide members (21a) and (21b) for guiding outward from the center side are provided, and both convergent flaps (8a) are provided when the connector (17) is displaced from the rear B side to the front A side. , (8b) such that the tips of the convergent flap drive links (2
8a) and (28b) are determined, and when the tips of both convergent flaps (8a) and (8b) come into contact with each other, the two reverse flaps (6a) and (6b)
Rotates and the exhaust passage (12) and the spaces (5a), (5b)
Guide links (25a), (25
b) and guide members (21a) and (21b) having a predetermined shape.