JPH0544577A - Variable nozzle for flying object propulsion machinery - Google Patents

Abstract

PURPOSE:To improve engine performance by stopping discharge through a nozzle during transfer from booster propulsion to ram jet propulsion and adjusting the throat area of a nozzle to a proper value during ram jet propulsion, in a propulsion machinery having a ram jet engine burner for a flying object filled with a booster propellant. CONSTITUTION:In a flying object propulsion machinery having a burner 3 for a ram jet engine having an air intake duct and filled with a booster propellant 2, a nozzle is provided with moving plates each comprised of two front and rear plates 18 and 19 intercoupled through a hinge 21. The two moving plates, making a pair, are arranged to the outlet part of the burner 3 in a manner to be positioned facing each other. The front plate 18 of each moving plate is mounted on the casing 3' of the burner 3 by means of a hinge 20.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a variable nozzle for a propulsion device for a flying object such as a flying object flying at supersonic speed.

[0002]

2. Description of the Related Art FIG. 3 shows a conventional example of a booster-incorporated liquid ramjet engine for a flying vehicle. The liquid ramjet engine with built-in booster includes a combustor 3 and a combustor 3
The booster propellant 2 filled inside, the ramjet exhaust nozzle 4 provided at the outlet of the combustor 3, the fuel pump 5, the fuel control device 6 connected to the fuel pump 5, and the fuel control device 8 A fuel pipe 7, which is connected and has a fuel nozzle 8 at its tip, a ramjet ignition device 9, a port cover 10,
It comprises a booster exhaust nozzle 11 provided inside the ramjet exhaust nozzle 4 and a booster ignition device 12. These are combined with an air intake duct 13 whose rear end is connected to the combustor 3 and a fuel tank 14 to form a propulsion device, which is arranged at the rear part of the flying vehicle 1. The fuel pump 5 is connected to a fuel tank 14, the fuel nozzle 8 is arranged in an air intake duct 13, and the port cover 10 is arranged in a connection portion between the air intake duct 13 and the combustor 3. There is.

When the booster propellant 2 is ignited by the booster ignition device 12, the projectile 1 is accelerated to supersonic speed by the booster. When the booster propellant 2 is completely burned off, the port cover 10 is removed, and the air vigorously flows into the combustor 3 through the air intake duct 13 and is discharged from the ramjet exhaust nozzle 4 together with the booster exhaust nozzle 11. ..

After the port cover 10 and the booster exhaust nozzle 11 are discharged, the fuel pump 5 sucks the liquid fuel from the fuel tank 14 and is arranged in the air intake duct 13 through the fuel control device 6 and the fuel pipe 7. When the liquid fuel is sent to the fuel nozzle 8 and sprayed into the air stream, and the liquid fuel is ignited by the ramjet ignition device 9, the high temperature gas generated in the combustor 3 is ejected backward at high speed through the exhaust nozzle 4. By doing so, thrust in the forward direction is generated, and the ramjet engine operates even if the ramjet ignition device 9 is stopped thereafter.

FIG. 4 shows an enlarged view of a conventional exhaust nozzle portion. The exhaust nozzle part is provided with two types of exhaust nozzles, a booster exhaust nozzle 11 and a ramjet exhaust nozzle 4, and the booster exhaust nozzle 11 is housed in the ramjet exhaust nozzle 4 and fixed by a clamp 15. Has been done. When transitioning from the booster to the ramjet, the bolt 16 of the clamp 15 is blown up and the clamp 15 is removed, whereby the booster exhaust nozzle 11 is discharged and the ramjet exhaust nozzle 4 appears.

[0006]

When a projectile equipped with the conventional booster-equipped ramjet engine is launched from an aircraft, the booster propellant burns out several seconds after launch, and the booster exhaust nozzle 11 is released. , It is very dangerous because it is likely to collide with the launch mother plane.

Further, the conventional exhaust nozzle 4 for ramjet is used.
Since the throat area is fixed, the optimum throat area cannot be obtained with respect to the air flow rate and the fuel flow rate taken in from the air intake except the design point, and the engine performance is poor.

The present invention is intended to provide a variable nozzle for an aircraft propulsion device which can solve the above problems.

[0009]

The variable nozzle of the aircraft propulsion device of the present invention is a hinge in a vehicle propulsion device in which a booster propellant is filled in a combustor of a ramjet engine having an air intake duct. The two movable plates, which are the front and rear plates connected to each other, are arranged as a pair so as to face each other at the outlet of the combustor, and the plate in front of the movable plate is connected to the casing of the combustor via a hinge. I installed it.

[0010]

In the variable nozzle comprising the movable plate of the present invention, the common variable nozzle is used both when the booster propellant is burned and when the ramjet fuel is burned, and the exhaust nozzle is not discharged.

Further, when the flow rate of the air taken in from the air intake and the flow rate of the fuel increase during the operation of the ramjet, the movable plate composed of the two plates rotates around the hinge, and the exhaust gas is exhausted according to the air flow rate and the fuel flow rate. The throat area of the nozzle is optimally adjusted.

Further, the mechanism is simple, lightweight and highly reliable, and since the area ratio of the throat of the variable nozzle can be made large, the variable range is wide.

[0013]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described with reference to FIGS. This embodiment relates to a booster built-in liquid ramjet engine similar to that shown in FIG. 3, in which the same parts are designated by the same reference numerals, and the description thereof will be omitted. The points will be described.

A variable nozzle 17 is formed at the outlet of the rear end of the cylindrical combustor 3 filled with the booster propellant 2. The variable nozzle 17 is composed of four movable plates.
Each of the movable plates is composed of a front plate 18 and a rear plate 19 which are connected to each other by a hinge 21 so as to be curved in a rounded V shape as shown in FIG. These four sets of movable plates are arranged in a casing 3'of the combustor 3 in a cross shape and facing each other so as to project inward of the casing 3 ', and the front end of the plate 18 in front of each movable plate is the casing. 3'is attached by a hinge 20 so that the rear end of the rear plate 19 can slide on the casing 3 '.

In this embodiment, when the booster propellant 2 filled in the combustor 3 burns, the combustion gas is ejected rearward from the variable nozzle 17 composed of four sets of movable plates.

Also, when the liquid fuel is burned after the booster propellant 2 burns, the combustion gas is ejected rearward from the variable nozzle 17, but is introduced into the air intake duct 13 and the combustor 3. As the air flow rate and the liquid fuel flow rate increase, the plates 18, 19 of each movable plate move toward the hinges 20, 21.
It rotates around and moves from the position shown by the solid line in FIG. 2 to the positions of 18a and 19a which are close to the casing 3'as shown by the chain line.

Therefore, the throat area of the variable nozzle 17 formed by four sets of movable plates changes depending on the flow rates of the air and the liquid fuel introduced into the combustor 3, and an appropriate throat area can be obtained. The performance of can be improved.

The movable plate has a simple structure in which the two plates 18 and 19 are connected to each other by a hinge 21 and the front end of the front plate 18 is attached to the casing 3'of the combustor 3 via the hinge 20. In addition, it can operate smoothly depending on the flow rates of air and liquid fuel.

Further, as described above, the common variable nozzle 17 is used both when the booster propellant is combusted and when the liquid fuel is combusted, and there is no discharge of the booster exhaust nozzle as in the conventional case, and the safety of the mother machine is improved. improves.

In the above embodiment, the four movable plates are arranged facing each other in a cross shape. However, two movable plates may be provided so as to face each other, and an even number of six or more movable plates is provided. Alternatively, two movable plates may be provided in pairs, and the two movable plates forming the pair may be arranged to face each other.

[0021]

As described above, according to the present invention, two movable plates composed of two front and rear plates connected to each other are arranged as a pair so as to face each other at the outlet of the combustor, and each movable plate is connected. By attaching the front plate of the to the combustor casing via the hinge, it is possible to improve the safety of the mother machine by making it a non-emission type nozzle, and it is optimal according to the air flow rate and fuel flow rate. You can set the throat area to improve engine performance.

[Brief description of drawings]

FIG. 1 is a side view of an embodiment of the present invention.

FIG. 2 is an enlarged view of a main part of the embodiment, FIG. 2 (a) is a vertical sectional front view, and FIG. 2 (b) is a vertical sectional side view.

FIG. 3 is a side view of a conventional booster built-in type liquid ramjet engine.

FIG. 4 is an enlarged view of an exhaust nozzle of the conventional liquid ramjet engine in a booster device, FIG. 4 (a) is a longitudinal side view, and FIG. 4 (b) is a front view.

[Explanation of symbols]

 1 Flying Body 2 Booster Propellant 3 Combustor 3'Combustor Casing 4 Ramjet Exhaust Nozzle 5 Fuel Pump 6 Fuel Control Device 7 Fuel Pipe 8 Fuel Nozzle 9 Ramjet Ignition Device 10 Port Cover 11 Booster Exhaust Nozzle 12 Booster Ignition device 13 Air intake duct 14 Fuel tank 15 Clamp 16 Bolt 17 Variable nozzle 18,19 Movable plate plate 20,21 Hinge

Claims (1)

[Claims] 1. A vehicle propulsion apparatus in which a booster propellant is filled in a combustor of a ramjet engine having an air intake duct, wherein a movable plate composed of two front and rear plates connected to each other by a hinge is used. A variable nozzle for an aircraft propulsion device, characterized in that two pieces are arranged as a pair so as to face each other at an outlet of a combustor, and a plate in front of each movable plate is attached to a casing of the combustor via a hinge.