JPH084588A - Propulsion device - Google Patents

Abstract

PURPOSE:To improve combustion efficiency and to simplify structure, in a propulsion device operated in a supersonic area. CONSTITUTION:In a propulsion device 1 operated in a supersonic area, solid fuel 3 is arranged along the inner surface of the interior of a burner 2 opened to the head part side and the tail part side and an injector 6 for fuel component surplus gas is arranged at the inner central part of the head part of the burner 2.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a propulsion device for a flying vehicle, and more particularly to a propulsion device used for accelerating a flying vehicle by starting operation in a supersonic range.

[0002]

2. Description of the Related Art A propulsion device of this type is shown in FIG. In the propulsion device 100 shown in the figure, a solid fuel 102 is provided in a liner shape on the inner surface of a cylindrical combustor 101, and at the inside of the head of the combustor 101, a core 103 carrying a liquid fuel and its outer periphery are arranged. A surrounding branching device 104 is concentrically provided, and a liquid fuel combustion chamber 105 and an internal nozzle 106 are connected to a tail portion of the branching device 104.

In the propulsion device 100, a shock wave S is generated by the core 103 in the supersonic region, and the solid fuel 102 is burned by the boundary layer combustion method by the supersonic airflow introduced from the air intake 107, while the branching device is used. Introduced air having a subsonic flow in 104 and liquid fuel injected from the core 103 are mixed and combusted in a combustion chamber 105, and the combustion gas is injected from the internal nozzle 106 as a supersonic flow. Thrust is obtained by injecting from 108.

Such a propulsion device is known as AIAA 90-
2076 A Numerical Study of
Solid Fuel Combustion Und
er Supersonic Crossflows
It is described in.

[0005]

However, in the conventional propulsion device as described above, the introduced air is the combustor 10
It is divided into one side and the branch device 104 side, and on the branch device 104 side, the liquid fuel is combusted to some extent in the combustion chamber 105 by the introduced air decelerated to the subsonic flow, and the combustion gas is injected into the combustor 101. The combustion is completed. Therefore, there is a problem that the structure is complicated due to the branching of the introduced air, and there is a limit to increase the energy of the combustion gas from the combustion chamber 105. Therefore, on the combustor 101 side, introduction of a supersonic flow is performed. There is a problem that the combustion state of the solid fuel 102 in the combustor 101 by air is not always sufficient, and it has been a problem to solve these problems.

[0006]

SUMMARY OF THE INVENTION The present invention was made in view of the above-mentioned conventional problems, and in a propulsion device operating in the supersonic range,
It is an object of the present invention to provide a propulsion device that can improve combustion efficiency and realize simplification of structure.

[0007]

A propulsion device according to the present invention is, as claim 1, a propulsion device which operates in a supersonic range, and which is provided inside a combustor opened to a head side and a tail side. The primary combustion in which the solid fuel is provided along the inner surface of the combustor, and an injector for the excess fuel component gas is provided in the center of the inside of the head of the combustor, and the injector is opened in the combustor. A chamber having a chamber and a solid fuel having self-combustibility loaded in the primary combustion chamber, and the solid fuel in the injector is an end-face combustion type,
As a fourth aspect, an injection hole for opening the primary combustion chamber into the combustor is provided at the center of the tail portion of the injector, and as the fifth aspect, the solid fuel in the primary combustion chamber contains a combustion improver. The above configuration is used as a means for solving the problem.

In the solid fuel, for example, a glycidyl azide polymer (GAP: Glycidyl) which can be burned as a substance having self-combustibility without depending on an oxidant.
Azide Polymer) can be used.

[0009]

In the propulsion device according to the first aspect of the present invention, the supersonic air flow is introduced with almost no deceleration and the solid fuel provided on the inner surface of the combustor is supersonicly burned by the boundary layer combustion method. At the same time, the introduced air and the fuel component excess gas injected from the injector are mixed and burned. That is, the introduced air is sandwiched between the excess fuel component gas and the solid fuel from inside and outside so that sufficient combustion is performed.

As in the propulsion device according to the second aspect of the present invention, the solid fuel having self-combustibility is used as the source of the fuel component excess gas to raise the temperature in the combustor. Like the propulsion device according to claim 3, by making the solid fuel in the primary combustion chamber of the injector an end-face combustion type, the supply of excess fuel component gas is made constant to stabilize combustion, and Like the related propulsion device, by providing an injection hole for the fuel component excess gas at the center of the tail portion of the injector, the distribution of the fuel component excess gas to be injected is made uniform, and combustion is further stabilized. As in the propulsion device according to No. 5, the solid fuel in the primary combustion chamber containing the combustion improver is used to further increase the energy.

[0011]

1 to 3 are views for explaining an embodiment of a propulsion device according to the present invention.

A propulsion device 1 shown in FIG. 1 (a) is provided inside a combustor 2 which is open to the head side (left side in FIG. 1) and the tail side and has a slightly smaller diameter on the head side. A solid fuel 3 is provided along the inner surface. The combustor 2 has an air intake 4 on the head side and an exhaust nozzle 5 on the tail side.

As the solid fuel 3, for example, glycidyl azide polymer is used. Further, the solid fuel 3 is formed in a taper shape in which the thickness gradually decreases toward the ends on the head side and the tail side, and the middle portion is formed to have a substantially uniform thickness over a predetermined length. There is.

At the center of the head side of the combustor 2, an injector 6 for the fuel component excess gas is provided. The injector 6 has a conical shape with its tip facing the head side, and is supported by a stay (not shown) in a state in which the tip is projected from the combustor 2.

Further, as shown in FIG. 1 (b), the injector 6 is provided with a primary combustion chamber 7 opened in the combustor 2 and an end face combustion type solid fuel 8 is provided in the primary combustion chamber 7. It is loaded. The solid fuel 8 is of the same quality as the solid fuel provided in the previous combustor 2, or the solid fuel contains metal powder such as boron as a combustion improver in order to achieve higher energy. Is used.

Further, an igniter 9 for igniting the solid fuel 8 in the primary combustion chamber 7 is attached to the injector 6, and the primary combustion chamber 7 is opened in the combustor 2 at the center of the tail. An injection hole 10 is provided. This injection hole 10
Is formed by a ring 11 fixed to the tail end of the primary combustion chamber 7.

As shown in FIG. 2, the propulsion device 1 is used, for example, as an intermediate acceleration means of the rocket R for observation.
In this case, the rocket R is equipped with a main propulsion device used for starting and accelerating, and two propulsion devices 1 and 1 are provided.

In the supersonic region, the propulsion device 1 allows the supersonic air flow introduced from the air intake port 4 to flow into the combustor 2 with almost no deceleration, and causes the solid fuel 3 provided on the inner surface of the combustor 2 to flow. Boundary layer combustion method is used for supersonic combustion. On the other hand, the solid fuel 8 in the injector 6 is ignited by the igniter 9, the fuel component excess gas generated by the primary combustion of the solid fuel 8 is injected from the injection hole 10, and the fuel component excess gas and the introduced air are supplied. Are mixed and burned, and the combustion gas generated by the combustion of the solid fuel 3 and the fuel component excess gas is ejected from the exhaust nozzle 5 to obtain thrust.

At this time, the propulsion device 1 puts the air introduced by the fuel component excess gas (fuel) and the solid fuel 3 from the inside to the outside so that sufficient combustion is performed.

Here, FIG. 3 is a diagram (a) for explaining the distribution of the air-fuel ratio in the range from the center immediately after the internal nozzle 106 to the surface of the solid fuel 102 in the conventional propulsion device, and FIG. FIG. 3B is a diagram (b) illustrating the distribution of the air-fuel ratio in the range from the center immediately after the injection hole 10 to the surface of the solid fuel 3 having self-combustibility in the propulsion device 1.

That is, in the conventional propulsion device, considering the combustion region from the range L of the air-fuel ratio for steady combustion, the width is L1, whereas in the propulsion device 1 of this embodiment, self-combustion is performed. In the case of solid fuel having properties, the width of the combustion region is L1 + L2, and it can be seen that the propulsion device 1 of this embodiment has a larger combustion region and higher combustion efficiency.

Further, the propulsion apparatus 1 uses the solid fuel 8 having self-combustibility as a source of the fuel component excess gas to raise the temperature in the combustor 2 to remove the solid fuel 3 in the combustor 2. While trying to promote combustion,
The solid fuel 8 in the primary combustion chamber 7 of the injector 6 is of end-face combustion type, so that the excess fuel component gas is supplied constantly, and the excess fuel component is provided at the center of the tail portion of the injector 6. By providing the gas injection holes 10, the distribution of the injected fuel component excess gas is made uniform to further stabilize the combustion.

[0023]

As described above, according to the propulsion device of the first aspect of the present invention, the introduced air is sandwiched between the fuel component excess gas and the solid fuel so that the fuel and the air are separated from each other. A large contact area can be obtained, the combustion efficiency can be greatly improved, and the structure can be made extremely simple. Accordingly, the weight can be reduced.

Further, by adopting the solid fuel having self-combustibility as the source of the fuel component excess gas as in the propulsion device according to the second aspect, the temperature in the combustor is raised and the solid in the combustor is increased. It is possible to promote the combustion of fuel and obtain a better combustion state.

As in the propulsion device according to the third aspect, the solid fuel in the injector is of the end-face combustion type, so that the supply of the excess fuel component gas is made constant and the combustion is stabilized in the combustor. In addition, as in the propulsion device according to claim 4, by providing an injection hole for the fuel component excess gas at the center of the tail portion of the injector, the distribution of the fuel component excess gas to be injected is made uniform. Claim 5 can contribute to stabilization of combustion in
Like the propulsion device according to (1), by adding the combustion improver to the solid fuel in the primary combustion chamber, it is possible to further increase the energy.

[Brief description of drawings]

FIG. 1 is a sectional view (a) illustrating an embodiment of a propulsion device according to the present invention and an enlarged sectional view (b) of a main part of an injector.

FIG. 2 is a cross-sectional view showing an observation rocket equipped with the propulsion device shown in FIG.

FIG. 3A is a diagram for explaining the distribution of the air-fuel ratio in the range from the center immediately after the internal nozzle to the solid fuel surface in the conventional propulsion device, and FIG. It is a figure (b) explaining the distribution of the air-fuel ratio in the range which reaches the surface of the self-combustible solid fuel.

FIG. 4 is a cross-sectional view illustrating a conventional propulsion device.

[Explanation of symbols]

 1 Propulsion Device 2 Combustor 3 Solid Fuel (Solid Fuel in Combustor) 6 Injector 7 Primary Combustion Chamber 8 Solid Fuel (Solid Fuel in Primary Combustion Chamber) 9 Igniter 10 Injection Hole

Claims (5)

[Claims] 1. A propulsion device that operates in the supersonic range, comprising:
In the inside of the combustor opened to the head side and the tail side, solid fuel is provided along the inner surface of the combustor, and an injector for excess fuel component gas is provided in the center inside the head of the combustor. Propulsion device. 2. The propulsion unit according to claim 1, wherein the injector has an open primary combustion chamber in the combustor, and the solid fuel having self-combustibility is loaded in the primary combustion chamber. apparatus. 3. The propulsion device according to claim 2, wherein the solid fuel in the injector is an end-face combustion type. 4. The propulsion device according to claim 2, wherein an injection hole for opening the primary combustion chamber into the combustor is provided at the center of the tail portion of the injector. 5. The propulsion device according to claim 2, wherein the solid fuel in the primary combustion chamber contains a combustion improver.