JPH07208266A - Device for igniting rocket engine - Google Patents

Abstract

PURPOSE:To miniaturize a device for igniting a rocket engine, improve the reliability, and provide the igniting ability to promote the ignition excellent in a wide range. CONSTITUTION:A plurality of igniting devices 1a to jet out the ignited flame 1b in the direction inclined relative to the thrusting direction are provided in a combustion chamber 1c on the downstream side of a fuel burner 1d, the flame contact area 1f of the ignited flame Ib with the fuel 1e is increased to improve the igniting ability, and the igniting devices 1a are miniaturized. Thus, the miniaturization can be realized, and the maintenance can be facilitated.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a rocket engine ignition device for igniting a rocket engine.

[0002]

2. Description of the Related Art FIG. 3 is a vertical sectional view showing an entire conventional rocket engine. The fuel 3a of the engine is introduced into the fuel injector 3b, and is injected as the injected fuel 3d into the combustion chamber 3c on the downstream side of the plurality of injection holes 3b '. on the other hand,
One ignition device 3e arranged at the center of the fuel injector 3b
Mixes and combusts the fuel 3f and the oxidizer 3g, and injects the combustion gas into the combustion chamber 3c as the ignition flame 3h. The ignition flame 3h and the injected fuel 3d come into contact with each other to ignite.
The high-energy combustion gas generated by the combustion is further appropriately expanded by the jet expansion device 3i on the rear side and vigorously ejects into the jet flow 3j on the rear side of the engine.

The rocket engine obtains thrust T by the reaction force of the jet 3j. Note that FIG.
In the figure, A is an engine mounting base, and as described above, the ignition device 3e is arranged at the center of the fuel injector 3b, so that the ignition device 3e is installed below the engine mounting base A.

FIG. 4 is a vertical sectional view showing details of a conventional rocket engine ignition device. This conventional rocket engine igniter uses a fuel 3f and an oxidizer 3g to ignite the device 3
e in the pre-combustion chamber 4a, the ignition flame gas 4b is ejected through the flame gas passage pipe 4c, and then a plurality of injection fuels 3d are separately ejected around the ignition device 3e. In general, a device for injecting the fuel from the hole 3b 'and bringing the fuel into contact with the flame contact region 3k around the ignition flame 3h to ignite the whole is common.

[0005]

In the above conventional rocket engine ignition device, since the ignition flame 3h is ejected substantially linearly, the ignition flame 3h and the fuel 3d injected around the ignition device are in flame contact with each other. Since the region 3k is limited to a small area, it takes a long time to ignite, and there is a problem that a reliable ignition cannot be obtained and a miss ignition occurs. Therefore, for example, when it takes a long time to ignite, the amount of fuel injected around the igniter is excessive for that amount of time, and it ignites in a form close to an explosion, which causes damage to surrounding equipment. . Also, in the case of a misfire, the rocket launch fails, which is a serious situation.

In order to solve this problem, an ignition flame 3h ejected from the flame gas passage pipe 4c of the ignition device 3e.
Enlarging the flame contact region 3k with the fuel 3d injected around the ignition device is an effective means for improving the ignition performance of the ignition device.

Further, conventionally, since there is only one ignition device 3e for each rocket engine, there are problems of reliability and an increase in size of the ignition device 3e. In addition, since the ignition device position 3e is limited to the center axis of the engine, it must be installed under the engine mount A, and the engine mount A must be removed for maintenance. There is a problem with sex.

The present invention is intended to provide a rocket engine ignition device that can solve the above problems.

[0009]

In the rocket engine ignition system of the present invention, a plurality of ignition systems for ejecting ignition flame in a direction inclined toward the propulsion direction are provided in the combustion chamber on the downstream side of the fuel injector. Is characterized by.

[0010]

In the present invention, the direction from the ignition device into the combustion chamber is inclined with respect to the propulsion direction, that is, the direction with respect to the injection direction of the fuel injected from the fuel injector injected in the opposite direction to the propulsion direction. Ignition flame is ejected. Therefore, the flame contact area between the ignition flame and the fuel is expanded, and in a short time,
A wide range of reliable and good ignition conditions can be obtained. Further, since the plurality of ignition devices are provided, the ignition device is downsized and its reliability is improved.

Further, since the plurality of ignition devices are installed in the combustion chamber on the downstream side of the fuel injector so as to eject the ignition flame in the direction inclined with respect to the propulsion direction, the ignition device is installed in the fuel injector. Since it is arranged on the downstream side, the ignition device can be taken out without removing the engine mount, and maintenance can be performed easily.

[0012]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described with reference to FIGS.

Reference numeral A is an engine mounting base of the rocket body, and a fuel injector 1d to which the fuel 1e is supplied is mounted below the mounting base A. A plurality of injection holes 1d 'are provided at the downstream end of the fuel injector 1d, and the fuel 1e is directed downstream, that is, in the direction opposite to the propulsion direction, as indicated by the arrow in FIG. 1 (a). The fuel is injected into the combustion chamber 1c that is connected to the downstream side of the fuel injector 1d.

The three ignition devices 1a to which the fuel 2a and the oxidant 2b are supplied are equidistantly arranged on the same circumference of the combustion chamber 1c, and the ignition device 1a is formed by the fuel 2a and the oxidant 2b. The ignition flame 1b is arranged so as to incline toward the downstream side from the ignition device 1a and to be ejected into the combustion chamber 1c so as to intersect with the central axis of the combustion chamber 1c. Although not shown, a jet expansion device similar to that shown in FIG. 3 is connected downstream of the combustion chamber 1c.

As shown in FIG. 2, each of the ignition devices 1a has a pre-combustion chamber 2 to which a fuel 2a and an oxidant 2b are supplied.
and a fuel 2a and an oxidizer 2b in the same pre-combustion chamber 2c.
Are mixed with each other to burn the fuel 2a, and the ignition flame gas 1b '
Passes through the flame gas passage pipe 2d connected to the pre-combustion chamber 1c, and as described above, the ignition flame 1b inclines toward the downstream side in the combustion chamber 1c, and at the center axis of the combustion chamber 1c. It is jetted so that it may cross.

In this embodiment, the fuel 1e injected from the fuel injector 1d by the ignition flame 1b from the ignition device 1a.
Are ignited and burned, three ignition devices 1a are provided around the combustion chamber 1c, and the ignition flame 1b from each ignition device 1a inclines toward the downstream side, and Since it is jetted into the combustion chamber 1c so as to intersect with the central axis of 1c, the flame contact area 1f between the fuel 1e and the ignition flame 1b is expanded, and a reliable and good ignition state is achieved in a short time and in a wide range. Obtainable.

Further, since the plurality of ignition devices 1a are provided, the ignition device can be downsized and its reliability can be improved.

Furthermore, since the ignition device 1a is arranged around the combustion chamber 1c, the ignition device 1a can be taken out without removing the engine mount A, and maintenance can be performed easily.

[0019]

The present invention provides a conventional rocket engine ignition device by providing a plurality of igniters for ejecting ignition flame in a direction inclined with respect to the propulsion direction in the combustion chamber on the downstream side of the fuel injector. In comparison, it is possible to provide a rocket engine ignition device that is smaller in size, has a more reliable ignition capability that promotes excellent ignition over a wide range, and is easy to maintain.

[Brief description of drawings]

1 shows an embodiment of the present invention, FIG. 1 (a) is a vertical sectional front view thereof, and FIG. 1 (b) is a vertical sectional side view thereof.

FIG. 2 is a sectional view taken along the line AA of FIG.

FIG. 3 is a vertical cross-sectional view showing the entire conventional rocket engine.

FIG. 4 is a vertical sectional view showing details of a conventional rocket engine ignition device.

[Explanation of symbols]

 1a Ignition device 1b Ignition flame 1c Combustion chamber 1d Fuel injector 1d 'Nozzle 1e Fuel 1f Flame contact area 2a Fuel 2b Oxidant 2c Pre-combustion chamber 2d Flame gas passage pipe A Engine mount

Claims (1)

[Claims] 1. A rocket engine ignition device comprising a plurality of ignition devices for ejecting an ignition flame in a direction inclined with respect to a propelling direction in a combustion chamber downstream of a fuel injector.