JPH0626402A - Rocket engine - Google Patents

Abstract

PURPOSE:To provide a rocket engine capable of suppressing vibratory combustion to conduct the stable combustion in a wide operating range. CONSTITUTION:A rocket engine comprises a combustion chamber 3 of a rocket engine, a vibration sensor 5 disposed in an injector 1 or a required position in piping or the like and at least one of valves 11, 12 for suppressing vibration by controlling combustion pressure or air fuel ratio on the basis of vibratory combustion sensed by the vibration sensors 5 and an acoustic cavity 2a for suppressing the vibration by changing an opening area, volume, etc., on the basis of the vibration.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a rocket engine capable of obtaining stable combustion under a wide range of operating conditions.

[0002]

2. Description of the Related Art FIG. 4 is a side view of a conventional rocket engine, in which an injector 1 supplied with fuel and an oxidizer from separate lines injects them into a combustion chamber 3 having an acoustic cavity 2, The combustion gas is ejected as shown by the arrow in the figure to obtain thrust.

Here, the acoustic cavity 2 is located upstream of the combustion chamber 3 as shown in the figure, and is an annular body having a large number of cavities 9 on its circumference, as shown in a partially cutaway perspective view of FIG. The combustion gas contained in the cavity 9 and the combustion gas repelled from inside interfere with each other to cancel the vibration so that vibration combustion does not occur.

[0004]

The above conventional rocket engine has the following problems to be solved.

That is, vibration combustion is a serious problem for a rocket engine that requires stable combustion. When it is severe, it causes melting and burning of the injector and combustion chamber, resulting in a serious accident. Therefore, conventionally, the acoustic cavity 2
To avoid approaching the dangerous points estimated from the shapes of the injector and combustion chamber, the combustion pressure used, the mixing ratio, etc. However, in the future, when a rocket engine is used for a manned space plane or the like, it is conceivable that a wide operating range will be required in order to suppress the acceleration to about 2 G, which an ordinary person can endure, and to optimally use fuel. An object of the present invention is to provide a rocket engine capable of ensuring stable combustion in a wide operating range according to the above requirements and flexibly responding to unexpected vibration combustion.

[0006]

Means for Solving the Problems As a means for solving the above problems, the present invention provides a vibration sensor disposed at a required location such as a combustion chamber of a rocket engine, an injector or a pipe, and vibration combustion detected by the vibration sensor. Of the acoustic cavity that controls the combustion pressure, the mixing ratio, etc. to suppress the above-mentioned vibration based on the generation information of An object of the present invention is to provide a rocket engine characterized by comprising at least one of them.

The acoustic cavity is located between the combustion chamber and the injector, and several small chambers having an appropriate opening area and volume determined by calculation in the circumferential direction are arranged to acoustically vibrate the combustion gas. Is to absorb.

[0008]

Since the present invention is constructed as described above, it has the following actions.

That is, vibration combustion is detected by a vibration sensor attached to a required portion such as a combustion chamber of a rocket engine, an injector, or a pipe, and combustion pressure and a mixing ratio are controlled by a valve based on the vibration information. Vibration is suppressed by changing the opening area or volume of the acoustic cavity.

[0010]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS The first and second embodiments of the present invention will be described with reference to FIGS. The same components as those in the conventional example are designated by the same reference numerals, and the description thereof will be omitted unless necessary.

(First Embodiment) A first embodiment will be described with reference to FIGS. 1 and 2. FIG. 1 is a side view of the rocket engine of this embodiment, and FIG. 2 is a cross-sectional view of the acoustic cavity 2a of FIG. In FIG. 1, the actuator 7 of FIG. 2 and accessories attached thereto are omitted.

In both figures, 2a is an acoustic cavity capable of changing the volume of the cavity 9a, 4 is a controller for controlling the acoustic cavity 2a or the valves 11 and 12 based on the information from the vibration sensor 5,
Reference numeral 5 is a vibration sensor fixed to the outer periphery of the injector 1, combustion chamber 3, etc., 6 is a signal line for controlling the acoustic cavity 2a from the controller 4, and 6a is a valve 1
Actuating signal lines for controlling 1 and 12, 7 is an actuator for operating the partition plate 8 of the acoustic cavity 2a, 8 is a partition plate for changing the volume of the cavity 9a, and 9a is a cavity (room) of the acoustic cavity 2a. , 11 are fuel control valves controlled by the controller 4, and 12 are also oxidant control valves.

Next, the operation of the above configuration will be described.

The controller 4 judges the signal obtained by the vibration sensor 5 attached to the combustion chamber 3, the injector 1 and the like, and moves the valves 11 and 12 through the operation signal line 6 to control the mixing ratio, the combustion pressure and the like and vibrate. Suppress combustion. Alternatively, the actuator 7 is operated via the signal line 6 to change the volume of the acoustic cavity 2a, that is, the cavity 9a by the lateral movement of the partition plate 8 to suppress the oscillating combustion.

In this embodiment, an example in which both the valves 11 and 12 and the acoustic cavity 2a are controlled has been shown, but only one of them may be used.

(Second Embodiment) A second embodiment of the present invention will be described with reference to FIG.

FIG. 3 is a cross-sectional view of the acoustic cavity 2b of this embodiment. The acoustic cavity 2b shown in this figure is the acoustic cavity 2a of FIG.
The second embodiment is similar to the first embodiment, except that 3 (a) is a cross-sectional view, and FIG. 3 (b) is (a).
3 is a cross-sectional view taken along the line AA of FIG.

In FIG. 3, the inner depth of the cavity 9b is 4
One quadrant in the quadrant is eccentrically faced and closed by a thick disk-shaped partition plate 8a that is cut out, and the partition plate 8a is rotatably connected in its plane by a motor 7a via a rotary shaft. .

Next, the operation of the above configuration will be described.

An oscillating wave (pressure wave) entering the cavity 9b from the left side of FIG. 3 (a) passes through the thickness of the partition plate 8a and hits the inner bottom of the cavity 9b to be reflected.
Since the cutout portion of the partition plate 8a is hidden or appears above the cavity 9b due to the rotation of the motor 7a, the opening area changes depending on the degree of hiding, and the reflectance of the vibration wave changes. The controller 4 selects the optimum value to suppress oscillatory combustion.

As described above, according to the first and second embodiments, the controller 4 controls the valves 11 and 12 in accordance with the information of the vibration combustion detected by the vibration sensor 5 to change the mixing ratio of the fuel and the oxidizer. , Or by changing the combustion pressure, or the acoustic cavity 2a,
By changing the volume or opening area of 2b, there is an advantage that vibration combustion can be suppressed appropriately and promptly.

[0022]

Since the present invention is constructed as described above, it has the following effects (1) and (2). (1). Since it is not necessary to avoid the oscillating combustion region, it is possible to operate with a wide range of combustion pressures and mixing ratios. (2). Damage can be prevented because it is possible to shift to a stable combustion condition range against unexpected vibration combustion.

[Brief description of drawings]

FIG. 1 is a schematic side view of a rocket engine according to a first embodiment of the present invention,

FIG. 2 is a cross-sectional view of the acoustic cavity of the first embodiment,

FIG. 3 is a diagram of an acoustic cavity according to a second embodiment of the present invention, in which (a) is a cross-sectional view and (b) is A- in (a).
A sectional view taken along arrow A,

FIG. 4 is a schematic side view of a conventional rocket engine,

FIG. 5 is a partial perspective view of a conventional acoustic cavity.

[Explanation of symbols]

 1 Injector 2a, 2b Acoustic cavity 3 Combustion chamber 4 Controller 5 Vibration sensor 6 Signal line 6a Actuation signal line 7 Actuator 7a Motor 8, 8a Partition plate 9a, 9b Cavity 11, 12 Valve

Claims (1)

[Claims] 1. A vibration sensor disposed at a required location such as a rocket engine combustion chamber, an injector, or a pipe, and a combustion pressure, a mixing ratio, and the like based on the occurrence information of the vibration combustion detected by the vibration sensor. A valve for controlling the vibration to suppress the vibration, or at least one of acoustic cavities for suppressing the vibration by changing the opening area, volume, etc. based on the information on the occurrence of the vibration. Rocket engine to do.