KR101598707B1

KR101598707B1 - A Gas flow adjuster

Info

Publication number: KR101598707B1
Application number: KR1020140106134A
Authority: KR
Inventors: 남궁혁준; 심창열
Original assignee: 현대로템 주식회사
Priority date: 2014-08-14
Filing date: 2014-08-14
Publication date: 2016-03-02
Also published as: KR20160021381A

Abstract

The present invention relates to a gas flow rate regulator, and more particularly, to a gas flow rate regulator which is provided with a flow rate regulating valve that slidably operates through hydraulic pressure or air pressure supplied to the inside of a housing so that the discharge flow rate of combustion gas or unburned gas generated in the housing, Thereby improving the combustion efficiency and facilitating the thrust control of the rocket. A gas flow rate regulator comprising: a housing having a valve receiving groove formed at a center of an inner side thereof in the axial direction and having a plurality of arc-shaped gas jet ports formed at one side of the valve receiving groove; A flow control valve coupled to the valve receiving groove so as to be slidable and having at least one gas flow path for discharging a high-temperature high-pressure combustion gas or unburned gas generated inside the housing as an intermediate portion; A fluid mixing tower formed on an outer surface of the housing and having an arch shape and guiding a supersonic gas to a subsonic flow; .

Description

A gas flow adjuster

The present invention relates to a gas flow rate regulator, and more particularly, to a gas flow rate regulator which is provided with a flow rate regulating valve that slidably operates through hydraulic pressure or air pressure supplied to the inside of a housing so that the discharge flow rate of combustion gas or unburned gas generated in the housing, Thereby improving the combustion efficiency and facilitating the thrust control of the rocket.

Generally, a rocket or ramjet engine is used to jet a gas into the air compressed by the ram pressure, to jet the jet directly, or to compress air with inflow air pressure due to the ram pressure generated during high- A gas flow regulator is provided for regulating the flow rate of the gas supplied to the combustion chamber in order to mix and burn the combustion gas or the unburned gas with the air or the oxidizer to obtain the driving force of the combustion engine.

However, since the conventional gas flow rate regulator regulates the flow rate by opening the window by the motor after receiving the valve signal, it is difficult to uniformly mix the gas and the air or the oxidizer due to the asymmetric injection of the primary combustion gas, There is a problem that precise control becomes difficult due to the decrease in the area of the gas ejection port.

In the conventional gas flow rate regulator, since the angle of the flow control valve for sliding operation is deflected or formed to an acute angle (angle larger than 0 ° and less than 90 °), the pressure of the combustion gas or the unburned gas generator There is a problem that uniform injection is not achieved due to the change.

Further, in the conventional gas flow rate regulator, mixing of gas and air is not uniformly and smoothly performed, and the combustion efficiency is lowered.

SUMMARY OF THE INVENTION Accordingly, the present invention has been made to solve the above-mentioned problems, and it is an object of the present invention to provide a method of controlling the flow rate of a combusted gas or an unburnt gas in a solid fuel, -buzz) control, and to improve the combustion efficiency by uniform mixing of combustion gas or unburned gas and air

According to an aspect of the present invention, there is provided a gas flow rate regulator including: a valve receiving groove having a depth in an axial direction formed at a center of an inner side thereof; a plurality of arc-shaped gas discharging holes formed at one side of the valve receiving groove A housing; A flow control valve coupled to the valve receiving groove so as to be slidable and having at least one gas flow path for discharging a high-temperature high-pressure combustion gas or unburned gas generated inside the housing as an intermediate portion; A fluid mixing tower formed on an outer surface of the housing and having an arch shape and guiding a supersonic gas to a subsonic flow; .

A fluid supply passage for controlling the movement of the flow control valve is formed at one side of the valve receiving groove.

An arc-shaped gas jet port having a height corresponding to the width of the air inlet port is formed on the outer side of the gas channel.

The gas flow path is formed only on one side of the donut-shaped circumferential surface of the flow control valve whose middle partial cross-section is in the form of a donut so that the discharge of the combustion gas or the unburned gas is performed in one direction.

The fluid mixing tower is installed in a direction orthogonal to the gas flow path and the gas spouting port.

Two air mixing holes are formed on the outer side of the fluid mixing tower and two air mixing holes are formed on the outer side of the housing at an angle of 90 °.

As described above, the present invention has the effect of removing sludge deposited in the vicinity of the gas spouting port through the flow rate control valve that adjusts the opening / closing area of the gas flow path while moving in the axial direction, and controlling the flow rate at the choked area have.

In addition, the present invention has an effect of improving mixing characteristics of gas and air injected at supersonic speed through a fluid mixing tower for mixing inflow air with combustion gas or unburned gas to improve secondary combustion efficiency in the combustion chamber .

The present invention also relates to a method and apparatus for mixing and mixing a combustion gas or an unburned gas generated from a solid propellant of a ductile rocket through an air inlet and an air introduced through an air inlet, ) To improve the combustion efficiency, thereby reducing the length of the combustion chamber of the rocket and increasing the range of the rocket and improving the maneuverability of the rocket.

Further, the present invention has an effect that it is possible to control the combustion chamber pressure by controlling the flow rate of the unburned gas and also to control the anti-buzz which is the air intake performance.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a schematic illustration of a partially separated state of a gas flow regulator according to a preferred embodiment of the present invention; FIG.
Fig. 2 is a view showing the coupling state of Fig. 1. Fig.
3 is a sectional view taken along the line AA in Fig.
4 is a cross-sectional view taken along the line BB in Fig.
5 is a cross-sectional view taken along the line CC of Fig.
FIG. 6 is a view showing an operation state of a gas flow rate regulator according to a preferred embodiment of the present invention.

Hereinafter, preferred embodiments of the gas flow rate controller according to the present invention will be described in more detail with reference to the accompanying drawings.

Hereinafter, elements having the same function in all the following drawings will be denoted by the same reference numerals, and repetitive description will be omitted. Further, the following terms are defined in consideration of functions in the present invention, Should be interpreted as.

As shown in FIGS. 1 to 6, the gas flow controller 100 of the present invention is generally divided into a housing 110, a flow control valve 120, and a fluid mixing tower 130.

The housing 110 is formed with a valve receiving groove 111 having a depth in the axial direction at the center of the inner side and a plurality of arc-shaped gas jetting outlets 112 are formed at one side of the valve receiving groove 111 do.

A fluid supply path 111a for controlling the movement of the flow control valve 120 is formed at one side of the valve receiving groove 111.

An air inlet 113 for smooth combustion of combustion gas or unburned gas is formed at one side of the housing 110.

The plurality of air intake openings (113) are formed on the outer side corresponding to the respective gas discharge openings (112).

The gas outlet 112 is preferably formed to have a generally trapezoidal shape with a wider outside than the inside so as to smoothly and easily discharge the unburned gas or the unburned gas.

The gas outlet 112 is preferably formed to have a length and height corresponding to the width of the air inlet 113 so as to smoothly mix the gas to be ejected with the air to be introduced.

The flow control valve 120 is slidably coupled to the valve receiving groove 111 and includes an intermediate portion for discharging the rich combustion gas or the unburned gas at a high temperature and pressure generated inside the housing 110 At least one gas channel 121 is formed.

The intermediate portion of the flow control valve 120 in which the gas flow path 121 is formed is formed in a generally donut-shaped cross-section.

The gas flow path 121 may be formed only on one side of the donut-shaped circumferential surface so as to discharge the combustion gas or the unburned gas in one direction.

The flow rate control valve 120 having such a configuration can be moved in the axial direction (left and right directions) by the difference in the combustion pressure generated in the housing 110 when the air pressure (compressed air) or the hydraulic pressure is supplied to the fluid supply path 111a, Right or front, rear, or both) of the gas flow path 121 and the gas discharge port 112, respectively.

That is, when the flow control valve 120 moves to the left or front and the gas ejection opening of the gas passage 121 and the gas ejection opening 111 becomes narrow, the pressure of the housing 110 increases, The flow rate of the combustion gas or the unburned gas discharged through the gas outlet 112 increases, thereby increasing the thrust of the rocket or the flying object in the traveling direction.

In contrast, when the flow control valve 120 moves to the right or to the rear to increase the gas blowing area of the gas passage 121 and the gas blowing port 112, the pressure of the housing 110 decreases and the gas passage 121 and / The flow rate of the combustion gas or unburned gas discharged through the gas outlet 112 is reduced, so that the thrust of the rocket or the force of pushing the traveling object or the flying object in the traveling direction decreases.

In this way, by controlling the discharge flow rate of the gas combusted or unburned in the housing 110 due to the mounting of the flow control valve 120, the thrust can be increased or decreased to control the rocket to be sent to a desired range have.

In addition, since choke (a pressure difference exists in the gaseous body due to the adjustment of the gas blowout area of the gas passage 121), a flow is generated. However, if the pressure ratio is increased, the flow velocity at the minimum cross- (Supersonic) of Mach number 1 is injected to remove the deposited sludge around the gas ejection port 112. In this case, And the flow rate at the choked area can be accurately controlled.

The fluid mixing tower 130 is formed on the outer surface of the housing 110 and has an arch shape and serves to induce a sub-supersonic gas jet.

In addition, the fluid mixing tower 130 is preferably formed as a curved surface of an approximately " a " shape.

The fluid mixing tower 130 may be installed in a direction substantially orthogonal to the gas flow path 121 and the gas spouting port 112.

In addition, an air inlet 113 is formed on the outer side of the fluid mixing tower 130 so as to surround the fluid mixing tower 130.

Two air mixing holes 130 are formed on the outer side of the housing 110 so that the air mixing holes 130 are formed at an angle of 90 ° with respect to the housing 110, It is possible to further efficiently mix the combustion gas or the unburned gas with the air.

The height, width, and number of the fluid mixing tower 130 can be appropriately adjusted according to the design specifications of the rocket.

In addition, the cross-sectional shape of the fluid mixing tower 130 is preferably a shark's fin shape such as a shark.

In the fluid mixing tower 130 having such a configuration, the speed of the combustion gas or the unburned gas ejected through the gas channel 121 and the gas ejection port 112 is changed from supersonic speed to subsonic speed The velocity of the flow when it is slower than the speed of the sound wave propagating in the fluid, which is generally referred to as a subsonic or supersonic speed depending on whether the speed of the moving object is slower or faster than the speed of sound) By forming a vortex, the mixing efficiency can be maximized and the air fuel mixture ratio and combustion stability can be ensured.

That is, the combustion gas or the unburned gas ejected through the gas passage 121 and the gas ejection port 112 collides with the curved surface formed inside the fluid mixing tower 130, thereby reducing the speed and becoming a subsonic speed, The combustion gas or the unburned gas propagates along the curved surface of the fluid mixing tower 130 while being in contact with the subsonic air introduced thereinto and is vortexed by a swirling flow in the direction opposite to the main flow The shape of the fluid that flows while rotating is referred to as a vortex or a vortex) and is quickly and uniformly mixed.

Thus, the combustion efficiency in the combustion chamber can be remarkably improved by increasing the mixing efficiency of the combustion gas or the unburned gas with the air.

In addition, the change in the area of the gas passage 121 allows the control of the combustion chamber pressure by controlling the flow rate of the gas combusted in the solid fuel, so that an anti-buzz (shock wave) It is possible to facilitate the control of the phenomenon of inhalation).

In the case where the change in the area of the gas passage 121 is not formed, since the pressure of the combustion chamber in which the combustion gas or the unburned gas injected through the gas passage 121 and the gas outlet 112 is generated by the secondary combustion can not be controlled, The vertical shock wave of the air is in front of the air intake port 113 and the air is not sucked properly. Therefore, the combustion gas and the air are not mixed smoothly, and thus the combustion efficiency can not be improved.

That is, when the fluid mixing tower 130 is not formed, shock waves of the combustion gas or the unburned gas injected through the gas passage 121 and the gas outlet 112 are diffused to the front of the air inlet 113, Since the intake is not properly performed, the combustion gas and the air are not mixed with each other, so that the combustion efficiency can not be improved.

The operation state of the present invention having the above-described structure will now be described.

First, the flow rate of the combustion gas or unburned gas generated through the housing 110, which is a gas generator, is controlled to obtain the thrust of the rocket engine or the ramjet engine equipped with the gas flow rate controller 100 according to the present invention The fluid supply passage 111a of the valve receiving groove 111 is designed to supply or discharge hydraulic pressure or air pressure.

At the same time, the flow control valve 120 moves forward and backward in the horizontal axis direction by the hydraulic pressure or the air pressure to adjust the gas ejection area of the gas channel 121 and the gas ejection port 112 to narrow or widen.

That is, when the flow rate control valve 120 moves to the left or front and the gap of the gas flow path 121 becomes narrow, the pressure of the housing 110 increases, and the combustion gas discharged through the gas flow path 121 or the unburned As the flow rate of the gas increases, the thrust of the rocket increases.

In contrast, when the flow control valve 120 moves to the right or to the rear and the gas ejection opening area of the gas flow passage 121 and the gas ejection opening 112 becomes wider, the pressure of the housing 110 decreases and the gas flow passage 121 The flow rate of the combustion gas or the unburned gas ejected through the combustion chamber is reduced, so that the thrust of the rocket is reduced.

In this way, the throttle can be increased or decreased by adjusting the flow rate of the combustion gas or the unburned gas in the housing 110 as the gas generator.

Subsequently, the combustion gas or unburned gas discharged at supersonic speed is reduced in speed at a subsonic speed while contacting with the fluid mixing tower 130. At the same time, a vortex is generated while being in contact with the air introduced through the air inlet 113, The control of the combustion pressure is made possible by controlling the flow rate of the unburned gas (fuel), so that the shock wave is prevented from advancing to the front of the air inlet 113

The combustion gas or the unburned gas evenly mixed with the air can remarkably improve the combustion efficiency.

Accordingly, the gas flow rate regulator according to the present invention increases the mixing efficiency of the combustion gas or the unburned gas supplied to the combustion chamber of the rocket or ramjet engine, thereby achieving complete combustion, thereby improving the propulsion efficiency, The length of the combustion chamber of the rocket is reduced, thereby improving the range of the rocket and improving the maneuverability of the rocket.

It will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the spirit or scope of the invention. And will be apparent to those skilled in the art to which the invention pertains.

100: gas flow regulator 110: housing
111: valve receiving groove 111a: fluid supply path
112: gas outlet 113: air inlet
120: Flow control valve 121: Gas flow path
130: fluid mixing tower

Claims

As a gas flow controller,
A valve housing groove formed in the center of the inner side at a depth in the axial direction and having a plurality of arc-shaped gas blowing openings formed at one side of the valve receiving groove;
A flow control valve coupled to the valve receiving groove so as to be slidable and having at least one gas flow path for discharging a high-temperature high-pressure combustion gas or unburned gas generated inside the housing as an intermediate portion;
A fluid mixing tower formed on an outer surface of the housing to form an arch shape and to induce a supersonic gas to be subsonic; And a gas flow rate regulator.

The method according to claim 1,
And a fluid supply passage for controlling the movement of the flow control valve is formed at one side of the valve receiving groove.

The method according to claim 1,
And an arc-shaped gas ejection port having a height corresponding to a width of the air inlet port is formed on the outer side of the gas passage.

The method according to claim 1,
Wherein the gas flow path is formed only on one side of the donut-shaped circumferential surface of the flow control valve whose middle partial cross-section is formed in a donut shape so as to discharge the combustion gas or the unburned gas in one direction.

The method according to claim 1,
Wherein the fluid mixing tower is installed in a direction orthogonal to the gas flow path and the gas spouting port.

The method according to claim 1,
Wherein two air mixing holes are formed on the outer side of the fluid mixing tower so as to form an angle of 90 DEG with respect to the outer side of the housing and a plurality of fluid mixing beds are formed inside each of the air mixing holes, regulator.