KR100654412B1 - Liquid propellant rocket engine - Google Patents

Abstract

A liquid propellant rocket engine is provided to improve the reliability of the rocket engine by maintaining a stable combustion temperature of a gas generating unit. In a liquid propellant rocket engine(100), a fuel supplying pump(120) supplied fuel to a combustion chamber(110). An oxidizer supplying pump(130) supplies an oxidizer to the combustion chamber. A gas generating unit(140) generates gas by receiving a part of the fuel and the oxidizer supplied from the fuel supplying pump and the oxidizer supplying pump. A turbine(150) is rotated by the gas supplied from the gas generating unit and drives the fuel supplying pump and the oxidizer supplying pump. A thrust controlling valve(160) controls the quantity of oxidizer supplied to the gas generating unit. An oxidizer bypass tube(170) is diverged from the gas generating unit of the thrust controlling valve. A mixing ratio stabilizer controls the fuel supplied from the gas generating unit according to the pressure of the oxidizer supplied to the oxidizer bypass tube.

Description

Liquid propellant rocket engine

1 is a schematic view of a liquid propellant rocket engine according to an embodiment of the present invention;

FIG. 2 is a cross-sectional view of the mixed stabilizer of FIG. 1 in a half-opened state;

3 is a cross-sectional view of the mixed non-stabilizer of FIG. 1 in an open state.

<Explanation of symbols for the main parts of the drawings>

100 Liquid Propellant Rocket Engine 110 Combustion Chamber

111.Combustion chamber flow regulator 112.Combustion chamber fuel supply valve

115.Combustion chamber oxidant supply valve 120 ... fuel supply pump

125,135 ... rotary shaft 126 ... fuel booster pump

136 Oxidizer Booster Pump 130 Oxidizer Supply Pump

140 gas generator 150 turbine

160 Thrust Control Valve 170 Oxidizer Bypass Pipe

200 ... Mixed Ratio Stabilizer 210 ... Body

211 Fuel injection hole 212 Fuel discharge hole

213 ... through through oxidant oil

215 Sealing element 220 Spool guide

221 ... 1 orifice 230 ... diaphragm

231 ... 240 240 Spool

241 ... Orific 2nd 250 ... Retainer

260 ... Spring 261 ... Spring adjustment bolt

The present invention relates to a liquid propellant rocket engine, and more particularly, to a liquid propellant rocket engine that is heated to heat generated when a liquid is combusted in a combustion chamber, becomes a gaseous state, and expands and has kinetic energy.

In general, liquid propulsion rocket engines, unlike turbojet or ramjet propulsion engines, store oxygen in themselves, mix liquid oxidants, burn them in the combustion chamber, and eject the exhaust gases through the nozzles. It is a flying device to get. Such liquid rockets can easily control the amount of combustion through valves and pumps, and are easily favored over solid rockets due to their easy re-ignition.

 Such a liquid propellant rocket engine must adjust the thrust of the engine according to the mission. However, when the thrust is adjusted, the mixing ratio of the propellant flowing into the gas generator is changed, so that the gas temperature rises above the design temperature, at which time the turbine blade melts or breaks at high temperatures. In addition, when the oxidant and the fuel are mixed and burned in the combustion chamber, the fuel is introduced at a predetermined mixing ratio or more of the oxidant and the fuel, and there is a problem in that surplus material of the fuel burned by mixing with the oxidant is wasted.

The present invention has been made to solve the above problems, an object of the present invention is to provide an improved liquid propellant rocket engine to maintain the mixing ratio of the propellant flowing into the gas generator when adjusting the thrust of the engine.

Other objects and advantages of the invention will be described below and will be appreciated by the embodiments of the invention. Furthermore, the objects and advantages of the invention can be realized in particular by the means and combinations indicated in the claims.

Liquid propellant rocket engine according to the present invention for achieving the above object, the combustion chamber; A fuel supply pump for supplying fuel to the combustion chamber; An oxidant supply pump for supplying an oxidant to the combustion chamber; A gas generator for generating a gas by receiving a part of the fuel and the oxidant supplied from the fuel supply unit and the oxidant supply unit; A turbine which receives and rotates the gas generated by the gas generator and drives the fuel supply pump and the oxidant supply pump; A thrust control valve for controlling the amount of oxidant supplied to the gas generator; An oxidant bypass pipe branched at the gas generator side of the thrust control valve; And a mixing ratio stabilizer for controlling the fuel supplied to the gas generator in accordance with the oxidant pressure supplied to the oxidant bypass pipe.

Here, the mixing ratio stabilizer is a oxidant oil supply line that is supplied with the fuel supplied from the fuel supply pump, the fuel injection hole and the fuel discharge hole for discharging are formed at a predetermined position, and the oxidant supplied to the bypass pipe is supplied. A body having a through hole; A spool guide formed in a hollow shape in the body and having a first orifice formed at a predetermined position corresponding to the fuel injection hole and the fuel discharge hole; A diaphragm formed inside the body and moving in accordance with an oxidant pressure supplied to the oxidant passage hole; One end of the diaphragm may be coupled to each other to include a spool having a second orifice formed at a predetermined position corresponding to the first orifice, reciprocating in the spool guide according to the movement of the diaphragm.

In addition, as the diaphragm moves, the penetration areas of the first orifice and the second orifice change to control the amount of fuel.

The body may have a hole formed at a predetermined position of an outer circumferential surface of the diaphragm, and a sealing member may be inserted into the hole.

In addition, the diaphragm may include a protrusion formed to protrude toward the body.

The mixing ratio stabilizer may include: a retainer coupled to one end of the spool guide; One end may be coupled to the retainer, and the other end may further include a spring coupled to the spool.

In addition, the spring, one end is coupled to the spool guide, the other end may be provided with a spring adjustment bolt coupled to the retainer.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings.

Prior to this, the terms or words used in this specification and claims should not be construed as being limited to the ordinary or dictionary meanings, and the inventors should properly explain the concept of terms in order to best explain their own invention. Based on the principle that can be defined, it should be interpreted as meaning and concept corresponding to the technical idea of the present invention.

Therefore, the embodiments described in the specification and the drawings shown in the drawings are only one of the most preferred embodiments of the present invention and do not represent all of the technical idea of the present invention, various modifications that can be replaced at the time of the present application It should be understood that there may be equivalents and variations.

1 is a schematic view of a liquid propellant rocket engine according to an exemplary embodiment of the present invention, FIG. 2 is a cross-sectional view of the mixed stabilizer of FIG. 1 being half-opened, and FIG. 3 is a cross-sectional view of the mixed stabilizer of FIG. 1 being opened. .

First, referring to FIG. 1, the rocket engine 100 includes a combustion chamber 110, a fuel supply pump 120, an oxidant supply pump 130, a gas generator 140, a turbine 150, The thrust control valve 160, the oxidant bypass pipe 170 and the mixing ratio stabilizer 200 is provided.

In detail, the combustion chamber 110 receives fuel from the fuel supply pump 120, and receives an oxidant from the oxidant supply pump 130. In addition, the gas generator 140 receives a portion of the fuel and the oxidant supplied from the fuel supply pump 120 and the oxidant supply pump 130 to generate a gas.

The gas generator 140 is operated by a starter (not shown) such as a solid motor to expand the heated high temperature high pressure fuel and the oxidant. The expanded fuel and the oxidant flow into the turbine 150, and the turbine 150 is driven by rotating the rotary shafts 125 and 135 respectively connected to the fuel supply pump 120 and the oxidant supply pump 130. Let's do it.

In addition, the internal pressure of the fuel supply pump 120 and the oxidant supply pump 130 is increased by the operation of the rotating shaft, and the fuel booster pump 126 in which the fuel is stored and the oxidant booster pump 136 in which the oxidant is stored are respectively increased. Liquid flows.

A portion of the oxidant supplied by the oxidant supply pump 130 is supplied to the combustion chamber 110, and the rest of the oxidant is supplied to the gas generator 140. The thrust control valve 160 adjusts the amount supplied to the gas generator 140.

The thrust control valve 160 controls the amount of fuel supplied to the gas generator 140 according to the pressure of the oxidant supplied to the oxidant bypass pipe 170. The adjusted fuel is introduced into the gas generator 140 through the mixing ratio stabilizer 200.

In addition, the fuel flows from the fuel supply pump 120 to the mixing ratio stabilizer 200 and also to the combustion chamber flow regulator 111. In addition, the oxidant flows from the oxidant supply pump 130 to the thrust control valve 160 and also flows into the combustion chamber oxidant supply valve 115.

In addition, the fuel introduced into the combustion chamber flow regulator 111 is introduced into the combustion chamber 110 which generates propulsion force through the combustion chamber fuel supply valve 112. In addition, the oxidant introduced into the combustion chamber oxidant supply valve 115 flows into the combustion chamber 110. The mixed fuel and oxidant are burned in the combustion chamber 110, and the exhaust gas is blown out through a nozzle (not shown) to obtain a driving force according to the action-reaction principle.

The mixing ratio stabilizer 200 according to the pressure of the oxidant, with reference to FIGS. 2 and 3, having a body 210, a spool guide 220, a diaphragm 230, and a spool 240. It is preferable.

More specifically, the body 210 receives the fuel supplied from the fuel supply pump 120, and the fuel injection hole 211 and the fuel discharge hole 212 for discharging are shown in FIGS. 2 and 3. Likewise, it is formed at a predetermined position. Here, the fuel injection hole 211 is formed at a position corresponding to the fuel supply pump 120 so that the fuel supplied from the fuel supply pump 120 can be injected. In addition, the fuel discharge hole 212 is formed at a position corresponding to the gas generator 140 so that fuel can be discharged to the gas generator 140.

In addition, a through hole 213 may be formed as an oxidant oil supplied with the oxidant supplied to the oxidant bypass pipe 170. In this case, the oxidant flow passage 213 is formed at a position corresponding to the oxidant bypass pipe 170 so that the oxidant flows from the oxidant bypass pipe 170.

The spool guide 220 may be formed in a hollow shape in the body 210, and a first orifice 221 may be formed at a position corresponding to the fuel injection hole 211.

In addition, the diaphragm 230 is formed inside the body 210 and may move in accordance with the oxidant pressure supplied to the oxidant flow passage through hole 213. The diaphragm 230 prevents the fuel flowing into the mixing ratio stabilizer 200 from being mixed with the oxidant flowing into the through hole 213 through the oxidant oil passage, and is an elastic plate.

In addition, the diaphragm 230, as shown in FIGS. 2 and 3, may include a protrusion 231 protruding toward the body 210. The protrusion 231 may further increase the elastic force of the diaphragm 230.

In addition, one end of the spool 240 is coupled to the diaphragm 230, and the spool 240 reciprocates in the spool guide 220 according to the movement of the diaphragm 230. The second orifice 241 is formed at the corresponding position.

In this case, as the diaphragm 230 moves, the penetration areas of the first orifice 221 and the second orifice are changed to control the amount of fuel.

In addition, the body 210 has an insertion groove 214 is formed at a predetermined position of the outer peripheral surface of the diaphragm 230, the sealing member 215 may be inserted into the insertion groove 214.

In addition, the mixing ratio stabilizer 200, the retainer 250 is coupled to one end of the spool guide 220, one end is coupled to the retainer 250, the other end is coupled to the spool 240 260 may be further included.

In addition, the spring 260, one end is coupled to the spool guide 220, the other end is preferably provided with a spring adjustment bolt 261 is coupled to the retainer 260. The spool guide 220 and the spool 240 and the retainer 260 corresponding thereto are preferably in an annular shape concentric with the inner surface of the body 210. Here, the pre-compression length of the spring 260 may be adjusted by moving the retainer 260 from side to side by rotating the spring adjustment bolt 261.

Looking at the operation of the mixed ballast according to a preferred embodiment of the present invention of the above structure, as shown in Figures 1 to 3, when the opening degree of the thrust control valve 160 is widened to the gas generator 140 The flow rate of the oxidant introduced increases, and at the same time, the flow rate of the oxidant flowing into the bypass pipe 170 also increases, so that the increased oxidant may further apply the pressure.

 Thus, the pressure in the wake of the diaphragm 230 may increase and the diaphragm 230 may be bent toward the body 210.

The bent diaphragm 230 pushes out the spool 240, and as shown in FIG. 2, a small amount of the flow path area of the first orifice 221 is blocked by the spool 240, as shown in FIG. 3. As described above, the size of the flow path area of the first orifice 221 and the second orifice 241 is increased. Therefore, the through areas of the first orifice 221 and the second orifice 241 are changed to control the fuel amount, and the flow rate of the fuel may be increased.

In addition, the spring 260 is interposed so that the diaphragm 230 pushes the spool 240 so that the spring 260 contracts as shown in FIG. 3. When the back pressure is reduced again, as shown in FIG. 2, the spring 260 is restored in the longitudinal direction.

Liquid propellant rocket engine according to a preferred embodiment of the present invention according to the above structure can maintain a constant mixing ratio of the propellant flowing into the gas generating unit.

As described above, the liquid propellant rocket engine of the present invention provides the following effects.

First, it is possible to maintain the mixing ratio of the propellant flowing into the gas generator when adjusting the thrust of the engine.

Second, it maintains a stable combustion temperature of the gas generator to increase the reliability of the rocket engine.

Third, the adjustment performance of the mixing ratio stabilizer is improved by the spring and the spring adjustment bolt.

As mentioned above, although this invention was demonstrated by the limited embodiment and drawing, this invention is not limited to this and it is described by the person of ordinary skill in the art to this invention, and below. Various modifications and variations are possible without departing from the scope of the appended claims.

Claims (7)

A combustion chamber; A fuel supply pump for supplying fuel to the combustion chamber; An oxidant supply pump for supplying an oxidant to the combustion chamber; A gas generator for generating a gas by receiving a part of the fuel and the oxidant supplied from the fuel supply unit and the oxidant supply unit; A turbine which receives and rotates the gas generated by the gas generator and drives the fuel supply pump and the oxidant supply pump; A thrust control valve for controlling the amount of oxidant supplied to the gas generator; An oxidant bypass pipe branched at the gas generator side of the thrust control valve; A liquid propellant rocket engine comprising a mixing ratio stabilizer for controlling the fuel supplied to the gas generator in accordance with the oxidant pressure supplied to the oxidant bypass pipe. The method of claim 1, The mixing ratio stabilizer, A body in which a fuel injection hole and a fuel discharge hole for receiving and discharging the fuel supplied from the fuel supply pump are formed at a predetermined position, and a through hole is formed through the oxidant oil through which the oxidant supplied to the bypass pipe is supplied; A spool guide formed in a hollow shape in the body and having a first orifice formed at a predetermined position corresponding to the fuel injection hole and the fuel discharge hole; A diaphragm formed inside the body and moving in accordance with an oxidant pressure supplied to the oxidant passage hole; One end is coupled to the diaphragm, the liquid propellant comprising a spool reciprocating in the spool guide according to the movement of the diaphragm, the second orifice is formed at a predetermined position corresponding to the first orifice Rocket engine. The method of claim 2, As the diaphragm moves, the penetration area of the first orifice and the second orifice is changed to control the amount of fuel. The method of claim 2, The body is a liquid propellant rocket engine, characterized in that the hole is formed in a predetermined position of the outer peripheral surface of the diaphragm, the sealing member is inserted into the hole. The method of claim 2, The diaphragm is a liquid propellant rocket engine, characterized in that it comprises a projection formed to project toward the body. The method of claim 2, The mixing ratio stabilizer, A retainer coupled to one end of the spool guide; One end is coupled to the retainer, the other end is a liquid propellant rocket engine further comprises a spring coupled to the spool. The method of claim 6, The spring has a one end is coupled to the spool guide, the other end has a spring adjustment bolt coupled to the retainer.

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