RU2559224C1 - Liquid-propellant rocket engine (lpre) - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: liquid-propellant rocket engine contains a chamber, a gas generator, pumps, fuel supply pipelines, starting valves, control gas supply pipelines, the electropneumatic valve, the valves tees with inlet unions for control gas, the control working body inlet, an the control gas and the working body outlet are installed in the control gas supply pipelines, between input branch pipes for the control working body of valves tees and fuel supply pipelines downstream the pumps the control working body pipelines are installed. In the valve tee housing the seat from the side of the control gas supply is made, the adapter with the seat from the side of supply of the control working body and the gate with fluoroplastic seal interacting with seats are installed.

EFFECT: design simplification and weight decrease.

2 cl, 2 dwg

Description

The invention relates to a liquid-propellant rocket engine with a chamber, a gas generator, pumps, cryogenic fuel supply pipelines, starting valves, control gas supply pipelines, electro-pneumatic valves (EPC), and is intended to simplify the control system, replacing the control gas supplied to the cryogenic component start valves to open them when starting the LRE, to the control working fluid to hold the start valves in the open position during operation of the LRE and closing the start valves when the LRE is turned off by the pressure drop yayuschego working fluid.

Known liquid propellant rocket engine with a valve (patent RU 2489626, IPC F16K 1/12, F16K 15/02) containing a housing with inlet and outlet pipes, a shutter, a piston.

The disadvantage of this valve is the need to supply and hold the pressure of the control gas from the EPA for the entire time the LRE and the discharge of the control gas to close the valve.

It is well known that for actuating a valve in a liquid propellant rocket, a high pressure control gas cylinder and EPA are used. For pre-start purging of the chamber and the LPRE gas generator, a high-pressure gas cylinder and EPA are also installed, while after the purge in the cylinder, the gas pressure drops sharply. The presence of two cylinders and an additional EPA complicates the design of the rocket engine and increases its mass.

Known liquid propellant rocket engine with a three-way valve (patent RU 2502005, IPC F16K 11/10) containing a housing with inlet, outlet, drainage and control cavities, inlet and drainage valves interconnected via a rod. The drain valve is connected to a piston, which is pressed by a spring.

The disadvantage of this three-way valve is the inoperability of the rubber rings that seal the piston of the control cavity when operating on cryogenic fuels.

Known liquid propellant rocket engine with a valve (patent RU 2502911, IPC F16K 31/22) containing an inlet chamber, an exhaust chamber, an actuator and a control chamber. The valve moves from the closed position to the open when the medium is fed into the control cavity through the orifice plate of the diaphragm.

The disadvantage of this valve is the slow opening of the valve, the complex design of the valve, increased weight.

The known scheme of liquid propellant rocket engines with a pumping fuel supply system (EB Volkov and other liquid rocket engines. M., Voenizdat, 1970, Fig. 0.9, p. 20, 21. - prototype), containing a chamber, gas generator, pumps, pipelines fuel supply, start valves, control gas pipelines from EPK.

The disadvantage of this scheme LRE, adopted as a prototype, is the need to supply and hold the pressure of the control gas from the EPA to the starting valves throughout the entire operation of the LRE and the discharge of the control gas to close the valves, which complicates the design of the LRE and increases its mass.

The aim of the invention is to simplify the LRE scheme by replacing the control gas from the EPC supplied to the start valves to open them when the LRE starts, by the control working fluid to hold the start valves in the open position during the operation of the LRE and to close the start valves when the LRE is turned off by the pressure drop of the control worker body, simplifying the design of the rocket engine, reducing the mass of the rocket engine.

The problem is solved as follows.

In the known scheme of a liquid propellant rocket engine with a fuel delivery system containing a chamber, a gas generator, pumps, fuel supply pipes, start valves, control gas supply pipes, EPCs, according to the invention, tee valves are installed in the control gas supply pipes with fittings for the control gas inlet, control inlet the working fluid, the output of the control gas and the working fluid, while between the nozzles of the input of the control working fluid of the tees and the fuel supply pipes after the pumps installed piping gadgets of the controlling working fluid.

In addition, a seat on the supply side of the control gas is made in the body of the tee valve, an adapter with a seat on the side of the control working fluid, a shutter with fluoroplastic seals interacting with the seats are installed in the body.

The proposed LRE scheme is shown in FIG. 1 and 2,

Where:

1 - camera;

2 - gas generator;

3 - pumps;

4 - fuel supply pipelines;

5 - starting valves;

6 - pipelines for the supply of control gas;

7 - EPA;

8 - valves tees;

9 - pipelines for supplying the control working fluid;

10 - valve body of the tee;

11 - adapter with a saddle;

12 - shutter with fluoroplastic seals;

Input A - input of the control gas;

Input B is the input of the controlling working fluid;

Output B is the output of the control gas and the working fluid.

The LPRE contains a chamber 1, a gas generator 2, pumps 3, fuel supply pipelines 4, start valves 5, control gas supply pipelines 6, EPK 7, control fluid supply pipelines 9 and tee valves 8 having fittings for the control gas inlet A, input the control working fluid B, the output of the control gas and working fluid B and consisting of a valve body of the tee 10, an adapter with a seat 11 and a shutter with fluoroplastic seals 12.

The LRE works as follows: at start-up, gas pressure is supplied to purge the heads of the chamber 1, gas generator 2 and tee valves 8 as control pressure to open the start valves 5. The shutter with fluoroplastic seals 12 moves to fit the adapter 11. The control gas pressure enters into the outlet cavity of the tee valve 8 and then to the pneumatic actuators of the start valves 5. The start valves 5 open and the fuel components enter the chamber 1 and the gas generator 2. The LPRE starts and enters the main mode. The components in the supply pipelines of the control working fluid 9 act on the shutter with fluoroplastic seals 12 of the tee valves 8. After 1-2 seconds after the LRE reaches the main mode, the pressure of the control gas drops and the shutter with fluoroplastic seals 12 returns to its original position. The control pressure of the gas is replaced by the control pressure of the working fluid. This position of the start valves 5 is maintained throughout the entire operation of the engine. When the engine is turned off, the pressure of the control working fluid drops and the start valves 5 are closed.

Since the proposed LRE invention is planned to be used in rocket technology, its parts are made of materials: a bolt with fluoroplastic seals of the tee valve of their bronze BRAZH 9-4 and fluoroplast-4, the tee valve spring is made of 12X18H10T steel, the remaining parts are made of steel 07X16H6.

Thus, the use of this invention allows to expand the possibility of using liquid propellant rocket engines by replacing the control gas supplied to the start valves with the control pressure of the working fluid in mechanical engineering products operating according to the control commands for opening and closing the start valves, simplify the design and reduce weight.

Claims (2)

1. A liquid rocket engine containing a chamber, a gas generator, pumps, fuel supply pipelines, start valves, control gas supply pipelines, an electro-pneumatic valve, characterized in that tee valves are installed in the control gas supply pipelines with fittings for the control gas inlet, control fluid inlet , the output of the control gas and the working fluid, while pipelines are installed between the inlets of the control fluid of the control tees and the fuel supply pipes after the pumps melting working fluid. 2. A liquid-propellant rocket engine according to claim 1, characterized in that a seat on the supply side of the control gas is made in the tee valve body, an adapter with a seat on the supply side of the control working fluid and a shutter with fluoroplastic seals interacting with the seats are installed.

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