Liquid propellant rocket power plant

FIELD: liquid propellant rocket power plants with turbopump units.

SUBSTANCE: the liquid propellant rocket power plant having liquid-hydrogen and liquid-oxygen tanks with booster pumps and main turbopump units uses also an electrochemical generator with an oxygen inlet and outlet and a hydrogen inlet and outlet, oxygen ejector, hydrogen ejector and two electric motors, one of which is connected to the shaft of the oxygen booster pump, and the other-to the shaft of the hydrogen booster pump, the oxygen inlet of the electrochemical generator is connected through a pipe to the gas cushion of tank with liquid oxygen, and the outlet-to the inlet of oxygen ejector, whose outlet is connected to the gaseous oxygen supply pipe to the reaction chamber: the hydrogen inlet of the electrochemical generator is connected through a pipe to the gas, cushion of the tank with liquid hydrogen, and the outlet is connected to the inlet of the hydrogen ejector, whose outlet is connected to the gaseous hydrogen supply line to the reaction chamber.

EFFECT: provided reliable multiple starting of the liquid propellant rocket power plant.

1 dwg

 

The invention relates to a liquid-propellant rocket propulsion plants (lprps) with turbopump units (TNA).

Known lprps [1], including tanks with liquid components, for example with hydrogen and oxygen gas cushions in each tank, a jet chamber units turbopump feed systems, mains gas and liquid fuel components with the nozzle for connecting the drive turbine to the pressure of the starting gas.

The use of compressed gas for the initial promotion of the turbopump Assembly (TNA) in the known technical solution is to run the liquid propellant rocket engine as applied to modern high-performance engines, made by the scheme with afterburning gas jet (traction) the camera has great disadvantages. The reason for this is the low pressure drop characteristic of the drive turbine of the main TNA, as a consequence, the supply of compressed gas to the main turbine for the known technical solution in the process of filling the fuel lines in the absence of back pressure leads to a very quick promotion rotor TNA with the inevitable cavitation breakdown of the fuel pumps. As a result, the start of the aircraft (LA) with the liquid propellant rocket engine is terminated by an accident.

To improve reliability in the liquid propellant rocket engine, taken as a prototype [2], including tanks with liquid components, for example with hydrogen IC oxygen, with gas cushions in each tank, jet chamber, in the line of flow of the liquid fuel components in the reactive chamber has consistently set the booster and main pumps are mounted with their shafts of turbines. The entrance of the main turbine connected to a generator, and the output from the reactive chamber and the booster turbine is connected to a source of inrush of high pressure gas and socket power booster turbine.

Starting the high-pressure gas, according to the prototype, serves on the turbine booster pump. This eliminates cavitation breakdown of the fuel pumps, but does not preclude cavitation breakdown booster pumps, which can also cause a crash.

A significant disadvantage of the prototype is the inability multiple engine start. This is because the compressed gas reserves are limited overall dimensions of the space object.

The present invention solves the technical problem of providing a reliable multiple launch the liquid propellant rocket engine. The expected technical result consists in the fact that the launch of the liquid propellant rocket engine is not associated with the presence of high-pressure gas source, which can lead to cavitation mode of operation of the pump and allows you to provide multiple starting of the engine, so as not associated with stocks of high pressure gas, which are limited resources.

Defined the technical problem is solved by in liquid rocket propulsion system, including tanks of liquid hydrogen and liquid oxygen from the gas cushions in each tank, mains supply of liquid oxygen and liquid hydrogen in the reactive chamber, with successively installed in these lines the valves supplying hydrogen and oxygen, respectively booster pumps hydrogen and oxygen, and the main pumps of hydrogen and oxygen, are installed on the shafts of the turbine hydrogen and oxygen backbone hydrogen yield of the reactive chamber to which is connected a pipeline with a valve hydrogen, attached with a gas cushion tank of liquid hydrogen, and pipelines, coupled with the inputs to the generators of hydrogen and oxygen, the outputs of which are connected by tubes to the inputs of turbines for each component; the outputs of the turbines are connected by a supply pipe components in the reactive chamber, the backbone oxygen outlet of the reactive chamber to which is connected a pipeline with a valve oxygen, attached with a gas cushion tank of liquid oxygen and pipelines, coupled with the inputs to the generators of hydrogen and oxygen, the outputs of which are connected by tubes to the inputs of turbines for each component entered the electrochemical generator with inlet and outlet oxygen and entry and exit of hydrogen, the ejector oxygen, e is the sector of hydrogen and two of the motor, one of which is connected to the shaft of the booster pump oxygen and the other with the shaft of the booster pump hydrogen, and the entrance of the electrochemical oxygen generator is connected to the inlet of oxygen in an electrochemical generator with a gas cushion tank with liquid oxygen, and the output of the piped output of the oxygen from the electrochemical generator to the input of the ejector oxygen, the output of which is connected to the pipe feeding the gaseous oxygen; hydrogen electrochemical generator is connected to the inlet of the hydrogen in the electrochemical generator with a gas cushion tank with liquid hydrogen, and the output is connected by a pipeline release of hydrogen from the electrochemical generator to the input of the ejector hydrogen, the output of which is connected to the pipeline supplying gaseous hydrogen

The drawing shows a functional diagram of the liquid propellant rocket engine, which includes:

1 - electrochemical generator (ECG);

2 - gas cushion tank with liquid hydrogen;

3 - gas cushion tank with liquid oxygen;

4 - tank of liquid hydrogen;

5 - tank liquid oxygen;

6 - supply line to the liquid hydrogen;

7 - line supply of liquid oxygen;

8 - supply valve hydrogen;

9 - valve oxygen;

10 - booster pump hydrogen;

11 - booster pump oxygen;

12 - the main pump hydrogen;

13 - main pump oxygen;

14 - motor;

15 - motor;

16 - turbine hydrogen;

17 - turbine oxygen;

18 - the hydrogen gas generator;

19 - oxygen gas generator;

20 - supply line hydrogen;

21 - pipeline supply oxygen

22 - backbone hydrogen yield;

23 - the backbone oxygen outlet;

24 - valve hydrogen;

25 - valve oxygen;

26 - pipeline;

27 - pipeline;

28 - ejector hydrogen;

29 - ejector oxygen;

30 - chute;

31 - nozzle;

32 - pipeline;

33 - pipeline;

34 - reactive Luggage.

The liquid propellant rocket engine contains electrochemical generator 1, the input of hydrogen which is connected by a pipe 32 with a gas cushion 2 tank with liquid hydrogen 4 and oxygen intake pipe 33 with a gas cushion 3 tank with liquid oxygen 5. On-line supply of liquid hydrogen 6 in the reactive chamber 34 sequentially installed valve of hydrogen supply 8, the booster pump hydrogen 10 and the main pump hydrogen 12. On-line supply of liquid oxygen 7 in the reactive chamber 34 sequentially installed valve oxygen supply 9, the booster pump oxygen 11 and the main pump oxygen 13.

To the shaft of the booster pump hydrogen 10 is connected to the motor 14. The entrance of the turbine hydrogen 16 is connected by a pipe 30 with o the house of the hydrogen gas generator 18, and out - through the supply line 20 hydrogen reactive with the camera 34.

To the shaft of the booster pump oxygen 11 is connected to the motor 15. The turbine inlet oxygen 17 is connected by a pipe 31 with the oxygen output oxygen gas generator 19, and the output through the pipeline oxygen supply 21 with a reactive chamber 34.

To the inputs of the oxygen gas generator 19 receives a small part of the hydrogen highway exit hydrogen 22 and the main part of the oxygen in the backbone oxygen outlet 23.

To the inputs of the hydrogen gas generator 18 receives a minor portion of oxygen in the backbone oxygen outlet 23 and the main part of the hydrogen highway exit hydrogen 22. The pipe 26 is connected through the ejector hydrogen 28 with the supply line 20 hydrogen.

The pipe 27 is connected through the ejector oxygen 29 with the pipeline oxygen supply 21. The valve of the oxygen 25 combines the backbone oxygen outlet 23 with a gas cushion tank with liquid oxygen 3.

The valve 24 hydrogen combines backbone hydrogen yield 22 with a gas cushion tank with liquid hydrogen 2.

The liquid propellant rocket engine works as follows. On the command "start," open the supply valve of the hydrogen 8 and the valve oxygen supply 9, and liquid hydrogen from the tank of liquid hydrogen 4, under the action of gaseous hydrogen in the gas cushion tank with liquid hydrogen 2, for alreet the supply line to the liquid hydrogen 6 and booster pump hydrogen 10, and liquid oxygen from a tank of liquid oxygen 5, under the action of gaseous oxygen in the gas cushion tank with liquid oxygen 3, fills the supply line to the liquid oxygen 7 and the booster pump oxygen 11. Then include the electric motor 14 on the shaft which is installed booster pump hydrogen 10, and the motor 15, the shaft of which is mounted booster pump oxygen 11.

Hydrogen from a tank of liquid hydrogen 4 starts to arrive in the reactive chamber 34 and then through line output 22 hydrogen in the hydrogen gas generator 18. In this gas generator through the pipeline output oxygen 23 receives a given amount of oxygen. The fuel mixture is ignited, forming a gaseous mixture with a large excess of hydrogen, which is supplied through pipe 30 to the inlet of the turbine hydrogen 16. Resulting in turbine hydrogen 16, on the shaft which is the main pump hydrogen 12 begins to rotate and the hydrogen will flow through line supply of liquid hydrogen 6 in the reactive chamber 34 and then through line output 22 hydrogen in the hydrogen gas generator 18 is already under the influence of the two pumps 10 and 12.

As a result of this increased quantity of the fuel mixture fed to the hydrogen gas generator 18. Turbine hydrogen 16, on the shaft which is the main pump hydrogen 12 begins to rotate with bol is our speed, reaching the specified required values, and the gaseous mixture with a large excess of hydrogen and high pressure begins to act on the supply line 20 hydrogen in the reactive chamber 34.

The same thing happens on-line oxygen. Oxygen from a tank of liquid oxygen 5 starts to arrive in the reactive chamber 34 and further along the backbone oxygen outlet 23 in the oxygen gas generator 19. In this gas generator according to the piping of the hydrogen release 22 receives a specified amount of hydrogen.

The fuel mixture flowing in the oxygen gas generator 19, is ignited, forming a gaseous mixture with a large excess of oxygen, which is supplied through pipe oxygen 31 to the input of the turbine oxygen 17.

Resulting in a turbine of oxygen 17, on the shaft which is the main pump oxygen 13 begins to rotate and oxygen starts flowing through line supply of liquid oxygen 7 in the reaction chamber 34 and further along the backbone oxygen outlet 23 in the oxygen gas generator 19 is already under the influence of the two pumps 11 and 13.

As a result of this increased quantity of the fuel mixture fed to the gasifier oxygen 19. Turbine oxygen 17 on the shaft which is the main pump oxygen 13 begins to rotate faster, reaching the specified required values, and the gaseous mixture with a large what sitcom hydrogen and high pressure begins to act on the pipeline oxygen supply 21 in the reactive chamber 34.

In the reactive chamber 34 gaseous mixture with an excess of hydrogen supplied through a supply line 20 hydrogen, and gaseous mixture with an excess of oxygen coming through the pipeline oxygen supply 21, ignited, creating a jet thrust and turning into vapor liquid hydrogen filling line output 22 hydrogen and liquid oxygen filling the backbone oxygen outlet 23. This opens the valve 24 hydrogen, gaseous filling hydrogen gas cushion 2 tank with liquid hydrogen 4, and the valve of the oxygen 25, filling gaseous oxygen gas cushion 3 tank with liquid oxygen 5.

An excessive amount of gaseous hydrogen and oxygen allows the electrochemical generator 1 can operate in forced mode, producing more electricity, flushing heat and water formed in the reaction of compounds of oxygen with hydrogen via pipeline 26 of the hydrogen release from the ECG and the pipe 27 to the output of the oxygen from the ECG. Heat the reaction products of the electrochemical generator (water vapor), the hydrogen passed through the ejector 28 hydrogen and oxygen is blown through the ejector oxygen 29, proceed through pipelines 26 and 27 of hydrogen and oxygen in the reactive chamber 34, which allows to increase the jet thrust of the engine.

Described in a specific example of the liquid jet, the Chairman setting allows quick engagement lprps in work, that saves a liquid rocket fuel of the aircraft. Along with this prevents the possibility of abrupt acceleration TNA unfilled liquid fuel pumps, which ensures reliable starting lprps without disruption of the operation of the pumps and destruction of the material and to increase the jet thrust of the engine. This is the technical result from the application of the invention.

Sources of information

1. Gahan - Design and design of liquid propellant rocket engines. M.: Mashinostroenie, 1989, s-69.

2. Patent RU 2084677, MPK F 02 K 9/48 from 20.07.97.

Liquid rocket propulsion installation including tanks of liquid hydrogen and liquid oxygen from the gas cushions in each tank, mains supply of liquid oxygen and liquid hydrogen in the reactive chamber to successively installed in these lines the valves supplying hydrogen and oxygen, respectively booster pumps hydrogen and oxygen and main pumps of hydrogen and oxygen, are installed on the shafts of the turbine hydrogen and oxygen backbone hydrogen yield of the reactive chamber to which is connected a pipeline with a valve hydrogen, attached with a gas cushion tank of liquid hydrogen, and pipelines, coupled with the inputs to the generators of hydrogen and oxygen, the outputs of which are connected connections with inputs of the for each component; the outputs of the turbines are connected by a supply pipe components in the reactive chamber, the backbone oxygen outlet of the reactive chamber to which is connected a pipeline with a valve oxygen, attached with a gas cushion tank of liquid oxygen, and pipelines, coupled with the inputs to the generators of hydrogen and oxygen, the outputs of which are connected by tubes to the inputs of turbines for each component, characterized in that it introduced an electrochemical generator with inlet and outlet oxygen and entry and exit of hydrogen, the ejector oxygen, the ejector hydrogen and two electric motors, one of which is connected to the shaft of the booster pump oxygen and the other with the shaft of the booster pump hydrogen, and the entrance of the electrochemical oxygen generator is connected by a pipe with a gas cushion tank with liquid oxygen, and the output piped to the inlet of the ejector oxygen, the output of which is connected to the supply line of oxygen; hydrogen electrochemical generator is connected by a pipe with a gas cushion tank with liquid hydrogen, and the output piped to the inlet of the ejector hydrogen, the output of which is connected to the supply line of hydrogen.



 

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