阅读说明：本技术 基于液氧膨胀循环的深度变推多次起动液体火箭发动机 (Liquid oxygen expansion cycle-based depth variable-thrust multi-start liquid rocket engine ) 是由 赵剑 马键 邢理想 刘小勇 王猛 陈园飞 李娟� 于 2019-07-03 设计创作，主要内容包括：本发明涉及一种火箭发动机,具体涉及一种基于液氧膨胀循环的深度变推多次起动液体火箭发动机；解决了现有登月火箭发动机性能偏低,推进剂有毒以及增压系统配件复杂的技术问题。一种基于液氧膨胀循环的深度变推多次起动液体火箭发动机,包括推力室、燃气流量调节装置、涡轮泵组、燃料流量调节装置、液氧节流阀、开关阀、第一气氧煤油火炬点火器、第二气氧煤油火炬点火器、氦气控制单元和气氧贮箱；第一气氧煤油火炬点火器设置在推力室的燃烧室上方；涡轮泵组包括依次同轴固连且相互隔离的主涡轮、氧化剂泵、强迫启动涡轮和燃料泵；第二气氧煤油火炬点火器设置在强迫启动涡轮上。(The invention relates to a rocket engine, in particular to a liquid rocket engine started for multiple times by changing depth and pushing based on liquid oxygen expansion cycle; the technical problems that the existing lunar landing rocket engine is low in performance, the propellant is toxic and the accessories of a pressurization system are complex are solved. A liquid rocket engine capable of starting multiple times in a depth variable-push mode based on liquid oxygen expansion circulation comprises a thrust chamber, a gas flow regulating device, a turbo pump set, a fuel flow regulating device, a liquid oxygen throttle valve, a switch valve, a first gas oxygen kerosene torch igniter, a second gas oxygen kerosene torch igniter, a helium control unit and a gas oxygen storage tank; the first gas oxygen kerosene torch igniter is arranged above the combustion chamber of the thrust chamber; the turbopump set comprises a main turbine, an oxidant pump, a forced starting turbine and a fuel pump which are coaxially and fixedly connected in sequence and are mutually isolated; the second kerosene torch igniter is arranged on the forced start turbine.)

1. A liquid rocket engine capable of starting multiple times in a depth variable-push mode based on liquid oxygen expansion circulation comprises a thrust chamber (1), a gas flow regulating device (3), a turbo pump set (4), a fuel flow regulating device (5), a liquid oxygen throttle valve (6), a switch valve (7), a first gas oxygen kerosene torch igniter (8), a second gas oxygen kerosene torch igniter (9) and a helium control unit (11); the thrust chamber (1) comprises a combustion chamber and a nozzle; a spray pipe cooling interlayer is arranged in the spray pipe;

the method is characterized in that:

also comprises a gas oxygen storage tank (2);

the turbopump set (4) comprises a main turbine (405), an oxidant pump (406), a forced start turbine (407) and a fuel pump (408) which are coaxially and fixedly connected and isolated from each other in sequence;

the first gas oxygen kerosene torch igniter (8) is arranged above the combustion chamber of the thrust chamber (1), a first gas oxygen inlet G2 is connected with an outlet (203) of the gas oxygen storage box (2), a kerosene inlet R2 is connected with an outlet of the kerosene storage box, and an outlet of the first gas oxygen kerosene torch igniter is arranged in the combustion chamber of the thrust chamber (1);

the second gas oxygen kerosene torch igniter (9) is arranged on the forced starting turbine (407), a first gas oxygen inlet G3 of the second gas oxygen kerosene torch igniter is connected with an outlet (203) of the gas oxygen storage tank (2), a kerosene inlet R3 of the second gas oxygen kerosene torch igniter is connected with an outlet of the kerosene storage tank, and an outlet of the second gas oxygen kerosene torch igniter is connected with an inlet of the forced starting turbine (407); the outlet of the forced starting turbine (407) is communicated with the outside;

the inlet of the fuel pump (408) is connected with the outlet of the kerosene storage tank, the outlet of the fuel pump (408) is sequentially connected with a fuel flow regulating device (5) and a switch valve (7), and the outlet of the switch valve (7) is connected into a combustion chamber of the thrust chamber (1);

the inlet of the oxidant pump (406) is connected with the outlet of the liquid oxygen storage tank, two outlets of the oxidant pump (406) are provided, one outlet is connected with the oxygen pre-pressurizing turbine driving inlet of the oxygen pre-pressurizing turbine pump, the other outlet is connected with the inlet of the spray pipe cooling interlayer after passing through the liquid oxygen throttle valve (6), the two outlets are evaporated into gas oxygen in the spray pipe cooling interlayer and divided into three paths, one path is connected with the first gas oxygen inlet (201) of the gas oxygen storage tank (2), and the other two paths respectively enter the combustion chamber of the thrust chamber (1) for combustion after passing through the gas flow regulating device (3) and the main turbine (405);

a second gas-oxygen inlet (202) of the gas-oxygen storage tank (2) is connected with an outlet of the high oxygen-enriched fuel gas storage tank;

the helium control unit (11) comprises a helium storage tank (1101), a switch and pressure reducing valve group (1102), two liquid oxygen pipeline controllers (DC1, DC2) and two kerosene pipeline controllers (DC3, DC 4);

two air control ports (C1 and C2) of the liquid oxygen throttle valve (6) are respectively connected with two liquid oxygen pipeline controllers (DC1 and DC 2);

two pneumatic control ports (C3 and C4) of the switch valve (7) are respectively connected with two kerosene pipeline controllers (DC3 and DC 4).

2. The liquid oxygen expansion cycle based variable depth push multiple start liquid rocket engine of claim 1 wherein: the gas flow regulating device (3) and the fuel flow regulating device (5) are both throttle valves.

3. The liquid oxygen expansion cycle based variable depth push multiple start liquid rocket engine of claim 1 wherein: the gas flow regulating device (3) and the fuel flow regulating device (5) are both flow regulators.

4. The liquid oxygen expansion cycle based variable depth push multiple start liquid rocket engine of claim 1 or 2 or 3 wherein: the liquid oxygen throttle valve (6) and the switch valve (7) are both electric air valves.

5. The liquid oxygen expansion cycle based variable depth push multiple start liquid rocket engine of claim 4 wherein: the thrust chamber nozzle area ratio is 200.

6. The liquid oxygen expansion cycle based variable depth push multiple start liquid rocket engine of claim 4 wherein: the nozzle cooling interlayer is arranged at a part with an area ratio of less than 12; the rest parts except the nozzle cooling interlayer are made of ablative composite materials.

7. The liquid oxygen expansion cycle based variable depth push multiple start liquid rocket engine of claim 6 wherein: the thrust chamber (1) is provided with a mechanical positioning pin injector.

Technical Field

The invention relates to a rocket engine, in particular to a liquid rocket engine started multiple times by changing depth and pushing based on liquid oxygen expansion cycle.

Background

In the process of lunar exploration and (manned) lunar landing tasks, in order to realize lunar orbit transfer and lunar soft landing, the engine is required to have the performances of multiple starting, working condition depth adjustment (10% -100%), long-time working (1000s), reliable working and the like.

The American Apollo lunar descent engine adopts a squeezing type system with hydrazine and dinitrogen tetroxide, and the engine of the type has simple structure, high reliability, low performance and toxic propellant.

The former soviet union proposed an "L-3" lunar chamber power system, in the form of an integration of a descent engine and an ascent engine, in which the main engine uses a gasifier cycle of unsymmetrical dimethylhydrazine and dinitrogen tetroxide, which is an open cycle, of moderate performance but relatively complex construction.

The 7500N lunar variable thrust engine proposed by China adopts an extrusion type system of unsymmetrical dimethylhydrazine and dinitrogen tetroxide and adopts a pintle injector to realize variable thrust, and the engine is simple and reliable, but the performance of the engine is inferior to that of a closed circulation system.

Disclosure of Invention

The invention provides a liquid rocket engine capable of starting multiple times by changing depth and pushing based on liquid oxygen expansion cycle, and aims to solve the technical problems that the existing lunar landing rocket engine is low in performance, a propellant is toxic and a pressurizing system is complex in fitting.

The technical solution of the invention is as follows:

a liquid rocket engine capable of starting multiple times in a depth variable-push mode based on liquid oxygen expansion circulation comprises a thrust chamber, a gas flow regulating device, a turbo pump set, a fuel flow regulating device, a liquid oxygen throttle valve, a switch valve, a first gas oxygen kerosene torch igniter, a second gas oxygen kerosene torch igniter and a helium control unit; the thrust chamber comprises a combustion chamber and a nozzle; a spray pipe cooling interlayer is arranged in the spray pipe; it is characterized in that:

also comprises a gas oxygen storage tank;

the turbopump set comprises a main turbine, an oxidant pump, a forced starting turbine and a fuel pump which are coaxially and fixedly connected and mutually isolated in sequence;

the first gas oxygen kerosene torch igniter is arranged above the combustion chamber of the thrust chamber, a first gas oxygen inlet G2 of the first gas oxygen torch igniter is connected with an outlet of the gas oxygen storage tank, a kerosene inlet R2 of the first gas oxygen torch igniter is connected with an outlet of the kerosene storage tank, and an outlet of the first gas oxygen torch igniter is arranged in the combustion chamber of the thrust chamber;

the second gas oxygen kerosene torch igniter is arranged on the forced starting turbine, a first gas oxygen inlet G3 of the second gas oxygen kerosene torch igniter is connected with an outlet of the gas oxygen storage box, a kerosene inlet R3 of the second gas oxygen kerosene torch igniter is connected with an outlet of the kerosene storage box, and an outlet of the second gas oxygen kerosene torch igniter is connected with an inlet of the forced starting turbine; the outlet of the forced starting turbine is communicated with the outside;

the inlet of the fuel pump is connected with the outlet of the kerosene storage tank, the outlet of the fuel pump is sequentially connected with a fuel flow regulating device and a switch valve, and the outlet of the switch valve is connected into a combustion chamber of the thrust chamber;

the inlet of the oxidant pump is connected with the outlet of the liquid oxygen storage tank, the outlet of the oxidant pump is two, one outlet is connected with the oxygen pre-pressing turbine driving inlet of the oxygen pre-pressing turbine pump, the other outlet is connected with the inlet of the spray pipe cooling interlayer after passing through the liquid oxygen throttle valve, the mixture is evaporated into gas oxygen in the spray pipe cooling interlayer and then divided into three paths, one path is connected with the first gas oxygen inlet of the gas oxygen storage tank, and the other two paths respectively enter the combustion chamber of the thrust chamber for combustion after passing through the gas flow regulating device and the main turbine;

a second gas-oxygen inlet of the gas-oxygen storage tank is connected with an outlet of the high oxygen-enriched fuel gas storage tank;

the helium control unit comprises a helium storage tank, a switch, a pressure reducing valve group, two liquid oxygen pipeline controllers (DC1 and DC2) and two kerosene pipeline controllers (DC3 and DC 4);

two air control ports (C1 and C2) of the liquid oxygen throttle valve are respectively connected with two liquid oxygen pipeline controllers (DC1 and DC 2);

two pneumatic control ports (C3 and C4) of the switch valve are respectively connected with two kerosene pipeline controllers (DC3 and DC 4).

Further, the gas flow regulating device and the fuel flow regulating device are both throttle valves.

Further, the gas flow regulating device and the fuel flow regulating device are both flow regulators.

Further, the liquid oxygen throttle valve and the switch valve are both electric gas valves.

Further, the thrust chamber nozzle area ratio is 200.

Further, the nozzle cooling interlayer is arranged at a part with an area ratio smaller than 12; the rest part of the spray pipe adopts ablation composite material.

Further, the thrust chamber is provided with a mechanical positioning pin injector.

Compared with the prior art, the invention has the beneficial effects that:

1. based on the principle of liquid oxygen regeneration cooling expansion circulation, the invention fully utilizes the advantages of large flow of gas oxygen and relatively low flow resistance of regeneration cooling, adopts liquid oxygen and kerosene as propellants, utilizes the liquid oxygen to carry out regeneration cooling on the thrust chamber, and the liquid oxygen is evaporated after absorbing heat to form gas oxygen with a certain temperature to drive a main turbine in a turbine pump set to do work and pressurize the propellants; the extrusion type extrusion die does not need to be provided with a precombustion chamber, has a simple structure, and has higher performance than an extrusion type system.

2. The gas oxygen pipeline and the kerosene pipeline are respectively provided with a gas flow regulating device and a fuel flow regulating device, and the thrust chamber is provided with a mechanical positioning pintle injector, wherein the gas flow regulating device can directly guide gas oxygen from the front of the main turbine to the back of the main turbine so as to regulate the power of the main turbine, so that the working condition of the invention can be deeply regulated; the fuel flow adjusting device is used for adjusting the kerosene flow in the working condition depth adjusting project, and ensures that the combustion stability of the thrust chamber is good and the cooling is reliable under low working conditions.

3. The thrust chamber of the invention adopts a gas oxygen kerosene torch igniter, and gas oxygen and kerosene for ignition are both from other devices, so that the invention can realize reliable starting (ignition) for many times, and the starting times are not less than 20 times.

4. The invention adopts a self-filling type gas oxygen storage tank which is used for storing part of gas oxygen obtained after liquid oxygen is evaporated and preparing for multiple ignition.

5. The turbopump set adopted by the invention comprises a forced starting turbine, and when the turbopump set is started, the second oxygen kerosene torch ignition device generates gas to drive the forced starting turbine to start, so that the quick starting can be realized.

6. The propellant of the invention is liquid oxygen and kerosene, and is nontoxic and environment-friendly.

Drawings

FIG. 1 is a schematic block diagram of one embodiment of the present invention;

the reference signs are:

1-thrust chamber, 2-gas oxygen storage tank, 201-first gas oxygen inlet, 202-second gas oxygen inlet, 203-outlet, 3-gas flow regulating device, 4-turbopump set, 405-main turbine, 406-oxidant pump, 407-forced starting turbine, 408-fuel pump, 5-fuel flow regulating device, 6-liquid oxygen throttle valve, 7-switch valve, 8-first gas oxygen kerosene torch igniter, 9-second gas oxygen kerosene torch igniter, 10-ball valve, 11-helium control unit, 1101-helium storage tank, 1102-switch and pressure reducing valve set.

Detailed Description

The invention is further described with reference to the following figures and specific embodiments.

Referring to fig. 1, the liquid rocket engine includes a thrust chamber 1, a gas oxygen tank 2, a gas flow regulating device 3, a turbo-pump set 4, a fuel flow regulating device 5, a liquid oxygen throttle valve 6, an on-off valve 7, a first gas oxygen kerosene torch igniter 8 and a second gas oxygen kerosene torch igniter 9, and a helium gas control unit 11. The thrust chamber 1 comprises a combustion chamber and a spray pipe, a spray pipe cooling interlayer is arranged in the spray pipe, and the first gas oxygen kerosene torch igniter 8 is arranged in the combustion chamber of the thrust chamber 1. The outlet of the gas oxygen storage tank 2 is provided with a ball valve 10.

The turbo-pump group 4 includes a main turbine 405, an oxidizer pump 406, a forced start turbine 407, and a fuel pump 408, which are coaxially attached and isolated from each other in this order.

The inlet of the oxidant pump 406 is connected with the outlet of the liquid oxygen storage tank, two outlets of the oxidant pump 406 are provided, one outlet is connected with the oxygen pre-pressurizing turbine driving inlet of the oxygen pre-pressurizing turbine pump, and the other outlet is connected with the inlet of the liquid oxygen throttle valve 6; the outlet of the liquid oxygen throttle valve 6 is connected with a spray pipe cooling interlayer of the thrust chamber 1; the outlet of the thrust chamber 1 is respectively connected with the first gas-oxygen inlet 201 of the gas-oxygen storage tank 2, the inlet of the gas flow regulating device 3 and the inlet of the turbo pump set 4. A second gas-oxygen inlet 202 of the gas-oxygen storage tank 2 is connected with the high oxygen-enriched gas storage tank, and the outlet of the gas-oxygen storage tank 2 is respectively connected with a first gas-oxygen inlet G2 of a first gas-oxygen kerosene torch igniter 8 and a first gas-oxygen inlet G3 of a second gas-oxygen kerosene torch igniter 9; a kerosene inlet R2 of the first gas oxygen kerosene torch igniter 8 and a kerosene inlet R3 of the second gas oxygen kerosene torch igniter 9 are respectively connected with an outlet of the kerosene storage tank; the outlet of the igniter 8 of the first gas-oxygen kerosene torch is arranged in the combustion chamber of the thrust chamber 1.

The inlet of the fuel pump 408 is connected to the outlet of the kerosene tank, the outlet of the fuel pump 408 is connected to the inlet of the fuel flow rate adjusting device 5, the outlet of the fuel flow rate adjusting device 5 is connected to the inlet of the on-off valve 7, and the outlet of the on-off valve 7 is connected to the combustion chamber of the thrust chamber 1.

The inlet of the forced starting turbine 407 is connected with the outlet of the second kerosene torch igniter 9, and the outlet of the forced starting turbine 407 is communicated with the outside.

The helium control unit 11 comprises a helium storage tank 1101, a switch and pressure reducing valve group 1102, two liquid oxygen pipeline controllers DC1 and DC2, two kerosene pipeline controllers DC3 and DC 4;

two air control ports C1 and C2 of the liquid oxygen throttle valve 6 are respectively connected with two liquid oxygen pipeline controllers DC1 and DC 2; two pneumatic control ports C3 and C4 of the switch valve 7 are respectively connected with two kerosene pipeline controllers DC3 and DC 4.

In the embodiment, the gas flow regulating device 3 and the fuel flow regulating device 5 are both flow regulators, the liquid oxygen throttle valve 6 and the switch valve 7 are both electric gas valves, the area ratio of the thrust chamber spray pipe is 200, the spray pipe cooling interlayer is arranged at the part with the area ratio smaller than 12, and the rest parts of the spray pipe are made of ablation composite materials. This embodiment employs a thrust chamber with a mechanically positioned pintle injector.

The working principle of the engine is as follows:

the second kerosene torch igniter 9 is ignited, and the forced start turbine 407 is started, which drives the main turbine 405, the oxidizer pump 406 and the fuel pump 408 to start.

The low-temperature liquid oxygen in the liquid oxygen storage tank enters from an inlet of the oxidant pump 406, then enters a spray pipe cooling interlayer of the thrust chamber 1 through the liquid oxygen throttle valve 6, regeneratively cools the thrust chamber 1, and is evaporated after absorbing heat to form gas oxygen with a certain temperature and then is divided into three parts, wherein most of the gas oxygen is used for driving the main turbine 405 to do work, and the rest of the gas oxygen is used for being injected into the gas oxygen storage tank 2 or enters a combustion chamber of the thrust chamber 1 for combustion after passing through the gas flow regulating device 3. The oxygen used to drive the main turbine 405 to do work also enters the combustion chamber of the thrust chamber 1 for combustion. The main turbine 405 is stopped by forcibly starting the turbine 407 after stabilizing its operation. The gas flow regulator 3 can lead the oxygen from the front of the main turbine 405 to the back of the main turbine 405 directly, thereby regulating the power of the main turbine 405, and the working condition of the engine can be deeply regulated. Kerosene in the kerosene storage tank enters from the inlet of the fuel pump 408, passes through the fuel flow regulating device 5 and the switch valve 7, enters the combustion chamber of the thrust chamber 1, and is mixed and combusted with gas oxygen in the combustion chamber of the thrust chamber 1.

The gas-oxygen storage tank 2 supplies gas oxygen for the first gas-oxygen kerosene torch igniter 8 and the second gas-oxygen kerosene torch igniter 9, and the kerosene storage tank supplies kerosene for the first gas-oxygen kerosene torch igniter 8 and the second gas-oxygen kerosene torch igniter 9. The first gas oxygen kerosene torch igniter 8 and the second gas oxygen kerosene torch igniter 9 can realize reliable ignition for a plurality of times, and the starting times are not less than 20 times. The gas oxygen storage tank 2 is used for storing regenerative cooling gas oxygen and storing gas oxygen for multiple ignition.

The helium gas control unit 11 controls the on/off of the liquid oxygen throttle valve 6 and the on/off valve 7.

The above description is only an embodiment of the present invention, and is not intended to limit the scope of the present invention, and all equivalent structural changes made by using the contents of the present specification and the drawings, or applied directly or indirectly to other related technical fields, are included in the scope of the present invention.