阅读说明：本技术 一种航天发射场液氢过冷度获取系统 (System for acquiring supercooling degree of liquid hydrogen of space launching field ) 是由 王磊 上官石 刘柏文 厉彦忠 谢福寿 马原 于 2020-04-22 设计创作，主要内容包括：一种航天发射场液氢过冷度获取系统,包括液氢储罐,液氢储罐的顶部增压口通过阀门和高压氦气瓶出口连接；液氢储罐底部出口通过循环泵连接氦-氢换热器的液氢侧入口,氦-氢换热器的液氢侧出口通过回流止回阀连接液氢储罐顶部回流口；氦-氢换热器的氦气侧出口通过冷氦压缩机连接液氢浴式换热器的氦气侧入口,液氢浴式换热器的氦气侧出口通过节流阀连接氦-氢换热器氦气侧入口；液氢浴式换热器的液氢入口通过浮子调节阀与液氢储槽底部出口连接,液氢浴式换热器的氢气出口经氢气泄流阀排空；本发明利用发射场大量存在的液氢冷源实施预冷,结合冷氦压缩机,可规模化实现大过冷度液氢的发射场现场制备；设备投资与改造成本低,易于工程实现。(A space launch field liquid hydrogen supercooling degree obtaining system comprises a liquid hydrogen storage tank, wherein a top pressurizing port of the liquid hydrogen storage tank is connected with an outlet of a high-pressure helium bottle through a valve; the outlet at the bottom of the liquid hydrogen storage tank is connected with the liquid hydrogen side inlet of the helium-hydrogen heat exchanger through a circulating pump, and the liquid hydrogen side outlet of the helium-hydrogen heat exchanger is connected with the top reflux port of the liquid hydrogen storage tank through a reflux check valve; a helium side outlet of the helium-hydrogen heat exchanger is connected with a helium side inlet of the liquid-hydrogen bath type heat exchanger through a cold helium compressor, and a helium side outlet of the liquid-hydrogen bath type heat exchanger is connected with a helium side inlet of the helium-hydrogen heat exchanger through a throttle valve; a liquid hydrogen inlet of the liquid hydrogen bath type heat exchanger is connected with an outlet at the bottom of the liquid hydrogen storage tank through a float adjusting valve, and a hydrogen outlet of the liquid hydrogen bath type heat exchanger is emptied through a hydrogen gas leakage valve; the invention uses the liquid hydrogen cold source existing in the transmitting field in large quantity to implement precooling, and can realize the field preparation of the transmitting field of the liquid hydrogen with large supercooling degree in large scale by combining the cold helium compressor; the equipment investment and the reconstruction cost are low, and the engineering realization is easy.)

1. The utility model provides a space launch field liquid hydrogen super-cooling degree obtains system, includes liquid hydrogen storage tank (5), its characterized in that: a top pressurizing port of the liquid hydrogen storage tank (5) is connected with an outlet of a high-pressure helium bottle (10) through a back pressure regulating valve (8) and a pressure release valve (9); an outlet at the bottom of the liquid hydrogen storage tank (5) is connected with an inlet of a circulating pump (6), an outlet of the circulating pump (6) is connected with a liquid hydrogen side inlet of the helium-hydrogen heat exchanger (4), a liquid hydrogen side outlet of the helium-hydrogen heat exchanger (4) is connected with an inlet of a backflow check valve (7), and an outlet of the backflow check valve (7) is connected with a backflow port at the top of the liquid hydrogen storage tank (5);

a helium side outlet of the helium-hydrogen heat exchanger (4) is connected with an inlet of a cold helium compressor (1), an outlet of the cold helium compressor (1) is connected with a helium side inlet of a liquid hydrogen bath type heat exchanger (2), a helium side outlet of the liquid hydrogen bath type heat exchanger (2) is connected with an inlet of a throttling valve (3), and an outlet of the throttling valve (3) is connected with a helium side inlet of the helium-hydrogen heat exchanger (4);

the liquid hydrogen inlet of the liquid hydrogen bath type heat exchanger (2) is connected with the outlet at the bottom of the liquid hydrogen storage tank (11) through a floater adjusting valve (12), and the hydrogen outlet of the liquid hydrogen bath type heat exchanger (2) is emptied through a first hydrogen gas drain valve (13).

2. The space launch field liquid hydrogen supercooling degree obtaining system of claim 1, wherein: a recooling device (14) is additionally arranged, a first helium inlet of the recooling device (14) is connected with a helium side outlet of the helium-hydrogen heat exchanger (4), a first helium outlet of the recooling device (14) is connected with an inlet of a cold helium compressor (1), an outlet of the cold helium compressor (1) is connected with a helium side inlet of a liquid hydrogen bath heat exchanger (2), a helium side outlet of the liquid hydrogen bath heat exchanger (2) is connected with a second helium inlet of the recooling device (14), a second helium outlet of the recooling device (14) is connected with an inlet of a throttling valve (3), and an outlet of the throttling valve (3) is connected with a helium side inlet of the helium-hydrogen heat exchanger (4).

3. The space launch field liquid hydrogen supercooling degree obtaining system of claim 1, wherein: placing the helium-hydrogen heat exchanger (4) in the liquid hydrogen storage tank (5), and directly supercooling liquid hydrogen in the liquid hydrogen storage tank (5) by using cold helium gas; the outlet of the throttle valve (3) is connected with the helium side inlet of the helium-hydrogen heat exchanger (4), and the helium side outlet of the helium-hydrogen heat exchanger (4) is connected with the inlet of the cold helium compressor (1); the outlet at the bottom of the liquid hydrogen storage tank (5) is connected with the inlet of a circulating pump (6), the outlet of the circulating pump (6) is connected with the inlet of a backflow check valve (7), and the outlet of the backflow check valve (7) is connected with the backflow port at the top of the liquid hydrogen storage tank (5).

4. The space launch field liquid hydrogen supercooling degree obtaining system according to claim 3, wherein the space launch field liquid hydrogen supercooling degree obtaining system comprises: and the helium-hydrogen heat exchanger (4) is wound on the outer surface of the inner shell of the liquid hydrogen storage tank (5), and the cold helium gas exchanges heat with the shell of the liquid hydrogen storage tank (5) to realize liquid hydrogen supercooling and cold insulation.

5. The utility model provides a space launch site liquid hydrogen super-cooling degree obtains system, adopts liquid hydrogen filling process to realize big super-cooling degree and obtains which characterized in that: the device comprises a liquid hydrogen storage tank (5), wherein a pressurizing outlet at the bottom of the liquid hydrogen storage tank (5) is connected with an inlet of a pressurizing and draining valve (15), an outlet of the pressurizing and draining valve (15) is connected with an inlet of an air bath type vaporizer (16), an outlet of the air bath type vaporizer (16) is connected with a top pressurizing port of the liquid hydrogen storage tank (5) through a pressurizing check valve (17), the bottom of the liquid hydrogen storage tank (5) is higher than the top of the air bath type vaporizer (16), and liquid supply is realized by means of gravity;

an outlet at the bottom of the liquid hydrogen storage tank (5) is connected with an inlet of a liquid hydrogen leakage valve (18), an outlet of the liquid hydrogen leakage valve (18) is connected with a liquid hydrogen side inlet of the helium-hydrogen heat exchanger (4), a liquid hydrogen side outlet of the helium-hydrogen heat exchanger (4) is connected with an inlet of a filling valve (19), an outlet of the filling valve (19) is connected with a filling port at the bottom of the rocket-mounted storage tank (20), and a pressurizing port at the top of the rocket-mounted storage tank (20) is connected with a high-pressure helium bottle (10) through a back pressure regulating valve (8) and a pressure release valve (9);

a helium side outlet of the helium-hydrogen heat exchanger (4) is connected with an inlet of a cold helium compressor (1), an outlet of the cold helium compressor (1) is connected with a helium side inlet of a liquid hydrogen bath type heat exchanger (2), a helium side outlet of the liquid hydrogen bath type heat exchanger (2) is connected with an inlet of a throttling valve (3), and an outlet of the throttling valve (3) is connected with a helium side inlet of the helium-hydrogen heat exchanger (4);

the liquid hydrogen inlet of the liquid hydrogen bath type heat exchanger (2) is connected with the outlet at the bottom of the liquid hydrogen storage tank (11) through a floater adjusting valve (12), and the hydrogen outlet of the liquid hydrogen bath type heat exchanger (2) is emptied through a first hydrogen gas relief valve (13).

6. The space launch field liquid hydrogen supercooling degree obtaining system according to claim 1 or 5, wherein: the liquid hydrogen storage tank (5) is vertically or horizontally arranged, is made of stainless steel, adopts vacuum powder heat insulation or multilayer vacuum heat insulation, and has the pressure bearing higher than 1 MPa.

7. The space launch field liquid hydrogen supercooling degree obtaining system of claim 1, wherein: the circulating pump (6) adopts immersion cooling or discharge cooling to ensure that the pump body is at the liquid hydrogen temperature, and the pressurizing pressure head of the pump is larger than the liquid hydrogen circulating flow pressure drop and the gravity pressure drop when the liquid hydrogen storage tank (5) is at the lowest liquid level; the circulating pump (6) or adopts a submerged pump structure, and at the moment, the circulating pump (6) is arranged in the liquid hydrogen storage tank (5).

8. The space launch field liquid hydrogen supercooling degree obtaining system of claim 1, wherein: the helium-hydrogen heat exchanger (4) adopts a shell-and-tube type, plate type and plate-fin type dividing wall type heat exchanger structure, and a helium side flow channel is provided with a heat exchange strengthening structure with fins; the exterior of the heat exchanger is filled with pearly-lustre sand for heat insulation.

9. The space launch field liquid hydrogen supercooling degree obtaining system according to claim 1 or 5, wherein: the cold helium compressor (1) is of a centrifugal and axial flow type structure, the inlet pressure is greater than 0.1MPa, and the pressure ratio is not less than 3.

10. The space launch field liquid hydrogen supercooling degree obtaining system according to claim 1 or 5, wherein: the throttle valve (3) can be replaced by a helium expander.

Technical Field

The invention relates to the technical field of preparation of a compact low-temperature fuel for a space launching field, in particular to a liquid hydrogen supercooling degree obtaining system for the space launching field.

Background

The liquid hydrogen/liquid oxygen is a group of propellant combination with the highest specific impulse at present, and the specific impulse is 30-40% higher than that of a normal-temperature propellant, so that the propellant applied to the upper stage of the carrier rocket can obviously improve the carrying capacity of the rocket.

The liquid hydrogen for spaceflight is usually at the saturation temperature of 20K and the density of about 71.3kg/m under normal pressure³. If the liquid hydrogen is supercooled, the liquid hydrogen density is increased, the volume of the storage tank is reduced, and the carrying capacity of the rocket is improved. When the liquid hydrogen is supercooled to 13.9K (hydrogen triple point), the density of the liquid hydrogen is 77.0kg/m³The density is improved by about 8.1 percent. In addition, the supercooled liquid hydrogen adopted in space launching is beneficial to managing the liquid hydrogen, and the supercooled liquid hydrogen adopted in deep space exploration can prolong the nondestructive storage life of the liquid hydrogen or reduce evaporation loss. The triple point temperature of hydrogen is 13.9K, the triple point pressure is about 7.1kPa, and if an evacuation system is adopted to prepare nearly triple point supercooling hydrogen, a multistage vacuum pump is required to be connected in series to achieve the aim, which provides extremely high technical challenge for a vacuum pump system.

Most of liquid supercooling is realized by using fluid heat exchange with lower temperature, and for hydrogen, only negative pressure saturated hydrogen and helium meet the requirements, but the low-temperature helium obtained by the conventional scheme has extremely high cost and extremely high energy consumption of equipment.

The method for obtaining the liquid hydrogen supercooling comprises the following steps: negative pressure hydrogen heat exchange method, helium bubbling method, helium refrigerator method. The negative pressure hydrogen heat exchange method requires the vacuumizing of a hydrogen system, the equipment is complex, potential safety hazards exist, the development difficulty of the hydrogen vacuum pump is very high, the cost is high, the multiple vacuum pumps are required to be arranged in series to obtain rated negative pressure, and the energy consumption is very high; the helium bubbling method obtains the supercooling degree by introducing helium into the propellant storage tank, has simple operation and high reliability, but has limited supercooling degree when being applied to supercooling liquid hydrogen, extremely high consumption of helium and higher investment cost; when the helium refrigerator is used for refrigerating in a liquid hydrogen temperature zone, the lowest temperature of the system is the target temperature of liquid hydrogen supercooling and is usually lower than 20K; the highest temperature of the system is room temperature. When refrigerating in the large temperature difference interval, the efficiency of the helium refrigerating system is extremely low, the power consumption is extremely high, and the equipment investment of the helium refrigerator is high.

At present, the aerospace field has realized supercooling of propellants such as liquid oxygen, liquid methane, kerosene and the like, but engineering application level supercooling operation on liquid hydrogen is not carried out, and the demand of future aerospace exploration on supercooling hydrogen is urgent. In the launching task of the oxyhydrogen rocket, a fuel storage tank of a launching field usually stores excessive liquid hydrogen, and after each task, the residual liquid hydrogen in a ground storage tank needs to be safely treated. If the redundant liquid hydrogen is used as a cold source and cannot influence normal space launching, at present, a cold helium compressor with the air inlet temperature and the air outlet temperature in a low temperature region is provided, and the lowest working temperature of the cold helium compressor can reach a helium temperature region.

Disclosure of Invention

In order to overcome the defects of the prior art, the invention aims to provide a space launching field liquid hydrogen supercooling degree obtaining system, helium is used as a cold transmission carrier, sufficient saturated liquid hydrogen in a launching field is used for precooling the helium, then the helium is expanded and refrigerated to prepare low-temperature helium with the temperature lower than 20K, and the cold helium and the liquid hydrogen exchange heat to prepare supercooled liquid hydrogen and even prepare solid-liquid mixed slurry hydrogen.

In order to achieve the purpose, the invention adopts the technical scheme that:

a space launch site liquid hydrogen supercooling degree obtaining system comprises a liquid hydrogen storage tank 5, wherein a top pressurizing port of the liquid hydrogen storage tank 5 is connected with an outlet of a high-pressure helium bottle 10 through a backpressure regulating valve 8 and a pressure release valve 9; an outlet at the bottom of the liquid hydrogen storage tank 5 is connected with an inlet of a circulating pump 6, an outlet of the circulating pump 6 is connected with a liquid hydrogen side inlet of the helium-hydrogen heat exchanger 4, a liquid hydrogen side outlet of the helium-hydrogen heat exchanger 4 is connected with an inlet of a backflow check valve 7, and an outlet of the backflow check valve 7 is connected with a backflow port at the top of the liquid hydrogen storage tank 5;

a helium side outlet of the helium-hydrogen heat exchanger 4 is connected with an inlet of a cold helium compressor 1, an outlet of the cold helium compressor 1 is connected with a helium side inlet of a liquid hydrogen bath type heat exchanger 2, a helium side outlet of the liquid hydrogen bath type heat exchanger 2 is connected with an inlet of a throttle valve 3, and an outlet of the throttle valve 3 is connected with a helium side inlet of the helium-hydrogen heat exchanger 4;

the liquid hydrogen inlet of the liquid hydrogen bath type heat exchanger 2 is connected with the outlet at the bottom of the liquid hydrogen storage tank 11 through a floater adjusting valve 12, and the hydrogen outlet of the liquid hydrogen bath type heat exchanger 2 is discharged through a first hydrogen discharge valve 13.

A recooling device 14 is additionally arranged, a first helium inlet of the recooling device 14 is connected with a helium side outlet of a helium-hydrogen heat exchanger 4, a first helium outlet of the recooling device 14 is connected with an inlet of a cold helium compressor 1, an outlet of the cold helium compressor 1 is connected with a helium side inlet of a liquid hydrogen bath heat exchanger 2, a helium side outlet of the liquid hydrogen bath heat exchanger 2 is connected with a second helium inlet of the recooling device 14, a second helium outlet of the recooling device 14 is connected with an inlet of a throttle valve 3, and an outlet of the throttle valve 3 is connected with a helium side inlet of the helium-hydrogen heat exchanger 4.

Placing the helium-hydrogen heat exchanger 4 in the liquid hydrogen storage tank 5, and directly supercooling liquid hydrogen in the liquid hydrogen storage tank 5 by using cold helium gas; an outlet of the throttle valve 3 is connected with a helium side inlet of the helium-hydrogen heat exchanger 4, and a helium side outlet of the helium-hydrogen heat exchanger 4 is connected with an inlet of the cold helium compressor 1; 5 end exit linkage circulating pump 6 entrances of liquid hydrogen storage tank, 6 exit linkage backflow check valve 7 entrances of circulating pump, 5 top backward flow mouths of backflow check valve 7 exit linkage liquid hydrogen storage tank.

The helium-hydrogen heat exchanger 4 is wound on the outer surface of the shell of the liquid hydrogen storage tank 5, and the cold helium gas exchanges heat with the shell of the liquid hydrogen storage tank 5, so that the supercooling and heat preservation of the liquid hydrogen in the liquid hydrogen storage tank 5 are realized.

A space launch site liquid hydrogen supercooling degree obtaining system adopts a liquid hydrogen filling process to achieve obtaining of large supercooling degree and comprises a liquid hydrogen storage tank 5, wherein a pressurizing outlet at the bottom of the liquid hydrogen storage tank 5 is connected with an inlet of a pressurizing and draining valve 15, an outlet of the pressurizing and draining valve 15 is connected with an inlet of an air bath type vaporizer 16, an outlet of the air bath type vaporizer 16 is connected with a top pressurizing port of the liquid hydrogen storage tank 5 through a pressurizing check valve 17, the bottom of the liquid hydrogen storage tank 5 is higher than the top of the air bath type vaporizer 16, and liquid supply is achieved by means of gravity;

an outlet at the bottom of the liquid hydrogen storage tank 5 is connected with an inlet of a liquid hydrogen leakage valve 18, an outlet of the liquid hydrogen leakage valve 18 is connected with a liquid hydrogen side inlet of the helium-hydrogen heat exchanger 4, a liquid hydrogen side outlet of the helium-hydrogen heat exchanger 4 is connected with an inlet of a filling valve 19, an outlet of the filling valve 19 is connected with a filling port at the bottom of the rocket upper storage tank 20, and a pressurizing port at the top of the rocket upper storage tank 20 is connected with an outlet of a high-pressure helium bottle 10 through a back pressure regulating valve 8 and a pressure;

a helium side outlet of the helium-hydrogen heat exchanger 4 is connected with an inlet of a cold helium compressor 1, an outlet of the cold helium compressor 1 is connected with a helium side inlet of a liquid hydrogen bath type heat exchanger 2, a helium side outlet of the liquid hydrogen bath type heat exchanger 2 is connected with an inlet of a throttle valve 3, and an outlet of the throttle valve 3 is connected with a helium side inlet of the helium-hydrogen heat exchanger 4;

the liquid hydrogen inlet of the liquid hydrogen bathroom heat exchanger 2 is connected with the outlet at the bottom of the liquid hydrogen storage tank 11 through a float adjusting valve 12, and the hydrogen outlet of the liquid hydrogen bathroom heat exchanger 2 is emptied through a first hydrogen discharge valve 13.

The cold helium compressor 1 adopts a centrifugal and axial flow type structure, the inlet pressure is more than 0.1MPa, and the pressure ratio is not less than 3.

The liquid hydrogen bath type heat exchanger 2 adopts a shell-and-tube heat exchanger structure, helium is arranged on the tube side, and liquid hydrogen is arranged on the shell side; the helium pipe adopts a structure of a snake-shaped coil pipe and an internal thread pipe; the length of the helium pipe is set by that the temperature of outlet helium is lower than 25K; the shell side liquid level is regulated by a float regulating valve 12.

The helium-hydrogen heat exchanger 4 adopts a shell-and-tube type, plate type and plate-fin type dividing wall type heat exchanger structure, and a helium side flow channel is provided with a heat exchange strengthening structure of fins; the exterior of the heat exchanger is filled with pearly-lustre sand for heat insulation or vacuum heat insulation.

The liquid hydrogen storage tank 5 is vertically or horizontally arranged, is made of stainless steel, is insulated by vacuum powder or vacuum multilayer, and has the pressure bearing higher than 1 MPa.

The circulating pump 6 is immersed and cooled to ensure that the pump body is at the liquid hydrogen temperature, and the pressurizing pressure head of the pump is larger than the liquid hydrogen circulating flow pressure drop and the gravity pressure drop when the liquid hydrogen storage tank 5 is at the lowest liquid level; the circulation pump 6 may be of a submerged pump structure, and in this case, the circulation pump 6 is built in the liquid hydrogen storage tank 5.

The throttle valve 3 can also be replaced by a cryogenic helium expander.

The invention has the beneficial effects that:

the invention can prepare large supercooled liquid hydrogen by utilizing a liquid hydrogen cold source which is greatly existed in the transmitting field and combining the cold helium compressor, thereby effectively changing the current situation that the supercooled liquid hydrogen can not be prepared in a large scale at present. The device investment and the transformation cost for obtaining the liquid hydrogen with large supercooling degree are reduced by utilizing the conditions of the transmitting field, and the engineering realization is easy.

The super-supercooled liquid hydrogen with the temperature close to the triple point can be obtained, the obtained liquid hydrogen has a large supercooling degree, and the advantages of the supercooled liquid hydrogen are fully utilized; solid-liquid slurry hydrogen can also be prepared.

The characteristic that the cold helium compressor is suitable for the low-temperature region to work is utilized, the working temperature region of the refrigerating system is limited to be below the liquid hydrogen temperature region, and compared with the conventional helium refrigerating scheme, the refrigerating system has higher operating efficiency; meanwhile, a large amount of liquid hydrogen resources in the launching field are utilized to pre-cool the helium refrigeration system before throttling expansion, so that the performance of the refrigeration system is greatly improved.

The invention uses helium as a heat exchange carrier to realize the supercooling of liquid hydrogen, and because the helium has stable property, the safety risk can not be generated even if the helium leaks, the liquid hydrogen can not be polluted, and the operation is safer; in addition, when cold helium gas exchanges heat with liquid hydrogen, the heat exchange rate at the helium side is convenient to control, so that quantitative supercooling target temperature is obtained, and the risk of ice blockage at the liquid hydrogen side is avoided.

The invention has flexible arrangement, can carry out supercooling on a ground storage tank and can also carry out supercooling on liquid hydrogen in a storage tank on an arrow; the supercooling of the liquid hydrogen can be realized by an external heat exchanger, or the heat exchanger can be arranged in the liquid hydrogen storage tank or a cold helium pipeline is wound on the wall surface of the liquid hydrogen storage tank, so that the double effects of supercooling and cold insulation are realized, namely after the supercooled liquid hydrogen is prepared on the ground, the supercooling degree of the supercooled liquid hydrogen is maintained through the indirect work of a refrigerating system.

In conclusion, the invention has the advantages of simple structure, safe and stable operation, large available supercooling degree, low investment and transformation cost, high system operation efficiency, flexible and various arrangement and the like, and has considerable application prospect.

Drawings

Fig. 1 is a schematic structural diagram of embodiment 1 of the present invention.

Fig. 2 is a schematic structural diagram of embodiment 2 of the present invention.

Fig. 3 is a schematic structural diagram of embodiment 3 of the present invention.

Fig. 4 is a schematic structural diagram of embodiment 4 of the present invention.

Fig. 5 is a schematic structural diagram of embodiment 5 of the present invention.

Detailed Description

The invention is described in detail below with reference to the figures and examples.