CN110469429B - Low-temperature fluid cooling management device - Google Patents
Low-temperature fluid cooling management device Download PDFInfo
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- CN110469429B CN110469429B CN201910806008.XA CN201910806008A CN110469429B CN 110469429 B CN110469429 B CN 110469429B CN 201910806008 A CN201910806008 A CN 201910806008A CN 110469429 B CN110469429 B CN 110469429B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/605—Reservoirs
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Abstract
The invention provides a low-temperature fluid cooling management device which comprises a liquid storage tank, a propellant throttling delivery pipe, a throttle valve, a first guide plate, a second guide plate, a cooling heat exchange coil, a circulating pipe, a circulating pump and a storage tank, wherein the propellant throttling delivery pipe is arranged in the liquid storage tank; the liquid storage tank, the propellant throttling delivery pipe, the throttle valve, the first guide plate, the second guide plate and the cooling heat exchange coil are all arranged in the storage box; the first guide plate and the second guide plate are respectively positioned on the first side and the second side of the liquid storage tank and are respectively connected with the first side and the second side of the liquid storage tank; the circulating pipe penetrates through the storage tank and is communicated with the liquid storage tank; the circulating pump is arranged on the circulating pipe; the liquid storage tank is surrounded by a wall surface, the wall surface comprises N layers of screens, and N is an integer not less than 2. For the N layers of screens on the wall surface of the liquid storage tank, a rib structure spacing layer is arranged between at least one pair of adjacent screens; the fin structure spacing layer comprises a plurality of fins arranged in parallel.
Description
Technical Field
The invention belongs to the field of design and manufacture of microgravity cryogenic fluid storage and management systems, and particularly relates to a cryogenic fluid cooling management device.
Background
In the long-time orbit of the low-temperature propellant, the thermal stratification in the storage tank has the particularity that: under microgravity, convection is remarkably weakened, and a non-uniform heat source and transient heat can generate serious thermal stratification. Thermal stratification directly affects the vaporization of the cryogenic propellant, causing the reservoir pressure to rise. To ensure the safety of the cryogenic tank and to reduce the liquid saturation temperature, the pressure in the tank is conventionally controlled by venting.
However, in the long-term on-orbit process of the spacecraft, the low-temperature liquid is greatly lost due to frequent exhaust, and the utilization rate of the propellant is reduced. In addition, in order to realize safe exhaust and pressure control under microgravity, gas-liquid separation is usually realized by forward pushing and bottom sinking, which causes large consumption of auxiliary propellant carried by a bottom sinking engine and loss of effective load of an aircraft.
The above approach controls the pressure rise from thermal stratification at the expense of aircraft payload loss. However, since thermal stratification is not eliminated, frequent venting and pressure control is required, which is costly. In view of the above problems, it is urgently needed to provide a technical solution for fundamentally eliminating thermal stratification in a microgravity environment, so as to inhibit evaporation of low-temperature liquid and reduce a pressure rise rate of the low-temperature liquid cooling management device, thereby reducing exhaust frequency and paying a low cost.
Through searching the prior documents and technologies, the Chinese patent with the publication number of CN1O5627638A, namely 'a low-temperature propellant rapid supercooling device', discloses a low-temperature propellant rapid supercooling device which comprises a storage tank assembly filled with a low-temperature propellant, wherein the low-temperature propellant rapid supercooling device combines the processes of decompression, evacuation and refrigeration and adiabatic throttling refrigeration together to play a role in rapid supercooling of the low-temperature propellant. The invention is suitable for the heat stratification elimination and the pressure control of the storage tank under the condition of the on-orbit microgravity.
Chinese patent publication No. CN1O5674038A, "a device for storing cryogenic liquid on-track for a long time and a cooling method thereof," discloses a device for storing cryogenic liquid on-track for a long time and a cooling method thereof, the device comprising: the storage box is cooled in an internal and external dual active mode, and the zero-evaporation storage of low-temperature liquid on the track for a long time is realized. The invention adopts a passive mode to realize long-term on-orbit storage tank heat stratification elimination and pressure control.
The Chinese patent with the publication number of CN1O6650242A discloses a cost evaluation method for long-term on-orbit evaporation rate control of a low-temperature propellant, and the cost evaluation method is used for the long-term on-orbit evaporation rate control of the low-temperature propellant, obtains the optimal design working condition with the minimum weight cost and is used for guiding the design of an on-orbit storage system of the low-temperature propellant. The invention provides an on-track fluid cooling management device which is suitable for long-term on-track pressure control of a low-temperature propellant.
The Chinese patent with the publication number of CN1O6762226A discloses an evaporation capacity active control method suitable for long-term on-track storage of low-temperature propellant, which comprises a propellant storage tank provided with an evaporation capacity active control device, wherein the evaporation capacity active control device comprises a composite heat insulation layer, a steam cooling screen, a heat exchanger, a throttling component, a circulating pump, a bypass valve and a steam cooling screen exhaust valve, and realizes the discharge of a small amount of pure gaseous propellant under the condition of uncertain gas-liquid positions under the microgravity condition, so that the evaporation loss is reduced. The invention is suitable for passive evaporation capacity control and pressure control under microgravity condition; compared with the prior patent, the invention can realize that part of liquid is positioned at the bottom of the storage tank, thereby reducing evaporation loss and having better pressure control effect. The problems of increased exhaust loss and poor pressure control effect caused by uncertain gas-liquid interfaces are solved.
Literature (summary of long-term on-track storage of cryogenic propellants, manned space, vol.18) mentions that NASA studies fluid mixing techniques, the primary objective being to eliminate thermal stratification to suppress the pressure rise of the tank. This technique pumps the liquid from the tank through a pump and back to the tank. The injected liquid drives the fluid in the storage tank to move, the hot liquid layer is eliminated, and part of steam can be condensed. Tests and simulations demonstrate that cryogenic fluid mixing techniques can significantly eliminate thermal stratification and reduce the amount of evaporation within the tank, thereby reducing the pressure within the tank. However, as the on-track time increases, the temperature of the liquid rises and it is difficult to control the tank pressure rise with the fluid mixing technique. Furthermore, mixed flow technology requires ensuring that cryopump inlet liquid is not entrained, and NASA proposes a solution for positioning liquid using surface tension management, but the difficulty arises from two aspects: one is that the surface tension of the commonly used cryogenic fluids is much lower than that of the conventional fluids. Making it difficult to design and manufacture a safe and reliable surface tension management device; and secondly, the low-boiling point of the cryogenic fluid is low, the cryogenic fluid is easy to evaporate, and the liquid storage capacity of the management device can be failed due to trace parasitic heat leakage.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a low-temperature fluid cooling management device which fundamentally eliminates thermal stratification in a microgravity environment, further inhibits the evaporation of low-temperature liquid and reduces the pressure rise rate, thereby reducing the exhaust frequency and paying little cost. The technical scheme of the invention is as follows:
a low-temperature fluid cooling management device comprises a liquid storage tank, a propellant throttling delivery pipe, a throttle valve, a first guide plate, a second guide plate, a cooling heat exchange coil, a circulating pipe, a circulating pump and a storage tank;
the liquid storage tank, the propellant throttling delivery pipe, the throttle valve, the first guide plate, the second guide plate and the cooling heat exchange coil are all arranged in the storage box;
the first guide plate and the second guide plate are respectively positioned on the first side and the second side of the liquid storage tank and are respectively connected with the first side and the second side of the liquid storage tank;
the circulating pipe penetrates through the storage tank and is communicated with the liquid storage tank; the circulating pump is arranged on the circulating pipe;
the liquid storage tank is surrounded by a wall surface, the wall surface comprises N layers of screens, and N is an integer not less than 2.
Optionally, for N layers of screens on the wall surface of the liquid storage tank, a rib structure spacing layer is arranged between at least one pair of adjacent screens; the fin structure spacing layer comprises a plurality of fins arranged in parallel.
Optionally, the wall of the reservoir comprises an outer screen and an inner screen.
Optionally, a rib structure spacing layer is arranged between the outer side screen and the inner side screen; the fin structure spacing layer comprises a plurality of fins arranged in parallel.
Optionally, for the N layers of screens on the wall surface of the liquid storage tank, the mesh diameter of each screen is 5-10 μm, and the distance between adjacent screens is less than 1 mm.
Optionally, the distance between adjacent fins of said fin spacer layer is less than 10 mm.
Optionally, the first baffle is arranged corresponding to the first side of the storage tank, and forms a first narrow gap with the inner wall of the first side of the storage tank;
the second guide plate is arranged corresponding to the second side of the storage box, and forms a second narrow slit with the inner wall of the second side of the storage box.
Optionally, the first baffle forms a vertical included angle with an inner wall tangent of the first side of the tank; the second guide plate and the tangent line of the inner wall of the second side of the storage box form a vertical included angle.
Optionally, the first and second baffles enter the interior of the reservoir through first and second sides of the reservoir, respectively.
Optionally, the throttle valve is disposed on the propellant throttle delivery pipe; the propellant throttling conveying pipe is arranged at the top of the liquid storage tank, one end of the propellant throttling conveying pipe is communicated with the liquid storage tank, and the other end of the propellant throttling conveying pipe is connected with the cooling heat exchange coil.
Optionally, the cooling heat exchange coil comprises three portions which are communicated with each other, and the first portion is arranged inside the liquid storage tank; the second part is communicated with the outside of the storage tank through a first guide plate; the third part is communicated with the outside of the storage tank through a second guide plate.
Optionally, at least a part of the cooling heat exchange coil is of a spiral bent structure.
Optionally, the first baffle is fixed on a first bracket corresponding to the first side of the storage tank, and the first bracket is fixed on a reinforcing rib corresponding to the inner wall of the first side of the storage tank 8;
the second guide plate is fixed on a second support corresponding to the second side of the storage tank, and the second support is fixed on a reinforcing rib corresponding to the inner wall of the second side of the storage tank 8.
Optionally, the liquid storage tank and the circulation pipe are fixed to the bottom inside the tank.
Optionally, the apparatus further comprises a control system comprising a pressure sensor and a controller; when the pressure of the storage tank reaches the highest or lowest limit value, the pressure sensor transmits the pressure to the controller, and the controller controls the starting or stopping of the circulating pump.
Compared with the prior art, the invention has the following beneficial effects:
the invention adopts a capillary low-temperature fluid management device, which can convey low-temperature propellant in microgravity environment at small flow, and simultaneously cool the low-temperature propellant to condense vapor into liquid. By the aid of the low-temperature propellant storage device, the low-temperature propellant can be stored well in the low-temperature propellant management device under the conditions of forward pushing or no forward pushing and bottom sinking, evaporation of internal liquid is inhibited, and the low-temperature propellant can be drawn to flow into the channel and the liquid storage tank through the pore capillary action of the screen mesh and is conveyed to the circulating pipe.
The throttling cooling heat exchanger is based on the coke-soup throttling cooling principle, the propellant is cooled by the heat exchanger to generate small supercooling degree, and flowing phase change heat exchange of the propellant is effectively utilized. After cooling, the liquid propellant with zero dryness flows in a cooling mode, the latent heat of liquid vaporization is completely utilized, the precooling and cooling rate is optimized, and the propellant utilization rate is improved.
Conventional solutions control the pressure rise from thermal stratification at the expense of aircraft payload loss. But because the elimination of thermal stratification still exists, the pressure rise is fast, the exhaust is frequent, and the payment cost is high. According to the technical scheme, thermal stratification is fundamentally eliminated in the microgravity environment, so that low-temperature liquid evaporation is inhibited, and the boosting rate is reduced.
The first guide plate and the second guide plate are respectively in narrow gaps formed with the inner wall of the storage tank, and liquid propellants on two sides are respectively guided to the bottom of the storage tank by the internal liquid bridge force and capillary action of the narrow gaps to supply liquid for the liquid storage tank.
The liquid can be continuously drawn by the capillary action of the screen pores of the fluid management device, and the fluid management device can be stably filled. And because the equivalent pore size of the screen is small, the pressure difference of the breaking point can be improved.
A multilayer screen structure with narrow slit spacing layers is designed, and gas is prevented from penetrating through the screen by means of liquid bridge force and capillary action in narrow slits. Thereby overcoming the problem of difficulty in designing and manufacturing a safe and reliable surface tension management device due to the much lower surface tension of the commonly used cryogenic fluids than conventional fluids.
According to the invention, the stainless steel rib spacing layers are arranged between the adjacent screens, and the liquid infiltration area is increased in the micro channels of the spacing layers, so that the drying by distillation of the screens and the penetration of air mass through the screens are effectively inhibited.
According to the invention, after a small part of liquid is introduced into the internal cooling heat exchanger for throttling and cooling, the liquid flows through the inner side of the heat exchanger to cool the propellant at the outer side, so that the low-temperature propellant is ensured to maintain a liquid state, and meanwhile, the heat leakage of the management device is taken away. Therefore, the problem of liquid storage capacity failure of the management device caused by low boiling point, easy evaporation and trace parasitic heat leakage of the cryogenic fluid is solved.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
figure 1 is a schematic diagram of the structure of a cryogenic fluid cooling management device according to an embodiment of the present invention;
fig. 2 is a schematic diagram of a cooling heat exchange coil structure in a liquid storage tank and a multilayer screen structure on the wall surface of the liquid storage tank of a cryogenic fluid cooling management device according to an embodiment of the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Under microgravity environment, as shown in fig. 1, a cryogenic fluid cooling management device comprises a liquid storage tank 1, a propellant throttling delivery pipe 2, a throttle valve 3, a first guide plate 41, a second guide plate 42, a cooling heat exchange coil 5, a circulating pipe 6, a circulating pump 7 and a storage tank 8;
the liquid storage tank 1, the propellant throttling delivery pipe 2, the throttle valve 3, the first guide plate 41, the second guide plate 42 and the cooling heat exchange coil 5 are all arranged in the storage tank 8;
the first guide plate 41 and the second guide plate 42 are respectively positioned on the first side and the second side of the liquid storage tank 1 and are respectively connected with the first side and the second side of the liquid storage tank 1;
the circulating pipe 6 penetrates through the storage tank 8 and is communicated with the liquid storage tank 1; the circulation pump 7 is disposed above the circulation pipe 6:
the liquid storage tank 1 is surrounded by a wall surface, the wall surface comprises N layers of screens, and N is an integer not less than 2.
For the N layers of screens on the wall surface of the liquid storage tank, the mesh diameter of each screen is 5-10 mu m, and the distance between every two adjacent screens is less than 1 mm.
Preferably, for the N layers of screens on the wall surface of the liquid storage tank, a rib structure spacing layer is arranged between at least one pair of adjacent screens; the fin structure spacing layer comprises a plurality of fins arranged in parallel. The distance between adjacent fins of the fin spacing layer is less than 10 mm. After the rib structure spacing layer is arranged, the purpose of the invention can be better realized, but the invention does not limit whether the rib structure spacing layer is arranged or not.
In the present embodiment, the wall surface of the liquid storage tank 1 includes an outer screen 9 and an inner screen 11. Here, the wall of the liquid storage tank 1 may include not less than two layers of screens in practical application, and the invention does not limit the specific number of layers of screens.
In this embodiment, a rib structure spacing layer 10 is arranged between the outer side screen 9 and the inner side screen 11; the rib structure spacing layer 10 comprises a plurality of ribs arranged in parallel. The above-mentioned steps are only examples, and in practical application, no rib structure spacing layer may be provided between two layers of screens, and the present invention is not limited thereto.
Under the capillary action of the pores of the outer screen 9, the low-temperature liquid outside the liquid storage tank 1 flows into the rib spacing layers 10 through the pores of the screen and is continuously conveyed to the inner screen 11, so that the liquid supply of the liquid storage tank is ensured. The liquid reservoir delivers liquid propellant to the circulation pipe 6, the circulation pump 7.
A stainless steel rib spacing layer is arranged between the inner layer screen and the outer layer screen of the liquid storage tank, the liquid infiltration area is increased in a small channel of the spacing layer, and the drying to dryness of the screens and the penetration of air mass through the screens are effectively inhibited. The capillary fluid transport capacity of the screen structure is dependent on the capillary pressure difference, the first flow guide plate, and the second flow guide plate.
The first guide plate 41 and the second guide plate 42 respectively form vertical included angles with the tangent lines of the inner walls of the first side and the second side of the storage tank 8. The first baffle 41 is arranged corresponding to the first side of the storage tank 8, and forms a first narrow slit 411 with the inner wall of the first side of the storage tank 8; the second baffle 42 is disposed corresponding to the second side of the storage tank 8, and forms a second narrow slit 421 with the inner wall of the second side of the storage tank 8. The liquid propellant on the two sides is respectively guided to the bottom of the storage tank 8 by the internal liquid bridge force and capillary action of the two narrow slits to supply liquid for the liquid storage tank 1.
The first guide plate 41 and the second guide plate 42 are both stainless steel thin plates, and are easy to machine and form, and have a good adsorption effect with the liquid propellant. The first baffle 41, second baffle 42 configuration are sized according to the overall mission profile and tank configuration.
The first guide plate 41 and the second guide plate 42 are respectively fixed on the first support and the second support corresponding to the first side and the second side of the storage tank 8 by bolts, the first support is fixed on the reinforcing rib corresponding to the inner wall of the first side of the storage tank 8, and the second support is fixed on the reinforcing rib corresponding to the inner wall of the second side of the storage tank 8. The first guide plate 41 and the second guide plate 42 respectively convey the liquid propellant to the liquid storage tank 1, liquid forms an inner angle under the action of capillary force and flows, and the liquid flows to the storage tank 8 to form a liquid pool to submerge the liquid storage tank 1. Liquid wicking is a physical phenomenon in the field of interface science. Under microgravity, capillary action can cause the liquid to climb the wall.
The first and second baffles 41 and 42 pass through the first and second sides of the reservoir 1 into the interior of the reservoir, respectively.
The liquid storage tank 1 and the circulation pipe 6 are fixed to the bottom inside the tank 8.
The connection between the circulating pipe 6 and the circulating pump 7 is flange connection. The low-temperature propellant in the liquid storage tank 1 flows through the circulating pipe 6 and is pumped back to the storage tank 8 through the circulating pump 7, and the low-temperature propellant is pushed into the liquid storage tank 1 through the two narrow slits;
the circulation loop is used for eliminating liquid thermal stratification in the storage tank and controlling the pressure of the storage tank by using a low-temperature propellant.
The stored low-temperature propellant flows through a circulating pipe 6, passes through a circulating pump 7 and then is conveyed back to a storage tank 8 through a cooling heat exchange coil 5.
The throttle valve 3 is arranged on the propellant throttling delivery pipe 2 and is positioned outside the liquid storage tank 1; the propellant throttling conveying pipe 2 is arranged at the top of the liquid storage tank 1, one end of the propellant throttling conveying pipe is communicated with the liquid storage tank, and the other end of the propellant throttling conveying pipe is connected with the cooling heat exchange coil 5.
The cooling heat exchange coil 5 comprises three parts which are communicated with each other, and the first part is arranged in the liquid storage tank 1; the second part is communicated with the outside of the storage tank 8 through a first guide plate; the third portion communicates with the outside of the tank 8 via a second baffle.
Preferably, at least part of the cooling heat exchange coil 5 is of a spiral bending structure.
In this embodiment, cooling heat exchange coil 5 all has the spiral structure of buckling in including the three part of intercommunication each other, and this structure can cool off the heat transfer better. This is by way of example only and the invention is not so limited.
The cooling heat exchange coil 5 is a copper pipe and is fixed inside the first guide plate 41, the second guide plate 42 and the liquid storage tank 1 by a bracket. The inside of the cooling heat exchange coil 5 flows with the low-temperature propellant after throttling and cooling, and the propellant and the guide plate outside the cooling coil. And after the low-temperature propellant exchanges heat with the propellant on the outer side of the cooling heat exchange coil 5, the low-temperature propellant changes phase and gasifies and reaches the outside of the storage tank 8 along the cooling heat exchange coil 5.
The storage tank 8 is generally a spherical, cylindrical storage tank with an ellipsoidal shell.
The circulating pump 7, the circulating pipe 6, the liquid storage tank 1, the first guide plate 41 and the second guide plate 42 can realize the circulating flow of low-temperature propellant conveyed at a small flow rate, realize the temperature equalization of fluid, eliminate thermal stratification and reduce the pressure rise rate in the storage tank 8. The liquid storage tank 1, the propellant throttling delivery pipe 2, the throttling valve 3 and the cooling heat exchange coil 5 can supply a circulating pump with small flow rate to supercool low-temperature liquid propellant, and ensure that low-temperature liquid of a circulating precooling system does not sandwich gas under the microgravity condition.
The first guide plate 41 and the second guide plate 42 respectively form a vertical included angle with the inner wall of the storage tank, liquid flows in the included angle formed by liquid under the action of capillary force, and the liquid flows to the storage tank 8 to form a liquid pool to submerge the liquid storage tank 1. Liquid in a multilayer screen structure on the wall surface of the liquid storage tank 1 flows in a capillary manner, external liquid is continuously conveyed into the tank, enters the circulating pipe 6 through the cooling heat exchange coil 5, is pumped back to the storage tank 8 through the circulating pump 7, and controls the pressure of the storage tank 8 after exchanging heat with fluid in the storage tank 8, so that thermal stratification is eliminated.
Propellant in the liquid storage tank 1 flows through the propellant throttling delivery pipe 2 and the throttling valve 3 for throttling and cooling, enters the cooling heat exchange coil 5, absorbs heat of low-temperature propellant outside the coil in the flowing process, is gasified in a phase change manner, and cools the guide plate.
The flow rate of the cryogenic liquid propellant delivered can be regulated by means of the circulation pump 7. The temperature of the delivered cryogenic liquid propellant is regulated by means of a throttle valve 3. In addition, the pressure of the storage tank 8 can be adjusted to meet the supercooling degree and the conveying amount of the conveyed low-temperature liquid propellant. By optimizing the operational compatibility of the reservoir pressure, the circulation pump 7, the throttle valve 3 and the fluid management device, propellant evaporation losses and the rate of pressure rise in the reservoir can be reduced.
The present embodiment also includes a control system including a pressure sensor and a controller. When the pressure in the tank 8 reaches the maximum and minimum limit values, the pressure sensor transmits the pressure to the controller, and the controller controls the start and stop of the circulating pump 7.
Specific embodiments of the present invention are directed to long-term on-track low temperature propellant tank pressure control and boil-off loss control techniques. In the process of rail-staying sliding, the storage tank 8 is thermally layered due to heat leakage, the propellant is evaporated in a phase change manner, and the pressure of the storage tank 8 is increased. When the pressure of the storage tank 8 rises to a maximum limit value, the pressure sensor transmits the pressure to the controller, the controller starts the circulating pump 7, the liquid propellant in the liquid storage tank 1 is pumped back to the storage tank 8 through the circulating pipe 6 and the circulating pump 7 and is mixed with the fluid in the storage tank 8, heat stratification is eliminated through forced convection, the pressure of the storage tank is reduced, and evaporation capacity is reduced. The low-temperature propellant on the periphery of the wall surface of the liquid storage tank 1 flows into the screen mesh multilayer structure under the capillary action, flows through the outer side of the cooling heat exchange coil 5, is continuously pumped to the circulating pipe 6 after being cooled, and flows back to the storage tank 8. The circulation flow is carried out in such a way that the pressure of the storage tank 8 and the temperature of the propellant are reduced to the required conditions. When the pressure in the storage tank 8 reaches the lowest limit value, the pressure sensor transmits the pressure to the controller, and the controller stops the operation of the circulating pump 7.
The low-temperature propellant liquid in the liquid storage tank 1 enters from one end of the liquid throttling conveying pipe 2 communicated with the liquid storage tank 1, flows through the throttling valve 3 for throttling and cooling, flows through the inner side of the cooling heat exchange coil 5 through one end of the liquid throttling conveying pipe 2 communicated with the cooling heat exchange coil 5, is subjected to phase change gasification after heat absorption, and enters the outside of the storage tank 8 along the second part and the third part of the cooling heat exchange coil 5 respectively.
The throttling cooling generates small supercooling degree, and the flowing phase change heat exchange of the propellant is effectively utilized. After throttling and cooling, the liquid propellant with zero dryness flows in a cooling mode, the latent heat of liquid gasification is fully utilized, and the precooling and cooling rate is optimized.
The embodiments described above are intended to facilitate the understanding and use of the invention by those skilled in the art. It will be readily apparent to those skilled in the art that various modifications to these embodiments may be made, and the generic principles described herein may be applied to other embodiments without the use of the inventive faculty. Therefore, the present invention is not limited to the above embodiments, and those skilled in the art should make improvements and modifications within the scope of the present invention based on the disclosure of the present invention.
Claims (15)
1. A low-temperature fluid cooling management device is characterized by comprising a liquid storage tank, a propellant throttling delivery pipe, a throttle valve, a first guide plate, a second guide plate, a cooling heat exchange coil, a circulating pipe, a circulating pump and a storage tank;
the liquid storage tank, the propellant throttling delivery pipe, the throttle valve, the first guide plate, the second guide plate and the cooling heat exchange coil are all arranged in the storage box;
the first guide plate and the second guide plate are respectively positioned on the first side and the second side of the liquid storage tank and are respectively connected with the first side and the second side of the liquid storage tank;
the circulating pipe penetrates through the storage tank and is communicated with the liquid storage tank; the circulating pump is arranged on the circulating pipe;
the liquid storage tank is surrounded by a wall surface, the wall surface comprises N layers of screens, and N is an integer not less than 2.
2. The apparatus of claim 1, wherein for N layers of screens on the wall of said reservoir, at least one pair of adjacent screens has a ribbed spacer layer therebetween; the fin structure spacing layer comprises a plurality of fins arranged in parallel.
3. A device as claimed in claim 1 or claim 2, wherein the walls of the reservoir comprise an outer screen, an inner screen.
4. The apparatus of claim 3, wherein a ribbed structure spacer layer is disposed between the outer screen and the inner screen; the fin structure spacing layer comprises a plurality of fins arranged in parallel.
5. The apparatus of claim 1, wherein the screens have a mesh diameter of 5 to 10 μm for N screens on the wall of the reservoir, and the distance between adjacent screens is less than 1 mm.
6. The apparatus of claim 2, wherein a distance between adjacent fins of the fin spacer layer is less than 10 mm.
7. The apparatus of claim 1,
the first guide plate is arranged corresponding to the first side of the storage box, and forms a first narrow gap with the inner wall of the first side of the storage box;
the second guide plate is arranged corresponding to the second side of the storage box, and forms a second narrow slit with the inner wall of the second side of the storage box.
8. The apparatus of claim 7, wherein the first baffle is at a vertical angle to a tangent of an inner wall of the first side of the tank; the second guide plate and the tangent line of the inner wall of the second side of the storage box form a vertical included angle.
9. The apparatus of claim 1 wherein said first and second baffles enter the interior of said reservoir through respective first and second sides of said reservoir.
10. The apparatus of claim 1, wherein the throttle valve is disposed on the propellant throttle delivery tube; the propellant throttling conveying pipe is arranged at the top of the liquid storage tank, one end of the propellant throttling conveying pipe is communicated with the liquid storage tank, and the other end of the propellant throttling conveying pipe is connected with the cooling heat exchange coil.
11. The apparatus of claim 1 wherein said cooling heat exchange coil comprises three portions in communication with each other, a first portion being disposed within said reservoir; the second part is communicated with the outside of the storage tank through a first guide plate; the third part is communicated with the outside of the storage tank through a second guide plate.
12. The apparatus of claim 11, wherein the cooling heat exchange coil is at least partially in a spiral-bent configuration.
13. The apparatus of claim 1,
the first guide plate is fixed on a first support corresponding to the first side of the storage box, and the first support is fixed on a reinforcing rib corresponding to the inner wall of the first side of the storage box 8;
the second guide plate is fixed on a second support corresponding to the second side of the storage tank, and the second support is fixed on a reinforcing rib corresponding to the inner wall of the second side of the storage tank 8.
14. The apparatus of claim 1, wherein the reservoir and circulation tube are secured to the bottom of the interior of the tank.
15. The apparatus of claim 1, further comprising a control system comprising a pressure sensor and a controller; when the pressure of the storage tank reaches the highest or lowest limit value, the pressure sensor transmits the pressure to the controller, and the controller controls the starting or stopping of the circulating pump.
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