CN110715173B - Quick precooling transmission pipeline structure of low-temperature propellant - Google Patents
Quick precooling transmission pipeline structure of low-temperature propellant Download PDFInfo
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- CN110715173B CN110715173B CN201910932702.6A CN201910932702A CN110715173B CN 110715173 B CN110715173 B CN 110715173B CN 201910932702 A CN201910932702 A CN 201910932702A CN 110715173 B CN110715173 B CN 110715173B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D1/00—Pipe-line systems
- F17D1/08—Pipe-line systems for liquids or viscous products
- F17D1/082—Pipe-line systems for liquids or viscous products for cold fluids, e.g. liquefied gas
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D3/00—Arrangements for supervising or controlling working operations
- F17D3/01—Arrangements for supervising or controlling working operations for controlling, signalling, or supervising the conveyance of a product
Abstract
A low-temperature propellant rapid precooling transmission pipeline structure comprises a ground storage tank, wherein a low-temperature liquid outlet of the ground storage tank is connected with an inlet of a low-temperature transmission pipeline, an outlet of the low-temperature transmission pipeline is connected with a propellant filling port of an rocket storage tank, and the low-temperature transmission pipeline comprises an inner micro-rib vacuum tube and a vacuum straight tube; the vacuum straight pipe is formed into an annular cavity by an inner straight pipe and an outer pipe, the annular cavity is vacuumized, and the outer side of the inner straight pipe is wrapped by a plurality of layers of heat insulation layers; the inner micro-rib vacuum tube is an annular cavity formed by a micro-rib inner tube and an outer tube, the annular cavity is vacuumized, the outer side of the micro-rib inner tube is wrapped with a plurality of layers of heat insulation layers, and a micro-rib bulge of the micro-rib inner tube is formed by machining; the invention adopts the layout form of combining the inner micro-rib vacuum tube and the vacuum straight tube, fully utilizes the advantage of the inner micro-rib vacuum tube in the conversion from the intensified film boiling to the transitional boiling to realize the quick precooling, and simultaneously utilizes the advantage of the vacuum straight tube with small resistance to reduce the flow resistance of the whole low-temperature transmission pipeline and accelerate the precooling process.
Description
Technical Field
The invention relates to the technical field of aerospace low-temperature propellant ground filling, in particular to a low-temperature propellant rapid precooling transmission pipeline structure.
Background
Low temperature propellants have become the first choice propellants in aerospace, but the low boiling point and easy evaporation characteristics of low temperature propellants cause the low temperature propellants to experience complex two-phase flow difficulties in ground filling. Such as: before the low-temperature liquid is transferred and injected in a large scale, the temperature of the transmission pipe must be reduced to a low-temperature liquid temperature zone. The process of reducing the temperature of the pipeline system from room temperature to a low-temperature region is called precooling, and the precooling duration can influence the propellant refilling process.
Future space missions require rapid launch of the launch vehicle, and therefore the precooling process must be accelerated. At present, precooling of a low-temperature pipeline for aerospace launch takes about 1 hour in China. The heat exchange between the reinforced fluid and the pipe wall is beneficial to accelerating the precooling process, and the method of accelerating precooling by improving the liquid injection rate can cause the increase of flow resistance and even flow stagnation.
When low-temperature liquid is quickly injected into a room-temperature pipeline, the large-temperature-difference heat exchange between the fluid and a solid wall causes a two-phase flow distribution form of a gas film wrapped liquid column, the heat exchange at the stage is called as reverse-loop film boiling, and a gas film layer can isolate the liquid from contacting with a metal wall to cause low heat exchange rate. If the gas film of the reverse circular flow is damaged, the liquid is promoted to contact the metal wall as early as possible, and the precooling process is favorably accelerated.
According to precooling experiments, when liquid oxygen, liquid nitrogen and liquid methane are precooled, the temperature reduction of the tube wall is mainly governed by the reverse-loop fluid film state boiling, and the precooling time is long; and liquid hydrogen pre-cooling shows that the heat exchange in the pipe mainly comprises transition boiling and nucleate boiling, and film boiling is not seen. Therefore, when the liquid hydrogen is precooled, the pipe wall can reach the liquid hydrogen temperature zone in a very short time, and the precooling target is completed. The difference between liquid hydrogen precooling and other fluid precooling is that the number of pipe flow Re in hydrogen precooling is higher, and the flow inertia force is larger; the surface tension of hydrogen is small, and the stability of a gas-liquid interface is poor. Therefore, the reverse-loop flow formed by hydrogen precooling is easily damaged, and the film boiling of the reverse-loop flow is converted into transition boiling and nucleate boiling earlier.
The key for improving the precooling rate of the macromolecular cryogenic fluids such as liquid nitrogen, liquid oxygen, liquid methane and the like is to promote the earlier conversion of the reverse-loop flow from film boiling to transition boiling and film boiling. The researchers have proposed that a low-heat-conduction coating can be sprayed on the inner surface of a metal tube or a nano microstructure can be generated to improve the wall temperature of conversion from film boiling to transitional boiling, shorten the film boiling action interval, and preliminarily prove the effectiveness of the related scheme.
The corrugated pipe precooling experiment shows that the heat exchange efficiency of film boiling, transition boiling and nucleate boiling is similar in corrugated pipe temperature reduction, which is different from the straight pipe precooling phenomenon. This particular phenomenon can be explained as follows: in the film boiling region, the bellows substructure causes the existence of an obvious radial velocity component in the gas film layer, which can disturb the gas film layer and promote the earlier contact of liquid and the wall surface; however, the inner fin structure of the corrugated pipe also increases the thickness of the gas film layer in the whole boiling region, and affects the whole heat exchange effect.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide a rapid precooling transmission pipeline structure for a low-temperature propellant, which utilizes a metal inner wall micro-rib structure to destroy the stability of a reverse annular gas flow film and accelerate the conversion from film boiling to transition boiling and nucleate boiling, thereby accelerating the precooling process.
In order to achieve the purpose, the invention adopts the technical scheme that:
a low-temperature propellant rapid precooling transmission pipeline structure comprises a ground storage tank 1, wherein a low-temperature liquid outlet of the ground storage tank 1 is connected with an inlet of a low-temperature transmission pipeline, and an outlet of the low-temperature transmission pipeline is connected with a propellant filling port of an rocket storage tank 4; the low-temperature transmission pipeline comprises an inner micro-rib vacuum pipe 3 and a vacuum straight pipe 2;
the vacuum straight pipe 2 is an annular cavity formed by an inner straight pipe 6 and an outer pipe 5, the annular cavity is vacuumized, and the outer side of the inner straight pipe 6 is wrapped by a plurality of layers of heat insulation layers 7;
the inner micro-rib vacuum tube 3 is characterized in that a micro-rib inner tube 8 and an outer tube 5 form an annular cavity, the annular cavity is vacuumized, the outer side of the micro-rib inner tube 8 is wrapped by a plurality of heat insulation layers 7, and a micro-rib bulge 9 of the micro-rib inner tube 8 is formed through machining.
In practice, different arrangement modes of the micro-rib vacuum tube 3 and the vacuum straight tube 2 are set according to the working condition requirements: if the length of the low-temperature transmission pipeline is shorter than 30m, the low-temperature transmission pipeline is completely provided with a micro-rib vacuum tube 3, or the micro-rib vacuum tube 3 is arranged at the inlet section close to the low-temperature transmission pipeline, and the vacuum straight tube 2 is arranged at the outlet section close to the low-temperature transmission pipeline; if the low-temperature transmission pipe is longer than 30m, the low-temperature transmission pipe adopts a mode that the micro-rib vacuum pipes 3 and the vacuum straight pipes 2 are arranged alternately.
The ground storage tank 1 is made of stainless steel, the heat insulation mode is vacuum powder or vacuum fiber heat insulation, the storage tank is horizontal or vertical, a low-temperature liquid outlet is located at the bottom of the ground storage tank 1, and liquid hydrogen, liquid oxygen, liquid methane or liquid nitrogen is stored in the ground storage tank 1.
The wall surface material of the rocket storage tank 4 is aluminum alloy, stainless steel or polymer-based composite material, the storage tank is spherical or columnar, the wall thickness is 1-5 mm, a propellant filling port is positioned at the bottom or top of the rocket storage tank 4, and the surface of the rocket storage tank 4 is insulated by adopting foaming, multilayer heat-insulating materials or foaming and multilayer heat-insulating materials; the rocket storage tank 4 stores liquid hydrogen, liquid oxygen, liquid methane or liquid nitrogen.
Said innerThe straight pipe 6 and the outer pipe 5 are both made of stainless steel, and the vacuum degree of the annular cavity formed by the inner straight pipe 6 and the outer pipe 5 is better than 10-2Pa, the inner straight pipe 6 is provided with corrugated pipe wave compensation at intervals along the length direction.
The pipe material of the micro-rib inner pipe 8 is stainless steel, and the vacuum degree of the annular cavity formed by the micro-rib inner pipe 8 and the outer pipe 5 is better than 10-2Pa。
The multilayer heat insulation layer 7 is formed by metal reflecting screens and non-metal spacers at intervals, the layer density is 10-20 layers/cm, the metal reflecting screens are aluminum foils or aluminum-plated polyurethane films, and the non-metal spacers are terylene or silk screens.
The micro-rib bulges 9 are molded by adopting a hydraulic molding machine, a mechanical expansion type machine or a wave beating manufacturing machine; the rib height of the micro-rib bulges 9 is in the mm level, and the rib spacing is larger than the cm level; the cross section of the micro-rib protrusion 9 is rectangular or zigzag; the micro-rib protrusions 9 are in the form of axisymmetric annular bands, spiral bands or irregular inward protrusions.
The inner micro-rib vacuum tube 3 is connected with the vacuum straight tube 2 by a flange or welded.
The invention has the beneficial effects that:
the low-temperature transmission pipeline adopts a layout form of combining an inner micro-rib vacuum tube 3 and a vacuum straight tube 2. The micro-rib bulges 9 of the micro-rib inner tube 8 can enable fluid to generate radial velocity components in the precooling process, and when low-temperature liquid is injected into the section of the inner micro-rib vacuum tube 3, reverse annular fluid film boiling is easy to occur under the action of large temperature difference between the low-temperature liquid and the micro-rib inner tube 8, so that the heat exchange efficiency is low, and the precooling speed is slow. The introduction of the micro-rib protrusions 9 can cause radial components of flow velocity in the gas film, impact can be generated on a gas-liquid phase interface, the reverse annular flow liquid column is promoted to be torn earlier to cause contact of liquid and the micro-rib inner tube 8, earlier conversion from film boiling to transition boiling is achieved, and finally the precooling process is facilitated to be accelerated. In addition, different from a corrugated pipe, the micro-rib bulges 9 of the inner micro-rib vacuum pipe 3 have larger distance, so that the formation of flow dead zones among the micro-ribs and the thickening of an air film layer can be avoided to a limited extent, and the heat exchange efficiency is ensured to be at a higher level in the whole precooling and cooling process; the larger pitch of the micro-rib protrusions 9 also reduces the flow resistance loss.
The invention adopts the layout form of combining the inner micro-rib vacuum tube 3 and the vacuum straight tube 2, on one hand, the advantage of the inner micro-rib vacuum tube 3 for strengthening the conversion from film boiling to transitional boiling can be fully utilized to realize quick precooling, and on the other hand, the advantage of the vacuum straight tube 2 with small resistance can be utilized to reduce the flow resistance of the whole low-temperature transmission pipeline.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings.
As shown in fig. 1, a low-temperature propellant rapid precooling transmission pipeline structure comprises a ground storage tank 1, wherein a low-temperature liquid outlet of the ground storage tank 1 is connected with an inlet of a low-temperature transmission pipeline, an outlet of the low-temperature transmission pipeline is connected with a propellant filling port of an arrow storage tank 4, and low-temperature liquid in the ground storage tank 1 is filled into the low-temperature transmission pipeline and is cooled and precooled;
the low-temperature transmission pipeline comprises an inner micro-rib vacuum pipe 3 and a vacuum straight pipe 2; the vacuum straight pipe 2 is an annular cavity formed by an inner straight pipe 6 and an outer pipe 5, the annular cavity is vacuumized to reduce the heat transfer quantity from the outer pipe 5 to the inner straight pipe 6, the outer side of the inner straight pipe 6 is wrapped with a plurality of layers of heat insulation layers 7, and the radiation heat transfer quantity from the outer pipe 5 to the inner straight pipe 6 is reduced by the plurality of layers of heat insulation layers 7; the inner micro-rib vacuum tube 3 is characterized in that a micro-rib inner tube 8 and an outer tube 5 form an annular cavity, the annular cavity is vacuumized to reduce the heat transfer from the outer tube 5 to the micro-rib inner tube 8, the outer side of the micro-rib inner tube 8 is wrapped by a plurality of layers of heat insulation layers 7, the radiation heat transfer from the outer tube 5 to the micro-rib inner tube 8 is reduced by the plurality of layers of heat insulation layers 7, and a micro-rib bulge 9 of the micro-rib inner tube 8 is formed through machining.
In practice, different arrangement modes of the micro-rib vacuum tube 3 and the vacuum straight tube 2 are set according to the working condition requirements: if the low-temperature transmission pipe is shorter than 30m, the low-temperature transmission pipe is completely provided with a micro-rib vacuum pipe 3 or the micro-rib vacuum pipe 3 is arranged at the inlet section close to the low-temperature transmission pipe, and the vacuum straight pipe 2 is arranged at the outlet section close to the low-temperature transmission pipe; if the low-temperature transmission pipe is longer than 30m, the low-temperature transmission pipe adopts a mode that the micro-rib vacuum pipes 3 and the vacuum straight pipes 2 are arranged at intervals, and the micro-rib vacuum pipes 3 and the vacuum straight pipes 2 are connected by welding or flanges.
The ground storage tank 1 is made of stainless steel, the heat insulation mode is vacuum powder or vacuum fiber heat insulation, the storage tank is horizontal or vertical, a low-temperature liquid outlet is located at the bottom of the ground storage tank 1, and liquid hydrogen, liquid oxygen, liquid methane or liquid nitrogen and the like are stored in the ground storage tank 1.
The wall surface material of the rocket storage tank 4 is aluminum alloy, stainless steel or polymer-based composite material, the storage tank is spherical or columnar, the wall thickness is 1-5 mm, a propellant filling port is positioned at the bottom or top of the rocket storage tank 4, and the surface of the rocket storage tank 4 is insulated by adopting foaming, multilayer heat-insulating materials or foaming and multilayer heat-insulating materials; the on-arrow storage tank 4 stores liquid hydrogen, liquid oxygen, liquid methane or liquid nitrogen and the like.
The inner straight pipe 6 and the outer pipe 5 are both made of stainless steel, and the vacuum degree of the annular cavity formed by the inner straight pipe 6 and the outer pipe 5 is better than 10-2Pa, the inner straight pipe 6 is provided with corrugated pipe wave compensation at intervals along the length direction.
The pipe material of the micro-rib inner pipe 8 is stainless steel, and the vacuum degree of the annular cavity formed by the micro-rib inner pipe 8 and the outer pipe 5 is better than 10-2Pa。
The multilayer heat insulation layer 7 is formed by metal reflecting screens and non-metal spacers at intervals, the layer density is 10-20 layers/cm, the metal reflecting screens are aluminum foils or aluminum-plated polyurethane films, and the non-metal spacers are terylene or silk screens.
The micro-rib protrusions 9 are formed by adopting a hydraulic forming machine, a mechanical expansion type machine or a wave beating manufacturing machine, the rib height of the micro-rib protrusions 9 is in a mm level, the rib spacing is larger than a cm level, and the cross section of each micro-rib protrusion 9 is rectangular or zigzag; the micro-rib protrusions 9 are in the form of axisymmetric annular bands, spiral bands or irregular inward protrusions.
The working principle of the invention is as follows:
before the low-temperature propellant is filled in a large flow, firstly, precooling operation is carried out on a low-temperature transmission pipeline by low-temperature liquid from a ground storage tank 1; when low-temperature liquid is injected into a low-temperature pipeline at room temperature, under the action of large temperature difference between the inner wall of the vacuum tube and the low-temperature liquid, reverse annular flow distribution is formed, namely a gas film layer wraps a liquid column, so that the liquid cannot contact a hot wall surface, the heat exchange efficiency is low, and the temperature drop rate of the tube wall is slow. In the reverse-loop film-state boiling stage, the gas film layer and the liquid column are gradually pushed downstream, and a relatively stable phase interface shape is maintained. If the inner micro-rib vacuum tube 3 is used as a low-temperature transmission pipeline or a partial section thereof, when the inner micro-rib vacuum tube 3 is subjected to reverse annular film boiling, the radial flow velocity impact of the gas film layer generated by the micro-rib protrusions 9 affects the stability of the phase interface, the fluctuation of the phase interface can be caused, even the interface fluctuation contacts the metal wall, or the liquid is torn from the liquid column and contacts the wall surface, the reverse annular film boiling enters the transition boiling with higher heat exchange efficiency earlier, the temperature reduction rate of the tube wall is accelerated, and the pre-cooling target is realized in a shorter time. On the whole, the introduction of the inner micro-rib vacuum tube 3 can shorten the film boiling action temperature area and action time in the precooling process, and the transition boiling and nucleation boiling action temperature areas are enlarged, so the precooling process can be accelerated. By adopting the arrangement mode of combining the inner micro-rib vacuum tube 3 and the vacuum straight tube 2, the flow resistance pressure of the whole low-temperature transmission pipeline can be effectively reduced while the precooling rate is enhanced.
Claims (7)
1. The utility model provides a quick precooling transmission pipeline structure of low temperature propellant, includes ground storage tank (1), the cryogenic liquids export of ground storage tank (1) and the entry linkage of low temperature transmission pipeline, and the export of low temperature transmission pipeline and the propellant filler of storage tank (4) on the arrow are connected, its characterized in that: the low-temperature transmission pipeline comprises an inner micro-rib vacuum pipe (3) and a vacuum straight pipe (2);
the vacuum straight pipe (2) is an annular cavity formed by an inner straight pipe (6) and an outer pipe (5), the annular cavity is vacuumized, and the outer side of the inner straight pipe (6) is wrapped by a plurality of layers of heat insulation layers (7);
the inner micro-rib vacuum tube (3) is characterized in that a micro-rib inner tube (8) and an outer tube (5) form an annular cavity, the annular cavity is vacuumized, the outer side of the micro-rib inner tube (8) is wrapped with a plurality of heat insulation layers (7), and micro-rib protrusions (9) of the micro-rib inner tube (8) are formed through machining; the introduction of the micro-rib bulges (9) causes radial components of flow velocity in the gas film, and impacts a gas-liquid phase interface to promote the reverse annular flow liquid column to be torn earlier to cause the contact of liquid and the micro-rib inner tube (8), so that the earlier conversion from film boiling to transition boiling is realized, and the precooling process is accelerated;
in practice, different arrangement modes of the inner micro-rib vacuum tube (3) and the vacuum straight tube (2) are set according to the working condition requirements: if the low-temperature transmission pipeline is shorter than 30m, the low-temperature transmission pipeline completely adopts an inner micro-rib vacuum tube (3), or the inner micro-rib vacuum tube (3) is adopted at the section close to the inlet of the low-temperature transmission pipeline, and the vacuum straight tube (2) is adopted at the section close to the outlet of the low-temperature transmission pipeline; if the low-temperature transmission pipeline is longer than 30m, the low-temperature transmission pipeline adopts a mode that inner micro-rib vacuum tubes (3) and vacuum straight tubes (2) are arranged alternately;
the micro-rib bulges (9) are formed by adopting a hydraulic forming machine, a mechanical expansion forming machine or a wave beating manufacturing machine; the rib height of the micro-rib bulges (9) is in the mm level, and the rib spacing is in the cm level; the cross section of the micro-rib protrusion (9) is rectangular or zigzag; the micro-rib bulges (9) adopt the structural forms of axisymmetric annular belts, spiral line belts or irregular inward bulges.
2. The structure of the rapid precooling delivery pipeline for the cryogenic propellant as recited in claim 1, wherein: the ground storage tank (1) is made of stainless steel, the heat insulation mode is vacuum powder or vacuum fiber heat insulation, the storage tank is horizontal or vertical, the low-temperature liquid outlet is located at the bottom of the ground storage tank (1), and liquid hydrogen, liquid oxygen, liquid methane or liquid nitrogen are stored in the ground storage tank (1).
3. The structure of the rapid precooling delivery pipeline for the cryogenic propellant as recited in claim 1, wherein: the wall surface material of the rocket storage tank (4) is aluminum alloy, stainless steel or polymer-based composite material, the storage tank is spherical or columnar, the wall thickness is 1-5 mm, the propellant filling port is positioned at the bottom or top of the rocket storage tank (4), and the surface of the rocket storage tank (4) is insulated by adopting foamed and multi-layer heat-insulating materials or is wrapped by multi-layer heat-insulating materials; liquid hydrogen, liquid oxygen, liquid methane or liquid nitrogen is stored in the rocket storage tank (4).
4. The method of claim 1The utility model provides a quick precooling transmission pipeline structure of low temperature propellant which characterized in that: the inner straight pipe (6) and the outer pipe (5) are both made of stainless steel, and the vacuum degree of the annular cavity formed by the inner straight pipe (6) and the outer pipe (5) is better than 10- 2Pa, the inner straight pipe (6) is provided with corrugated pipe wave compensation at intervals along the length direction.
5. The structure of the rapid precooling delivery pipeline for the cryogenic propellant as recited in claim 1, wherein: the pipe material of the micro-rib inner pipe (8) is stainless steel, and the vacuum degree of the annular cavity formed by the micro-rib inner pipe (8) and the outer pipe (5) is better than 10-2Pa。
6. The structure of the rapid precooling delivery pipeline for the cryogenic propellant as recited in claim 1, wherein: the multilayer heat insulation layer (7) is formed by metal reflecting screens and non-metal spacers at intervals, the layer density is 10-20 layers/cm, the metal reflecting screens are aluminum foils or aluminum-plated polyurethane films, and the non-metal spacers are made of terylene.
7. The structure of the rapid precooling delivery pipeline for the cryogenic propellant as recited in claim 1, wherein: the inner micro-rib vacuum tube (3) and the vacuum straight tube (2) are connected by flanges or welded.
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| CN111457635B (en) * | 2020-04-01 | 2021-05-28 | 西安交通大学 | Methane mixed propellant modulation/anti-icing supercooling system |
| CN111749815B (en) * | 2020-06-02 | 2021-07-06 | 上海空间推进研究所 | Low-temperature attitude control engine propellant supply pipeline system |
| CN112282968B (en) * | 2020-10-09 | 2022-03-04 | 北京宇航系统工程研究所 | Low-temperature common-bottom storage tank for conveying propellant in inner |
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