CN115217673B - Propellant cooling capacity recovery system and method for liquid rocket engine test bed - Google Patents
Propellant cooling capacity recovery system and method for liquid rocket engine test bed Download PDFInfo
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- CN115217673B CN115217673B CN202210809307.0A CN202210809307A CN115217673B CN 115217673 B CN115217673 B CN 115217673B CN 202210809307 A CN202210809307 A CN 202210809307A CN 115217673 B CN115217673 B CN 115217673B
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- 238000011084 recovery Methods 0.000 title claims abstract description 133
- 239000003380 propellant Substances 0.000 title claims abstract description 90
- 239000007788 liquid Substances 0.000 title claims abstract description 35
- 238000012360 testing method Methods 0.000 title claims abstract description 25
- 238000000034 method Methods 0.000 title claims abstract description 22
- 238000001816 cooling Methods 0.000 title description 13
- 238000005057 refrigeration Methods 0.000 claims description 21
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 14
- 238000003860 storage Methods 0.000 claims description 10
- 239000002245 particle Substances 0.000 claims description 7
- 239000012530 fluid Substances 0.000 claims description 6
- 238000009413 insulation Methods 0.000 claims description 3
- 230000008569 process Effects 0.000 description 8
- 238000004064 recycling Methods 0.000 description 7
- 230000008859 change Effects 0.000 description 6
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- 239000003507 refrigerant Substances 0.000 description 2
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- 238000012546 transfer Methods 0.000 description 2
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
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- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
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Classifications
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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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
-
- 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
-
- 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
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention relates to a propellant cold recovery system and a method for a liquid rocket engine test bed, wherein the recovery system comprises: the system comprises a primary cold energy recovery module, a secondary cold energy recovery module, a working medium supply module and a control module; the primary cold recovery module is connected with the liquid rocket engine test bed to receive the low-temperature propellant; the primary cold energy recovery module is connected with the secondary cold energy recovery module in series; the working medium supply module is used for supplying cold carrying working medium to the primary cold energy recovery module and the secondary cold energy recovery module respectively; the working medium supply module circularly conveys the cold carrying working medium to recover the cold of the primary cold recovery module, and the cold carrying working medium with partial circulation is conveyed to the secondary cold recovery module to recover the cold; the control module is respectively connected with the primary cold energy recovery module and the working medium supply module.
Description
Technical Field
The invention relates to the field of aerospace, in particular to a propellant cold recovery system and method for a liquid rocket engine test bed.
Background
The low-temperature liquid rocket engine taking low-temperature mediums such as liquid oxygen, liquid hydrogen, liquid methane and the like as propellants has advanced power in development of aerospace, and has very broad application prospect in the field of aerospace by virtue of the advantages of low temperature, high energy, no toxicity, environmental protection and the like. In the process of low-temperature liquid rocket launching and ground test organization, in order to ensure that an engine can normally start to work, an engine turbopump system needs to be cooled in advance. In ground testing, low temperature propellants are typically used to cool the pipeline to the desired temperature by means of discharge pre-cooling. The method can cause a great deal of waste of the cooling capacity of the propellant in the discharging process, and has extremely important significance for recycling the cooling capacity and saving energy.
In the prior art, the problems of complex equipment, high manufacturing cost, low recycling rate and poor practicability exist in the process of recycling cold energy; the recovered cold energy is difficult to store, and the recycling rate of the cold energy is low; in addition, the existing technology is not suitable for the scene of cold recovery of a low-temperature liquid rocket engine test bed.
Disclosure of Invention
The invention aims to provide a propellant cold recovery system and method for a liquid rocket engine test bed.
In order to achieve the above object, the present invention provides a propellant cold recovery system for a liquid rocket engine test bed, comprising: the system comprises a primary cold energy recovery module, a secondary cold energy recovery module, a working medium supply module and a control module;
the primary cold recovery module is connected with the liquid rocket engine test bed to receive the low-temperature propellant;
the primary cold energy recovery module is connected with the secondary cold energy recovery module in series;
the working medium supply module is used for supplying cold carrying working medium to the primary cold energy recovery module and the secondary cold energy recovery module respectively; the working medium supply module circularly conveys the cold carrying working medium to recover the cold of the primary cold recovery module, and the cold carrying working medium with partial circulation is conveyed to the secondary cold recovery module to recover the cold;
the control module is respectively connected with the primary cold energy recovery module and the working medium supply module.
According to one aspect of the invention, the cold-carrying working medium sent to the secondary cold recovery module by the working medium supply module recovers cold in a phase-change manner.
According to one aspect of the present invention, the primary refrigeration recovery module includes: a propellant receiving tube, a heat exchange structure connected with the propellant receiving tube, and a secondary connecting tube connected with the heat exchange structure;
The heat exchange structure includes: a hollow cylindrical barrel, at least one heat exchange spiral tube installed in the barrel;
Opposite ends of the heat exchange spiral pipe are respectively connected with the propellant receiving pipe and the secondary connecting pipe.
According to one aspect of the invention, the cylinder is of a double-layer structure, and a vacuum environment is arranged between the inner layer and the outer layer of the cylinder;
the heat exchange spiral pipes are arranged in an array mode at intervals along the axial direction of the cylinder body;
The heat exchange spiral tube is positioned at the connecting end of the outer side of the cylinder body, and heat preservation layers are arranged on the outer sides of the propellant receiving tube and the secondary connecting tube.
According to one aspect of the present invention, the primary refrigeration recovery module further comprises: a propellant shunt tube, a shunt valve disposed on the propellant shunt tube;
Opposite ends of the propellant shunt tube are respectively connected with the propellant receiving tube and the secondary connecting tube.
According to one aspect of the invention, the secondary refrigeration recovery module includes: a hollow container, a centrifugal nozzle, a pintle injector, a collection tray and a propellant output tube arranged in the container;
the centrifugal nozzle and the pintle injector are oppositely arranged in the container;
the collection tray is located below the centrifugal nozzle and the pintle injector.
According to one aspect of the invention, the centrifugal nozzle is connected with the secondary connection pipe;
The pintle injector is an axial slit radial hole type pintle injector and is connected with the working medium supply module.
According to one aspect of the invention, the working fluid supply module comprises: a first pipeline, a working medium storage tank connected with the first pipeline, a water pump connected with the working medium storage tank, a flow divider connected with the water pump, a second pipeline and a third pipeline respectively connected with two output ends of the flow divider;
the second pipeline is connected with the input end of the cylinder body, and the first pipeline is connected with the output end of the cylinder body;
the third pipeline is connected with the needle bolt injector.
In order to achieve the above object, the present invention provides a recovery method of a propellant cold recovery system for a liquid rocket engine test bed, comprising:
s1, circularly conveying a cold-carrying working medium to the primary cold recovery module through a working medium supply module;
S2, introducing low-temperature propellant output by a liquid rocket engine test bed into the primary cold recovery module;
s3, the cold-carrying working medium with partial circulation is sent to the secondary cold quantity recovery module to be contacted with the low-temperature propellant passing through the primary cold quantity recovery module and entering the secondary cold quantity recovery module.
According to one aspect of the invention, in step S3, the low-temperature propellant entering the secondary refrigeration recovery module is sprayed out in a conical air film through a centrifugal nozzle in the secondary refrigeration recovery module;
The cold carrying working medium entering the secondary cold energy recovery module is sprayed out in the form of vaporous liquid drops through a pintle injector in the secondary cold energy recovery module; wherein the particle diameter of the atomized liquid drops is 100-500 mu m.
According to the scheme provided by the invention, the cold energy contained in the precooling propellant discharged by the ground low-temperature liquid rocket engine test bed is effectively recovered and stored, so that the waste of the cold energy is greatly reduced, and the scheme has important significance in realizing the recovery and reutilization of energy sources.
According to the scheme of the invention, the recovered cold quantity can be used for cooling the thrust chamber, cooling the measurement and control cabinet, cooling the indoor temperature in summer and the like, so that additional refrigeration equipment can be saved, and the purchase and operation cost of the refrigeration equipment can be saved.
According to the scheme of the invention, the step recovery of the propellant cold of the low-temperature liquid rocket engine test bed is realized by combining forced convection and spray freezing, and the cold is stored by combining the latent heat and the sensible heat of the cold-carrying working medium, so that the excellent energy-saving and emission-reducing effects are achieved.
According to the scheme of the invention, one part of the secondary refrigerant is cooled by other test devices (such as an engine, a measurement and control room and other positions needing cooling after being recovered by the cold quantity of the primary cold quantity recovery device, and the other part of the secondary refrigerant is used for storing the cold quantity in a phase change mode by the secondary cold quantity recovery device, so that the secondary cold quantity recovery device is easy to store and transport, and the utilization scene of the cold quantity is expanded;
According to the scheme, the propellant discharge bypass is designed to ensure that the primary cold recovery device operates normally, and meanwhile, the secondary recovery quantity is increased, the total recovery quantity is not reduced, and the recovery efficiency is greatly improved.
Drawings
FIG. 1 is a block diagram schematically illustrating a propellant refrigeration recovery system according to one embodiment of the present invention;
FIG. 2 is a block diagram schematically showing a primary refrigeration recovery apparatus according to an embodiment of the present invention;
FIG. 3 is a block diagram schematically illustrating a pintle injector according to one embodiment of the present invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments will be briefly described below. It is apparent that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
In describing embodiments of the present invention, the terms "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer" and the like are used in terms of orientation or positional relationship based on that shown in the drawings, which are merely for convenience of description and to simplify the description, rather than to indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operate in a specific orientation, and thus the above terms should not be construed as limiting the present invention.
The present invention will be described in detail below with reference to the drawings and the specific embodiments, which are not described in detail herein, but the embodiments of the present invention are not limited to the following embodiments.
As shown in fig. 1, according to an embodiment of the present invention, a propellant cold recovery system for a liquid rocket engine test bed of the present invention includes: the system comprises a primary cold energy recovery module 1, a secondary cold energy recovery module 2, a working medium supply module 3 and a control module 4. In this embodiment, the primary refrigeration recovery module 1 is connected to a liquid rocket engine test bed to receive cryogenic propellant. In the present embodiment, the primary refrigeration recovery module 1 and the secondary refrigeration recovery module 2 are connected in series; the low-temperature propellant realizes the first-stage cold energy recovery in the first-stage cold energy recovery module 1, and then enters the second-stage cold energy recovery module 2 through the low-temperature propellant of the first-stage cold energy recovery module 1 to realize the second-stage cold energy recovery, thereby realizing the cascade cold energy recovery effect. Finally, since the cold of the low-temperature propellant is recovered, the low-temperature propellant can be output to a downstream device through a subsequent pipeline to realize storage for subsequent recycling.
In this embodiment, in order to achieve the normal operation of the primary cold energy recovery module 1 and the secondary cold energy recovery module 2, the working medium supply module 3 is required to provide a corresponding cold-carrying working medium to achieve the absorption or storage of cold energy. Specifically, the working medium supply module 3 is respectively used for supplying cold-carrying working medium to the primary cold energy recovery module 1 and the secondary cold energy recovery module 2; wherein, the working medium supply module 3 circularly conveys the cold carrying working medium to recycle the cold of the first-stage cold recycling module 1, and the cold carrying working medium with partial circulation is conveyed to the second-stage cold recycling module 2 to recycle the cold.
In this embodiment, the control module 4 is connected with the primary cold energy recovery module 1 and the working medium supply module 3 respectively, so as to monitor the temperature and flow in the cold energy recovery process, and control the flow in the pipeline according to the monitored data, so as to realize the efficient and stable operation of the whole cold energy recovery system.
As shown in fig. 1, according to an embodiment of the present invention, the cold-carrying working medium sent to the secondary cold recovery module 2 by the working medium supply module 3 recovers cold in a phase-change manner. In this embodiment, the cold-carrying working medium for recovering cold in the two recovery modules is stored in the working medium supply module 3, and the cold-carrying working medium has the characteristic of phase change in different temperature ranges, so that the phase change is realized during secondary cold recovery to achieve the effect of storing cold, and the cold-carrying working medium is convenient to transport and easy to store.
As shown in fig. 1 and 2 in combination, according to an embodiment of the present invention, a primary refrigeration recovery module 1 includes: a propellant receiving tube 11, a heat exchange structure 12 connected to the propellant receiving tube 11, and a secondary connection tube 13 connected to the heat exchange structure 12. In the present embodiment, the heat exchange structure 12 includes: a hollow cylindrical barrel 121, at least one heat exchanging spiral tube 122 mounted within the barrel 121. In this embodiment, both the inlet and outlet ends of the heat exchanging coil 122 are provided through the cylinder 121 to facilitate communication with the external propellant receiving tube 11 and the secondary connection tube 13. In this embodiment, the inlet end and the outlet end of the heat exchanging spiral tube 122 respectively penetrate through the wall of the cylinder in the radial direction of the cylinder 121 and are connected in a sealing manner at the connection position, so that the series connection of the propellant receiving tube 11 and the secondary connection tube 13 with the heat exchanging spiral tube 122 in the radial direction of the cylinder 121 can be realized.
Through the arrangement, the heat exchange structure 12 can realize that the cold-carrying working medium flows along the axial direction of the cylinder 121 and fully contacts with the heat exchange spiral tube by arranging the cylindrical cylinder 121 and installing the heat exchange spiral tube in the cylinder 121, so that the heat exchange efficiency is ensured.
As shown in connection with fig. 1 and 2, according to one embodiment of the present invention, the cylinder 121 has a double-layered structure, and a vacuum environment is provided between the inner layer and the outer layer of the cylinder 121.
As shown in connection with fig. 1 and 2, according to one embodiment of the present invention, a plurality of heat exchanging spiral pipes 122 are arranged in a spaced array along the axial direction of the cylinder 121.
As shown in connection with fig. 1 and 2, according to one embodiment of the present invention, the connection end of the heat exchanging spiral pipe 122 at the outside of the cylinder 121, and the outside of the propellant receiving tube 11 and the secondary connection tube 13 are provided with insulation layers. In this embodiment, the inlet ends of the heat exchanging spiral pipe 122 at the outer side of the cylinder 121 are respectively connected to the propellant receiving pipe 11 through pipelines, the outlet ends at the outer side of the cylinder 121 are respectively connected to the secondary connecting pipe 13 through pipelines, and heat insulation layers are required to be respectively arranged on the pipelines which are connected to isolate the heat exchanging spiral pipe from the external environment, so that the loss of cold energy in the transmission process is reduced or eliminated. In this embodiment, the heat insulating layer may be a polystyrene heat insulating layer.
By adopting the mode of coating the heat preservation layer, the connection positions of the propellant receiving pipe 11, the secondary connecting pipe 13 and the propellant receiving pipe 11 and the heat exchange spiral pipe can be effectively realized, the connection positions of the secondary connecting pipe 13 and the heat exchange spiral pipe are fully covered, the heat preservation performance is effectively ensured, and the heat exchange efficiency of the invention is improved.
As shown in fig. 1, according to an embodiment of the present invention, the primary refrigeration recovery module 1 further includes: a propellant shunt tube 14, and a shunt valve 15 provided on the propellant shunt tube 14. In the present embodiment, the opposite ends of the propellant shunt tube 14 are connected to the propellant receiving tube 11 and the secondary connection tube 13, respectively. By arranging the propellant shunt pipe and the shunt valve, the low-temperature propellant received on the propellant receiving pipe 11 can be subjected to shunt control, so that the stability of the heat exchange process of the primary cold recovery module is realized, and the purpose of flexible control is achieved. For example, considering that the ambient temperature in winter is low, when the usage of the cold-carrying working medium obtained after heat exchange in the first-stage cold energy recovery module (for example, the coolant for other equipment is cooled) is reduced, the low-temperature propellant can be directly shunted to the second-stage cold energy recovery module without entering or with a small amount entering the first-stage cold energy recovery module through the propellant shunt tube 14, so as to participate in the construction of the low-temperature environment, and meanwhile, the flow of the cold-carrying working medium entering the second-stage cold energy recovery module is increased by adjusting the ratio of the water pump and the shunt in the working medium supply module 3 so as to generate more solid cold-carrying working medium, so that the cold energy of the low-temperature propellant is stored in a latent heat cold storage mode so as to be convenient for subsequent use.
In addition, through the mode of connecting the propellant shunt tubes to the second grade connecting tube, the propellant that exports in the first grade cold recovery module mixes with the propellant that shunts to make the propellant of different temperatures mix, and then can make the temperature of the propellant that shunts improve, in order to make things convenient for the stable blowout to the propellant after mixing in the follow-up second grade cold recovery module.
As shown in fig. 1, according to an embodiment of the present invention, a secondary refrigeration recovery module 2 includes: a hollow container 21, a centrifugal nozzle 22, a pintle injector 23, a collection tray and a propellant outlet tube 24 arranged in the container 21. In this embodiment, the container 21 may be configured as a cubic hollow container, and of course, in order to facilitate installation of each structure inside, a split structure may be used, for example, the container 21 may include: the upper end open-ended box and with the upper cover that the box opened and shut and set up, centrifugal nozzle 22 and the inside pin injector 23 are relative to the injection propellant and carry cold working medium's in-process, and the upper cover is sealed lock with the box to guarantee inside heat transfer process and external isolation, when need to maintain the additional structures such as collection dish to inner structure, open the upper cover and can be convenient operation. In this embodiment, the whole container 21 is made of heat-insulating material to isolate heat exchange between the inside and the outside, ensure the efficiency of recovering the cold in the inside, and eliminate the loss of the cold.
In the present embodiment, the centrifugal nozzle 22 and the pintle injector 23 are disposed in opposition to each other in the container 21. The method has the advantages that the relative injection of the propellant and the cold-carrying working medium is conveniently realized, the heat exchange can be realized in a mode that the propellant and the cold-carrying working medium are in direct contact, the conduction process of an intermediate medium is omitted, the high efficiency and the high speed of the heat exchange are realized, and the loss in the heat exchange process is effectively eliminated.
In this embodiment, the collection tray is located below the centrifugal nozzle 22 and the pintle injector 23. In this embodiment, the opening of the collecting tray is disposed upward, and the coverage area of the opening of the collecting tray is required to satisfy the falling range of the cold-carrying medium after the phase change formed after the heat exchange between the centrifugal nozzle 22 and the pintle injector 23, so that the cold-carrying medium can be effectively ensured to fall into the collecting tray effectively, and the collecting and storing of the cold-carrying medium are facilitated.
As shown in fig. 1, according to an embodiment of the present invention, a centrifugal nozzle 22 is connected to the secondary connection pipe 13; the pintle injector 23 is an axial slot radial hole type pintle injector and is connected with the working medium supply module 3.
As shown in fig. 3, according to one embodiment of the present invention, the pintle injector 23 includes: an annular flow ejection structure 231 and a radial flow ejection structure 232. In the present embodiment, the radial flow ejection structure 232 is coaxially disposed with the annular flow ejection structure 231 and penetrates through the annular flow ejection structure 231, wherein one end of the radial flow ejection structure 232 is provided with a radial ejection opening 232a, and the radial ejection opening 232a is formed by a plurality of arc-shaped openings arranged at intervals or a plurality of hole-shaped openings (such as round holes, rectangular holes, etc.) arranged at intervals, so as to be used for radially ejecting radial jet flows;
In the present embodiment, an annular gap is provided between the annular ejection structure 231 and the connection position of the radial ejection structure 232 at a position close to the radial ejection structure 232a to form an axial ejection opening 231a, and an axial liquid film is formed by the axial ejection opening 231a for ejecting an axial circulation in the axial direction. Further, the radial jet and the axial liquid film jet are broken and atomized after being impacted to form tiny liquid drops.
In the present embodiment, the annular flow ejection structure 231 includes: the base 2311. In the present embodiment, the seat body 2311 is provided with a first annular passage 2311a for communicating with the axial ejection port 231a, and a second annular passage 2311b communicating with the first annular passage 2311 a. In the present embodiment, the first annular channel 2311a and the second annular channel 2311b have a spaced communication arrangement along the axial direction of the seat body 2311.
In this embodiment, the cross-sectional area of the second annular channel 2311b is larger than that of the first annular channel 2311a, so that more flow can be stored through the second annular channel 2311b to ensure stable output of the axial ejection port 231 a.
In this embodiment, the seat body 2311 is further provided with a material conveying channel 2311c for communicating with the second annular channel 2311b, for receiving a stream outputted from the outside.
In this embodiment, the radial flow spraying structure 232 is a hollow cylinder with one end open and one end closed, and the radial spraying opening 232a is disposed on the side wall of the closed end, so as to realize radial spraying of the internal cold-carrying working medium.
In the present embodiment, the radial direction ejection port 232a is provided so that the axial direction thereof is perpendicular to the axial direction of the axial direction ejection port 231 a.
As shown in fig. 1, according to an embodiment of the present invention, a working fluid supply module 3 includes: the hydraulic system comprises a first pipeline 31, a working medium storage tank 32 connected with the first pipeline 31, a water pump 33 connected with the working medium storage tank 32, a flow divider 34 connected with the water pump 33, a second pipeline 35 and a third pipeline 36 respectively connected with two output ends of the flow divider 34. In this embodiment, the water pump 33 is connected to the working fluid tank 32 through a pipeline, and is used for pumping out the cold-carrying working fluid in the working fluid tank 32 for circulation. The flow divider 34 is connected with the water pump 33 through a pipeline, and divides the cold-carrying working medium output by the water pump into two paths for output, and then the cold-carrying working medium is sent to a corresponding device through a second pipeline 35 and a third pipeline 36 which are connected with each other to realize cold recovery. In this embodiment, the flow divider 34 is implemented by a venturi, and may be implemented by a venturi with different sizes according to the flow of the input cold-carrying medium to control the output flow.
In the present embodiment, the second pipe 35 is connected to the input end of the cylinder 121, and the first pipe 31 is connected to the output end of the cylinder 121. Wherein, the cold energy utilization device M is installed on the second pipeline 35 to realize the primary utilization of energy. In this embodiment, the third line 36 is connected to the pintle injector 23; the third pipeline 36 is connected to the material flow inlet on the cover 2312 and the opening end of the nozzle 2322 in the radial spraying structure 232.
As shown in fig. 1, according to one embodiment of the present invention, the control module 4 includes: a PLC controller, a temperature sensor and a flow sensor. In the present embodiment, the control module 4 is configured to adjust the operation state of each module according to the state of the recovery system. In this embodiment, the control module 4 senses the operation state of the recovery system through a temperature sensor and a flow sensor, and monitors the temperature and the flow of key points of the system to achieve corresponding sensing capability. Specifically, a temperature sensor and a flow sensor may be respectively installed on the propellant receiving tube 11, the first pipeline 31, the second pipeline 35, the pipeline between the water pump 33 and the working medium storage tank 32, and the pipeline between the water pump 33 and the flow divider 34. And then comparing the monitored temperature and flow with the parameters of the key nodes which are initially set, and sending out an adjusting instruction. In the present embodiment, the control module 4 is also connected to the structure such as the diverter valve 15 and the water pump 33, so as to achieve the adjustment function. In this embodiment, the parameters of the key nodes that are initially set may be determined through theoretical calculation and experiments in advance, and the specific control algorithm may be implemented by using a fuzzy PID algorithm.
According to one embodiment of the invention, the cold-carrying working medium is water. Of course, other types of cold-carrying working media can be selected according to actual needs or different propellant types, as long as corresponding phase change performance can be realized.
As shown in fig. 1, according to an embodiment of the present invention, a recovery method using the aforementioned propellant refrigeration recovery system of the present invention includes:
S1, circularly conveying a cold carrying working medium to a primary cold recovery module 1 through a working medium supply module 3;
s2, introducing low-temperature propellant output by a liquid rocket engine test bed into the primary cold recovery module 1;
s3, the cold-carrying working medium with partial circulation is sent to the secondary cold quantity recovery module 2 to be contacted with the low-temperature propellant passing through the primary cold quantity recovery module 1 and entering the secondary cold quantity recovery module 2.
As shown in fig. 1, in step S3, the low-temperature propellant entering the secondary refrigeration recovery module 2 is sprayed out through the centrifugal nozzle 22 in the secondary refrigeration recovery module 2 with a conical air film at a certain speed, and a low-temperature environment can be formed in the secondary refrigeration recovery module 2; the cold carrying working medium entering the secondary cold energy recovery module 2 is sprayed out in the form of vaporous liquid drops through a pintle injector 23 in the secondary cold energy recovery module 2; wherein the particle diameter of the atomized liquid drops is 100-500 mu m. In the embodiment, the crushed and atomized cold-carrying working medium is contacted with the low-temperature propellant so as to quickly perform heat exchange and generate solid particles with corresponding particle diameters (namely 100-500 mu m), and the solid particles fall into a collecting tray below to achieve the effects of heat exchange and cold energy storage.
Through the arrangement, the small liquid drops which atomize the cold-carrying working medium into the particle size are contacted with the low-temperature working medium, so that the cold-carrying working medium can be contacted with the propellant with extremely large surface area and speed in the continuous spraying process, the improvement of the convective heat transfer coefficient is facilitated, and the phase change speed and the cold recovery efficiency of the cold-carrying working medium are further improved.
According to the propellant cooling gradient recovery scheme, the cooling capacity of the externally discharged propellant is recovered by adopting a mode of combining forced convection heat exchange and spray freezing on the premise of not affecting the normal operation of a test system, and the recovered cooling capacity is stored through sensible heat cold accumulation and latent heat cold accumulation, so that the waste of the cooling capacity is greatly reduced, and the method has important significance for the green low-carbon high-quality development of low-temperature liquid rocket engine test equipment.
The foregoing is merely exemplary of embodiments of the invention and, as regards devices and arrangements not explicitly described in this disclosure, it should be understood that this can be done by general purpose devices and methods known in the art.
The above description is only one embodiment of the present invention, and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. Propellant cold recovery system for liquid rocket engine test bed, characterized by comprising: the system comprises a primary cold energy recovery module (1), a secondary cold energy recovery module (2), a working medium supply module (3) and a control module (4);
The primary cold energy recovery module (1) is connected with a liquid rocket engine test bed so as to receive low-temperature propellant;
The primary cold energy recovery module (1) is connected in series with the secondary cold energy recovery module (2);
The working medium supply module (3) is used for supplying cold carrying working medium to the primary cold energy recovery module (1) and the secondary cold energy recovery module (2) respectively; the working medium supply module (3) circularly conveys the cold carrying working medium to recover the cold of the primary cold energy recovery module (1), and the cold carrying working medium with partial circulation is conveyed to the secondary cold energy recovery module (2) to recover the cold;
The control module (4) is respectively connected with the primary cold energy recovery module (1) and the working medium supply module (3);
the primary refrigeration recovery module (1) comprises: a propellant receiving tube (11), a heat exchange structure (12) connected to the propellant receiving tube (11), a secondary connection tube (13) connected to the heat exchange structure (12);
The heat exchange structure (12) comprises: a hollow cylindrical cylinder (121), at least one heat exchanging spiral tube (122) installed in the cylinder (121);
opposite ends of the heat exchange spiral pipe (122) are respectively connected with the propellant receiving pipe (11) and the secondary connecting pipe (13);
The cylinder body (121) is of a double-layer structure, and a vacuum environment is arranged between the inner layer and the outer layer of the cylinder body (121);
The heat exchange spiral pipes (122) are arranged in an array at intervals along the axial direction of the cylinder body (121);
the heat exchange spiral pipe (122) is positioned at the connecting end of the outer side of the cylinder body (121), and heat insulation layers are arranged on the outer sides of the propellant receiving pipe (11) and the secondary connecting pipe (13);
the primary cold recovery module (1) further comprises: a propellant shunt tube (14), a shunt valve (15) provided on the propellant shunt tube (14);
opposite ends of the propellant shunt tube (14) are respectively connected with the propellant receiving tube (11) and the secondary connecting tube (13);
the secondary refrigeration recovery module (2) comprises: a hollow container (21), a centrifugal nozzle (22), a pintle injector (23), a collection tray and a propellant output tube (24) arranged in the container (21);
the centrifugal nozzle (22) and the pintle injector (23) are oppositely arranged in the container (21);
The collection tray is located below the centrifugal nozzle (22) and the pintle injector (23).
2. Propellant cold recovery system according to claim 1, characterized in that the cold-carrying medium fed to the secondary cold recovery module (2) by the medium supply module (3) recovers cold in a phase-change manner.
3. Propellant cold energy recovery system according to claim 2, characterized in that the centrifugal nozzle (22) is connected to the secondary connection tube (13);
the pintle injector (23) is an axial slit radial hole type pintle injector and is connected with the working medium supply module (3).
4. A propellant cold recovery system according to claim 3, wherein the working fluid supply module (3) comprises: a first pipeline (31), a working medium storage tank (32) connected with the first pipeline (31), a water pump (33) connected with the working medium storage tank (32), a flow divider (34) connected with the water pump (33), a second pipeline (35) and a third pipeline (36) respectively connected with two output ends of the flow divider (34);
the second pipeline (35) is connected with the input end of the cylinder (121), and the first pipeline (31) is connected with the output end of the cylinder (121);
the third line (36) is connected to the pintle injector (23).
5. A recovery method employing the propellant cold recovery system for a liquid rocket engine test bed of any one of claims 1 to 4, comprising:
S1, circularly conveying a cold carrying working medium to the primary cold recovery module (1) through the working medium supply module (3);
S2, introducing low-temperature propellant output by a liquid rocket engine test bed into the primary cold energy recovery module (1);
S3, the cold-carrying working medium with partial circulation is sent to the secondary cold quantity recovery module (2) so as to be in contact with the low-temperature propellant passing through the primary cold quantity recovery module (1) and entering the secondary cold quantity recovery module (2).
6. The recovery method according to claim 5, characterized in that in step S3, the low-temperature propellant entering the secondary cold recovery module (2) is ejected in a conical gas film through a centrifugal nozzle (22) in the secondary cold recovery module (2);
the cold-carrying working medium entering the secondary cold recovery module (2) is sprayed out in the form of vaporous liquid drops through a pintle injector (23) in the secondary cold recovery module (2); wherein the particle diameter of the atomized liquid drops is 100-500 mu m.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2640322A1 (en) * | 1988-12-09 | 1990-06-15 | Europ Propulsion | Rocket motor, or combined motor for a space vehicle with an essentially closed auxiliary hydraulic circuit |
| CN110219751A (en) * | 2019-06-28 | 2019-09-10 | 蓝箭航天空间科技股份有限公司 | A kind of multiple starting system and starting method of recyclable liquid-propellant rocket engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| FR2948152B1 (en) * | 2009-07-17 | 2012-02-03 | Snecma | CRYOTECHNIC ERGOL FUSE MOTOR |
| CN102441290A (en) * | 2010-10-11 | 2012-05-09 | 中国科学院理化技术研究所 | Oil gas condensation recovery method and device based on turboexpander refrigeration |
| CN112431692B (en) * | 2020-11-17 | 2021-08-03 | 中国人民解放军战略支援部队航天工程大学 | Cooperation air-breathing liquid rocket engine propellant supply system |
| CN113607448B (en) * | 2021-07-19 | 2022-08-16 | 江苏科技大学 | Heat exchanger performance test bed for oil gas liquefaction recovery and test method thereof |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2640322A1 (en) * | 1988-12-09 | 1990-06-15 | Europ Propulsion | Rocket motor, or combined motor for a space vehicle with an essentially closed auxiliary hydraulic circuit |
| CN110219751A (en) * | 2019-06-28 | 2019-09-10 | 蓝箭航天空间科技股份有限公司 | A kind of multiple starting system and starting method of recyclable liquid-propellant rocket engine |
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