CN109579351A - Big flow liquid oxygen based on Supersonic Ejector crosses cooling method - Google Patents
Big flow liquid oxygen based on Supersonic Ejector crosses cooling method Download PDFInfo
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- CN109579351A CN109579351A CN201811375459.4A CN201811375459A CN109579351A CN 109579351 A CN109579351 A CN 109579351A CN 201811375459 A CN201811375459 A CN 201811375459A CN 109579351 A CN109579351 A CN 109579351A
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- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 title claims abstract description 99
- 238000001816 cooling Methods 0.000 title abstract description 6
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 125
- 239000007789 gas Substances 0.000 claims abstract description 83
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 61
- 238000002156 mixing Methods 0.000 claims abstract description 56
- 238000004781 supercooling Methods 0.000 claims abstract description 54
- 239000007788 liquid Substances 0.000 claims abstract description 53
- 238000002347 injection Methods 0.000 claims abstract description 39
- 239000007924 injection Substances 0.000 claims abstract description 39
- 229920006395 saturated elastomer Polymers 0.000 claims abstract description 9
- 239000011555 saturated liquid Substances 0.000 claims abstract description 8
- 238000000034 method Methods 0.000 claims description 28
- 230000003068 static effect Effects 0.000 claims description 20
- 230000006835 compression Effects 0.000 claims description 17
- 238000007906 compression Methods 0.000 claims description 17
- 238000004364 calculation method Methods 0.000 claims description 12
- 238000011084 recovery Methods 0.000 claims description 12
- 238000001704 evaporation Methods 0.000 claims description 9
- 230000008020 evaporation Effects 0.000 claims description 9
- 238000013461 design Methods 0.000 claims description 6
- 239000002737 fuel gas Substances 0.000 claims description 5
- 238000007599 discharging Methods 0.000 claims description 3
- 230000002123 temporal effect Effects 0.000 claims description 3
- 238000009834 vaporization Methods 0.000 claims description 3
- 230000008016 vaporization Effects 0.000 claims description 3
- 238000011049 filling Methods 0.000 abstract description 11
- 239000003380 propellant Substances 0.000 description 17
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 8
- 238000009792 diffusion process Methods 0.000 description 7
- 239000013526 supercooled liquid Substances 0.000 description 7
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 6
- 239000001301 oxygen Substances 0.000 description 6
- 229910052760 oxygen Inorganic materials 0.000 description 6
- 230000008569 process Effects 0.000 description 5
- 238000005057 refrigeration Methods 0.000 description 5
- 235000015842 Hesperis Nutrition 0.000 description 4
- 235000012633 Iberis amara Nutrition 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 4
- 230000008602 contraction Effects 0.000 description 3
- 238000000605 extraction Methods 0.000 description 3
- 238000005429 filling process Methods 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 238000003860 storage Methods 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000009835 boiling Methods 0.000 description 2
- 230000006837 decompression Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 229910001873 dinitrogen Inorganic materials 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000002309 gasification Methods 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 230000000704 physical effect Effects 0.000 description 2
- 238000005381 potential energy Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000005514 two-phase flow Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000004401 flow injection analysis Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- QJGQUHMNIGDVPM-UHFFFAOYSA-N nitrogen(.) Chemical compound [N] QJGQUHMNIGDVPM-UHFFFAOYSA-N 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B19/00—Machines, plants or systems, using evaporation of a refrigerant but without recovery of the vapour
- F25B19/005—Machines, plants or systems, using evaporation of a refrigerant but without recovery of the vapour the refrigerant being a liquefied gas
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B41/00—Fluid-circulation arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B2341/00—Details of ejectors not being used as compression device; Details of flow restrictors or expansion valves
- F25B2341/001—Ejectors not being used as compression device
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Thermal Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The invention discloses a kind of, and the big flow liquid oxygen based on Supersonic Ejector crosses cooling method, will be used as first-class heat exchanger using heat exchanger used in conventional saturated liquid nitrogen supercooling liquid oxygen, can will cross cold flow and is greater than the liquid oxygen of 4500L/min and cross from 92K and be cooled to 80K；Secondary heat exchanger is set in the downstream of first-class heat exchanger, can will cross be cooled to 80K and cross liquid oxygen of the cold flow greater than 4500L/min and cross and be cooled to 67K or less；Liquid nitrogen in a saturated state is filled in secondary heat exchanger, interior liquid nitrogen temperature is no more than 64K, and gas outlet is connected with Supersonic Ejector by injection air flow inlet；The injection air flow inlet of Supersonic Ejector connects the gas outlet of gas generator；Supersonic Ejector successively includes the mixing section being coaxially disposed, ultra-expanded section and sub- expansion section along airflow direction；Mixing section is the taper equipressure mixing chamber of cross-sectional constriction.The present invention can satisfy the needs that big flow liquid oxygen before CZ-5 etc. emits is quickly cooled down filling.In addition, the sucking rate of Supersonic Ejector can be made to match with load, it is safer, reliable.
Description
Technical Field
The invention relates to the field of space low-temperature carrier rockets, in particular to a high-flow liquid oxygen supercooling method based on an ultrasonic ejector.
Background
With the vigorous development of aerospace industry in China, new requirements are put forward on the carrying capacity of a carrier rocket. In order to improve the carrying capacity and meet the implementation requirements of future large space stations and lunar exploration projects, the long-standing carrier rockets 5, 6 and 7 of the cryogenic liquid propellant are used in succession. At present, low-temperature propellants adopted by a carrier rocket are all in a saturated state, most of thermodynamic states are near boiling point temperature, thermophysical properties are insufficient, and particularly, density and unit volume refrigeration capacity are small. When the mass of the low-temperature propellant is fixed, the small density can lead the volume size of the low-temperature propellant storage box to be increased, so that the total takeoff mass of the carrier rocket is increased. The small refrigeration capacity per unit volume can increase the gasification loss of the propellant, and the propellant needs to be replenished for many times before being launched, so that the propellant cannot meet the requirement of emergency launching. Meanwhile, for long-term on-orbit spacecraft, the low refrigeration capacity can cause the gasification loss of the low-temperature propellant to be increased, and the spacecraft needs to frequently deflate and reduce the pressure, thereby causing the waste of the propellant.
The supercooling of the propellant can improve the thermodynamic performance of the cryogenic propellant. For a liquid hydrogen/liquid oxygen rocket, the supercooling of the propellant can reduce the structural mass of the takeoff rocket by about 20 percent, and the carrying capacity of the high-thrust rocket is obviously improved. The high apparent refrigeration capacity advantage of the super-cooling propellant can also be applied to lunar exploration engineering and deep space exploration, the task time of the spacecraft is prolonged, and the deep space exploration range is widened.
The new generation of high thrust rockets uses liquid oxygen as the main oxidant. The rapid supercooling filling of the large-flow liquid oxygen can improve the density and the sensible cooling capacity of the liquid oxygen, remarkably improve the carrying capacity and the launching standby time of the rocket, effectively prevent two-phase flow in the liquid oxygen filling process and have important engineering application value.
The new generation of high thrust launch vehicles, represented by CZ-5, use liquid oxygen as the primary oxidizer. At present, a large-flow filling process of a launching base adopts saturated liquid oxygen and has the defects of low density, low apparent cooling capacity and the like. The supercooling heat exchange is carried out on the liquid oxygen, the density and the refrigeration capacity of the liquid oxygen can be improved, the carrying capacity and the launching standby time of the rocket are obviously improved, two-phase flow in the filling process is effectively prevented, and the supercooling heat exchange has very important engineering application value. At present, the supercooling guarantee capacity of a launching base to large-flow liquid oxygen is limited, the problems of small supercooling flow, low supercooling degree and the like exist, and the launching requirement of rapid supercooling of large-flow liquid oxygen is difficult to adapt.
Decompression subcooling is the usual subcooling means used for cryogenic propellants. When the high-flow liquid oxygen is supercooled, a vacuum compressor is required to maintain lower air pillow pressure and continuously pump high-flow steam.
Heat exchange supercooling and evacuation decompression supercooling are two common low-temperature propellant supercooling modes. The national NASA Greenwich research center adopts a three-stage vacuum compressor to decompress and supercool liquid nitrogen and then utilizes the supercooled liquid nitrogen to exchange heat and cool liquid oxygen. The liquid oxygen supercooling system can reduce the pressure of a liquid nitrogen air pillow to 17.24-68.95 KPa, the flow rate of supercooled liquid oxygen is 700L/min, the temperature of outlet liquid oxygen is reduced to 66.67K, and the density of liquid oxygen is improved by about 10%. A supercooling system needs to maintain a high vacuum degree and a large amount of liquid nitrogen evaporation in the working process, and the performance requirement on a multistage vacuum compressor is high. At present, the technical level of domestic vacuum compressors is difficult to meet the requirement of a large-flow liquid oxygen rapid supercooling heat exchanger.
At present, application research of supercooled low-temperature propellants in China just starts, the guarantee capability of a launching base for supercooling of large-flow liquid oxygen is limited, saturated liquid nitrogen supercooled liquid oxygen (the liquid oxygen can be supercooled from 92K to about 80K) is mainly adopted in a supplement process before injection, and the application of the supercooled liquid oxygen in a new generation of liquid rocket engine is restricted.
The applicant is taken as a link between a base and an industrial department, and the supersonic ejector-based large-flow liquid oxygen supercooling method is designed by cooperation of colleges and universities, bases and industrial departments aiming at the problems that the domestic vacuum compressor process level is difficult to meet the requirement of a large-flow liquid oxygen rapid supercooling heat exchanger and the supercooling flow is small, the supercooling degree is low and the like when saturated liquid nitrogen is adopted for supercooling liquid oxygen.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a large-flow liquid oxygen supercooling method based on an ultrasonic ejector, aiming at the defects of the prior art, the large-flow liquid oxygen supercooling method based on the ultrasonic ejector creatively introduces the ultrasonic ejector into a saturated liquid nitrogen supercooling liquid oxygen method, can cool the liquid oxygen to below 67K, and can ensure that the liquid oxygen supercooling flow is more than 4500L/min, so that the requirements of large-flow liquid oxygen rapid cooling and filling before emission of CZ-5 and the like can be met. In addition, the air extraction quantity of the supersonic ejector can be matched with the load, and the supersonic ejector is safer and more reliable.
In order to solve the technical problems, the invention adopts the technical scheme that:
a high-flow liquid oxygen supercooling method based on an ultrasonic ejector takes a heat exchanger used by conventional saturated liquid nitrogen supercooling liquid oxygen as a primary heat exchanger, and the primary heat exchanger can supercool liquid oxygen with supercooling flow of more than 4500L/min from 92K to 80K; and a secondary heat exchanger is arranged at the downstream of the primary heat exchanger, and can supercool the liquid oxygen with the supercooling flow rate of more than 4500L/min to below 67K to 80K.
Liquid nitrogen in a saturated state is filled in the secondary heat exchanger, the temperature of the liquid nitrogen in the secondary heat exchanger is not more than 64K, and the air outlet of the secondary heat exchanger is connected with the injected airflow inlet of the supersonic ejector.
The jet air inlet of the supersonic ejector is connected with the air outlet of the fuel gas generator.
The supersonic ejector sequentially comprises a mixing section, a super-expansion section and a sub-expansion section which are coaxially arranged along the airflow direction; the mixing section is a conical isobaric mixing chamber with a contracted section, and the static pressure on the inlet, the outlet and the whole inner wall surface of the mixing section is equal.
And the liquid nitrogen steam in the secondary heat exchanger is injected airflow, and the total flow of the gas generator and the physical parameters of the supersonic ejector are designed according to the parameters of the injected airflow and the evaporation capacity of the liquid nitrogen.
The design method of total flow and supersonic ejector physical parameters of the gas generator includes the following steps:
step 1, calculating the compression ratio CR of the supersonic ejector:
in the formula, p4Static pressure of mixed gas at the longitudinal section of an outlet of the sub-expansion section; p is a radical of02For the liquid nitrogen in the secondary heat exchanger to be kept atThe temporal air pillow pressure or saturated steam pressure; wherein,
and 2, searching the relation between the ejection coefficient n and the compression ratio CR of the supersonic ejector, and specifically comprising the following steps:
step 21, mixing section specific heat ratio gamma3Searching the relation between the injection coefficient n:
in the formula, gamma2Specific heat ratio of the injected air flow, gamma1Specific heat ratio of jet air flow, mu1For injecting the molecular weight of the gas flow, mu2Is the molecular weight of the injected air flow.
Step 22, mixing section exit velocity factor λ3Calculated using the following formula:
wherein,
in the formula, R1For injection of gas constant, R2Is an injected gas constant, R3Is the gas constant at the outlet of the mixing section; t is01For injecting the total temperature of the gas, T02The total temperature of the injected gas; lambda [ alpha ]1For injecting gas velocity coefficient, lambda2Is the velocity coefficient of the injected gas;
will be described in detail21 calculated gamma3And c is substituted into the above formula to obtain lambda3And n.
Step 23, the total pressure recovery coefficient sigma in the mixed gas flow deceleration processTThe calculation of (2):
σT＝σshockσsub
wherein,
in the formula, σshockFor total pressure recovery of the over-extension section, σsubThe total pressure recovery coefficient of the sub-expansion section is 1.0; ma3The Mach number of the inlet of the super-expanding section is; gamma calculated from steps 21 and 223And lambda3Substituting the above formula to obtain σTAnd n.
And step 24, discharging speed coefficient lambda of sub-expansion section of the supersonic ejector4And (4) calculating.
Wherein,
in the formula, psi is the area expansion ratio of the sub-expansion segment, and the value is 2.0; gamma calculated in step 23、λ3And σ calculated in step 23TSubstituting into the above formula to obtain λ4The relationship between n;
step 25, total pressure p of the mixing section03Total pressure p of injected air flow02And (3) calculating a ratio:
wherein,
step 26, calculating a formula of the supersonic ejector compression ratio CR:
wherein,
converting the gamma calculated in steps 21 to 253、σT、λ4Andsubstituting the pressure ratio CR of the supersonic ejector and the ejection coefficient n into the step 26 to obtain the relation between the compression ratio CR and the ejection coefficient n of the supersonic ejector;
step 3, determining the injection coefficient n value: and (3) substituting the CR value obtained by calculation in the step (1) into the relation between CR and n searched in the step (2), so as to determine the injection coefficient n value.
Step 4, total flow m of gas generator1And calculating, comprising the following steps.
Step 41, calculating the evaporation capacity of liquid nitrogen according to the following formula
In the formula,representing the rate of liquid oxygen evolution heat in the secondary heat exchanger; h is that liquid nitrogen in the secondary heat exchanger is kept atLatent heat of vaporization in time.
Step 42 total flow m of gasifier1And (3) calculating:
substituting the injection coefficient n determined in the step 3 into the formula to obtain the total flow m of the gas generator1The value is obtained.
And 5, calculating the physical parameters of the supersonic ejector: the physical parameters of the supersonic ejector comprise a mixed section shrinkage ratio phi, and the mixed section shrinkage ratio phi is calculated by adopting the following formula:
wherein,
the injection coefficient n determined in the step 3 and the gamma calculated according to the formula in the step 23And λ3Substituting the formula into the formula to obtain the mixed section shrinkage ratio phi.
In step 41, the rate of heat release of liquid oxygen in the secondary heat exchangerThe calculation formula of (a) is as follows:
wherein, Cp＝A+BT+CT2+DT3+ET4
In the formula, CpThe specific heat at low temperature of liquid oxygen is expressed by the unit of J/kmol/K, and the application range of a calculation formula is 54.36K-142K; A. b, C, D and E are both constants;the set liquid oxygen heat exchange flow is obtained; t is1Represents the temperature, T, of the liquid oxygen entering the secondary heat exchanger2Represents the temperature, T, of the liquid oxygen as it leaves the secondary heat exchanger2≤67K。
In step 41, T1＝80K，T2＝67K，A＝1.7543×105，B＝-6152.3，C＝113.92，D＝-0.92382，E＝0.0027963，Then
The invention has the following beneficial effects:
1. the invention creatively introduces the supersonic ejector into the method for saturated liquid nitrogen supercooled liquid oxygen, can cool the liquid oxygen to below 67K, and can ensure that the supercooled liquid oxygen flow is more than 4500L/min, thereby meeting the requirement of high-flow liquid oxygen rapid cooling and filling before emission of CZ-5 and the like.
2. The invention can match the air extraction quantity of the supersonic ejector with the load, including matching the ejector exhaust air pressure with the environmental pressure, matching the ejected gas static pressure with the liquid nitrogen air pillow pressure, matching the ejector air extraction quantity with the liquid nitrogen heat exchange evaporation quantity and the like, and can save the working stability of the system while meeting the supercooling requirement.
3. The supersonic ejector can continuously vacuumize in large flow. The supercooling system based on the supersonic ejector can meet the emission requirement of large-flow liquid oxygen rapid supercooling filling. Meanwhile, the ultra-strong pumping capacity of the ejector can provide technical reserve for the pressure reduction and supercooling of the liquid hydrogen in the future. The high-flow liquid oxygen supercooling system based on the ejector has strong innovativeness, frontier performance and practicability.
4. The supersonic ejector is also called jet pump, and is a supersonic gas jet technology. The high-pressure injection gas expands through the supersonic velocity injection nozzle to form high-speed low-pressure injection gas flow, and simultaneously the low-speed low-pressure injected gas flow enters the injection mixing chamber through the inlet of the injection pipeline; the two airflows are fully mixed in the injection mixing chamber through the action of molecular diffusion, turbulent flow pulsation, airflow vortex, shock wave and the like, the injection airflow transmits kinetic energy to the injected airflow, and high-speed low-pressure mixed airflow is obtained at the outlet of the mixing chamber; then, the mixed gas flow is subjected to speed reduction and pressurization through a diffuser, the kinetic energy is converted into pressure potential energy, and finally the pressure potential energy is discharged into the atmosphere at the ambient static pressure. Compared with the traditional vacuum compressor system, the supersonic ejector adopted in the invention has the advantages of simple structure, no rotating part, small volume, quick reaction, flexibility and the like.
5. The invention adopts a cone contraction type isobaric mixing chamber. Theoretical analysis and engineering practice prove that the isobaric mixing chamber ejector has stronger ejection capacity and higher performance than the equal-section mixing chamber ejector. Meanwhile, the cone shrinkage type isobaric mixing chamber is simple in structure, small in machining error, low in manufacturing cost and suitable for a large-flow injection system. The injection efficiency and the processing cost can be considered in the cone shrinkage type isobaric mixing chamber.
6. The supersonic ejector is firstly used for building a rocket engine high altitude test run vacuum system in aerospace, and is widely applied to a hypersonic large free jet test system in recent years. The long-time stable working capability of the supersonic ejector is fully verified. The invention is hopeful to promote the application of the supercooling propellant in the launching guarantee in space flight. The achievement formed by the application can be directly applied to the design and construction of a large-scale liquid oxygen supercooling system, and the capacity of guaranteeing the high-flow liquid oxygen rapid supercooling of CZ-5 and CZ-7 carrier rockets of the new generation is improved.
Drawings
Fig. 1 shows a schematic diagram of the principle of a high-flow liquid oxygen supercooling method based on a supersonic ejector.
Fig. 2 shows a schematic diagram of the supersonic ejector.
Fig. 3 shows a schematic view of the structure of the gasifier.
Fig. 4 shows a graph of the ejection coefficient n and the supersonic ejector compression ratio CR.
Among them are:
10. liquid oxygen tank car; 11. a liquid oxygen pump; 12. a liquid oxygen filling valve;
20. a liquid nitrogen tank car; 21. a first liquid nitrogen filling valve; 22. a second liquid nitrogen filling valve;
30. a primary heat exchanger;
40. a secondary heat exchanger;
50. a supersonic ejector;
51. an inlet section; 52. a mixing section; 53. a super-expanding section; 54. sub-expanding section;
60. a gas generator; 61. a torch igniter; 62. an alcohol chamber; 63. an oxygen chamber; 64. a combustion chamber;
70. a liquid oxygen storage tank; 71. liquid oxygen collection valve.
In addition, in fig. 2:
1 represents the longitudinal section of an injection airflow inlet; 2 represents the longitudinal section of the injected airflow inlet; 3 denotes the mixing section outlet longitudinal section; 4 represents the longitudinal section of the outlet of the sub-expansion section.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific preferred embodiments.
As shown in figure 1, a large-flow liquid oxygen supercooling method based on an ultrasonic ejector takes a heat exchanger used for conventional saturated liquid nitrogen supercooling liquid oxygen as a primary heat exchanger 30, and the primary heat exchanger can supercool liquid oxygen with supercooling flow of more than 4500L/min from 92K to 80K.
Liquid oxygen in the liquid oxygen tank wagon 10 is respectively connected with the inlet of the heat exchange tube in the primary heat exchanger 30 through a liquid oxygen pump 11 and a liquid oxygen filling valve 12. Wherein the temperature of the liquid oxygen in the liquid oxygen tank wagon is about 92K.
And a secondary heat exchanger 40 is arranged at the downstream of the primary heat exchanger, the secondary heat exchanger can supercool the liquid oxygen which is supercooled to 80K and has the supercooling flow rate of more than 4500L/min to be lower than 67K, and the supercooled liquid oxygen is collected in a liquid oxygen storage tank 70 after passing through a liquid oxygen collection valve 71.
The liquid nitrogen in the liquid nitrogen tank wagon 20 is connected with the liquid nitrogen pool of the primary heat exchanger through a liquid nitrogen filling valve I21 on the one hand, and is connected with the liquid nitrogen pool of the secondary heat exchanger through a liquid nitrogen filling valve II 22 on the other hand.
The temperature of liquid nitrogen in the liquid nitrogen tank car is 77K, so that the temperature of the liquid nitrogen in the liquid nitrogen pool of the primary heat exchanger is 77K, the temperature of the liquid nitrogen in the secondary heat exchanger is not more than 64K and is preferably equal to 64K, and the air outlet of the secondary heat exchanger is connected with the injected airflow inlet of the supersonic ejector 50.
Namely, the liquid nitrogen evaporated from the secondary heat exchanger is the injected airflow.
The parameters of the injected airflow are as follows:
total pressure p02Total temperature T02Specific heat ratio gamma2Molecular weight μ2Coefficient of velocity λ2Flow rate m2Flow area F2。
p02Also for the liquid nitrogen in the secondary heat exchanger to be maintained atThe pressure of the air pillow at that time; wherein,in the present invention,preferably equal to 64K, and inquiring a liquid nitrogen saturated steam pressure meter to obtain the gas pillow pressure p of the liquid nitrogen in the secondary heat exchanger at the moment02＝0.145952bar。
When steam boiling in the nitrogen bath reaches the inlet of the ejector, the temperature slightly rises due to heat leakage and the like, and the physical properties are as follows:
T02＝70K，p02＝0.14595bar，Ma＝0.1，V2＝17.04m/s，γ2＝1.4，μ2＝28。
the above flow area F2The variables to be designed.
As shown in fig. 2, the supersonic ejector includes an inlet section 51, a mixing section 52, a super-expanding section 53 and a sub-expanding section 54 which are coaxially arranged in sequence along the airflow direction.
The inlet section comprises an injection airflow inlet positioned in the center and an injected airflow inlet positioned at the periphery of the injection airflow inlet. Wherein the induced airflow inlet is connected to the air outlet of the gasifier 60. The area of the longitudinal section 1 of the injection airflow inlet is F1The longitudinal section 2 of the injected airflow inlet is F2Defining an area ratio
The super-expanding section is short for a supersonic speed diffusion section, and the sub-expanding section is short for a subsonic speed diffusion section.
As shown in fig. 3, the gas generator includes a combustion chamber 64, an oxygen chamber 63 provided on the combustion chamber, an alcohol chamber 63, and a torch igniter 61.
The burnt gas of the gas generator is used as injection gas flow, and the injection gas flow parameters are as follows:
total pressure p01Total temperature T01Specific heat ratio gamma1Molecular weight μ1Coefficient of velocity λ1Flow rate m1Flow area F1。
The high-temperature fuel gas is generated by burning water-containing alcohol and oxygen. The mass ratio of alcohol in the aqueous alcohol is 20%. The oxygen to alcohol equivalence ratio was 1. Total pressure design of gasifier p0130bar, the pressure after expansion of the gas is matched to the static pressure of the nitrogen in longitudinal section 3 (p)20.14494 bar). The expansion ratio of the fuel gas is 207. The physical parameters of the outlet air flow can be obtained through thermal calculation:
T01＝1533.73K，T1＝536.95K，p01＝30bar，p1＝0.14494bar，γ1＝1.2905，Ma1＝3.872，μ1＝21.432。
static temperature T1536.95K ensures that no icing or condensation occurs during the mixing process.
The mixing section is a conical isobaric mixing chamber with a contracted section, and the static pressure on the inlet, the outlet and the whole inner wall surface of the mixing section is equal.
The mixing chamber is long enough that the gas flows are completely mixed when reaching the outlet of the mixing chamber, and the mixed gas flow parameter:
total pressure p03Total temperature T03Specific heat ratio gamma3Molecular weight μ3Coefficient of velocity λ3Flow rate m3Flow area F3。
Assuming equal static pressure at the mixing section inlet, outlet and the entire inner wall surface, the mixing chamber contraction ratio is definedDefined as the area expansion ratio of the sub-expanded segmentWherein, F3Corresponding to mixing section outlet longitudinal section 3 in fig. 2; f4Corresponding to the longitudinal section 4 of the outlet of the sub-expansion section.
Under the condition of high compression ratio, the airflow at the outlet of the mixing chamber is still supersonic airflow, and in order to achieve the purpose of speed reduction and pressurization, the rear part of the mixing chamber is connected with a section of supersonic velocity diffusion section with a uniform section and then connected with a section of subsonic velocity diffusion section with an expanded area, so as to achieve the highest possible static pressure recovery.
And the liquid nitrogen steam in the secondary heat exchanger is injected airflow, and the total flow of the gas generator and the physical parameters of the supersonic ejector are designed according to the parameters of the injected airflow and the evaporation capacity of the liquid nitrogen.
The design method of total flow and supersonic ejector physical parameters of the gas generator includes the following steps:
step 1, calculating the compression ratio CR of the supersonic ejector.
In the formula, p4The static pressure of the mixed gas at the longitudinal section 4 of the outlet of the sub-expansion section is generally greater than or equal to the atmospheric environment pressure in order to ensure the smooth discharge of the gas flow; p is a radical of02For the liquid nitrogen in the secondary heat exchanger to be kept atThe temporal air pillow pressure or saturated steam pressure; wherein,
in the present invention,preferably equal to 64K, and the pressure of the saturated vapor of the liquid nitrogen is inquired to obtain the second timeGas pillow pressure p of liquid nitrogen in stage heat exchanger02＝0.145952bar。
Assuming that the pressure of the sub-expanded section vented to atmosphere is one atmosphere, i.e. p41atm 1.01325bar, the design compression ratio of the supersonic ejector (hereinafter may be simply referred to as the ejector) can be obtained
And 2, searching the relation between the ejection coefficient n and the compression ratio CR of the supersonic ejector, and specifically comprising the following steps.
Step 21, mixing section specific heat ratio gamma3And searching the relation between the injection coefficient n and the injection coefficient.
In the formula, gamma2Specific heat ratio of the injected air flow, gamma1Specific heat ratio of jet air flow, mu1For injecting the molecular weight of the gas flow, mu2Is the molecular weight of the injected air flow.
Step 22, mixing section exit velocity factor λ3Calculated using the following formula:
wherein,
in the formula, R1For injection of gas constant, R2Is an injected gas constant, R3Is the gas constant at the outlet of the mixing section; t is01For injecting the total temperature of the gas, T02The total temperature of the injected gas; lambda [ alpha ]1For injecting gas velocity coefficient, lambda2Is the velocity coefficient of the injected gas, RuFor general gas constants, 8.314 was typically taken.
Gamma calculated in step 213And c is substituted into the above formula to obtain lambda3And n.
Step 23, the total pressure recovery coefficient sigma in the mixed gas flow deceleration processTThe calculation of (2):
due to the obtained lambda3>1, the mixed airflow is changed into subsonic airflow through a normal shock wave in the super-expanding section, and the total pressure recovery coefficient is sigmashock。
σT＝σshockσsub
Wherein,
in the formula, σshockFor total pressure recovery of the over-extension section, σsubIs the total pressure recovery coefficient of the subsonic diffusion section, and further decelerates and boosts the pressure of the subsonic airflow in the subsonic diffusion sectionGenerally, it is assumed that the resistance of the sub-expansion section to airflow is small, sosub＝1.0。
Ma3The Mach number of the inlet of the super-expanding section is; gamma calculated from steps 21 and 223And lambda3Substituting the above formula to obtain σTAnd n.
And step 24, discharging speed coefficient lambda of sub-expansion section of the supersonic ejector4And (4) calculating.
Defining the total pressure recovery coefficient in the deceleration process of the mixed gas flowAnd σT＝σshockσsub. According to a one-dimensional flow formula:
m3＝m4
in the formula, m3Represents the flow of the mixed gas through the mixing section outlet longitudinal section 3; m is4Representing the mixed gas flow passing through the outlet longitudinal section 4 of the sub-expansion section; t is03Represents the total temperature of the mixed gas at the longitudinal section 3 of the mixing section outlet; t is04The total temperature of the mixed gas at the longitudinal section 4 of the outlet of the sub-expansion section is shown; p is a radical of03Represents the total pressure of the mixed gas at the longitudinal section 3 of the outlet of the mixing section; p is a radical of04The total pressure of the mixed gas at the longitudinal section 4 of the outlet of the sub-expansion section is shown.
Wherein,
defining the area expansion ratio of the sub-expanded segmentIn general, 2.0 is used. Definition of coefficient of restitution from total pressureEnergy conservation of the longitudinal section 3 of the mixing section outlet and the longitudinal section 4 of the sub-expansion section outlet: t is03＝T04(ii) a Since the physical properties of the mixing section outlet longitudinal section 3 and the sub-expansion section outlet longitudinal section 4 are slightly different, R can be considered to be3＝R4，γ3＝γ4I.e. C (R)3,γ3)＝C(R4,γ4)。
The equation can be simplified as:
wherein,
in the formula, psi is the area expansion ratio of the sub-expansion segment, and the value is 2.0; gamma calculated in step 23、λ3And σ calculated in step 23TSubstituting into the above formula to obtain λ4And n.
Step 25, total pressure p of the mixing section03Total pressure p of injected air flow02And (3) calculating a ratio:
because the mixing chamber is an isobaric mixing chamber, the pressure in the mixing chamber is equal, and the following can be obtained:
p3＝p1＝p2
wherein p is1The static pressure of the longitudinal section 1 of the injection airflow inlet is shown; p is a radical of2The static pressure of the longitudinal section 2 of the injected airflow inlet is shown; p is a radical of3The static pressure of the mixing section outlet longitudinal section 3 is shown.
p03π(λ3,γ3)＝p02π(λ2,γ2)
Wherein,
the same principle has the relation:
step 26, calculating a formula of the supersonic ejector compression ratio CR:
p4＝p04π(λ4,γ4)＝p04π(λ4,γ3)＝p03σTπ(λ4,γ3)
defining the compression ratio of the ejectorThe solution equation is:
that is to say
Wherein,
converting the gamma calculated in steps 21 to 253、σT、λ4Andthe relationship between the compression ratio CR of the supersonic ejector and the ejection coefficient n can be obtained by substituting the above-mentioned two into step 26, as shown by the curve in fig. 4.
Step 3, determining the injection coefficient n value: and (3) substituting the CR value obtained in the step (1), such as CR (6.942), into the relation between CR and n searched in the step (2), so as to determine the injection coefficient n value. When CR is 6.942, n is 0.4758, which can be obtained by bisection, and can be obtained from the curve in fig. 4. The pressure matching condition is met: p is a radical of4Matching the ambient pressure, p02The pressure of the air pillow is matched with that of the liquid nitrogen heat exchanger.
Step 4, total flow m of gas generator1And calculating, comprising the following steps.
Step 41, calculating the evaporation capacity of liquid nitrogen according to the following formula
In the formula,representing the rate of liquid oxygen evolution heat in the secondary heat exchanger; h is of the second orderLiquid nitrogen is maintained in the heat exchangerLatent heat of vaporization in time.
Heat release rate of liquid oxygen in the secondary heat exchangerThe calculation formula of (a) is as follows:
wherein, Cp＝A+BT+CT2+DT3+ET4
In the formula, CpThe specific heat of the liquid oxygen at low temperature is expressed, the unit is J/kmol/K, and the application range of a calculation formula is 54.36K-142K; A. b, C, D and E are both constants;the set liquid oxygen heat exchange flow is obtained; t is1Represents the temperature, T, of the liquid oxygen entering the secondary heat exchanger2Represents the temperature, T, of the liquid oxygen as it leaves the secondary heat exchanger2≤67K。
By T1＝80K，T2For example, 67K, a 1.7543 × 105，B＝-6152.3，C＝113.92，D＝-0.92382，E＝0.0027963，Then
Step 42 total flow m of gasifier1And (3) calculating:
substituting the injection coefficient n determined in the step 3 into the formula to obtain the total flow m of the gas generator1The value is obtained.
I.e. total flow m of the gas generatorburnedComprises the following steps:
the oxygen flow of the gas generator is 5.34kg/s, and the fuel flow is 12.78kg/s (wherein the alcohol is 2.56kg/s, and the water is 10.22 kg/s).
And 5, calculating the physical parameters of the supersonic ejector: the physical parameters of the supersonic ejector comprise a mixed section shrinkage ratio phi, and the mixed section shrinkage ratio phi is calculated by adopting the following formula:
wherein,
the injection coefficient n determined in the step 3 and the gamma calculated according to the formula in the step 23And λ3The mixed-stage shrinkage ratio Φ was 0.4089 by substituting the above equation.
Further, substituting n-0.4758 into each equation in step 2 will simultaneously result in intermediate parameters:
R3＝358.59J/(kg·K)，γ3＝1.3134，F3＝0.3489m2，Ma3＝2.3441，λ3＝1.8480,λ4＝0.2440。
the preferred parameters of the present invention are now summarized as follows:
a secondary heat exchanger:
volumetric flow rate of liquid oxygen heat exchangeMass flow rateThe liquid oxygen inlet temperature is 80K, and the liquid oxygen outlet temperature is 67K. The temperature of the liquid nitrogen bath is 64K, and the pressure p of the air pillow of the liquid nitrogen bath is p020.14595bar, evaporation quality of liquid nitrogen
A gas generator:
the oxygen flow rate is 5.34kg/s, the fuel flow rate is 12.78kg/s (wherein, the alcohol is 2.56kg/s, and the water is 10.22 kg/s); total pressure p of combustion chamber0130bar, total gas temperature T011533.73K, static temperature T of gas outlet1536.95K, gas outlet static pressure p10.14493 bar; specific heat ratio gamma of gas outlet11.2905, gas outlet Mach number Ma13.872, exit molecular weight of fuel gas μ121.432; characteristic velocity c*1186.7 m/s; throat area Ft＝0.0072m2Area of outlet F1＝0.1296m2。
Supersonic ejector:
the injection coefficient n is 0.4758, and the compression ratio CR is 6.9419.
Injection gas inlet longitudinal section 1: total pressure p0130bar, total gas temperature T011533.73K, static temperature T1Static pressure p of 536.95K10.14493 bar; specific heat ratio gamma11.2905 molecular weight μ121.432; mach number Ma13.872; area F1＝0.1296m2。
Longitudinal section 2 of injected gas inlet: nitrogen gas suction speed V217.04 m/s; total temperature T0270K, static temperature T269.86K, total pressure p020.14595bar, static pressure p20.14494 bar; specific heat ratio gamma of nitrogen21.4, molecular weight of nitrogen gas μ228; area F2＝0.7236m2。
Mixing chamber outlet longitudinal section 3: coefficient of speed lambda31.8480; total temperature T031341.4K, static temperature T3720.8K, total pressure p031.9573bar, static pressure p30.14493 bar; area F3＝0.3489m2The isobaric mixing chamber contraction ratio Φ is 0.4089; gas constant R of mixed gas3358.59J/(kg. K), specific heat ratio of mixer gamma3＝1.3134。
Ejector outlet longitudinal section 4: coefficient of speed lambda40.2440, area F4＝0.6979m2。
Although the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the details of the embodiments, and various equivalent modifications can be made within the technical spirit of the present invention, and the scope of the present invention is also within the scope of the present invention.
Claims (5)
1. A high-flow liquid oxygen supercooling method based on a supersonic ejector is characterized in that: the heat exchanger used by conventional saturated liquid nitrogen for supercooling liquid oxygen is used as a primary heat exchanger, and the primary heat exchanger can supercool the liquid oxygen with the supercooling flow rate of more than 4500L/min from 92K to 80K; a secondary heat exchanger is arranged at the downstream of the primary heat exchanger, and can supercool liquid oxygen with the supercooling flow rate of more than 4500L/min to below 67K to 80K;
liquid nitrogen in a saturated state is filled in the secondary heat exchanger, the temperature of the liquid nitrogen in the secondary heat exchanger is not more than 64K, and an air outlet of the secondary heat exchanger is connected with an injected airflow inlet of the supersonic ejector;
the ejection airflow inlet of the supersonic ejector is connected with the air outlet of the fuel gas generator;
the supersonic ejector sequentially comprises a mixing section, a super-expansion section and a sub-expansion section which are coaxially arranged along the airflow direction; the mixing section is a conical isobaric mixing chamber with a contracted section, and the static pressure on the inlet, the outlet and the whole inner wall surface of the mixing section is equal.
2. The supersonic ejector-based high-flow liquid oxygen supercooling method according to claim 1, characterized in that: and the liquid nitrogen steam in the secondary heat exchanger is injected airflow, and the total flow of the gas generator and the physical parameters of the supersonic ejector are designed according to the parameters of the injected airflow and the evaporation capacity of the liquid nitrogen.
3. The supersonic ejector-based high-flow liquid oxygen supercooling method according to claim 2, characterized in that: the design method of total flow and supersonic ejector physical parameters of the gas generator includes the following steps:
step 1, calculating the compression ratio CR of the supersonic ejector:
in the formula, p4Static pressure of mixed gas at the longitudinal section of an outlet of the sub-expansion section; p is a radical of02For the liquid nitrogen in the secondary heat exchanger to be kept atThe temporal air pillow pressure or saturated steam pressure; wherein,
and 2, searching the relation between the ejection coefficient n and the compression ratio CR of the supersonic ejector, and specifically comprising the following steps:
step 21, mixing section ratioHeat ratio gamma3Searching the relation between the injection coefficient n:
in the formula, gamma2Specific heat ratio of the injected air flow, gamma1Specific heat ratio of jet air flow, mu1For injecting the molecular weight of the gas flow, mu2The molecular weight of the injected airflow;
step 22, mixing section exit velocity factor λ3Calculated using the following formula:
wherein,
in the formula, R1For injection of gas constant, R2Is an injected gas constant, R3Is the gas constant at the outlet of the mixing section; t is01For injecting the total temperature of the gas, T02The total temperature of the injected gas; lambda [ alpha ]1For injecting gas velocity coefficient, lambda2Is the velocity coefficient of the injected gas;
gamma calculated in step 213And c is substituted into the above formula to obtain lambda3And n;
step 23, the total pressure recovery coefficient sigma in the mixed gas flow deceleration processTThe calculation of (2):
σT＝σshockσsub
wherein,
in the formula, σshockFor total pressure recovery of the over-extension section, σsubThe total pressure recovery coefficient of the sub-expansion section is 1.0; ma3The Mach number of the inlet of the super-expanding section is; gamma calculated from steps 21 and 223And lambda3Substituting the above formula to obtain σTAnd n;
and step 24, discharging speed coefficient lambda of sub-expansion section of the supersonic ejector4And (3) calculating:
wherein,
in the formula, psi is the area expansion ratio of the sub-expansion segment, and the value is 2.0; converting the gamma calculated in step 23、λ3And σ calculated in step 23TSubstituting into the above formula to obtain λ4The relationship between n;
step 25, total pressure p of the mixing section03Total pressure p of injected air flow02And (3) calculating a ratio:
wherein,
step 26, calculating a formula of the supersonic ejector compression ratio CR:
wherein,
converting the gamma calculated in steps 21 to 253、σT、λ4Andsubstituting the pressure ratio CR of the supersonic ejector and the ejection coefficient n into the step 26 to obtain the relation between the compression ratio CR and the ejection coefficient n of the supersonic ejector;
step 3, determining the injection coefficient n value: substituting the CR value obtained by calculation in the step 1 into the relation between CR and n searched in the step 2 to determine the value of the injection coefficient n;
step 4, total flow m of gas generator1And (3) calculating, comprising the following steps:
step 41, calculating the evaporation capacity of liquid nitrogen according to the following formula
In the formula,representing the rate of liquid oxygen evolution heat in the secondary heat exchanger; h is that liquid nitrogen in the secondary heat exchanger is kept atLatent heat of vaporization in time;
step 42 total flow m of gasifier1And (3) calculating:
substituting the injection coefficient n determined in the step 3 into the formula to obtain the total flow m of the gas generator1A value;
and 5, calculating the physical parameters of the supersonic ejector: the physical parameters of the supersonic ejector comprise a mixed section shrinkage ratio phi, and the mixed section shrinkage ratio phi is calculated by adopting the following formula:
wherein,
the injection coefficient n determined in the step 3 and the gamma calculated according to the formula in the step 23And λ3Substituting the formula into the formula to obtain the mixed section shrinkage ratio phi.
4. The supersonic ejector-based high-flow liquid oxygen supercooling method according to claim 3, wherein the method comprises the following steps: in step 41, the rate of heat release of liquid oxygen in the secondary heat exchangerThe calculation formula of (a) is as follows:
wherein, Cp＝A+BT+CT2+DT3+ET4
In the formula, CpThe specific heat of the liquid oxygen at low temperature is expressed, the unit is J/kmol/K, and the application range of a calculation formula is 54.36K-142K; A. b, C, D and E are both constants;the set liquid oxygen heat exchange flow is obtained; t is1Represents the temperature, T, of the liquid oxygen entering the secondary heat exchanger2Represents the temperature, T, of the liquid oxygen as it leaves the secondary heat exchanger2≤67K。
5. The supersonic ejector-based high-flow liquid oxygen supercooling method according to claim 4, wherein the method comprises the following steps: in step 41, T1＝80K，T2＝67K，A＝1.7543×105，B＝-6152.3，C＝113.92，D＝-0.92382，E＝0.0027963，Then
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