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 PDF

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Publication number
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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flow
liquid oxygen
heat exchanger
supersonic ejector
section
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Inventor
包恒
聂万胜
王辉
侯志勇
苏凌宇
刘凯希
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Peoples Liberation Army Strategic Support Force Aerospace Engineering University
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Peoples Liberation Army Strategic Support Force Aerospace Engineering University
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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

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

Big flow liquid oxygen based on Supersonic Ejector crosses cooling method
Technical field
The present invention relates to space flight low temperature carrier rocket field, especially a kind of big flow liquid oxygen based on Supersonic Ejector Cross cooling method.
Background technique
With flourishing for China's aerospace industry, new demand is proposed to the carrying capacity of carrier rocket.In order to mention High carrying capacity, the implementation needs for meeting following large space station and moon exploration program, using the Long March 5 of cryogenic liquid propellant Number, No. 6 and No. 7 carrier rockets come into operation in succession.Currently, cryogenic propellant used by carrier rocket is all saturation state, Thermodynamic state it is most of all in boiling temperature near, thermophysical property is insufficient, and especially density and unit volume show cooling capacity It is small.The timing of cryogenic propellant quality one, density is small to will lead to the increase of cryogenic propellant tank volume size, keeps carrier rocket total Quality of taking off increases.The aobvious cooling capacity of unit volume is small to will increase propellant gasification loss, needs repeatedly to be added before transmitting, cannot Adapt to the needs of emergency transmitting.Meanwhile for long-term in-orbit spacecraft, aobvious cooling capacity is small to will lead to cryogenic propellant gasification loss Increase, spacecraft needs frequent bleed, causes the waste of propellant.
Propellant supercooling can improve cryogenic propellant thermodynamic property.For liquid hydrogen/oxygen rocket, propellant supercooling can To reduce takeoff rocket architecture quality about 20%, it is obviously improved the carrying capacity of thrust-augmented rocket.The Gao Xianleng of propellant is subcooled Amount advantage can also be applied to moon exploration program and deep space exploration, extend the task time of spacecraft, widen the range of deep space exploration.
Thrust-augmented rocket of new generation is using liquid oxygen as primary oxidizers.The quick supercooling filling of big flow liquid oxygen can mention High LIQUID OXYGEN DENSITY and aobvious cooling capacity are obviously improved rocket carrying capacity and transmitting stand-by time, effectively prevent in liquid oxygen filling process There is two phase flow, there is important engineering application value.
Using CZ-5 as the high thrust carrier rocket of new generation of representative by liquid oxygen as main oxidant.Currently, transmitting base The defects such as ground large flow rate filling process uses the liquid oxygen of saturation state, and small, aobvious cooling capacity that there are density is low.Supercooling is carried out to liquid oxygen to change The density and aobvious cooling capacity of liquid oxygen can be improved in heat, is obviously improved rocket carrying capacity and transmitting stand-by time, effectively prevent filling Occur two phase flow in the process, there is very important engineering application value.Currently, firing base protects the supercooling of big flow liquid oxygen Barrier ability is limited, there is the problems such as cold flow is smaller, degree of supercooling is low, it is difficult to which adapting to the transmitting that big flow liquid oxygen is quickly subcooled needs It wants.
Decompression supercooling is that mode is commonly subcooled in cryogenic propellant.When ensureing the supercooling of big flow liquid oxygen, vacuum compression is needed Machine maintains lower pneumatic die cushion pressure, and persistently aspirates big flow steam.
Heat exchange supercooling and evacuation decompression supercooling are two kinds of common cryogenic propellant supercooling modes.The research of U.S.'s NASA Glenn Center is using three-level vacuum compressor compressor decompression overfreezing liquid nitrogen, the cooling liquid oxygen of recycling overfreezing liquid nitrogen heat exchange.The liquid oxygen mistake Liquid nitrogen pneumatic die cushion pressure reduction to 17.24~68.95KPa, supercooled liquid oxygen flow 700L/min can be exported liquid oxygen temperature by cooling system Degree is reduced to 66.67K, and LIQUID OXYGEN DENSITY promotes about 10%.It needs to maintain higher vacuum degree and liquid in supercooling system work process Nitrogen evaporation capacity is larger, very high to the performance requirement of multi-stage vacuum compressor.Currently, domestic vacuum compressor technological level is also difficult to Meet the quick needs for crossing cold heat exchanger of big flow liquid oxygen.
Currently, the application study of China's supercooling cryogenic propellant is at the early-stage, big flow liquid oxygen is subcooled in firing base Supportability it is limited, mainly added before penetrating in process using saturated liquid nitrogen supercooling liquid oxygen (liquid oxygen can be subcooled to by 92K 80K or so), constrain application of the supercooling liquid oxygen in liquid-propellant rocket engine of new generation.
Tie of the applicant as base and industrial department, by the cooperation of universities and colleges and base, industrial department, for the country Vacuum compressor technological level is difficult to meet the quick needs for crossing cold heat exchanger of big flow liquid oxygen, and is subcooled using saturated liquid nitrogen It is existing when liquid oxygen to cross the problems such as cold flow is smaller, degree of supercooling is low, devise the big stream based on Supersonic Ejector of the application Amount liquid oxygen crosses cooling method.
Summary of the invention
In view of the above-mentioned deficiencies of the prior art, the technical problem to be solved by the present invention is to provide one kind to be drawn based on supersonic speed The big flow liquid oxygen of emitter crosses cooling method, which crosses cooling method creatively will be ultrasonic Fast injector is introduced into the method for saturated liquid nitrogen supercooling liquid oxygen, liquid oxygen can be cooled to 67K hereinafter, and can ensure that liquid oxygen crosses cold flow Amount is greater than 4500L/min, and big flow liquid oxygen is quickly cooled down the needs of filling before emitting so as to CZ-5 etc..In addition, can make to surpass The sucking rate of velocity of sound injector matches with load, safer, reliable.
In order to solve the above technical problems, the technical solution adopted by the present invention is that:
A kind of big flow liquid oxygen based on Supersonic Ejector crosses cooling method, liquid oxygen institute will be subcooled using conventional saturated liquid nitrogen For the heat exchanger used as first-class heat exchanger, which can will cross liquid oxygen of the cold flow greater than 4500L/min from 92K mistake It is cooled to 80K；Secondary heat exchanger is set in the downstream of first-class heat exchanger, which, which can will cross, is cooled to 80K and crosses cold flow Liquid oxygen greater than 4500L/min, which is crossed, is cooled to 67K or less.
Liquid nitrogen in a saturated state is filled in secondary heat exchanger, in secondary heat exchanger liquid nitrogen temperature be no more than 64K, two The grade gas outlet of heat exchanger and being connected by injection air flow inlet for Supersonic Ejector.
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 For the taper equipressure mixing chamber of cross-sectional constriction, static pressure is equal on mixing section entrance, outlet and entire inner wall.
Liquid nitrogen vapor in secondary heat exchanger be by injection air-flow, according to by injection flow parameter and liquid nitrogen vaporization amount, into The design of row gas generator total flow and Supersonic Ejector physical parameter.
The design method of gas generator total flow and Supersonic Ejector physical parameter, includes the following steps:
Step 1, the compression ratio CR of Supersonic Ejector is calculated:
In formula, p4For the sub- static pressure for expanding section and exporting the mixed gas of longitudinal section；p02It is maintained at for liquid nitrogen in secondary heat exchangerWhen pneumatic die cushion pressure or saturated vapour pressure；Wherein,
Step 2, the lookup of mass ratio of induced-to-inducing air n and Supersonic Ejector compression ratio CR relationship, specifically comprises the following steps:
Step 21, mixing section specific heat ratio γ3Relationship is searched between mass ratio of induced-to-inducing air n:
In formula, γ2For by the specific heat ratio of injection air-flow, γ1For the specific heat ratio of injection air-flow, μ1For the molecule of injection air-flow Amount, μ2For by the molecular weight of injection air-flow.
Step 22, mixing section muzzle velocity coefficient lambda3It is calculated using following formula:
Wherein,
In formula, R1For ejection gas constant, R2For by ejection gas constant, R3For the gas constant of mixing section outlet；T01For Ejection gas total temperature, T02For by ejection gas total temperature；λ1For ejection gas velocity coeffficient, λ2For by ejection gas velocity coeffficient；
The γ that step 21 is calculated3And c substitutes into above formula, can obtain λ3Relational expression between n.
Step 23, total pressure recovery coefficient σ in mixed airflow moderating processTCalculating:
σT=σshockσsub
Wherein,
In formula, σshockFor the total pressure recovery coefficient of ultra-expanded section, σsubFor the sub- total pressure recovery coefficient for expanding section, value 1.0；Ma3 For ultra-expanded section entrance Mach number；The γ that step 21 and 22 are calculated3And λ3Above formula is substituted into, can obtain σTRelational expression between n.
Step 24, section velocity of discharge coefficient lambda is expanded in Supersonic Ejector Asia4It calculates.
Wherein,
In formula, Ψ is the sub- area expansion ratio for expanding section, value 2.0；The γ calculated in step 23、λ3It is calculated with step 23 σTAbove formula is substituted into, can obtain λ4Relationship between n；
Step 25, mixing section stagnation pressure p03With by injection air-flow stagnation pressure p02Ratio calculation:
Wherein,
Step 26, Supersonic Ejector compression ratio CR calculation formula:
Wherein,
The γ that will be calculated in step 21 to 253、σT、λ4WithIt substitutes into step 26, Supersonic Ejector can be obtained Relationship between compression ratio CR and mass ratio of induced-to-inducing air n；
Step 3, mass ratio of induced-to-inducing air n value determines: the pass of CR and n that the CR value being calculated in step 1 substitution step 2 is found It is that can determine mass ratio of induced-to-inducing air n value in formula.
Step 4, gas generator total flow m1It calculates, includes the following steps.
Step 41, liquid nitrogen vaporization amount is calculated as follows
In formula,Indicate liquid oxygen rate of heat release in secondary heat exchanger；H is that liquid nitrogen is maintained in secondary heat exchangerWhen Gasification latent heat.
Step 42, gas generator total flow m1It calculates:
The mass ratio of induced-to-inducing air n value that step 3 is determined substitutes into above formula, and gas generator total flow m can be obtained1Value.
Step 5, the calculating of Supersonic Ejector physical parameter: Supersonic Ejector physical parameter includes mixing section shrinkage ratio Φ, mixing section shrinkage ratio Φ are calculated using following formula:
Wherein,
The mass ratio of induced-to-inducing air n value that step 3 is determined, and the γ calculated by step 2 formula3And λ3Above formula is substituted into, can be acquired Mixing section shrinkage ratio Φ.
In step 41, liquid oxygen rate of heat release in secondary heat exchangerCalculation formula it is as follows:
Wherein, Cp=A+BT+CT2+DT3+ET4
In formula, CpIndicate liquid oxygen low temperature under specific heat, unit J/kmol/K, the calculation formula scope of application for 54.36K~ 142K；A, B, C, D and E are constant；For the liquid oxygen heat exchange flow of setting；T1It indicates when liquid oxygen enters secondary heat exchanger Temperature, T2Indicate temperature when liquid oxygen leaves secondary heat exchanger, T2≤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. Supersonic Ejector is creatively introduced into the method for saturated liquid nitrogen supercooling liquid oxygen by the present invention, can be cold by liquid oxygen But 67K is arrived hereinafter, and can ensure that liquid oxygen crosses cold flow greater than 4500L/min, so as to big flow liquid oxygen before the transmitting such as CZ-5 It is quickly cooled down the needs of filling.
2. the present invention can make the sucking rate of Supersonic Ejector match with load, including injector discharge air pressure and environment Pressure match, by ejection gas static pressure and liquid nitrogen pneumatic die cushion pressure match, injector sucking rate and liquid nitrogen heat exchange evaporation are flux matched etc., While meeting supercooling demand, the stability of system work can be saved.
3. Supersonic Ejector can continuously big flow vacuumize.Cooling system excessively based on Supersonic Ejector can ensure The mission need of filling is quickly subcooled in big flow liquid oxygen.Meanwhile the superpower suction capactity of injector can be the following liquid hydrogen decompression Supercooling provides technological reserve.Big flow liquid oxygen based on injector, which crosses cooling system, has stronger innovative, frontier nature and practical Property.
It is a kind of supersonic gas jet technology 4. Supersonic Ejector is also known as jet pump.High pressure injection gas passes through super Velocity of sound nozzles with injector expands the injection air-flow to form high velocity, low pressure, while low speed low pressure by injection air-flow passes through injection pipeline Entrance enters injection mixing chamber；Two strands of air-flows pass through molecule diffusion, turbulence pulsation, air flow swirl and shock wave in injection mixing chamber The effects of be sufficiently mixed, injection air-flow passes to kinetic energy by injection air-flow, and it is mixed to obtain high velocity, low pressure in mixing chamber outlet Close air-flow；Then, mixed airflow is slowed down by diffuser and is pressurized, and kinetic energy is changed into pressure potential, finally with environment static pressure row It puts into atmosphere.The Supersonic Ejector used in the present invention is compared with traditional vacuum compressor assembly, the simple, nothing with structure The advantages that rotatable parts, small in size, fast reaction, maneuverability.
5. the present invention uses circular cone shrinkage type equipressure mixing chamber.Theory analysis and engineering practice prove that isobaric mixing chamber draws The ejector capacity of emitter is stronger, and performance is higher than cross-section mixing chamber injector.Meanwhile circular cone shrinkage type equipressure mixing cell structure letter Single, mismachining tolerance is small, and manufacturing cost is low, is suitable for big flow ejection system.Circular cone shrinkage type equipressure mixing chamber, which can be taken into account, to be drawn Penetrate efficiency and processing cost.
6. Supersonic Ejector is initially used for building the high blank test vacuum system of rocket engine in aerospace, in recent years It is widely used in hypersonic large-scale free jet test system again.The long-term stable work ability of Supersonic Ejector obtains Sufficiently verifying.Innovation of the invention is expected to promote application of the supercooling propellant in space launch guarantee.The application is formed by Achievement can directly apply to the design and construction that large-scale liquid oxygen crosses cooling system, promoted and ensure CZ-5, CZ-7 new generation's carrier rocket The ability that big flow liquid oxygen is quickly subcooled.
Detailed description of the invention
Fig. 1 shows that a kind of big flow liquid oxygen based on Supersonic Ejector of the present invention crosses the schematic illustration of cooling method.
Fig. 2 shows the structural schematic diagram of Supersonic Ejector.
Fig. 3 shows the structural schematic diagram of gas generator.
Fig. 4 shows the relational graph of mass ratio of induced-to-inducing air n Yu Supersonic Ejector compression ratio CR.
Wherein have:
10. liquefied oxygen tank vehicle；11. liquid oxygen pump；12. liquid oxygen fill valve；
20. liquid nitrogen tank car；21. liquid nitrogen fill valve one；22. liquid nitrogen fill valve two；
30. first-class heat exchanger；
40. secondary heat exchanger；
50. Supersonic Ejector；
51. entrance；52. mixing section；53. ultra-expanded section；54. section is expanded in Asia；
60. gas generator；61. torch lighter；62. alcohol chamber；63. oxygen chamber；64. combustion chamber；
70. liquid oxygen storage tank；71. liquid oxygen collects valve.
In addition, in Fig. 2:
1 indicates injection air flow inlet longitudinal section；2 indicate by injection air flow inlet longitudinal section；3, which indicate that mixing section outlet is vertical, cuts Face；4 indicate that the sub- section that expands exports longitudinal section.
Specific embodiment
Xia Mianjiehefutuhejuti compare Jia Shishifangshiduibenfamingzuojinyibuxiangxishuoming.
As shown in Figure 1, a kind of big flow liquid oxygen based on Supersonic Ejector crosses cooling method, it will be using conventional saturated liquid nitrogen Heat exchanger used in liquid oxygen is subcooled as first-class heat exchanger 30, which can will cross cold flow and be greater than 4500L/min Liquid oxygen crossed from 92K and be cooled to 80K.
Liquid oxygen in liquefied oxygen tank vehicle 10 passes through liquid oxygen pump 11 and liquid oxygen fill valve 12 and changing in first-class heat exchanger 30 respectively Heat pipe entrance is connected.Wherein, the liquid oxygen temperature in liquefied oxygen tank vehicle is about 92K.
Secondary heat exchanger 40 is set in the downstream of first-class heat exchanger, which, which can will cross, is cooled to 80K and crosses cold flow Liquid oxygen of the amount greater than 4500L/min, which is crossed, is cooled to 67K hereinafter, the liquid oxygen after supercooling is collected after liquid oxygen collects valve 71 in liquid oxygen storage tank In 70.
On the one hand liquid nitrogen in liquid nitrogen tank car 20 passes through liquid nitrogen fill valve 1 and is connected with the liquid nitrogen bath of first-class heat exchanger, On the other hand it is connected by liquid nitrogen fill valve 2 22 with the liquid nitrogen bath of secondary heat exchanger.
Wherein, the liquid nitrogen temperature in liquid nitrogen tank car is 77K, so liquid nitrogen temperature is in the liquid nitrogen bath of first-class heat exchanger 77K, liquid nitrogen is boiling bathing pool in secondary heat exchanger, and temperature is no more than 64K, preferably equal to 64K, the gas outlet of secondary heat exchanger with Supersonic Ejector 50 is connected by injection air flow inlet.
Namely the liquid nitrogen evaporated from secondary heat exchanger is by injection air-flow.
It is as follows by the parameter of injection air-flow:
Stagnation pressure p02, total temperature T02, specific heat ratio γ2, molecular weight μ2, velocity coeffficient λ2, flow m2, circulation area F2。
p02Also it is maintained at for liquid nitrogen in secondary heat exchangerWhen pneumatic die cushion pressure；Wherein,In the present invention,Preferably equal to 64K inquires liquid nitrogen saturated vapor pressure table, the pneumatic die cushion pressure p of liquid nitrogen in available secondary heat exchanger at this time02 =0.145952bar.
Assuming that due to leakage heat etc., temperature slightly rises when the steam of nitrogen bathing pool boiling reaches injector entrance, Physical property is as follows:
T02=70K, p02=0.14595bar, Ma=0.1, V2=17.04m/s, γ2=1.4, μ2=28.
Above-mentioned circulation area F2The then variable for that need to design.
As shown in Fig. 2, Supersonic Ejector along airflow direction successively include coaxial arrangement entrance 51, mixing section 52, Ultra-expanded section 53 and sub- expansion section 54.
Entrance includes centrally located injection air flow inlet and being flowed by injection gas positioned at injection air flow inlet periphery Mouthful.Wherein, injection air flow inlet connects the gas outlet of gas generator 60.The area of injection air flow inlet longitudinal section 1 is F1, drawn Inflow entrance longitudinal section 2 emanate as F2, define area ratio
Above-mentioned ultra-expanded section is the abbreviation of Supersonic diffuser+, and the abbreviation that section is subsonic speed diffuser is expanded in Asia.
As shown in figure 3, gas generator includes combustion chamber 64, the oxygen chamber 63 being arranged on combustion chamber, 63 and of alcohol chamber Torch lighter 61.
For gas as injection air-flow, injection flow parameter is as follows after the burning of gas generator:
Stagnation pressure p01, total temperature T01, specific heat ratio γ1, molecular weight μ1, velocity coeffficient λ1, flow m1, circulation area F1。
High-temperature fuel gas is generated using aqueous alcohol and oxygen combustion.In aqueous alcohol, the mass ratio of alcohol is 20%.Oxygen It is 1 with alcohol equivalent proportion.Gas generator stagnation pressure is designed as p01=30bar, pressure and nitrogen are in longitudinal section 3 after combustion gas expansion Static pressure matches (p2=0.14494bar).The expansion ratio of combustion gas is 207.Pass through the physical property of the available exit flow of thermodynamic computing Parameter:
T01=1533.73K, T1=536.95K, p01=30bar, p1=0.14494bar, γ1=1.2905, Ma1= 3.872 μ1=21.432.
Static temperature T1It can guarantee that icing or condensate will not occur for mixed process for 536.95K.
Mixing section is the taper equipressure mixing chamber of cross-sectional constriction, static pressure phase on mixing section entrance, outlet and entire inner wall Deng.
Mixing chamber long enough, air-flow has been thoroughly mixed when reaching mixing chamber outlet, mixed airflow parameter:
Stagnation pressure p03, total temperature T03, specific heat ratio γ3, molecular weight μ3, velocity coeffficient λ3, flow m3, circulation area F3。
It is assumed that static pressure is equal on mixing section entrance, outlet and entire inner wall, mixing chamber shrinkage ratio is definedIt is defined as the sub- area expansion ratio for expanding sectionWherein, F3Vertical section of mixing section outlet in corresponding diagram 2 Face 3；F4The corresponding sub- section that expands exports longitudinal section 4.
In high compression ratio, the air-flow of mixing chamber outlet is still supersonic flow, in order to reach the mesh for pressurization of slowing down , one section of cross-section Supersonic diffuser+ is connect behind mixing chamber, then connect the subsonic speed diffuser of one section of area expansion, to reach to the greatest extent Static pressure that may be high restores.
Liquid nitrogen vapor in secondary heat exchanger be by injection air-flow, according to by injection flow parameter and liquid nitrogen vaporization amount, into The design of row gas generator total flow and Supersonic Ejector physical parameter.
The design method of gas generator total flow and Supersonic Ejector physical parameter, includes the following steps:
Step 1, the compression ratio CR of Supersonic Ejector is calculated.
In formula, p4For the sub- static pressure for expanding section and exporting the mixed gas of longitudinal section 4, in order to guarantee being smoothly discharged for air-flow, one As need be more than or equal to atmospheric environmental pressure；p02It is maintained at for liquid nitrogen in secondary heat exchangerWhen pneumatic die cushion pressure or saturation Steam pressure；Wherein,
In the present invention,Preferably equal to 64K inquires liquid nitrogen saturated vapor pressure table, in available secondary heat exchanger at this time The pneumatic die cushion pressure p of liquid nitrogen02=0.145952bar.
Assuming that the pressure that sub- expansion section is discharged into atmosphere is an atmospheric pressure, i.e. p4=1atm=1.01325bar can then be obtained To the design compression ratio of Supersonic Ejector (below can abbreviation injector)
Step 2, the lookup of mass ratio of induced-to-inducing air n and Supersonic Ejector compression ratio CR relationship, specifically comprises the following steps.
Step 21, mixing section specific heat ratio γ3Relationship is searched between mass ratio of induced-to-inducing air n.
In formula, γ2For by the specific heat ratio of injection air-flow, γ1For the specific heat ratio of injection air-flow, μ1For the molecule of injection air-flow Amount, μ2For by the molecular weight of injection air-flow.
Step 22, mixing section muzzle velocity coefficient lambda3It is calculated using following formula:
Wherein,
In formula, R1For ejection gas constant, R2For by ejection gas constant, R3For the gas constant of mixing section outlet；T01For Ejection gas total temperature, T02For by ejection gas total temperature；λ1For ejection gas velocity coeffficient, λ2For by ejection gas velocity coeffficient, Ru For universal gas constant, 8.314 are generally taken.
The γ that step 21 is calculated3And c substitutes into above formula, can obtain λ3Relational expression between n.
Step 23, total pressure recovery coefficient σ in mixed airflow moderating processTCalculating:
Due to gained λ3> 1, mixed airflow becomes subsonic airflow, total pressure recovery by one of normal shock wave in ultra-expanded section Coefficient is σshock。
σT=σshockσsub
Wherein,
In formula, σshockFor the total pressure recovery coefficient of ultra-expanded section, σsubThe total pressure recovery coefficient for expanding section for Asia, due to subsonic speed Air-flow further slows down in subsonic speed diffuser to be pressurized, and generally assumes that the sub- section resistance airflow resistance that expands is smaller, therefore σsub=1.0.
Ma3For ultra-expanded section entrance Mach number；The γ that step 21 and 22 are calculated3And λ3Above formula is substituted into, can obtain σTWith n it Between relational expression.
Step 24, section velocity of discharge coefficient lambda is expanded in Supersonic Ejector Asia4It calculates.
Define the total pressure recovery coefficient in mixed airflow moderating processAnd σT=σshockσsub.According to one-dimensional Flow formula:
m3=m4
In formula, m3Indicate the mixed gas flow that longitudinal section 3 is exported by mixing section；m4Indicate vertical by the outlet of sub- expansion section The mixed gas flow in section 4；T03Indicate the total temperature of the mixed gas of mixing section outlet longitudinal section 3；T04It indicates sub- and expands section outlet The total temperature of the mixed gas of longitudinal section 4；p03Indicate the stagnation pressure of the mixed gas of mixing section outlet longitudinal section 3；p04It indicates sub- and expands section Export the stagnation pressure of the mixed gas of longitudinal section 4.
Wherein,
The sub- area expansion ratio for expanding section of definitionGenerally take Ψ=2.0.According to the definition of total pressure recovery coefficientMixing section exports longitudinal section 3 and the sub- section that expands exports 4 conservation of energy of longitudinal section: T03=T04；Since mixing section exports Longitudinal section 3 and sub- expansion section outlet 4 physical difference of longitudinal section are smaller, it is believed that R3=R4, γ3=γ4, i.e. C (R3,γ3)=C (R4,γ4)。
Equation can simplify are as follows:
Wherein,
In formula, Ψ is the sub- area expansion ratio for expanding section, value 2.0；The γ calculated in step 23、λ3It is calculated with step 23 σTAbove formula is substituted into, can obtain λ4Relationship between n.
Step 25, mixing section stagnation pressure p03With by injection air-flow stagnation pressure p02Ratio calculation:
Since mixing chamber is isobaric mixing chamber, it is equal to mix indoor pressure, available:
p3=p1=p2
Wherein, p1Indicate the static pressure of injection air flow inlet longitudinal section 1；p2It indicates by the quiet of injection air flow inlet longitudinal section 2 Pressure；p3Indicate the static pressure of mixing section outlet longitudinal section 3.
p03π(λ3,γ3)=p02π(λ2,γ2)
Wherein,
Similarly there is relational expression:
Step 26, Supersonic Ejector compression ratio CR calculation formula:
p4=p04π(λ4,γ4)=p04π(λ4,γ3)=p03σTπ(λ4,γ3)
Define injector compression ratioSolve equation are as follows:
Namely
Wherein,
The γ that will be calculated in step 21 to 253、σT、λ4WithIt substitutes into step 26, Supersonic Ejector can be obtained Relationship between compression ratio CR and mass ratio of induced-to-inducing air n, as shown in the graph in fig. 4.
Step 3, mass ratio of induced-to-inducing air n value determines: the CR value that will be calculated in step 1, such as CR=6.942, substitutes into step 2 and seeks In the relational expression of the CR and n that look for, that is, it can determine mass ratio of induced-to-inducing air n value.It, can be in the hope of n=by dichotomy as CR=6.942 0.4758, it can also correspond to and obtain from the curve in Fig. 4.Meet pressure match condition: p4It is matched with environmental pressure, p02It is changed with liquid nitrogen Hot device pneumatic die cushion pressure match.
Step 4, gas generator total flow m1It calculates, includes the following steps.
Step 41, liquid nitrogen vaporization amount is calculated as follows
In formula,Indicate liquid oxygen rate of heat release in secondary heat exchanger；H is that liquid nitrogen is maintained in secondary heat exchangerWhen Gasification latent heat.
Liquid oxygen rate of heat release in above-mentioned secondary heat exchangerCalculation formula it is as follows:
Wherein, Cp=A+BT+CT2+DT3+ET4
In formula, CpIndicate liquid oxygen low temperature under specific heat, unit J/kmol/K, the calculation formula scope of application for 54.36K~ 142K；A, B, C, D and E are constant；For the liquid oxygen heat exchange flow of setting；T1It indicates when liquid oxygen enters secondary heat exchanger Temperature, T2Indicate temperature when liquid oxygen leaves secondary heat exchanger, T2≤67K。
With T1=80K, T2For=67K, A=1.7543 × 105, B=-6152.3, C=113.92, D=-0.92382, E=0.0027963,Then
Step 42, gas generator total flow m1It calculates:
The mass ratio of induced-to-inducing air n value that step 3 is determined substitutes into above formula, and gas generator total flow m can be obtained1Value.
Namely the total flow m of gas generatorburnedAre as follows:
Obtain gas generator oxygen flow 5.34kg/s, fuel flow rate 12.78kg/s (wherein alcohol 2.56kg/s, water 10.22kg/s)。
Step 5, the calculating of Supersonic Ejector physical parameter: Supersonic Ejector physical parameter includes mixing section shrinkage ratio Φ, mixing section shrinkage ratio Φ are calculated using following formula:
Wherein,
The mass ratio of induced-to-inducing air n value that step 3 is determined, and the γ calculated by step 2 formula3And λ3Above formula is substituted into, can be acquired Mixing section shrinkage ratio Φ=0.4089.
In addition, n=0.4758 is substituted into the separate equations in step 2, intermediate parameters will be obtained simultaneously:
R3=358.59J/ (kgK), γ3=1.3134, F3=0.3489m2, Ma3=2.3441, λ3=1.8480, λ4 =0.2440.
Now preferred parameter of the invention is summarized as follows:
Secondary heat exchanger:
Liquid oxygen heat exchange volume flowMass flowLiquid oxygen entrance temperature Spend 80K, liquid oxygen outlet temperature 67K.Liquid nitrogen bathing pool temperature 64K, liquid nitrogen bathing pool pneumatic die cushion pressure p02=0.14595bar, liquid nitrogen vaporization Quality
Gas generator:
Oxygen flow 5.34kg/s, fuel flow rate 12.78kg/s (wherein alcohol 2.56kg/s, water 10.22kg/s)；Burning Room stagnation pressure p01=30bar, combustion gas total temperature T01=1533.73K, gas outlet static temperature T1=536.95K, gas outlet static pressure p1= 0.14493bar；Gas outlet specific heat ratio γ1=1.2905, gas outlet Mach number Ma1=3.872, gas outlet molecular weight μ1 =21.432；Characteristic velocity c*=1186.7m/s；Throat opening area Ft=0.0072m2, discharge area F1=0.1296m2。
Supersonic Ejector:
Design mass ratio of induced-to-inducing air n=0.4758, design compression ratio CR=6.9419.
Injection gas entrance longitudinal section 1: stagnation pressure p01=30bar, combustion gas total temperature T01=1533.73K, static temperature T1=536.95K, Static pressure p1=0.14493bar；Specific heat ratio γ1=1.2905, molecular weight μ1=21.432；Mach number Ma1=3.872；Area F1= 0.1296m2。
By injection gas entrance longitudinal section 2: nitrogen is pumped into speed V2=17.04m/s；Total temperature T02=70K, static temperature T2= 69.86K stagnation pressure p02=0.14595bar, static pressure p2=0.14494bar；Nitrogen specific heat ratio γ2=1.4, nitrogen molecule amount μ2= 28；Area F2=0.7236m2。
Mixing chamber outlet longitudinal section 3: velocity coeffficient λ3=1.8480；Total temperature T03=1341.4K, static temperature T3=720.8K, Stagnation pressure p03=1.9573bar, static pressure p3=0.14493bar；Area F3=0.3489m2, isobaric mixing chamber shrinkage ratio Φ= 0.4089；Gaseous mixture gas constant R3=358.59J/ (kgK), mixer specific heat ratio γ3=1.3134.
Injector exports longitudinal section 4: velocity coeffficient λ4=0.2440, area F4=0.6979m2。
The preferred embodiment of the present invention has been described above in detail, still, during present invention is not limited to the embodiments described above Detail a variety of equivalents can be carried out to technical solution of the present invention within the scope of the technical concept of the present invention, this A little equivalents all belong to the scope of protection of the present invention.

Claims (5)

1. a kind of big flow liquid oxygen based on Supersonic Ejector crosses cooling method, it is characterised in that: will be using conventional saturated liquid nitrogen Heat exchanger used in liquid oxygen is subcooled as first-class heat exchanger, which can will cross cold flow greater than 4500L/min's Liquid oxygen is crossed from 92K is cooled to 80K；Secondary heat exchanger is set in the downstream of first-class heat exchanger, which can be cooled to 80K for crossing And it crosses liquid oxygen of the cold flow greater than 4500L/min and crosses and be cooled to 67K or less；
Liquid nitrogen in a saturated state is filled in secondary heat exchanger, liquid nitrogen temperature is no more than 64K in secondary heat exchanger, and second level is changed The gas outlet of hot device 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 to cut The taper equipressure mixing chamber that face is shunk, static pressure is equal on mixing section entrance, outlet and entire inner wall.
2. the big flow liquid oxygen according to claim 1 based on Supersonic Ejector crosses cooling method, it is characterised in that: second level Liquid nitrogen vapor in heat exchanger is, according to by injection flow parameter and liquid nitrogen vaporization amount, to carry out gas generator by injection air-flow The design of total flow and Supersonic Ejector physical parameter.
3. the big flow liquid oxygen according to claim 2 based on Supersonic Ejector crosses cooling method, it is characterised in that: combustion gas The design method of generator total flow and Supersonic Ejector physical parameter, includes the following steps:
Step 1, the compression ratio CR of Supersonic Ejector is calculated:
In formula, p4For the sub- static pressure for expanding section and exporting the mixed gas of longitudinal section；p02It is maintained at for liquid nitrogen in secondary heat exchangerWhen Pneumatic die cushion pressure or saturated vapour pressure；Wherein,
Step 2, the lookup of mass ratio of induced-to-inducing air n and Supersonic Ejector compression ratio CR relationship, specifically comprises the following steps:
Step 21, mixing section specific heat ratio γ3Relationship is searched between mass ratio of induced-to-inducing air n:
In formula, γ2For by the specific heat ratio of injection air-flow, γ1For the specific heat ratio of injection air-flow, μ1For the molecular weight of injection air-flow, μ2 For by the molecular weight of injection air-flow；
Step 22, mixing section muzzle velocity coefficient lambda3It is calculated using following formula:
Wherein,
In formula, R1For ejection gas constant, R2For by ejection gas constant, R3For the gas constant of mixing section outlet；T01For injection Gas total temperature, T02For by ejection gas total temperature；λ1For ejection gas velocity coeffficient, λ2For by ejection gas velocity coeffficient；
The γ that step 21 is calculated3And c substitutes into above formula, can obtain λ3Relational expression between n；
Step 23, total pressure recovery coefficient σ in mixed airflow moderating processTCalculating:
σT=σshockσsub
Wherein,
In formula, σshockFor the total pressure recovery coefficient of ultra-expanded section, σsubFor the sub- total pressure recovery coefficient for expanding section, value 1.0；Ma3It is super Expand section entrance Mach number；The γ that step 21 and 22 are calculated3And λ3Above formula is substituted into, can obtain σTRelational expression between n；
Step 24, section velocity of discharge coefficient lambda is expanded in Supersonic Ejector Asia4It calculates:
Wherein,
In formula, Ψ is the sub- area expansion ratio for expanding section, value 2.0；The γ that will be calculated in step 23、λ3The σ calculated with step 23T Above formula is substituted into, can obtain λ4Relationship between n；
Step 25, mixing section stagnation pressure p03With by injection air-flow stagnation pressure p02Ratio calculation:
Wherein,
Step 26, Supersonic Ejector compression ratio CR calculation formula:
Wherein,
The γ that will be calculated in step 21 to 253、σT、λ4WithIt substitutes into step 26, Supersonic Ejector compression can be obtained Than the relationship between CR and mass ratio of induced-to-inducing air n；
Step 3, mass ratio of induced-to-inducing air n value determines: the relational expression of CR and n that the CR value being calculated in step 1 substitution step 2 is found In, that is, it can determine mass ratio of induced-to-inducing air n value；
Step 4, gas generator total flow m1It calculates, includes the following steps:
Step 41, liquid nitrogen vaporization amount is calculated as follows
In formula,Indicate liquid oxygen rate of heat release in secondary heat exchanger；H is that liquid nitrogen is maintained in secondary heat exchangerWhen gas Change latent heat；
Step 42, gas generator total flow m1It calculates:
The mass ratio of induced-to-inducing air n value that step 3 is determined substitutes into above formula, and gas generator total flow m can be obtained1Value；
Step 5, the calculating of Supersonic Ejector physical parameter: Supersonic Ejector physical parameter includes mixing section shrinkage ratio Φ, Mixing section shrinkage ratio Φ is calculated using following formula:
Wherein,
The mass ratio of induced-to-inducing air n value that step 3 is determined, and the γ calculated by step 2 formula3And λ3Above formula is substituted into, mixing can be acquired Section shrinkage ratio Φ.
4. the big flow liquid oxygen according to claim 3 based on Supersonic Ejector crosses cooling method, it is characterised in that: step In 41, liquid oxygen rate of heat release in secondary heat exchangerCalculation formula it is as follows:
Wherein, Cp=A+BT+CT2+DT3+ET4
In formula, CpIndicate specific heat under liquid oxygen low temperature, unit J/kmol/K, the calculation formula scope of application is 54.36K~142K； A, B, C, D and E are constant；For the liquid oxygen heat exchange flow of setting；T1Indicate temperature when liquid oxygen enters secondary heat exchanger, T2Indicate temperature when liquid oxygen leaves secondary heat exchanger, T2≤67K。
5. the big flow liquid oxygen according to claim 4 based on Supersonic Ejector crosses cooling method, it is characterised in that: step In 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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