CN110566368A - Rankine cycle rocket engine system - Google Patents
Rankine cycle rocket engine system Download PDFInfo
- Publication number
- CN110566368A CN110566368A CN201910947552.6A CN201910947552A CN110566368A CN 110566368 A CN110566368 A CN 110566368A CN 201910947552 A CN201910947552 A CN 201910947552A CN 110566368 A CN110566368 A CN 110566368A
- Authority
- CN
- China
- Prior art keywords
- rankine cycle
- booster pump
- propellant
- engine system
- rocket engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000003380 propellant Substances 0.000 claims abstract description 42
- 239000000446 fuel Substances 0.000 claims abstract description 35
- 230000005540 biological transmission Effects 0.000 claims abstract description 17
- 239000007800 oxidant agent Substances 0.000 claims description 37
- 230000001590 oxidative effect Effects 0.000 claims description 31
- 239000012530 fluid Substances 0.000 claims description 14
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 claims description 7
- VLKZOEOYAKHREP-UHFFFAOYSA-N n-Hexane Chemical compound CCCCCC VLKZOEOYAKHREP-UHFFFAOYSA-N 0.000 claims description 6
- MSSNHSVIGIHOJA-UHFFFAOYSA-N pentafluoropropane Chemical compound FC(F)CC(F)(F)F MSSNHSVIGIHOJA-UHFFFAOYSA-N 0.000 claims description 4
- FYIRUPZTYPILDH-UHFFFAOYSA-N 1,1,1,2,3,3-hexafluoropropane Chemical compound FC(F)C(F)C(F)(F)F FYIRUPZTYPILDH-UHFFFAOYSA-N 0.000 claims description 3
- -1 R600 Chemical compound 0.000 claims description 3
- 239000002826 coolant Substances 0.000 claims description 3
- 239000000203 mixture Substances 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- 229910021529 ammonia Inorganic materials 0.000 claims description 2
- 230000008878 coupling Effects 0.000 claims description 2
- 238000010168 coupling process Methods 0.000 claims description 2
- 238000005859 coupling reaction Methods 0.000 claims description 2
- 230000013011 mating Effects 0.000 claims 1
- 230000008901 benefit Effects 0.000 abstract description 3
- 239000007788 liquid Substances 0.000 description 21
- 239000013526 supercooled liquid Substances 0.000 description 13
- 238000000034 method Methods 0.000 description 9
- 238000001816 cooling Methods 0.000 description 8
- 238000002485 combustion reaction Methods 0.000 description 7
- 230000008569 process Effects 0.000 description 6
- 238000010521 absorption reaction Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- WFPZPJSADLPSON-UHFFFAOYSA-N dinitrogen tetraoxide Chemical compound [O-][N+](=O)[N+]([O-])=O WFPZPJSADLPSON-UHFFFAOYSA-N 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- HDZGCSFEDULWCS-UHFFFAOYSA-N monomethylhydrazine Chemical compound CNN HDZGCSFEDULWCS-UHFFFAOYSA-N 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- VHUUQVKOLVNVRT-UHFFFAOYSA-N Ammonium hydroxide Chemical compound [NH4+].[OH-] VHUUQVKOLVNVRT-UHFFFAOYSA-N 0.000 description 1
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 235000011114 ammonium hydroxide Nutrition 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 239000003990 capacitor Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000002309 gasification Methods 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 238000005184 irreversible process Methods 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K25/00—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for
- F01K25/08—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours
- F01K25/10—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K27/00—Plants for converting heat or fluid energy into mechanical energy, not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
Abstract
The invention relates to a Rankine cycle rocket engine system, which comprises a thrust chamber (1), a condenser (5), a propellant pressurization unit, an expansion machine (4), a Rankine cycle booster pump (6) and a motor, wherein the propellant pressurization unit is connected with the thrust chamber (1) and supplies fuel, the thrust chamber (1), the expansion machine (4), the condenser (5) and the Rankine cycle booster pump (6) are connected in series to form a Rankine cycle subsystem, and the expansion machine (4) is in transmission connection with the propellant pressurization unit or is simultaneously in transmission connection with the Rankine cycle booster pump (6); the propellant booster unit and/or the Rankine cycle booster pump (6) is connected to an electric motor providing additional power. Compared with the prior art, the battery has the advantages of greatly reduced weight, simplicity, reliability, easy control and low price.
Description
Technical Field
The invention relates to the field of engine systems, in particular to a Rankine cycle rocket engine system.
Background
Traditional pump-type rocket engine systems are divided into open-type cycles and closed-type cycles according to the engine cycle, the open-type cycles mainly comprise gas generator cycles, and the closed-type cycles mainly comprise staged combustion cycles and expansion cycles. In both open and closed cycles, the system is complex and the control involves complex feedback because it involves the use of partial propellant combustion or gasification to drive the turbine. Especially, in the closed cycle, the feedback degree is very deep, and the complexity and control difficulty of the system are the best of those of industrial products. In addition to the characteristics such as high temperature and high pressure of a thrust chamber, the pumping pressure type rocket engine system builds a high and unsmooth technical threshold for the rocket engine system, and only a few aerospace strong countries can control the rocket engine system.
And with the successful launching of the carrier rocket of the electronic number of 1 month and 21 days in 2018, the looseness appears in the field. The 'electronic number' carrier rocket indicates a brand-new way for the design of future rocket engines by the brand-new cycle of the electric rocket engine: the power source for pressurizing the propellant is not from the turbine, but is provided by the motor. The circulation mode enables the system to have the characteristics of simple design and debugging, high engine performance, easy maintenance and use, easy expansion and the like. The combination of the inexpensive launch price of the rocket company makes this technology known in the industry as "it is possible to significantly reduce the difficulty of designing and manufacturing small rocket engines".
However, the electric rocket engine cycle has a fatal weakness that the weight of the battery is too high. From analysis, even with the highest state of the art lithium batteries, the battery weight required to provide pump boost power for the rocket stage must reach 2t, while the total weight of the rocket body is no more than 10 t. Therefore, even if various weight-reducing methods are adopted, the nominal emission mass of the 500km solar synchronous orbit is only 150kg, and the mass of the payload actually carried in the first emission is only 39 kg. Too high weight of the battery has been the biggest obstacle to the development thereof.
Disclosure of Invention
The present invention has been made to solve the above-mentioned problems, and an object of the present invention is to provide a rankine cycle engine system, particularly for a rocket, which can greatly reduce the weight of a battery, is easy to control, is simple and reliable, and is inexpensive.
The purpose of the invention is realized by the following technical scheme:
a Rankine cycle rocket engine system comprises a thrust chamber, a condenser, a propellant pressurizing unit, an expander, a Rankine cycle booster pump and a motor, wherein the propellant pressurizing unit is connected with the thrust chamber and supplies fuel, the thrust chamber, the expander, the condenser and the Rankine cycle booster pump are connected in series to form a Rankine cycle subsystem, and the expander is in transmission connection with the propellant pressurizing unit or is in transmission connection with the Rankine cycle booster pump; the propellant booster unit and/or the rankine cycle booster pump are connected to an electric motor providing additional power.
When the system works, fuel and oxidant are mixed and combusted in the thrust chamber to release heat, the heat is transferred to liquid Rankine cycle working medium through the chamber wall, the Rankine cycle working medium changes from liquid to superheated steam after absorbing heat, does work outwards through an expansion machine (mechanical energy is transferred to a propellant pressurization unit and/or a Rankine cycle booster pump), changes into low-temperature low-pressure steam and then changes into supercooled liquid through a condenser, then the supercooled liquid is pressurized through the Rankine cycle booster pump to become high-pressure low-temperature liquid, and finally the high-pressure low-temperature liquid enters a Rankine cycle fluid channel of the thrust chamber to form Rankine cycle.
The system can adopt a control mode that the motor provides additional power, and when the motor is used as main power, the Rankine cycle subsystem only provides partial power; the system can also adopt a control mode that the motor only provides partial power and the main power is provided by the Rankine cycle subsystem; the control mode that a motor is not arranged in the system, the initial power is provided by the pressure of the fuel storage tank, and the subsequent power is provided by the Rankine cycle subsystem can be adopted.
When the scheme that the motor provides partial power is adopted, the required motor power is smaller, so that the required amount of the battery serving as a power source of the motor is smaller, the weight of the battery can be greatly reduced, and the control is easy; the super capacitor and the battery are reasonably matched to use, so that the weight of the battery is greatly reduced while the control is convenient.
Further, the electric motor comprises a first electric motor connected with the propellant booster unit and/or a second electric motor separately connected with the rankine cycle booster pump. The same motor is adopted to simultaneously provide power for the propellant pressurization unit and the Rankine cycle pressurization pump, so that the efficiency is higher in energy utilization, but the structural layout has larger limitation. The degree of freedom that the second motor provides power for the Rankine cycle booster pump alone is more in the control, can be convenient realize adjusting Rankine cycle operating pressure through adjusting the second motor rotational speed, and realize adjusting Rankine cycle operating flow through adjusting the first motor rotational speed, and then realize the purpose of adjusting whole engine system operating mode. At this time, the rankine cycle booster pump is not connected to the propellant booster unit.
furthermore, the propellant pressurizing unit is connected with the condenser firstly and then connected with the thrust chamber, the propellant can be used as a cold source, the energy exchange principle is better applied, and the energy utilization efficiency of the Rankine cycle subsystem is higher.
Further, the propellant pressurizing unit comprises a fuel pressurizing pump and an oxidant pressurizing pump, the fuel pressurizing pump is connected with the expander and/or the motor, and the oxidant pressurizing pump is connected with the expander and/or the motor.
Further, the fuel booster pump is used for boosting fuel, the oxidant booster pump is used for boosting oxidant, and the condenser adopts the boosted fuel and/or the boosted oxidant as cooling media. The cooling scheme is determined according to the heat absorbed by the cooling medium required by the system, wherein the fuel alone is safer to use as the cooling medium.
Furthermore, a heat regenerator is further arranged in the Rankine cycle subsystem, namely the heat regenerator is further arranged between the expansion machine and the condenser and used for transferring the heat of the low-temperature low-pressure working medium steam in front of the inlet of the condenser to the low-temperature high-pressure working medium liquid in front of the inlet of the fluid channel of the thrust chamber. Generally, the temperature of low-temperature low-pressure steam before the inlet of the condenser is higher than that of low-temperature high-pressure liquid before the inlet of a Rankine cycle fluid channel of the thrust chamber; the heat regenerator is arranged, so that the cooling load of the propellant and/or the oxidant can be effectively reduced, and the heat absorption capacity of the isobaric heat absorption process of the system is increased.
Further, the condenser and the heat regenerator are plate heat exchangers or tubular heat exchangers, and are all common heat exchanger types.
Further, the motor and the expansion machine provide power through a shaft system and/or a transmission device, and the transmission device comprises a gear, a belt transmission mechanism and a coupler which are mutually matched and connected and is a common transmission device.
Further, the expander is a turbine or screw expander, which are two types of expanders commonly used in rankine cycles.
Further, the oxidant booster pump, the fuel booster pump and the rankine cycle booster pump are centrifugal pumps or plunger pumps, and are all commonly used pump types.
Further, the Rankine cycle subsystem is used for circulation of a Rankine cycle working fluid selected from water, liquid ammonia, an ammonia mixture, R41, R125, R218, R143a, R32, RE125, R1270, R290, R134a, R227ea, R161, R152a, RC270, R236fa, RE170, R600a, R236ea, R600, R245fa, Neo-C5H12One or more of R601a, R601 or n-hexane.
The thrust chamber of the pump-type rocket engine generally achieves the purpose of cooling the wall of the thrust chamber through regenerative cooling, and in the process, Rankine cycle working media in a Rankine cycle fluid channel of the thrust chamber cool the wall of the thrust chamber through absorbing combustion heat transmitted by the wall of the chamber; the process belongs to spontaneous transfer of heat from high temperature to low temperature, and the second law of thermodynamics shows that the process belongs to an irreversible process and can bring loss of system working capacity.
The invention mainly adopts Rankine cycle technology to absorb heat generated by combustion of the thrust chamber and convert the heat into mechanical energy for pressurizing fuel and/or oxidant in the expander, thereby achieving the purpose of greatly reducing the weight of the battery.
The Rankine cycle technology is adopted, heat generated by combustion of a propellant in the thrust chamber is used as a heat source, pressurized fuel and/or pressurized oxidant are used as a cold source, work is applied to the outside through the expansion machine, and power can be provided for the oxidant booster pump, the fuel booster pump and the Rankine cycle booster pump, so that the load of a motor is reduced, the power consumption is reduced, and the purpose of greatly reducing the weight of a battery is achieved.
Different from the traditional engine system, the Rankine cycle subsystem only has a heat exchange relation with the main engine system except for driving the pump, so that the Rankine cycle subsystem is low in coupling degree and easy to control. The characteristic also makes the invention and the electric circulating system can be compared in the aspects of simplicity, reliability, low price and the like.
In addition, the temperature of the cold source has great influence on the Rankine cycle efficiency, and the lower the temperature of the cold source is, the higher the Rankine cycle efficiency is; meanwhile, because the cold source has low temperature and enough cooling capacity, the temperature of the heat source can be increased, and the work capacity of the system is further enhanced; for a thrust chamber with extremely high combustion temperature, the temperature of the Rankine cycle working medium can be easily increased through design.
Taking a liquid hydrogen liquid oxygen engine as an example, when the system works, the high temperature of the Rankine cycle working medium can reach more than 500 ℃, and the low temperature can reach below-150 ℃, compared with the efficiency of the Rankine cycle working medium adopting the method in the embodiment 2, the high temperature of the Rankine cycle working medium and the low temperature of 50 ℃ can not be in the same day. Therefore, for the liquid rocket engine widely using the low-temperature propellant, the Rankine cycle mode has the unique advantage of reducing rocket quotation.
The invention can be applied to the carrier rocket, and the carrying capacity can be greatly improved on the basis of simplicity, reliability and low cost, thereby greatly improving the competitiveness. More significantly, after the Rankine efficiency is greatly improved by adopting the low-temperature propellant and/or the low-temperature oxidant as a cold source at the condenser, the thrust and the specific impulse of the system are basically the same as those of a closed cycle, and the weight of the battery is basically negligible compared with the total weight of the rocket body. At the moment, the rocket can utilize the characteristic of more flexible control to complete tasks with higher control difficulty, such as the recovery of a first-stage rocket.
By applying the scheme in the satellite and deep space detector, the electric power of the solar cell panel can be effectively utilized, and the performance of the engine is further improved on the existing basis. The method has important significance for prolonging the on-orbit working time of the high-orbit satellite and saving the propellant of the deep space controller.
Compared with the prior art, the invention has the following advantages:
1. The motor and the expander are adopted to cooperate to provide power for the oxidant booster pump, the fuel booster pump and the Rankine cycle booster pump, so that the weight of a matched battery can be greatly reduced and even reduced to be close to zero, and the expansion type booster pump is suitable for rockets and the like with strict requirements on weight.
2. The pressurized propellant and the oxidant firstly pass through the condenser and then enter the thrust chamber, so that the characteristic of low temperature of the fuel and the oxidant can be effectively utilized, and the heat of the Rankine cycle working medium is transferred out.
3. The heat regenerator is arranged to reduce the cooling load of the pressurized fuel and oxidant.
4. the system has few components, simple circulation loop, greatly reduced control difficulty and low price.
Drawings
FIG. 1 is a schematic view of a Rankine cycle rocket engine system according to embodiment 1;
FIG. 2 is a schematic view of a Rankine cycle rocket engine system according to embodiment 2;
FIG. 3 is a schematic structural view of a Rankine cycle rocket engine system according to embodiment 3;
FIG. 4 is a schematic structural view of a Rankine cycle rocket engine system according to embodiment 4;
FIG. 5 is a schematic structural diagram of a Rankine cycle rocket engine system according to embodiment 5.
In the figure: 1-a thrust chamber; 2-oxidant booster pump; 3-fuel booster pump; 4-an expander; 5-a condenser; 6-Rankine cycle booster pump; 7-a first motor; 8-a heat regenerator; 9-a second motor.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments.
Example 1
As shown in figure 1, the Rankine cycle rocket engine system comprises a thrust chamber 1, a condenser 5, a propellant pressurizing unit, an expander 4, a Rankine cycle booster pump 6 and a motor, wherein the propellant pressurizing unit is connected with the thrust chamber 1 in series to form an engine subsystem, the thrust chamber 1, the expander 4, the condenser 5 and the Rankine cycle booster pump 6 are connected in series to form a Rankine cycle subsystem, the propellant pressurizing unit is connected with the condenser 5 and then connected with the thrust chamber 1, the propellant pressurizing unit comprises a fuel booster pump 3 for pressurizing fuel and an oxidant booster pump 2 for pressurizing oxidant, the condenser 5 adopts pressurized fuel and/or pressurized oxidant as cooling media, the motor is a first motor 7 directly connected with the oxidant booster pump 2, the first motor 7 and the expander 4 are an oxidant booster pump 2 through a shafting and/or a transmission device, The fuel booster pump 3 and the Rankine cycle booster pump 6 provide power, and the transmission device comprises gears, a belt transmission mechanism and a coupler which are mutually matched and connected.
In the figure, a solid line is a flow route of fuel and oxidant, a dotted line is a flow route of Rankine cycle working medium, when the system works, the fuel and the oxidant are mixed and combusted in the thrust chamber 1 to release heat and transmit the heat to the liquid Rankine cycle working medium, the Rankine cycle working medium changes from the liquid state into superheated steam after absorbing heat, does work outwards through the expansion machine 4, changes into low-temperature low-pressure steam and then becomes supercooled liquid through the condenser 5, the supercooled liquid is pressurized into high-pressure low-temperature liquid through the Rankine cycle booster pump 6, and finally the high-pressure low-temperature liquid enters a Rankine cycle fluid channel of the thrust chamber 1 to be heated and then becomes.
Wherein, the condenser 5 is a plate heat exchanger or a tubular heat exchanger; the expander 4 is a turbine or a screw expander; the oxidant booster pump 2, the fuel booster pump 3, and the rankine cycle booster pump 6 are centrifugal pumps or plunger pumps.
the Rankine cycle subsystem is used for the cycle of Rankine cycle working medium selected from water, liquid ammonia, ammonia water mixture, R41, R125, R218, R143a, R32, RE125, R1270, R290, R134a, R227ea, R161, R152a, RC270, R236fa, RE170, R600a, R236ea, R600, R245fa, Neo-C5H12One or more of R601a, R601 or n-hexane.
Example 2
As shown in fig. 2, basically the same as in embodiment 1, a regenerator 8 is provided between the expander 4 and the condenser 5, and between the rankine cycle booster pump 6 and the thrust chamber 1, for transferring heat of the low-temperature and low-pressure working fluid vapor before the inlet of the condenser 5 to the low-temperature and high-pressure working fluid before the inlet of the rankine cycle fluid passage of the thrust chamber 1.
when the system works, a propellant and an oxidant are mixed and combusted in the thrust chamber 1 to release heat and transmit the heat to a liquid Rankine cycle working medium, the Rankine cycle working medium absorbs heat and then is changed into superheated steam from the liquid state, the superheated steam does work outwards through the expansion machine 4, the superheated steam is changed into low-temperature low-pressure steam, the heat is released partially through the heat regenerator 8 and then is changed into supercooled liquid through the condenser 5, then the supercooled liquid is pressurized into high-pressure low-temperature liquid through the Rankine cycle booster pump 6, and finally the high-pressure low-temperature liquid enters the Rankine cycle fluid channel of the thrust chamber 1 after absorbing partial heat in the heat regenerator 8 and is heated to.
Taking a Rankine cycle engine system with NTO (dinitrogen tetroxide) and MMH (methylhydrazine) as propellants, R245fa as Rankine cycle working medium and thrust of 10000N as an example, the pressure in a storage tank is ignored, and the system pressure is 5MpaThe pressure of the thrust chamber is 3.5Mpain the lower steady state operation, about 120KW of thermal power is transmitted from the wall surface of the Rankine cycle fluid passage of the thrust chamber 1, and the temperature is 61 ℃ and the temperature is 3.4MpaAbout, the super-cooled liquid working medium with the flow rate of 0.5kg/s is heated to 160 ℃ and 3.4Mp in equal pressurealeft and right superheated steam; the superheated steam is then adiabatically expanded by means of an expander 4 to a temperature of 76 ℃ and a pressure of 0.34MpaThe superheated steam does work outwards in the process, and the output shaft power is about 13 KW. The superheated steam transfers part of heat to high-pressure supercooled liquid in front of a fluid channel of the wall of the thrust chamber 1 through the heat regenerator 8, the state of the superheated steam is changed into superheated steam with the temperature of 66 ℃ and the pressure of 0.34MPa, then the superheated steam is condensed into supercooled liquid with the pressure of 50 ℃ and the pressure of 0.34MPa through the condenser 5, and the temperature of the propellant is increased from 20 ℃ to 35 ℃. The supercooled liquid is subjected to adiabatic pressurization by a Rankine cycle booster pump 6 to reach the temperature of 51 ℃ and the pressure of 3.4MpaAbout supercooled liquid, the required shaft power of this process is about 1.6 KW. It is changed into 61 ℃ and 3.4Mp by the heat absorption of the heat regenerator 8aLeft and right supercooled liquids form a closed loop of the rankine cycle. The final output power can be boosted by the propellantThe cell provides a boost capacity of about 3.0MPa, and the battery weight can be reduced by about 60% in a battery system load proportional to the battery weight.
Example 3
As shown in fig. 3, substantially the same as in embodiment 2, the rankine cycle booster pump 6 is powered by the second motor 9 alone and not connected to the expander 4, and the oxidant booster pump 2 and the fuel booster pump 3 are powered by the first motor 7 and the expander 4 through a shafting and/or transmission.
Example 4
As shown in fig. 4, essentially the same as in example 2, without the first electric motor 7, the oxidizer booster pump 2 and the fuel booster pump 3 are initially powered by the pressure in the propellant tank, and then the oxidizer booster pump 2, the fuel booster pump 3 and the rankine cycle booster pump 6 are powered by the expander 4 through the shafting and/or the transmission.
When the system works, the pressure in the storage tank for storing the propellant drives the oxidant and the propellant fuel to enter the thrust chamber 1 for combustion, part of heat is transferred to the low-temperature high-pressure liquid Rankine cycle working medium, the Rankine cycle working medium is changed into superheated steam from the liquid after absorbing heat, and then the superheated steam is changed into low-temperature low-pressure steam through the expansion machine 4 for acting. The expander 4 is now used as a power source to power the oxidant booster pump 2, the fuel booster pump 3 and the rankine cycle booster pump 6 via a shafting and/or transmission. The low-temperature low-pressure steam passes through the heat regenerator 8 to emit partial heat and then is changed into supercooled liquid through the condenser 5, then the supercooled liquid is pressurized by the Rankine cycle booster pump 6 to be changed into high-pressure low-temperature liquid, and finally the high-pressure low-temperature liquid absorbs partial heat in the heat regenerator 8 and then enters the Rankine cycle fluid channel of the thrust chamber 1 to be heated and changed into superheated steam, so that Rankine cycle is formed.
example 5
As shown in fig. 5, basically the same as in embodiment 3, the first motor 7 is not provided, and the rankine cycle booster pump 6 is powered by the second motor 9 alone and is not connected to the expander 4.
The embodiments described above are described to facilitate an understanding and use of the invention by those skilled in the art. It will be readily apparent to those skilled in the art that various modifications to these embodiments may be made, and the generic principles described herein may be applied to other embodiments without the use of the inventive faculty. Therefore, the present invention is not limited to the above embodiments, and those skilled in the art should make improvements and modifications within the scope of the present invention based on the disclosure of the present invention.
Claims (10)
1. A rankine cycle rocket engine system, characterized in that the system comprises a thrust chamber (1), a condenser (5), a propellant pressurizing unit, an expander (4), a rankine cycle booster pump (6) and a motor, wherein the propellant pressurizing unit is connected with the thrust chamber (1) and supplies propellant, and the thrust chamber (1), the expander (4), the condenser (5) and the rankine cycle booster pump (6) are connected in series to form a rankine cycle subsystem;
The expansion machine (4) is in transmission connection with the propellant pressurization unit or is simultaneously in transmission connection with the propellant pressurization unit and the Rankine cycle booster pump (6);
The propellant booster unit and/or the Rankine cycle booster pump (6) is connected to an electric motor providing additional power.
2. Rankine cycle rocket engine system according to claim 1, wherein the propellant pressurization unit is connected to the condenser (5) before the thrust chamber (1).
3. Rankine cycle rocket engine system according to claim 2, wherein the propellant booster unit comprises a fuel booster pump (3) and an oxidant booster pump (2), the fuel booster pump (3) being connected to the expander (4) and/or the electric machine, the oxidant booster pump (2) being connected to the expander (4) and/or the electric machine.
4. Rankine cycle rocket engine system according to claim 3, wherein the fuel booster pump (3) is used for boosting propellant, the oxidizer booster pump (2) is used for boosting oxidizer, and the condenser (5) uses pressurized fuel and/or pressurized oxidizer as cooling medium.
5. The Rankine cycle rocket engine system according to claim 1, wherein a regenerator (8) is further provided in the Rankine cycle subsystem.
6. Rankine cycle rocket engine system according to claim 5, wherein the condenser (5) and regenerator (8) are plate heat exchangers or tube heat exchangers.
7. The Rankine cycle rocket engine system according to claim 1, wherein the electric motor and expander (4) are powered by a shafting and/or transmission comprising gears, belt drives and couplings in mating connection with each other.
8. Rankine cycle rocket engine system according to claim 1, wherein the expander (4) is a turbine or a screw expander.
9. Rankine cycle rocket engine system according to claim 3, wherein the oxidant booster pump (2), fuel booster pump (3), Rankine cycle booster pump (6) are centrifugal pumps or plunger pumps.
10. A rankine cycle rocket engine system according to any one of claims 1-9 wherein the rankine cycle subsystem is for the cycle of rankine cycle fluid selected from the group consisting of water, liquid ammonia, ammonia mixture, R41, R125, R218, R143a, R32, RE125, R1270, R290, R134a, R227ea, R161, R152a, RC270, R236fa, RE170, R600a, R236ea, R600, R245fa, Neo-C5H12One or more of R601a, R601 or n-hexane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910947552.6A CN110566368A (en) | 2019-09-29 | 2019-09-29 | Rankine cycle rocket engine system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910947552.6A CN110566368A (en) | 2019-09-29 | 2019-09-29 | Rankine cycle rocket engine system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110566368A true CN110566368A (en) | 2019-12-13 |
Family
ID=68783912
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910947552.6A Pending CN110566368A (en) | 2019-09-29 | 2019-09-29 | Rankine cycle rocket engine system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110566368A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116029586A (en) * | 2022-12-13 | 2023-04-28 | 中国人民解放军63921部队 | Task-oriented carrier rocket system contribution rate calculation method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080053064A1 (en) * | 2002-03-15 | 2008-03-06 | Erickson Christopher M | Rocket engine power cycle |
| US8250853B1 (en) * | 2011-02-16 | 2012-08-28 | Florida Turbine Technologies, Inc. | Hybrid expander cycle rocket engine |
| CN104794966A (en) * | 2015-04-22 | 2015-07-22 | 上海理工大学 | Organic Rankine cycle system experimental device |
| CN211116307U (en) * | 2019-09-29 | 2020-07-28 | 上海坤释流体科技有限公司 | Rankine cycle rocket engine system |
-
2019
- 2019-09-29 CN CN201910947552.6A patent/CN110566368A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080053064A1 (en) * | 2002-03-15 | 2008-03-06 | Erickson Christopher M | Rocket engine power cycle |
| US8250853B1 (en) * | 2011-02-16 | 2012-08-28 | Florida Turbine Technologies, Inc. | Hybrid expander cycle rocket engine |
| CN104794966A (en) * | 2015-04-22 | 2015-07-22 | 上海理工大学 | Organic Rankine cycle system experimental device |
| CN211116307U (en) * | 2019-09-29 | 2020-07-28 | 上海坤释流体科技有限公司 | Rankine cycle rocket engine system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116029586A (en) * | 2022-12-13 | 2023-04-28 | 中国人民解放军63921部队 | Task-oriented carrier rocket system contribution rate calculation method |
| CN116029586B (en) * | 2022-12-13 | 2024-04-23 | 中国人民解放军63921部队 | Task-oriented carrier rocket system contribution rate calculation method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3293373B1 (en) | Supercritical carbon dioxide power generation system | |
| US9494078B2 (en) | Prime mover with recovered energy driven compression of the working fluid | |
| US20110252796A1 (en) | Ultra-high-efficiency engines and corresponding thermodynamic system | |
| EP3314096B1 (en) | Power system and method for producing useful power from heat provided by a heat source | |
| US4051680A (en) | Modified rankine cycle engine apparatus | |
| CN111561363B (en) | Transcritical CO 2 Heat pump energy storage system driven by power generation | |
| WO2010151560A1 (en) | System and method for managing thermal issues in one or more industrial processes | |
| CA2882290A1 (en) | Supercritical working fluid circuit with a turbo pump and a start pump in series configuration | |
| WO2000071944A1 (en) | A semi self sustaining thermo-volumetric motor | |
| CN111102025B (en) | Supercritical carbon dioxide circulating power generation system suitable for regenerative cooling detonation combustion chamber | |
| CN112368464A (en) | System for recovering waste heat and method thereof | |
| CN211116307U (en) | Rankine cycle rocket engine system | |
| CN110566368A (en) | Rankine cycle rocket engine system | |
| CN107762579A (en) | A kind of compound backheat adiabatic compression air energy storage systems of high temperature | |
| CN112049692B (en) | 10 kW-level space nuclear energy closed Brayton cycle thermoelectric conversion system | |
| CN211573739U (en) | Compressed air energy storage system | |
| CN115234318B (en) | Carbon dioxide energy storage system matched with thermal power plant deep peak regulation and control method thereof | |
| US8156726B1 (en) | Semiclosed Brayton cycle power system with direct combustion heat transfer | |
| CN112282962B (en) | Waste heat recovery organic Rankine cycle system for replacing cylinder liner water of internal combustion engine by mixed working medium | |
| CN212803401U (en) | Airplane waste heat recovery device | |
| CN110905765B (en) | Compressed air energy storage system for efficiently utilizing low-grade heat energy and coupling gas turbine | |
| CN112303960A (en) | Cold power engine | |
| CN113217133A (en) | Method for improving heat efficiency of steam engine by cyclic working | |
| CN107288759B (en) | A kind of the external-burning air generation plants and method for transformation of split axle | |
| RU2447311C2 (en) | Operation mode and design of jet propulsion motor (versions) |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |