CN113882920A - Open type CO2semi-Brayton cooling and power generation system - Google Patents
Open type CO2semi-Brayton cooling and power generation system Download PDFInfo
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- CN113882920A CN113882920A CN202111075888.1A CN202111075888A CN113882920A CN 113882920 A CN113882920 A CN 113882920A CN 202111075888 A CN202111075888 A CN 202111075888A CN 113882920 A CN113882920 A CN 113882920A
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- 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
- F01K25/103—Carbon dioxide
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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- 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
- F01K19/00—Regenerating or otherwise treating steam exhausted from steam engine plant
- F01K19/02—Regenerating by compression
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- Combustion & Propulsion (AREA)
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- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The invention discloses an open CO2A semi-Brayton cooling and power generation system comprising CO2The system comprises a storage tank, a micro-channel heat exchanger, an expander and a power supply module. By CO2The storage tank provides high-pressure and low-temperature CO in a subcritical region to the system2(ii) a Transfer of aerodynamic heat to CO through a microchannel heat exchanger thermally coupled to a high temperature wall2Cooling is realized; passing the supercritical CO through an expander2Performing an expansion to produce work output; the output work of the expander is converted into electric energy by the electric power supply module for supply. The CO is2Absorbing heat from the high-temperature wall surface for expansion work, thereby realizing thermal protection and facing the aircraftProviding a supply of electrical energy. The invention is used for cooling the high-temperature wall surface caused by the aerodynamic heat effect on the hypersonic aerocraft, and utilizes the aerodynamic heat to generate electricity, thereby solving the problems of insufficient thermal protection and electric energy supply of the aerocraft.
Description
Technical Field
The invention relates to the technical field of wall surface thermal protectionIn particular to an open CO2A semi-brayton cooling and power generation system.
Background
In the field of thermal protection technology, due to the action of strong compression and friction, a severe pneumatic heating effect can be generated on the wall surface, and the high temperature of the wall surface can seriously affect the operation of the system. Among the thermal protection technologies for wall surfaces, a closed brayton cycle system is one of the main active cooling technologies at present. The closed Brayton cycle comprises four processes of an isentropic compression process, an isobaric heat absorption process, an isentropic expansion process and an isobaric heat release process, and working fluid is in a supercritical region in the four processes, which puts higher requirements on the design and energy coupling of a system, and the cooling capacity of the closed Brayton cycle is required to be further improved. Meanwhile, the closed Brayton system has a plurality of operating components and complex pipelines, so the system has a large volume. In addition, the isobaric heat release process of the closed Brayton system requires an environment to additionally provide a cold source for continuously cooling the circulating working medium of the system. In the circulating working medium, CO2Has the characteristic of drastic physical property change in a near critical zone, and the utilization of CO is considered from the aim of active cooling2The physical property characteristic of the transcritical process is used for designing a new operation condition of the Brayton system, so that the cooling capacity is improved, the flow of the system is simplified, and the volume of the system is reduced.
In the flying process of the aircraft, due to the action of strong compression and friction, a severe pneumatic heating effect can be generated, the total incoming flow temperature is rapidly increased, and a plurality of wall surfaces of the aircraft are in a severe high-temperature environment. As the aircraft flight mach number increases, for example, at mach 5, the temperature of the incoming flow at the aircraft head will reach above 1000K, while the temperature of the engine inlet and combustion chambers will exceed more than 3000K. The existing passive thermal protection is difficult to meet the thermal protection requirement of the existing hypersonic aircraft, and a more efficient active cooling technology needs to be developed. Meanwhile, the hypersonic aircraft has limited internal space and strict limitation on the volume of an active cooling system. On the other hand, with the development of hypersonic aircraft, the electrical demand of its onboard equipment is rapidly increasing. In order to meet the power requirement of a large aircraft during long-term flight, the improvement of the power supply capacity of the aircraft is imperative.
Disclosure of Invention
The invention aims to provide an open CO aiming at the defects of the prior art2And the semi-Brayton cooling and power generation system performs active cooling and expansion work power generation. The invention aims to make full use of CO2The characteristic of physical property change realizes the isobaric heat absorption process of the transcritical working condition, improves the cooling capacity of the system, and the system flow is an open flow, so the system flow is called a semi-Brayton process, the isobaric heat release and isentropic compression process of a closed Brayton system are abandoned, the energy coupling problem and the system complexity of the system are simplified, and the system volume is reduced.
The purpose of the invention is realized by the following technical scheme: open type CO2A semi-Brayton cooling and power generation system comprising CO2The system comprises a storage tank, a micro-channel heat exchanger, an expander, a pressure reducing valve, an exhaust channel and a generator; the CO is2Storage tank storing CO in subcritical state2At a temperature lower than CO2Critical temperature of (2) and pressure higher than CO2The working medium of the expander is supercritical CO2(ii) a The CO is2The storage tank is connected with the inlet of the micro-channel heat exchanger; the micro-channel heat exchanger is fixedly embedded in the wall surface of the device to be cooled and forms an integrated structure with the wall surface of the device to be cooled; subcritical state of CO in heat exchanger2Is heated to a supercritical state, and the outlet of the micro-channel heat exchanger is connected with the inlet of an expander for supercritical CO2Do work by expansion; the generator is coaxially connected with the expander, converts the output work of the expander into electric energy and outputs the electric energy to the storage battery; the outlet of the expansion machine is connected with a pressure reducing valve, and CO in a supercritical state2The pressure reducing and temperature reducing process is completed in a pressure reducing valve, the pressure reducing valve is connected with an exhaust channel, and CO after pressure reduction and temperature reduction is discharged2。
Further, the device wall surface needing cooling comprises an aircraft head surface or an aircraft engine air inlet channel wall surface; the wall surface of the device is heated by airflow in the flying process of the aircraft to generate a pneumatic heating effect; the heat of the wall surface is taken away by the heat exchange process of the micro-channel heat exchanger, the temperature of the wall surface is reduced, and the purpose of cooling is achieved.
Further, the expander is a positive displacement expander, including a piston expander and a scroll expander.
Further, the CO is2A throttle valve is arranged at the outlet of the storage tank when the CO is discharged2The temperature in the storage tank is not lower than CO2At critical temperature of (2), CO needs to be increased2Pressure in the tank, CO2CO discharged from the storage tank2The temperature and the pressure are reduced through the throttle valve, and the temperature and the pressure conditions required by the semi-Brayton process are achieved.
The invention has the beneficial effects that:
1. the invention provides an open CO2A semi-Brayton cooling and power generation system using CO2The active cooling is carried out to the high temperature wall that needs carry out the cooling to half brayton process, solves the problem that current passive thermal protection technique can't satisfy higher heat load.
2. The isobaric heat absorption process of the semi-Brayton process provided by the invention adopts CO2Compared with the cooling efficiency and the cooling capacity of closed Brayton cycle, the transcritical working condition is improved. Compared with the traditional closed Brayton cycle, the cooling efficiency of the semi-Brayton process provided by the invention is improved by more than 22%, and the unit mass of CO2The cooling capacity of the cooling system is improved by 40.9 percent, and the unit volume of CO2The cooling capacity of (2) is improved by 15.7%.
3. The invention provides an open CO2Half brayton cooling and power generation system compares closed brayton system, and its expander entry working medium's pressure is higher, has improved the output work of expander, also can improve the generating efficiency of system simultaneously.
4. The open CO proposed by the invention2The semi-Brayton system does not need a compressor, a cooler and a cold source environment, simplifies the energy coupling problem of the system, reduces the volume of the system and improves the operation reliability of the system.
Drawings
In order to more clearly illustrate the embodiments of the present invention, reference will now be made briefly to the embodiments or to the accompanying drawings that are needed in the description of the prior art. It is obvious that the drawings in the following description are some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 shows CO in the present invention2A graph of thermal conductivity change in the near critical region;
FIG. 2 shows CO in the present invention2A specific constant pressure heat capacity change diagram in a near critical zone;
FIG. 3 shows CO in the present invention2A schematic temperature entropy diagram of a semi-brayton open process; wherein (1) - (2) are isobaric endothermic processes; (2) - (3) is an isentropic expansion process; (3) - (4) is a throttling, cooling and depressurizing process; (0) and (1) is an isenthalpic throttling process. (1 ') - (2') is an isobaric endothermic process; (2 ') - (3') is an isentropic expansion process; (3 ') - (4') is an isobaric exothermic process; (4 ') - (1') is an isentropic compression process.
FIG. 4 is a schematic flow diagram of the system of the present invention;
in the figure, 1-CO2The system comprises a storage tank, a 2-microchannel heat exchanger, a 3-high-temperature wall surface, a 4-expander, a 5-pressure reducing valve, a 6-exhaust channel, a 7-power supply module, an 8-generator, a 9-storage battery, a 10-booster circuit and an 11-throttle valve.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
CO2The critical temperature of (A) is about 304K and the critical pressure is about 7.38 MPa. CO22The change of the thermal conductivity in the near critical region is shown in FIG. 1, and the change is characterized by CO below the critical temperature2The thermal conductivity of the heat exchanger is extremely high, the thermal conductivity is rapidly reduced near the critical temperature, and the thermal conductivity of the high-temperature section is lower. At the same time, CO2Increases with increasing pressure. The higher the heat conductivity coefficient is, the higher the heat exchange efficiency in the heat exchange process is. CO22In the isobaric heat absorption process of the microchannel heat exchanger 2, the high heat conductivity coefficient represents that the cooling efficiency is higher when the microchannel heat exchanger cools the high-temperature wall surface 3. The starting point temperature of the traditional closed Brayton cycle medium-pressure heat absorption process is higher than the critical temperature, and the average heat conductivity coefficient is lower, so that CO in the medium-pressure heat absorption process is reduced2Increasing the temperature of CO2The pressure of (2) can improve the heat conductivity coefficient of the active cooling process, namely, the cooling efficiency is improved.
CO2The change in the specific constant pressure heat capacity in the near-critical region is characterized by a large specific constant pressure heat capacity at a temperature lower than the critical temperature and a significantly reduced specific constant pressure heat capacity in the high-temperature region, as shown in FIG. 2. The higher the pressure, the smaller the magnitude of the change in heat capacity from the constant pressure. In addition, in the low-temperature section, the higher the pressure, the smaller the specific heat capacity; and in the high-temperature section, the higher the pressure is, the higher the specific heat capacity is. In the low temperature section, due to CO2The specific pressure heat capacity is large, the heat exchange with high-temperature incoming flow can keep larger heat exchange temperature difference, and the cooling efficiency can be improved, so that CO in the isobaric heat absorption process is reduced2The temperature of (2) can improve the heat exchange temperature difference in the active cooling process, namely, the cooling efficiency is improved. On the other hand, pressWhen the force is low, the specific pressure heat capacity fluctuation is large, the temperature matching process in the micro-channel heat exchanger 2 is not facilitated, and CO is generated at a high-temperature section2Has lower specific pressure heat capacity as a whole, and comprehensively reduces CO2Increasing the temperature of CO during isobaric endotherm2The pressure of the heat exchanger is beneficial to increasing the heat exchange temperature difference, namely, the cooling efficiency is improved.
As shown in FIG. 4, the present invention provides an open CO2A semi-Brayton cooling and power generation system comprising CO2The system comprises a storage tank 1, a micro-channel heat exchanger 2, an expander 4, a pressure reducing valve 5, an exhaust channel 6 and a generator 8; the CO is2The storage tank 1 stores CO in a subcritical state2At a temperature lower than CO2Critical temperature of (2) and pressure higher than CO2The working medium of the expander 4 is supercritical CO2(ii) a The CO is2The storage tank 1 is connected with an inlet of the micro-channel heat exchanger 2; for removing heat from microchannel heat exchangers, in which the CO is in subcritical state2Is heated to a supercritical state, and the outlet of the micro-channel heat exchanger 2 is connected with the inlet of an expander for supercritical CO2Do work by expansion; the generator 8 is coaxially connected with the expander 4, converts the output work of the expander 4 into electric energy and outputs the electric energy to the storage battery 9, and the storage battery 9 can supply electric energy for some parts in devices such as aircrafts and the like; the outlet of the expansion machine is connected with a pressure reducing valve 5, and CO in a supercritical state2The pressure reducing and temperature reducing process is completed in the pressure reducing valve 5, the pressure reducing valve 5 is connected with the exhaust channel 6, and CO after pressure reducing and temperature reducing is discharged2. Compared with a closed Brayton cycle system, the whole process is an open process, and CO is adopted2The state generates transcritical change, so the system flow is called a semi-Brayton process.
The micro-channel heat exchanger 2 is fixedly embedded on the surface of the head of the hypersonic aircraft or the wall surface of an air inlet channel of an engine of the aircraft and forms an integrated structure with the wall surface; the wall surface is heated by airflow in the flying process to generate a pneumatic heating effect; the heat of the wall surface is taken away by the heat exchange process of the micro-channel heat exchanger 2, the temperature of the wall surface is reduced, and the purpose of cooling is achieved. The combination of the expander 4, the generator 8 and the storage battery 9 is used for supplying power to the aircraft, so that the cooling efficiency of the active cooling system of the hypersonic aircraft can be improved, and the power supply capacity of the aircraft can be improved.
Example 1:
the invention provides an open CO2The semi-Brayton cooling and power generation system is used for cooling the surface of the head of the hypersonic aircraft or an air inlet channel of an engine of the aircraft; the temperature entropy diagram is shown in the processes of red lines (1) to (4) in fig. 3: CO22The starting point of the isobaric endothermic process is (1) in a subcritical region; CO22The gas-driven heat of the high-temperature wall surface is absorbed and then reaches the point (2), and the point (2) is positioned at CO2A supercritical region; subsequent CO2The isentropic expansion process from the point (2) to the point (3) is carried out, and CO outputs expansion work to the outside and simultaneously2Temperature and pressure drop of; finally, CO2And (4) performing an isenthalpic throttling process from (3) to (4), further reducing the temperature and the pressure, and discharging the temperature and the pressure into an exhaust passage 6 to finish a working process. The blue line in fig. 3 shows a schematic diagram of the temperature entropy of a conventional closed brayton system, which mainly differs from the following: the (1') point temperature of the isobaric endothermic process is higher than (1) point and higher than the critical temperature; the working pressure of the isobaric endothermic processes (1 ') to (2') is lower than that of the processes (1) to (2) of the semi-brayton process; CO22CO of closed Brayton system after expansion work is done to the (3') point state2The refrigerant is required to enter a cooler to finish the isobaric cooling process from (3 ') to (4'), and finally enters a compressor to finish the isentropic compression process from (4 ') to (1'), thereby finishing one working process.
The invention provides an open CO2The system flow chart of the semi-Brayton cooling and power generation system is shown in FIG. 4: CO22CO in the tank 12Corresponding to point (1) in FIG. 3, the CO2The tank 1 is in a cryogenic environment in the aircraft cabin, which is capable of cooling the temperature in the CO2 tank to below CO2Critical temperature of said CO2The pressure in the tank 1 is higher than CO2Critical pressure. The CO is2The storage tank 1 is connected with the micro-channel heat exchanger 2, and the micro-channel heat exchanger 2 is coupled with the high-temperature wall surface 3And is used for taking away the pneumatic heat of high-temperature incoming flow. CO22In the microchannel heat exchanger 2, the medium-pressure heat absorption process goes through a transcritical process, and a state of high temperature and high pressure is achieved, which corresponds to the point (2) in fig. 3. The outlet of the micro-channel heat exchanger 2 is connected with an expander 4, and high-temperature and high-pressure CO is obtained2And the mixture enters the expansion machine 4 to be expanded to do work. 4 the expansion machine is connected with the pressure reducing valve 5 to expand and work the CO2Corresponding to the point (3) in fig. 3, the CO discharged from the outlet of the expansion machine 4 enters the pressure reducing valve 5 to complete the isenthalpic throttling process, and the temperature and pressure of the CO are reduced2I.e., (4) in fig. 3, is discharged into the exhaust passage 6, completing one operation. The expander 4 is connected to a power generation supply module 7. The power supply module 7 includes a generator 8, a battery 9, and a booster circuit 10, and the generator 8 is coaxially connected to the expander 4 and converts the output work of the expander 4 into electric energy. The generator 8 is connected with a storage battery 9, and the storage battery 9 is used for storing the electric energy generated by the generator 8, because the generated electric energy has the problems of power fluctuation or intermittent output due to the discontinuity and instability of high-temperature incoming flow pneumatic heat. The storage battery 9 is connected with a booster circuit 10, and when the hypersonic aircraft has a power supply replenishment demand, the booster circuit 10 is used for boosting and supplying the electric energy stored in the storage battery according to the power supply demand. Preferably, the expander is a positive displacement expander, such as a piston expander or a scroll expander.
Example 2:
when the low-temperature environment cannot be provided in the aircraft cabin, the CO cannot be satisfied2CO when the storage temperature in the storage tank 1 is lower than the critical temperature2The storage temperature of (2) is higher than the starting temperature of the isobaric endothermic process in the half brayton process due to the environmental limitation, and in this embodiment, the storage temperature is set to 35 ℃. To meet the low temperature conditions required for the semi-Brayton process of the present invention, in this embodiment, an open CO is used2The semi-brayton cooling and power generation system adds a throttling process that can achieve lower temperatures by reducing a portion of the pressure. The invention provides an open CO2The temperature entropy diagram of the semi-Brayton cooling and power generation system is shown as red line in FIG. 3(0) The process from (4) to (4) is as follows: CO22Is (0) point, corresponds to a temperature above the critical temperature and a pressure above the critical pressure, and is above the (1) point pressure, CO2In the supercritical region; by isenthalpic throttling process, CO2The pressure and temperature of (2) are rapidly reduced, the temperature can be reduced to the temperature corresponding to the point (1), namely, the point (0) is subjected to isenthalpic throttling to the point (1), CO2In the subcritical region; throttled CO2Absorbing the aerodynamic heat of the high-temperature wall surface, completing the isobaric heat absorption process and reaching the point (2) of CO2In the supercritical region; the subsequent procedure was the same as in example 1.
The invention provides an open CO2The flow chart of the semi-Brayton cooling and power generation system is shown in FIG. 4: when the environment in the aircraft cabin does not have a low-temperature environment, CO2When the state in the storage tank 1 cannot reach the state required by the point (1) in FIG. 3, CO is increased2Method of internal pressure of tank 1, when said CO is present2The state in the storage tank 1 corresponds to the point (0) in FIG. 3, i.e., the CO2The temperature in the storage tank 1 is higher than CO2Critical temperature, pressure above CO2Critical pressure and above the (1) point corresponding pressure. The CO is2A throttle valve 11 and CO are arranged on a pipeline connecting the storage tank 1 and the micro-channel heat exchanger 22CO discharged from the storage tank 12After passing through the throttle valve 11, the temperature and pressure are reduced, causing CO2After the temperature of (2) reaches the temperature corresponding to the point (1) in fig. 3, the temperature is discharged and enters a microchannel heat exchanger 2, and the subsequent flow is the same as that in example 1.
The above-described embodiments are intended to illustrate rather than to limit the invention, and any modifications and variations of the present invention are within the spirit of the invention and the scope of the appended claims.
Claims (4)
1. Open type CO2Half brayton cooling and power generation system, its characterized in that: comprising CO2The system comprises a storage tank, a micro-channel heat exchanger, an expander, a pressure reducing valve, an exhaust channel and a generator; the CO is2Storage tank storing CO in subcritical state2At a temperature lower than CO2Critical temperature of (2) and pressure higher than CO2The working medium of the expander is supercritical CO2(ii) a The CO is2The storage tank is connected with the inlet of the micro-channel heat exchanger; the micro-channel heat exchanger is fixedly embedded in the wall surface of the device to be cooled and forms an integrated structure with the wall surface of the device to be cooled; subcritical state of CO in heat exchanger2Is heated to a supercritical state, and the outlet of the micro-channel heat exchanger is connected with the inlet of an expander for supercritical CO2Do work by expansion; the generator is coaxially connected with the expander, converts the output work of the expander into electric energy and outputs the electric energy to the storage battery; the outlet of the expansion machine is connected with a pressure reducing valve, and CO in a supercritical state2The pressure reducing and temperature reducing process is completed in a pressure reducing valve, the pressure reducing valve is connected with an exhaust channel, and CO after pressure reduction and temperature reduction is discharged2。
2. An open CO according to claim 12Half brayton cooling and power generation system, its characterized in that: the device wall surface needing cooling comprises an aircraft head surface or an aircraft engine air inlet channel wall surface; the wall surface of the device is heated by airflow in the flying process of the aircraft to generate a pneumatic heating effect; the heat of the wall surface is taken away by the heat exchange process of the micro-channel heat exchanger, the temperature of the wall surface is reduced, and the purpose of cooling is achieved.
3. An open CO according to claim 12Half brayton cooling and power generation system, its characterized in that: the expander is a positive displacement expander and comprises a piston expander and a vortex expander.
4. An open CO according to claim 12Half brayton cooling and power generation system, its characterized in that: the CO is2A throttle valve is arranged at the outlet of the storage tank when the CO is discharged2The temperature in the storage tank is not lower than CO2At critical temperature of (2), CO needs to be increased2Pressure in the tank, CO2CO discharged from the storage tank2The temperature and the pressure are reduced through the throttle valve, and the temperature and the pressure conditions required by the semi-Brayton process are achieved.
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2021
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| US20070175222A1 (en) * | 2006-01-31 | 2007-08-02 | United Technologies Corporation | Multipurpose gas generator ramjet/scramjet cold start system |
| CN106640242A (en) * | 2016-09-19 | 2017-05-10 | 清华大学 | Hypersonic flight vehicle engine heat recovery power generation system and control method thereof |
| US20190071995A1 (en) * | 2017-09-01 | 2019-03-07 | Southwest Research Institute | Double Wall Supercritical Carbon Dioxide Turboexpander |
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