Aero-engine based on supercritical working medium cycle driving and driving method thereof
By introducing a supercritical working fluid circulation system into the aero-engine, the air compressor is driven to form a closed cycle, which solves the problem of low performance in the existing technology, and achieves improved thermal efficiency, reduced material requirements, and increased thrust-to-weight ratio.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- SHANGHAI GENMAN TECH CO LTD
- Filing Date
- 2024-10-18
- Publication Date
- 2026-04-21
AI Technical Summary
Existing aero engines have low performance, stringent requirements for material selection and precision manufacturing, and turbines consume most of the energy, resulting in low thermal efficiency.
A supercritical working fluid circulation system is adopted, including an air compressor, a heat exchange chamber, and a supercritical working fluid circulation system. The supercritical working fluid flows through the heat exchange chamber and drives the air compressor, forming a closed loop and replacing the turbine function.
It improved the thermal efficiency of aero engines, reduced the requirements for materials, increased the thrust-to-weight ratio, and achieved a leapfrog improvement in performance.
Smart Images
Figure CN121897435A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to an aero-engine driven by a supercritical working fluid cycle and its driving method. Background Technology
[0002] Current aero engines mainly consist of a compressor, turbine, combustion chamber, bypass duct, and nozzle. High-temperature combustion gases in the combustion chamber drive the turbine to rotate at high speed, which in turn drives the compressor to rotate at high speed, compressing air into the combustion chamber and bypass duct. The airflow exits from the nozzle, generating thrust. The turbine, which converts the thermal energy of the high-temperature combustion gases into high-speed rotating mechanical energy, is the "heart" of the aero engine and determines its thrust quality. Furthermore, the higher the temperature of the combustion gases in the combustion chamber, the stronger the turbine's workmanship, and the better the engine's thrust quality. Advanced engines have combustion chamber temperatures reaching 1950℃ and turbine speeds reaching 30,000 RPM. In addition to withstanding extreme high temperatures, they must also withstand enormous centrifugal forces. Therefore, turbines place extremely stringent requirements on materials and precision manufacturing. Because the turbine consumes most of the energy, the exhaust velocity from the nozzle is generally around 300 m / s, but the exhaust temperature is still as high as 600–700℃, resulting in low thermal efficiency and relatively low performance in current aero engines. Summary of the Invention
[0003] The technical problem to be solved by the present invention is to overcome the shortcomings of the existing technology of low performance of aero engines and the stringent requirements for material selection and precision manufacturing, and to provide an aero engine based on supercritical working fluid cycle drive and its driving method.
[0004] The present invention solves the above-mentioned technical problems through the following technical solution:
[0005] An aero-engine driven by a supercritical working fluid cycle is characterized in that the aero-engine includes an air compressor, a heat exchange chamber, and a supercritical working fluid cycle system, wherein a supercritical working fluid is circulating within the supercritical working fluid cycle system, and the supercritical working fluid cycle system is connected to the air compressor and the heat exchange chamber.
[0006] After the supercritical working fluid in the supercritical working fluid circulation system passes through the heat exchange chamber, the supercritical working fluid flows to the air compressor and is used to drive the air compressor to move. The supercritical working fluid in the supercritical working fluid circulation system will circulate through the heat exchange chamber to form a closed supercritical working fluid cycle.
[0007] Preferably, the aero-engine further includes a nozzle; the heat exchange chamber includes a combustion chamber and a cold flow chamber, the combustion chamber and the cold flow chamber being disposed between the air compressor and the nozzle.
[0008] Preferably, the supercritical working fluid circulation system includes a heater, a cooler, and a compressor. The heater is located in the combustion chamber, the cooler is located in the cold flow chamber, the inlet and outlet of the compressor are respectively connected to the cooler and the heater, and the inlet and outlet of the air compressor are respectively connected to the heater and the cooler.
[0009] The supercritical working fluid starts from the compressor, flows sequentially through the heater, the compressor and the cooler, and then flows back to the compressor to complete the closed-loop circulation of the supercritical working fluid.
[0010] A driving method for an aero-engine based on supercritical working fluid cycle drive, characterized in that the driving method for the aero-engine based on supercritical working fluid cycle drive utilizes the aero-engine based on supercritical working fluid cycle drive as described above.
[0011] The driving method includes the following steps:
[0012] The temperature of the supercritical working fluid in the supercritical working fluid circulation system increases after passing through the heat exchange chamber.
[0013] The supercritical working fluid flows to the air compressor and drives the air compressor to move, so that the air compressor can compress air.
[0014] The compressed air enters the heat exchange chamber, and the supercritical working fluid in the supercritical working fluid circulation system will circulate through the heat exchange chamber and its temperature will decrease, so as to form a closed supercritical working fluid circulation.
[0015] Preferably, the aero-engine further includes a nozzle; the heat exchange chamber includes a combustion chamber and a cold flow chamber, the combustion chamber being located in the center of the cold flow chamber and the cold flow chamber being located outside the combustion chamber; the combustion chamber and the cold flow chamber are disposed between the air compressor and the nozzle;
[0016] The compressed air entering the heat exchange chamber specifically includes: a first part of the compressed air entering the heat exchange chamber is burned with fuel in the combustion chamber to produce high-temperature gas, which is used to heat the supercritical working fluid; a second part of the compressed air entering the heat exchange chamber flows through the cold flow chamber and cools the supercritical working fluid, mixes with the high-temperature gas at the inlet of the nozzle, and forms a supersonic jet stream through the nozzle.
[0017] Preferably, the supercritical working fluid circulation system includes a heater, a cooler, and a compressor, wherein the heater is located in the combustion chamber, the inlet and outlet of the compressor are respectively connected to the cooler and the heater, and the inlet and outlet of the air compressor are respectively connected to the heater and the cooler;
[0018] The supercritical working fluid closed-loop cycle specifically includes the following steps:
[0019] S1. The initial state of the supercritical working fluid is low temperature and low pressure state I. The supercritical working fluid passes through the compressor and is compressed so that the state of the supercritical working fluid changes to low temperature and high pressure state II.
[0020] S2. The supercritical working fluid will pass through the heater and be heated so that the state of the supercritical working fluid changes from low temperature and high pressure state II to high temperature and high pressure state III.
[0021] S3. The supercritical working fluid in the high temperature and high pressure III state will pass through the air compressor and be used to drive the air compressor to rotate, so that the state of the supercritical working fluid changes from the high temperature and high pressure III state to the medium temperature and low pressure IV state.
[0022] S4. The supercritical working fluid in the intermediate temperature and low pressure IV state will pass through the cooler, and the state of the supercritical working fluid will change from the intermediate temperature and low pressure IV state to the initial low temperature and low pressure I state.
[0023] Preferably, the temperature of the supercritical working fluid in the high temperature and high pressure III state is below 1200°C.
[0024] Preferably, the heater includes a heat exchanger disposed in the combustion chamber to allow heat exchange between the high-temperature combustion gas and the supercritical working fluid.
[0025] Preferably, the aero-engine further includes a flow control device disposed within the heat exchanger for regulating the flow rate of the supercritical working fluid flowing through the heat exchanger.
[0026] Preferably, the temperature of the supersonic jet stream is below 500°C;
[0027] And / or, the supercritical working fluid is carbon dioxide, helium, or water vapor.
[0028] Based on common knowledge in the field, the above-mentioned preferred conditions can be combined arbitrarily to obtain various preferred embodiments of the present invention.
[0029] The positive and progressive effects of this invention are as follows:
[0030] This invention relates to an aero-engine and its driving method based on supercritical working fluid cycle drive. The supercritical working fluid, heated in a heat exchange chamber, acts on an air compressor, converting its internal energy into mechanical energy. The air compressor then compresses air, which enters the aero-engine's heat exchange chamber for cooling, increasing the compressed air pressure. Simultaneously, the supercritical working fluid, cooled in the heat exchange chamber, flows back to the compressor for pressurization, completing a closed-loop supercritical working fluid cycle. This cycle drives the air compressor, continuously compressing air for the aero-engine's heat exchange chamber. Using this structural design and method, the supercritical working fluid closed-loop system replaces the current engine turbine, improving thermal efficiency. Air compression can be achieved without a turbine, increasing the aero-engine's thrust-to-weight ratio and achieving a significant performance improvement. Attached Figure Description
[0031] Figure 1 This is a schematic diagram of the structure of an aero-engine driven by a supercritical working fluid cycle according to an embodiment of the present invention.
[0032] Explanation of reference numerals in the attached figures:
[0033] Air compressor 1
[0034] Heat exchange chamber 2
[0035] Cold flow chamber 21
[0036] Combustion chamber 22
[0037] Cooler 23
[0038] Heater 24
[0039] Compressor 25
[0040] Supercritical working fluid circulation system 3 Detailed Implementation
[0041] The present invention will be described more clearly and completely below by way of embodiments and in conjunction with the accompanying drawings, but the present invention is not limited to the scope of the embodiments.
[0042] like Figure 1 As shown, this embodiment discloses an aero-engine driven by a supercritical working fluid cycle. The aero-engine driven by a supercritical working fluid cycle includes an air compressor 1, a heat exchange chamber 2, and a supercritical working fluid cycle system 3. The supercritical working fluid cycle system 3 contains a circulating supercritical working fluid and is connected to the air compressor 1 and the heat exchange chamber 2. After the supercritical working fluid flows through the heat exchange chamber 2, it flows to the air compressor 1 and drives the air compressor 1. The supercritical working fluid in the supercritical working fluid cycle system 3 circulates through the heat exchange chamber 2 to form a closed supercritical working fluid cycle.
[0043] In the operation of an aero-engine driven by a supercritical working fluid cycle, the supercritical working fluid in the supercritical working fluid cycle system 3 flows through the heat exchange chamber 2 and is heated. This heat then acts on the air compressor 1, converting the internal energy of the supercritical working fluid into mechanical energy. The air compressor 1 has blades that rotate, compressing air and allowing it to enter the heat exchange chamber 2 of the aero-engine for cooling, thus increasing the pressure of the compressed air. Simultaneously, the supercritical working fluid, after being cooled in the heat exchange chamber 2, flows back for pressurization, completing a closed-loop supercritical working fluid cycle. This cycle then drives the air compressor 1, which continuously compresses air into the heat exchange chamber 2 of the aero-engine. The supercritical working fluid cycle system 3, forming a closed-loop supercritical working fluid cycle, achieves air compression and replaces the function of the current engine turbine, improving thermal efficiency. Because the turbine is eliminated, the thrust-to-weight ratio of the aero-engine increases, achieving a significant leap in aero-engine performance.
[0044] The aero-engine also includes a nozzle; the heat exchange chamber 2 includes a combustion chamber 22 and a cold flow chamber 21, which are located between the air compressor 1 and the nozzle. Specifically, the cold flow chamber 21 is located between the combustion chamber 22 and the air compressor 1, and the combustion chamber 22 is located between the cold flow chamber 21 and the nozzle. At the nozzle inlet, because the high-temperature exhaust gas flowing from the heat exchange chamber 2 avoids the pressure drop caused by passing through the turbine, the air pressure at the inlet of the engine using this design is higher than that at the nozzle inlet of a conventional engine, resulting in a higher supersonic airflow velocity through the nozzle compared to conventional engines. Furthermore, because the engine using this design does not include a turbine, the requirements for material selection and manufacturing processes are significantly reduced.
[0045] The supercritical working fluid circulation system 3 includes a heater 24, a cooler 23, and a compressor 25. The heater 24 is located in the combustion chamber 22, and the cooler 23 is located in the cold flow chamber 21. The inlet and outlet of the compressor 25 are connected to the cooler 23 and the heater 24, respectively. The inlet and outlet of the air compressor 1 are connected to the heater 24 and the cooler 23, respectively. The supercritical working fluid starts from the compressor 25, flows through the heater 24, the compressor 25, and the cooler 23 in sequence, and then flows back to the compressor 25 to complete the supercritical working fluid closed-loop circulation.
[0046] The high-temperature and high-pressure supercritical working fluid in the supercritical working fluid circulation system 3 will be used to drive the air compressor 1. After being cooled and depressurized by the cooler 23, it will be compressed by the compressor 25 to form an ultra-high-pressure supercritical working fluid. The heater 24 is placed in the combustion chamber 22 to convert the heat energy of the gas into the internal energy of the supercritical working fluid, thereby improving the work capacity of the supercritical working fluid for the air compressor 1. The cooler 23 is used to reduce the temperature of the supercritical carbon dioxide, thereby improving the compression efficiency of the compressor 25.
[0047] This embodiment also discloses a driving method for an aero-engine based on supercritical working fluid cycle. This driving method utilizes the supercritical working fluid cycle-driven aero-engine described above. The driving method for the supercritical working fluid cycle-driven aero-engine includes the following steps: the supercritical working fluid in the supercritical working fluid cycle system 3 flows through the heat exchange chamber 2 and its temperature rises; the supercritical working fluid flows to the air compressor 1 and is used to drive the air compressor 1 to move, so that the air compressor 1 can compress air; the compressed air enters the heat exchange chamber 2, and the supercritical working fluid in the supercritical working fluid cycle system 3 will circulate through the heat exchange chamber 2 and its temperature will decrease, so as to form a closed supercritical working fluid cycle.
[0048] After the supercritical working fluid flows through the heater 24 in the heat exchange chamber 2 and its temperature rises, it acts on the air compressor 1, converting the internal energy of the supercritical working fluid into the kinetic energy of the high-speed rotation of the air compressor 1 blades. The blades compress the air and it enters the heat exchange chamber 2 of the aero-engine, where the compressed air pressure increases. Simultaneously, the supercritical working fluid circulates through the cooler 23 in the heat exchange chamber 2, where its temperature decreases, and then it passes through the compressor 25, where its pressure increases, completing the supercritical working fluid closed-loop cycle, which in turn drives the air compressor 1. With the above structural design and method, the supercritical closed-loop system replaces the current engine turbine, enabling compressed air to enter the heat exchange chamber 2 without a turbine, increasing the thrust-to-weight ratio of the aero-engine, and achieving a leapfrog improvement in aero-engine performance.
[0049] In the driving method of an aero-engine based on supercritical working fluid cycle, the compressed air entering the heat exchange chamber 2 specifically includes: a first portion of the compressed air entering the heat exchange chamber 2 is burned with fuel in the combustion chamber 22 to generate high-temperature gas, which is used to heat the supercritical working fluid; a second portion of the compressed air entering the heat exchange chamber 2 flows through the cold flow chamber 21 and cools the supercritical working fluid, then mixes with the high-temperature gas at the nozzle inlet, forming a supersonic jet stream through the nozzle. At the nozzle inlet, because the high-temperature gas flowing out of the heat exchange chamber 2 avoids the pressure drop caused by flowing through the turbine, the air pressure at the inlet of the engine using the above design is higher than that at the nozzle inlet of a conventional engine, thus forming a higher supersonic airflow velocity than a conventional engine. Furthermore, because the engine using the above design does not include a turbine, the requirements for material selection and manufacturing processes are significantly reduced. Preferably, the temperature of the supersonic jet stream can be below 500°C; the reduction in the temperature of the supersonic jet stream improves the thermal efficiency of the aero-engine.
[0050] The supercritical working fluid closed-loop cycle specifically includes the following steps: Step S1, the initial state of the supercritical working fluid is low temperature and low pressure state I. The supercritical working fluid passes through compressor 25 and is compressed to change the state of the supercritical working fluid to low temperature and high pressure state II; Step S2, the supercritical working fluid passes through heater 24 and is heated to change the state of the supercritical working fluid from low temperature and high pressure state II to high temperature and high pressure state III; Step S3, the supercritical working fluid in high temperature and high pressure state III passes through air compressor 1 and is used to drive air compressor 1 to rotate, so that the state of the supercritical working fluid changes from high temperature and high pressure state III to medium temperature and low pressure state IV; Step S4, the supercritical working fluid in medium temperature and low pressure state IV passes through cooler 23, and the state of the supercritical working fluid changes from medium temperature and low pressure state IV to the initial state of low temperature and low pressure state I.
[0051] In the supercritical working fluid circulation system 3, the high-temperature and high-pressure supercritical working fluid drives the air compressor 1. After being cooled and depressurized by the cooler 23, it is then compressed by the compressor 25 to form an ultra-high-pressure supercritical working fluid. The heater 24 is placed in the combustion chamber 22 to convert the thermal energy of the combustion gas into the internal energy of the supercritical working fluid, thereby improving the work capacity of the supercritical working fluid for the air compressor 1. The cooler 23 is used to reduce the temperature of the supercritical working fluid, thereby improving the compression efficiency of the compressor 25. By adopting the above structural design and method arrangement, the high specific heat capacity and high thermal conductivity of the supercritical working fluid are fully utilized to efficiently convert the internal energy of the supercritical working fluid into mechanical energy.
[0052] In this embodiment, the temperature of the supercritical working fluid in the high temperature and high pressure III state is below 1200°C. Controlling the temperature of the supercritical working fluid below 1200°C, which is below a preset threshold, reduces the material requirements for the piping and related equipment used to encapsulate the supercritical working fluid. For example, common stainless steel or copper can be used, thus reducing manufacturing costs.
[0053] The heater 24 includes a heat exchanger located within the combustion chamber 22 to facilitate heat exchange between the high-temperature combustion gas and the supercritical working fluid. The combination of the high-temperature combustion gas and the heat exchanger enables the high-temperature combustion gas to heat the supercritical working fluid, thereby improving the thermal efficiency of the aero-engine.
[0054] Aero engines also include a flow control device, which is located inside the heat exchanger and is used to regulate the flow rate of the supercritical working fluid flowing through the heat exchanger. By regulating the flow rate of the supercritical working fluid through the heat exchanger, the flow control device regulates the temperature of the supercritical working fluid flowing through the heat exchanger, which is convenient for regulation and control and has high safety and stability.
[0055] In this embodiment, the supercritical working fluid is carbon dioxide, and the supercritical carbon dioxide closed-loop cycle specifically includes the following steps: Step S1, the initial state of the supercritical working fluid is low temperature and low pressure state I. The supercritical working fluid passes through compressor 25 and is compressed to change the low temperature and low pressure state I of the supercritical working fluid to low temperature and high pressure state II. At this time, the pressure of the supercritical carbon dioxide is 25 MPa; Step S2, the supercritical working fluid passes through heater 24 and is heated to change the state of the supercritical working fluid from low temperature and high pressure state II to high temperature and high pressure state III. At this time, the pressure of the supercritical carbon dioxide is 25 MPa and the temperature is 600°C; Step S3, the supercritical working fluid in the high temperature and high pressure state III passes through air compressor 1 and is used to drive the air compressor 1 to rotate, so that the state of the supercritical working fluid changes from the high temperature and high pressure state III to the medium temperature and low pressure state IV; Step S4, the supercritical working fluid in the medium temperature and low pressure state IV passes through cooler 23, and the state of the supercritical working fluid changes from the medium temperature and low pressure state IV to the initial low temperature and low pressure state I. At this time, the pressure of the supercritical carbon dioxide is 8 MPa and the temperature is 50°C.
[0056] Due to the superior thermal conductivity of supercritical carbon dioxide, the thermal efficiency of aero-engines will be improved by 10%. By eliminating the turbine, the thrust-to-weight ratio of the aero-engine increases, the exhaust temperature can be controlled below 500℃, and the exhaust velocity can be increased to supersonic speeds exceeding 600m / s, achieving a leapfrog improvement in engine performance.
[0057] Of course, in other embodiments, the supercritical working fluid can also be helium or water vapor. The appropriate working fluid can be flexibly selected to meet the thrust requirements of the aero-engine in actual applications.
[0058] Currently, there are no products that apply supercritical working fluid closed-loop cycle to aero engines to replace engine turbines. This invention patent was first proposed by the inventor and is an original innovation. It will improve the thermal efficiency of aero engines by 10%. Furthermore, due to the elimination of the turbine, the thrust-to-weight ratio of the aero engine will increase, the exhaust temperature of the nozzle can be controlled below 500℃, and the exhaust speed can be increased to supersonic speeds of over 600m / s, achieving a leapfrog improvement in the performance of aero engines.
[0059] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.
Claims
1. An aero-engine driven by a supercritical working fluid cycle, characterized in that, The aero-engine includes an air compressor, a heat exchange chamber, and a supercritical working fluid circulation system. The supercritical working fluid circulation system contains a circulating supercritical working fluid and is connected to the air compressor and the heat exchange chamber. After the supercritical working fluid in the supercritical working fluid circulation system passes through the heat exchange chamber, the supercritical working fluid flows to the air compressor and is used to drive the air compressor to move. The supercritical working fluid in the supercritical working fluid circulation system will circulate through the heat exchange chamber to form a closed supercritical working fluid cycle.
2. The aero-engine based on supercritical working fluid cycle drive as described in claim 1, characterized in that, The aero-engine also includes a nozzle; the heat exchange chamber includes a combustion chamber and a cold flow chamber, which are disposed between the air compressor and the nozzle.
3. The aero-engine based on supercritical working fluid cycle drive as described in claim 2, characterized in that, The supercritical working fluid circulation system includes a heater, a cooler, and a compressor. The heater is located in the combustion chamber, the cooler is located in the cold flow chamber, the inlet and outlet of the compressor are respectively connected to the cooler and the heater, and the inlet and outlet of the air compressor are respectively connected to the heater and the cooler. The supercritical working fluid starts from the compressor, flows sequentially through the heater, the compressor and the cooler, and then flows back to the compressor to complete the closed-loop circulation of the supercritical working fluid.
4. A driving method for an aero-engine based on supercritical working fluid cycle, characterized in that, The driving method of the supercritical working fluid cycle-driven aero-engine utilizes the supercritical working fluid cycle-driven aero-engine as described in any one of claims 1-3. The driving method includes the following steps: The temperature of the supercritical working fluid in the supercritical working fluid circulation system increases after passing through the heat exchange chamber. The supercritical working fluid flows to the air compressor and is used to drive the air compressor to move, so that the air compressor can compress air; The compressed air enters the heat exchange chamber, and the supercritical working fluid in the supercritical working fluid circulation system will circulate through the heat exchange chamber and its temperature will decrease, so as to form a closed supercritical working fluid circulation.
5. The driving method for an aero-engine based on supercritical working fluid cycle as described in claim 4, characterized in that, The aero-engine also includes a nozzle; the heat exchange chamber includes a combustion chamber and a cold flow chamber, with the combustion chamber located in the center of the cold flow chamber and the cold flow chamber located on the outside of the combustion chamber; The combustion chamber and the cold flow chamber are disposed between the air compressor and the nozzle; The compressed air entering the heat exchange chamber specifically includes: a first part of the compressed air entering the heat exchange chamber is burned with fuel oil in the combustion chamber to produce high-temperature gas, which is used to heat the supercritical working fluid; The second portion of the compressed air entering the heat exchange chamber flows through the cold flow chamber and cools the supercritical working fluid. It mixes with the high-temperature combustion gas at the inlet of the nozzle and forms a supersonic jet stream through the nozzle.
6. The driving method for an aero-engine based on supercritical working fluid cycle as described in claim 5, characterized in that, The supercritical working fluid circulation system includes a heater, a cooler, and a compressor. The heater is located in the combustion chamber. The inlet and outlet of the compressor are respectively connected to the cooler and the heater. The inlet and outlet of the air compressor are respectively connected to the heater and the cooler. The supercritical working fluid closed-loop cycle specifically includes the following steps: S1. The initial state of the supercritical working fluid is low temperature and low pressure state I. The supercritical working fluid passes through the compressor and is compressed so that the state of the supercritical working fluid changes to low temperature and high pressure state II. S2. The supercritical working fluid will pass through the heater and be heated so that the state of the supercritical working fluid changes from low temperature and high pressure state II to high temperature and high pressure state III. S3. The supercritical working fluid in the high temperature and high pressure III state will pass through the air compressor and be used to drive the air compressor to rotate, so that the state of the supercritical working fluid changes from the high temperature and high pressure III state to the medium temperature and low pressure IV state. S4. The supercritical working fluid in the intermediate temperature and low pressure IV state will pass through the cooler, and the state of the supercritical working fluid will change from the intermediate temperature and low pressure IV state to the initial low temperature and low pressure I state.
7. The driving method for an aero-engine based on supercritical working fluid cycle as described in claim 6, characterized in that, The temperature of the supercritical working fluid in the high temperature and high pressure III state is below 1200℃.
8. The driving method for an aero-engine based on supercritical working fluid cycle as described in claim 6, characterized in that, The heater includes a heat exchanger disposed in the combustion chamber to allow the high-temperature gas and the supercritical working fluid to exchange heat.
9. The driving method for an aero-engine based on supercritical working fluid cycle as described in claim 8, characterized in that, The aero-engine also includes a flow control device, which is disposed in the heat exchanger and is used to regulate the flow rate of the supercritical working fluid flowing through the heat exchanger.
10. The driving method for an aero-engine based on supercritical working fluid cycle as described in claim 5, characterized in that, The temperature of the supersonic jet stream is below 500°C; And / or, the supercritical working fluid is carbon dioxide, helium, or water vapor.