Regenerative recuperated combined cycle aeroengine system based on kerosene steam reforming

Abstract

The present application relates to the technical field of engine, and provides a regenerative heat recovery combined cycle aero-engine system based on kerosene water vapor reforming, which comprises a gas generation unit, a steam generator, a gas-liquid separation unit, a mixer and a reforming unit; the gas generation unit is connected with the steam generator, and the steam generator is connected with the mixer; the steam generator is also connected with the gas-liquid separation unit, and the gas-liquid separation unit is used for heat exchange with the gas to condense water vapor in the gas into liquid, and separate the liquid; the mixer is filled with liquid phase kerosene, the liquid phase kerosene and superheated steam form mixed gas, the mixer is connected with the reforming unit, and the reforming unit is connected with the gas generation unit. The regenerative heat recovery combined cycle aero-engine system based on kerosene water vapor reforming maximizes the waste heat recovery capacity of condensed water through multi-path and multi-mode efficient coupling, and realizes the efficient cooling of the physical and chemical double-dimensional regenerative heat recovery and the hot end components of the engine.

Description

Technical Field

[0001] The present invention relates to the technical field of engines, and in particular to a regenerative heat recovery combined cycle aviation engine system based on kerosene steam reforming. Background Art

[0002] Traditional civil aviation power systems are typically designed based on a single Brayton cycle architecture. However, this approach has significant limitations in terms of fuel energy efficiency. First, the Brayton cycle is limited by the efficiency of the Carnot cycle, and its thermal efficiency is proportional to the temperature difference between the heat source and the cold source. However, due to the temperature resistance of the flame tube and turbine materials, it is difficult to further increase the gas temperature, making it difficult for the overall system to continue to increase the thermal efficiency limit. On the other hand, although the traditional Brayton system is suitable for utilizing high-temperature heat sources, the efficiency of utilizing the medium and low-temperature waste heat contained in the exhaust is very low, resulting in a large amount of waste heat being directly discharged with the gas and wasted.

[0003] Medium-temperature heat source cycles, such as the steam Rankine cycle, are ideal for aircraft gas turbine bottoming cycles. Using water as the working fluid, they extract waste heat from the exhaust gases of the Brayton cycle turbine. This heat is then reused through steam turbine power generation or water re-injection into the combustion chamber, improving the overall thermal efficiency of the combined cycle. Existing aircraft gas turbine combined cycle architectures are mostly based on a semi-closed steam Rankine cycle design, utilizing combustion products from the core engine exhaust to recycle condensed water as the working fluid for the Rankine cycle. However, existing aircraft engine systems fail to fully utilize the thermal management value of condensed water as a high heat sink. For example, cooling the combustor liner and high-pressure turbine guide vanes relies on compressed air from the high-pressure compressor. This compressed air does not participate in combustion, and its compression consumes additional compressor power, resulting in exergy losses. Furthermore, heat from low-temperature heat sources, such as cooling heat exchangers, is not recovered and reused, further wasting energy. Summary of the Invention

[0004] The present invention provides a regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming, which is used to solve the defect in the prior art that the thermal management potential caused by the high heat sink of the core engine exhaust condensate is not fully utilized.

[0005] The present invention provides a regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming, comprising: a gas generation unit, a steam generator, a gas-liquid separation unit, a mixer and a reforming unit; the gas generation unit is used to compress and burn air to generate gas, the gas generation unit is connected to the steam generator to use the gas to heat the circulating working medium in the steam generator into superheated steam, the steam generator is connected to the mixer to pass the superheated steam into the mixer; the steam generator is also connected to the gas-liquid separation unit to pass the gas into the gas-liquid separation unit, and the gas-liquid separation unit is used to perform heat exchange with the gas. So that the water vapor in the fuel gas is condensed into liquid, and the liquid is separated. The separated liquid enters the steam generator after heat exchange in the fuel gas generation unit; the mixer is filled with liquid kerosene, and the liquid kerosene evaporates into gaseous kerosene using the heat of the superheated steam. The gaseous kerosene is mixed with the superheated steam to form a mixed gas. The mixer is connected to the reforming unit, and the mixed gas undergoes a reforming reaction in the reforming unit. The heat of the mixed gas is absorbed during the reforming reaction to reduce the temperature of the mixed gas. The reforming unit is connected to the fuel gas generation unit, and the cooled mixed gas enters the fuel gas generation unit to cool the fuel gas generation unit and participate in combustion.

[0006] According to a regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming provided by the present invention, the gas generation unit includes: a first compression mechanism, a first heat exchanger, a second compression mechanism and a combustion chamber connected in sequence; the combustion chamber is connected to the steam generator, and the reforming unit is connected to the second compression mechanism and the combustion chamber.

[0007] According to a regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming provided by the present invention, the first compression mechanism includes: a first compressor and a first turbine, the first compressor is coaxially connected to the first turbine, and the first turbine rotates under the drive of the fuel gas to drive the first compressor to rotate.

[0008] According to a regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming provided by the present invention, the second compression mechanism includes: a second compressor and a second turbine, the second compressor is connected to the second turbine, the second turbine rotates under the drive of the fuel gas to drive the second compressor to rotate, and the second turbine is connected to the reforming unit.

[0009] According to a regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming provided by the present invention, the reforming unit includes a first reforming reactor, the first reforming reactor is arranged in the second turbine, and the two ends of the first reforming reactor are respectively connected to the mixer and the flame tube cooling interlayer of the combustion chamber.

[0010] According to a regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming provided by the present invention, the reforming unit also includes: a second reforming reactor and a third reforming reactor; the two ends of the second reforming reactor are respectively connected to the first reforming reactor and the flame tube cooling interlayer of the combustion chamber, and the two ends of the third reforming reactor are respectively connected to the flame tube cooling interlayer of the combustion chamber and the combustion chamber.

[0011] According to a regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming provided by the present invention, the gas-liquid separation unit includes: a second heat exchanger and a gas-liquid separator, the two ends of the second heat exchanger are respectively connected to the steam generator and the gas-liquid separator, and the gas-liquid separator is connected to the first heat exchanger.

[0012] According to the present invention, a regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming is provided, which also includes: a liquid storage tank and a first pump, the liquid storage tank is connected to the gas-liquid separator, the first pump is connected to the liquid storage tank, and the first pump is used to pump liquid to electrical equipment to cool the electrical equipment, and the cooled liquid enters the first heat exchanger.

[0013] According to the present invention, a regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming is provided, which also includes: a third turbine, a generator, a motor and a fan, wherein the third turbine is connected to the gas generation unit; the third turbine is connected to the generator, the generator is connected to the motor, and the motor is connected to the fan.

[0014] A regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming provided by the present invention further includes: a fuel tank and a second pump, wherein the fuel tank is connected to the mixer via the second pump.

[0015] The regenerative heat recovery combined cycle aviation engine system based on kerosene steam reforming provided by the present invention takes gas condensate as the core thermal management working medium, and by providing a steam generator and a gas-liquid separation unit, the water vapor in the gas is condensed into condensate, and the gas generating unit is cooled; by providing a reforming unit, the temperature of the mixed gas is reduced by utilizing the principle of heat absorption of the reforming reaction, so that the mixed gas cools the gas generating unit, and through multi-path and multi-mode efficient coupling, the waste heat recovery capacity of the condensate is maximized. After the gas generating unit is regeneratively cooled, the mixed gas carrying the recovered energy is reinjected to participate in combustion, thereby realizing regenerative heat recovery in both physical and chemical dimensions and achieving the purpose of cascade recovery and utilization of energy. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the present invention or the prior art, a brief introduction is given below to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0017] Figure 1 The diagram is a schematic structural diagram of a regenerative heat recovery combined cycle aero-engine system based on kerosene steam reforming provided by the present invention.

[0018] Reference numerals:

[0019] 11. First compressor; 12. First heat exchanger; 13. Second compressor; 14. Combustion chamber; 15. First turbine; 16. Second turbine; 20. Steam generator; 31. Second heat exchanger; 32. Gas-liquid separator; 40. Mixer; 51. First reforming reactor; 52. Second reforming reactor; 53. Third reforming reactor; 61. Liquid storage tank; 62. First pump; 63. Electrical equipment; 71. Third turbine; 72. Generator; 73. Motor; 74. Fan; 81. Fuel tank; 82. Second pump; 100. Air intake channel; 141. Flame tube cooling interlayer. DETAILED DESCRIPTION

[0020] To make the objectives, technical solutions, and advantages of the present invention more clear, the technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0021] The following combination Figure 1The present invention describes a regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming.

[0022] like Figure 1 As shown, in an embodiment of the present invention, a regenerative heat-recovery combined cycle aircraft engine system based on kerosene steam reforming includes: a gas generation unit, a steam generator 20, a gas-liquid separation unit, a mixer 40, and a reforming unit. The gas generation unit is used to compress and combust air to generate gas. The gas generation unit is connected to the steam generator 20. High-temperature gas enters the steam generator 20 as a heat source for steam generation, heating and evaporating the circulating working fluid within the steam generator 20 to produce superheated steam, which then enters the mixer 40. The steam generator 20 is also connected to the gas-liquid separation unit. The gas, which has absorbed heat, enters the gas-liquid separation unit and exchanges heat with the air in the gas-liquid separation unit, lowering the gas temperature to below the condensation temperature. The water vapor in the gas condenses into condensed water. The two-phase exhaust gas containing liquid water undergoes gas-liquid separation in the gas-liquid separation unit. The separated liquid enters the gas generation unit, absorbs heat, and then enters the steam generator 20. In this embodiment of the present invention, the steam generator 20 includes a tube side and a shell side, with condensed water and gas flowing in the tube side and shell side, respectively.

[0023] The mixer 40 is filled with liquid kerosene, which is atomized and sprayed into the superheated steam and evaporated into gaseous kerosene. The gaseous kerosene and the superheated steam are fully mixed in the mixer 40 to form a mixed gas of gaseous fuel oil and water vapor. The mixed gas enters the reforming unit to undergo a reforming reaction. During the reforming reaction, a large amount of heat from the mixed gas is absorbed, which reduces the temperature of the mixed gas. In this process, the heat absorbed by the reforming reaction is converted into additional chemical energy of the mixed gas. The cooled mixed gas enters the gas generating unit to cool the gas generating unit, and then participates in combustion to produce high-temperature gas.

[0024] The regenerative heat recovery combined cycle aviation engine system based on kerosene steam reforming provided by the embodiment of the present invention takes gas condensate as the core thermal management working medium. By setting up a steam generator and a gas-liquid separation unit, the water vapor in the gas is condensed into condensate, and the gas generation unit is cooled; by setting up a reforming unit, the principle of heat absorption of the reforming reaction is utilized to reduce the temperature of the mixed gas, so that the mixed gas cools the gas generation unit. Through multi-path and multi-mode efficient coupling, the waste heat recovery capacity of the condensate is maximized. After cooling the gas generation unit, the mixed gas participates in combustion again, realizing regenerative heat recovery in both physical and chemical dimensions, and achieving cascade recovery and utilization of energy.

[0025] like Figure 1As shown, in an embodiment of the present invention, the gas generation unit includes: a first gas compression mechanism, a first heat exchanger 12, a second gas compression mechanism, and a combustion chamber 14 connected in sequence. The combustion chamber 14 is connected to a steam generator 20, and the reforming unit is connected to the second gas compression mechanism and the combustion chamber 14.

[0026] Specifically, the gas enters the core engine from the internal duct of the engine. The air is first compressed by the first compressor mechanism, and then enters the first heat exchanger 12. After heat exchange with the circulating condensed water in the first heat exchanger 12, the temperature of the air is reduced, thereby reducing the exergy loss in the subsequent compression process. The air then enters the second compressor mechanism for secondary compression to become high-pressure gas, and then enters the combustion chamber 14 to burn and produce high-temperature combustion gas. The high-temperature combustion gas enters the steam generator 20, heats and evaporates the condensed water in the steam generator 20 to obtain superheated steam. When the reforming reaction occurs in the reforming unit, the heat of the mixed gas is absorbed, which reduces the temperature of the mixed gas. The mixed gas enters the second compressor mechanism to cool the second compressor mechanism. Afterwards, the mixed gas enters the flame tube cooling interlayer 141 of the combustion chamber 14 to cool the flame tube cooling interlayer 141, thereby ensuring that the flame tube wall temperature is lower than the material allowable temperature.

[0027] like Figure 1 As shown, in the embodiment of the present invention, the first compression mechanism includes: a first compressor 11 and a first turbine 15, and the first compressor 11 is coaxially connected to the first turbine 15. The second compression mechanism includes: a second compressor 13 and a second turbine 16, and the second compressor 13 is coaxially connected to the second turbine 16.

[0028] After being compressed by the first compressor 11, the air enters the first heat exchanger 12, where it exchanges heat with the condensed water within the first heat exchanger 12, lowering the air temperature and, in turn, reducing exergy losses during the subsequent compression process. During this process, the condensed water is heated, reducing the heat exchange load on the subsequent steam generator 20. The air then enters the second compressor 13 for further pressurization before entering the combustion chamber 14 for combustion, generating high-temperature combustion gas. The high-temperature combustion gas then enters the first turbine 15 and the second turbine 16, where its internal energy is converted into mechanical energy through expansion work. This drives the first and second turbines 15, 16, and in turn, drives the first and second compressors 11, 13.

[0029] Furthermore, the regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming also includes: a third turbine 71, a generator 72, a motor 73, and a fan 74. An air intake duct 100 is provided outside the aircraft engine system, and a fan 74 is provided inside the aircraft engine system. Air enters the aircraft engine system through the air intake duct 100. Under the action of the fan 74, the air is divided into two airflows. One airflow enters the outer duct, flows through the gas-liquid separation unit, is heated in the gas-liquid separation unit, and is ejected to directly generate thrust; the other airflow enters the first compressor 11 through the inner duct. The high-temperature combustion gas generated during combustion enters the third turbine 71, driving the third turbine 71 to rotate. The third turbine 71 is connected to the generator 72, which converts mechanical energy into electrical energy. The generator 72 supplies power to the motor 73, which drives the fan 74.

[0030] like Figure 1 As shown, in an embodiment of the present invention, the gas-liquid separation unit includes: a second heat exchanger 31 and a gas-liquid separator 32, the two ends of the second heat exchanger 31 are respectively connected to the steam generator 20 and the gas-liquid separator 32, and the gas-liquid separator 32 is connected to the first heat exchanger 12.

[0031] Specifically, the high-temperature combustion gas enters the steam generator 20, heating and evaporating the condensed water in the steam generator 20 into superheated steam. The superheated steam then enters the mixer 40. The gas then enters the second heat exchanger 31, where it undergoes heat exchange with the bypass air. This lowers the gas temperature to below the condensation temperature, condensing the water vapor in the gas to form condensed water. Simultaneously, the bypass air temperature rises, increasing the air volume flow rate and generating additional thrust. In the second heat exchanger 31, the water content in the gas gradually condenses. The two-phase exhaust gas containing liquid water separates the liquid condensed water in the gas-liquid separator 32. The condensed water then enters the first heat exchanger 12 as a circulating working fluid, recovering some of the heat from the first compressor 11 to raise the condensed water temperature and reduce the heat exchange load on the steam generator 20.

[0032] Furthermore, as described above, air enters the aircraft engine system through the air inlet passage 100. Under the action of the fan 74, the air is divided into two air flows. One air flow enters the outer duct, is heated by the second heat exchanger 31, and is ejected to directly generate thrust; the combustion gas flows through the steam generator 20 and enters the second heat exchanger 31 again to exchange heat with the outer duct air. The temperature of the outer duct air increases, the air volume flow rate increases, the jet speed increases, and additional thrust is generated.

[0033] Furthermore, the regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming further includes a liquid storage tank 61 and a first pump 62. Liquid condensed water separated by the gas-liquid separator 32 enters the liquid storage tank 61 and is pumped to the electrical equipment 63 by the first pump 62 to cool the electrical equipment 63. The condensed water then enters the first heat exchanger 12. In this embodiment, the electrical equipment 63 primarily includes heat-prone devices such as batteries, motors, and electronic control systems.

[0034] In this embodiment, the condensed water heat sink follows the principle of cascaded utilization of cooling capacity, i.e., matching the temperatures of the cold and heat sources. The circulating condensed water is first used to cool the electrical equipment 63 operating at a lower temperature, absorbing waste heat and then heating up. It then enters the first heat exchanger 12 to recover some of the heat from the compressed air at the outlet of the first compressor 11. By lowering the air temperature, the power consumption of the second compressor 13 is reduced. The further heated circulating condensed water enters the steam generator 20, where it utilizes its latent heat of vaporization and heat capacity to recover waste heat from the core engine fuel gas.

[0035] like Figure 1 As shown, in an embodiment of the present invention, the regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming further includes: a fuel tank 81 and a second pump 82. The fuel tank 81 stores liquid fuel, which is pumped to the mixer 40 by the second pump 82 and evenly sprayed into the superheated steam in the form of fuel liquid mist. The fuel is vaporized by the high temperature of the superheated steam and is fully mixed with the superheated steam in a certain proportion to generate a gaseous fuel / water vapor mixture.

[0036] like Figure 1 As shown, in an embodiment of the present invention, the reforming unit includes a first reforming reactor 51, which is arranged in the second turbine 16, and the two ends of the first reforming reactor 51 are respectively connected to the mixer 40 and the flame tube cooling layer 141 of the combustion chamber 14.

[0037] Specifically, the gaseous fuel / steam mixture enters the first reforming reactor 51, located within the guide vanes of the second turbine 16. While cooling the guide vanes of the second turbine 16, the mixture utilizes the heat generated to drive the kerosene steam reforming reaction. It then cools the flame tube cooling layer 141 of the combustion chamber 14. In the prior art, a portion of the gas compressed by the second compressor 13 is used as cooling gas to cool the guide vanes of the second turbine 16. This cooling gas does not participate in combustion in the combustion chamber, but is compressed by the first and second compressors 11, 13, resulting in exergy losses in the first and second compressors 11, 13. In this embodiment, the gas compressed by the first and second compressors 11, 13 is fully utilized for combustion, thus avoiding exergy losses.

[0038] Furthermore, the reforming unit further includes a second reforming reactor 52 and a third reforming reactor 53. The two ends of the second reforming reactor 52 are respectively connected to the first reforming reactor 51 and the flame tube cooling interlayer 141 of the combustion chamber 14, and the two ends of the third reforming reactor 53 are respectively connected to the flame tube cooling interlayer 141 of the combustion chamber 14 and the combustion chamber 14.

[0039] Specifically, the fuel that undergoes preliminary reforming in the first reforming reactor 51 enters the second reforming reactor 52, where its residual heat further propels the reforming reaction. The heat absorbed by the reforming reaction lowers the temperature of the reformed fuel mixture, providing an additional heat sink for cooling the flame tube cooling layer 141 of the combustion chamber 14. The reformed fuel mixture then enters the flame tube cooling layer 141 of the combustion chamber, cooling it. The reformed fuel mixture then enters the third reforming reactor 53, further propeling the reforming reaction until it reaches its upper limit, ultimately producing a hydrogen-rich gaseous fuel mixture (H₂, CO, CO₂, water, small hydrocarbons, etc.). This hydrogen-rich gaseous fuel mixture is thoroughly mixed with high-pressure air at the head of the combustion chamber 14, utilizing humidified gas-phase combustion to mitigate issues such as nozzle coking and soot emissions. The resulting high-temperature combustion gas then enters the various turbines for expansion and power generation, completing the cycle.

[0040] The regenerative heat recovery combined cycle aero-engine system based on kerosene steam reforming provided by the embodiment of the present invention fully utilizes the hot end components of the turbine as a heat source, converts low-energy grade thermal energy into high-energy grade chemical energy, and reduces the exergy loss generated at the combustion end from the source; uses the core engine gas condensate as the core thermal management working fluid, and maximizes the waste heat recovery capacity through multi-path and multi-mode efficient coupling between cold and heat sources; by using the waste heat for fuel reforming and steam heating and then reinjecting it into the combustion chamber, physical and chemical dual-dimensional regenerative heat recovery is realized, achieving cascade recovery and utilization of energy; after fuel reforming, the complex kerosene liquid mist combustion process is converted into gas-phase fuel humidified combustion, which increases the air / fuel mixing speed and helps to suppress combustion hot spots. Possible soot emissions are basically eliminated. Hot spot suppression and the addition of water vapor also help to reduce nitrogen oxide emissions. Water vapor carries the recovered energy and is injected back into the combustion chamber through the reforming structure, which greatly increases the mass flow rate and heat capacity of the gas, and significantly improves the working capacity of the gas. The physical and chemical dual heat sinks of the water vapor and fuel mixture are used to efficiently cool the turbine guide vanes and the combustion chamber flame tube, so that the system no longer relies on high-pressure compressor bleed air as cooling air, which greatly reduces the compression work demand of the compressor. The physical and chemical heat recovery capacity of water is fully tapped, and the entire combined cycle system is efficiently connected in series with a single bottom circulation working fluid, thereby improving the system integration. Through the cascade recovery of waste heat, efficient cold and heat interaction is achieved, effectively improving the thermal efficiency of the entire machine.

[0041] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming, characterized in that: include: Gas generation unit, steam generator, gas-liquid separation unit, mixer and reforming unit; The gas generation unit is used to compress and burn air to generate gas. The gas generation unit is connected to the steam generator to use the gas to heat the circulating working medium in the steam generator into superheated steam. The steam generator is connected to the mixer to pass the superheated steam into the mixer. The steam generator is also connected to the gas-liquid separation unit so that the gas is passed into the gas-liquid separation unit. The gas-liquid separation unit is used to perform heat exchange with the gas to condense the water vapor in the gas into liquid and separate the liquid. The separated liquid enters the steam generator after heat exchange in the gas generation unit. The mixer is filled with liquid kerosene, which evaporates into gaseous kerosene using the heat of superheated steam. The gaseous kerosene is mixed with the superheated steam to form a mixed gas. The mixer is connected to the reforming unit, and the mixed gas undergoes a reforming reaction in the reforming unit. During the reforming reaction, the heat of the mixed gas is absorbed by chemical reactions to reduce the temperature of the mixed gas. The reforming unit is connected to the gas generation unit, and the cooled mixed gas enters the gas generation unit to cool the gas generation unit and participate in combustion.

2. The regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming according to claim 1, characterized in that: The gas generation unit comprises: a first gas compression mechanism, a first heat exchanger, a second gas compression mechanism and a combustion chamber connected in sequence; The combustion chamber is connected to the steam generator, and the reforming unit is connected to the second compression mechanism and the combustion chamber.

3. The regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming according to claim 2, characterized in that: The first compression mechanism includes: a first compressor and a first turbine. The first compressor is coaxially connected to the first turbine. The first turbine rotates under the drive of the gas to drive the first compressor to rotate.

4. The regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming according to claim 3, characterized in that: The second compression mechanism includes: a second compressor and a second turbine. The second compressor is connected to the second turbine. The second turbine rotates under the drive of the fuel gas to drive the second compressor to rotate. The second turbine is connected to the reforming unit.

5. The regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming according to claim 4, characterized in that: The reforming unit includes a first reforming reactor, which is arranged in the second turbine. Both ends of the first reforming reactor are respectively connected to the mixer and the flame tube cooling interlayer of the combustion chamber.

6. The regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming according to claim 5, characterized in that: The reforming unit further comprises: a second reforming reactor and a third reforming reactor; The two ends of the second reforming reactor are respectively connected to the first reforming reactor and the flame tube cooling interlayer of the combustion chamber, and the two ends of the third reforming reactor are respectively connected to the flame tube cooling interlayer of the combustion chamber and the combustion chamber.

7. The regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming according to claim 2, characterized in that: The gas-liquid separation unit includes: a second heat exchanger and a gas-liquid separator. Both ends of the second heat exchanger are connected to the steam generator and the gas-liquid separator respectively. The gas-liquid separator is connected to the first heat exchanger.

8. The regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming according to claim 7, characterized in that: Also includes: A liquid storage tank and a first pump, wherein the liquid storage tank is connected to the gas-liquid separator, and the first pump is connected to the liquid storage tank. The first pump is used to pump liquid to the electrical equipment to cool the electrical equipment, and the cooled liquid enters the first heat exchanger.

9. The regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming according to claim 1, characterized in that: Also includes: a third turbine, a generator, a motor and a fan, wherein the third turbine is connected to the gas generation unit; The third turbine is connected to the generator, the generator is connected to the motor, and the motor is connected to the wind turbine.

10. The regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming according to claim 1, characterized in that: Also includes: A fuel tank and a second pump, wherein the fuel tank is connected to the mixer via the second pump.

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