Regeneration and regenerative combined cycle aero-engine system based on kerosene steam reforming

Abstract

The invention relates to the technical field of engines, and provides a kerosene steam reforming-based regeneration and heat regeneration combined cycle aero-engine system which comprises a fuel gas generation unit, a steam generator, a gas-liquid separation unit, a mixer and a reforming unit, the fuel gas generating unit is connected with the steam generator, and the steam generator is connected with the mixer; the steam generator is further connected with the gas-liquid separation unit, and the gas-liquid separation unit is used for carrying out heat exchange with the fuel gas, so that water vapor in the fuel gas is condensed into liquid, and the liquid is separated out; liquid-phase kerosene is injected into the mixer, the liquid-phase kerosene and the superheated steam form mixed gas, the mixer is connected with the reforming unit, and the reforming unit is connected with the fuel gas generation unit. According to the regeneration and heat regeneration combined cycle aero-engine system based on kerosene steam reforming, through multi-path and multi-mode efficient coupling, the waste heat recovery capacity of condensate water is maximized, and physicochemical two-dimensional regeneration and heat regeneration and efficient cooling of engine hot end components are achieved.

Description

Technical Field

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

[0002] Traditional civil aviation power systems are usually 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 limitations of the flame tube and turbine material temperature resistance, the gas temperature is difficult to further increase, making it difficult for the overall system to continue to increase the upper limit of thermal efficiency; on the other hand, although the traditional Brayton system is suitable for utilizing high-temperature heat sources, the utilization efficiency of 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] The medium-temperature heat source cycle represented by the steam Rankine cycle is an ideal bottom cycle for aviation gas turbines. It can use water as the working fluid to extract the waste heat in the combustion gas after the Brayton cycle turbine, and then reuse the recovered heat energy through steam turbine work or water injection into the combustion chamber, thereby improving the overall thermal efficiency of the combined cycle. The existing aviation gas turbine combined cycle architecture is mostly based on the semi-closed steam Rankine cycle design, which uses the combustion products in the core engine exhaust and recycles the condensed water as the working fluid of the Rankine cycle. However, the existing aviation engine system has not fully utilized the thermal management value brought by the high heat sink of condensed water. For example, when cooling the flame tube of the combustion chamber and the guide vane of the high-pressure turbine, it relies on the compressed air of the high-pressure compressor for cooling. This part of the compressed air does not participate in the combustion work, and its compression brings additional compressor compression power consumption, resulting in exergy loss; for example, the heat of low-temperature heat sources such as cooling heat exchangers is not recovered and reused, resulting in further waste of 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 exhaust condensate of the core engine 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, 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 generating unit; the mixer is filled with liquid kerosene, and the liquid kerosene evaporates into gaseous kerosene by 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 generating unit, and the cooled mixed gas enters the fuel gas generating unit to cool the fuel gas generating 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 air compression mechanism, a first heat exchanger, a second air 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 air 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] A regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming provided by the present invention 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, 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] A regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming provided by the present invention also includes: a third turbine, a generator, a motor and a fan, 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 also includes: a fuel tank and a second pump, and the fuel tank is connected to the mixer through the second pump.

[0015] The regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming provided by the present invention takes fuel gas condensate as the core thermal management working fluid, and by providing a steam generator and a gas-liquid separation unit, the water vapor in the fuel gas is condensed into condensate, and the fuel gas generating unit is cooled; by providing a reforming unit, the temperature of the mixed gas is reduced by utilizing the heat absorption principle of the reforming reaction, so that the mixed gas cools the fuel gas generating unit, and through multi-path and multi-mode efficient coupling, the waste heat recovery capacity of the condensate is maximized. After the fuel 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 step-by-step 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, the following briefly introduces 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 creative work.

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

[0018] Reference numerals: 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 passage; 141. Flame tube cooling interlayer. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0020] Combine the following Figure 1 The invention describes a regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming.

[0021] 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 burn air to generate gas. The gas generation unit is connected to the steam generator 20. The high-temperature gas enters the steam generator 20 as a steam generation heat source, heats and evaporates the circulating working medium in the steam generator 20 to obtain superheated steam, and the superheated steam enters the mixer 40. The steam generator 20 is also connected to the gas-liquid separation unit. The gas that has absorbed heat enters the gas-liquid separation unit and performs heat exchange with the air in the gas-liquid separation unit to reduce the temperature of the gas to below the condensation temperature. The water vapor in the gas is condensed into condensed water. The two-phase exhaust gas containing liquid water is separated into gas and liquid in the gas-liquid separation unit. The separated liquid enters the gas generation unit and enters the steam generator 20 after absorbing heat. In an embodiment of the present invention, the steam generator 20 includes a tube side and a shell side, and condensed water and gas flow in the tube side and the shell side, respectively.

[0022] 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, causing the temperature of the mixed gas to decrease. 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 generate high-temperature fuel gas.

[0023] The regenerative heat recovery combined cycle aircraft engine system based on kerosene steam reforming provided by the embodiment of the present invention takes fuel gas condensed water as the core thermal management working fluid, and condenses water vapor in the fuel gas into condensed water by providing a steam generator and a gas-liquid separation unit, and cools the fuel gas generating unit; by providing a reforming unit, the temperature of the mixed gas is reduced by utilizing the heat absorption principle of the reforming reaction, so that the mixed gas cools the fuel gas generating unit, and through multi-path and multi-mode efficient coupling, the waste heat recovery capacity of the condensed water is maximized. After cooling the fuel gas generating unit, the mixed gas participates in combustion again, realizing regenerative heat recovery in both physical and chemical dimensions, and achieving step-by-step recovery and utilization of energy.

[0024] like Figure 1 As 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 the steam generator 20, and the reforming unit is connected to the second gas compression mechanism and the combustion chamber 14.

[0025] 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, and heats and evaporates the condensed water in the steam generator 20 to obtain superheated steam. When the reforming unit undergoes a reforming reaction, it absorbs the heat of the mixed gas, which reduces the temperature of the mixed gas. The mixed gas enters the second compressor mechanism to cool the second compressor mechanism. After that, 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.

[0026] 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.

[0027] After being compressed by the first compressor 11, the air enters the first heat exchanger 12 and exchanges heat with the condensed water in the first heat exchanger 12 to reduce the temperature of the air, thereby reducing the exergy loss in the subsequent compression process. In this process, the condensed water is heated to reduce the heat exchange load of the subsequent steam generator 20. After that, the air enters the second compressor 13 for further pressurization, and then enters the combustion chamber 14 for combustion to generate high-temperature combustion gas. The high-temperature combustion gas enters the first turbine 15 and the second turbine 16 in turn, and converts its internal energy into mechanical energy through expansion work, driving the first turbine 15 and the second turbine 16 to rotate, thereby driving the first compressor 11 and the second compressor 13 to rotate.

[0028] 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 channel 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 channel 100. Under the action of the fan 74, the air is divided into two air flows. One air flow enters the outer duct, flows through the gas-liquid separation unit, is heated in the gas-liquid separation unit and then ejected to directly generate thrust; the other air flow enters the first compressor 11 through the inner duct. The high-temperature combustion gas generated during combustion enters the third turbine 71 to drive the third turbine 71 to rotate. The third turbine 71 is connected to the generator 72 to convert mechanical energy into electrical energy. The generator 72 supplies power to the motor 73, and the motor 73 drives the fan 74 to operate.

[0029] 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, both 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.

[0030] Specifically, the high-temperature gas generated by combustion enters the steam generator 20, heats and evaporates the condensed water in the steam generator 20 into superheated steam, and the superheated steam enters the mixer 40. The gas enters the second heat exchanger 31, exchanges heat with the outer duct air, and the gas temperature is reduced to below the condensation temperature, condensing the water vapor in the gas to form condensed water. At the same time, the outer duct air temperature increases, the air volume flow rate increases, and additional thrust is generated. In the second heat exchanger 31, the water in the gas is gradually condensed, and the two-phase exhaust gas containing liquid water separates the liquid condensed water in the gas-liquid separator 32. The condensed water enters the first heat exchanger 12 as a circulating working fluid, recovering part of the heat of the first compressor 11 to increase the temperature of the condensed water and reduce the heat exchange load of the steam generator 20.

[0031] Further, according to the foregoing, air enters the aircraft engine system through the air intake 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 outer duct air temperature increases, the air volume flow rate increases, the jet speed increases, and additional thrust is generated.

[0032] 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. The 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. Then, the condensed water enters the first heat exchanger 12. In this embodiment, the electrical equipment 63 mainly refers to: devices that are prone to heat, such as batteries, motors, and electronic control systems.

[0033] In this embodiment, the use of the heat sink of the condensed water follows the principle of cascade utilization of cold, that is, matching the temperature of the cold and heat sources. The circulating condensed water is first used to cool the electrical equipment 63 with a lower operating temperature, absorbs waste heat and then heats up, and then enters the first heat exchanger 12 to recover part of the heat in 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 circulating condensed water after further heating enters the steam generator 20, and uses the latent heat of vaporization and heat capacity to recover the waste heat in the core engine fuel gas.

[0034] 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 also includes: a fuel tank 81 and a second pump 82. The fuel tank 81 stores liquid fuel, and the liquid fuel is pumped to the mixer 40 by the second pump 82, and is evenly sprayed into the superheated steam in the form of fuel liquid mist. The fuel is gasified by relying on 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 mixed gas.

[0035] like Figure 1 As shown, in an embodiment of the present invention, the reforming unit includes a first reforming reactor 51, which is disposed in the second turbine 16, and both ends of the first reforming reactor 51 are respectively connected to the mixer 40 and the flame tube cooling interlayer 141 of the combustion chamber 14.

[0036] Specifically, the gaseous fuel / water vapor mixed gas enters the first reforming reactor 51 arranged inside the guide vane of the second turbine 16. The mixed gas cools the guide vane of the second turbine 16 while using the heat obtained to drive the kerosene steam reforming reaction, and then cools the flame tube cooling interlayer 141 of the combustion chamber 14. In the prior art, part of the gas compressed by the second compressor 13 needs to be used as cooling gas to cool the guide vane of the second turbine 16. The cooling gas does not participate in the combustion in the combustion chamber, but needs to be compressed by the first compressor 11 and the second compressor 13, resulting in exergy loss of the first compressor 11 and the second compressor 13. In this embodiment, the gas compressed by the first compressor 11 and the second compressor 13 can all participate in the combustion, avoiding the generation of exergy loss.

[0037] 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.

[0038] Specifically, the fuel that has undergone preliminary reforming in the first reforming reactor 51 enters the second reforming reactor 52, and uses the waste heat it carries to further promote the reforming reaction process. The reforming reaction absorbs heat and reduces 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 enters the flame tube cooling layer 141 of the combustion chamber to cool the flame tube cooling layer 141. After that, the reformed fuel mixture enters the third reforming reactor 53, further promoting the reforming reaction process, reaching the upper limit of the reaction process, and finally obtaining a hydrogen-rich gas phase fuel mixture (H 2 ,CO,CO 2, water, small molecular hydrocarbons, etc.). The hydrogen-rich gas phase fuel mixture is fully mixed with the high-pressure air at the head of the combustion chamber 14, and the problems of nozzle coking and combustion soot emission are avoided by humidified gas phase combustion. The high-temperature combustion gas generated by the combustion further enters each turbine to expand and do work, completing the entire cycle.

[0039] The regenerative heat recovery combined cycle aeroengine system based on kerosene steam reforming provided by the embodiment of the present invention makes full use of the hot end components of the turbine as the 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; takes the core engine fuel 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; uses the waste heat for fuel reforming and steam heating and then injects it back into the combustion chamber, realizes physical and chemical dual-dimensional regenerative heat recovery, and achieves the 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, greatly increasing the mass flow rate and heat capacity of the fuel gas, and significantly improving the working capacity of the fuel 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, greatly reducing 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 whole machine.

[0040] 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 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 medium in the steam generator into superheated steam, and 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 so as 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 generating unit, and the cooled mixed gas enters the gas generating unit to cool the gas generating 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 gas 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 driving 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, and 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 comprises a first reforming reactor, which is arranged in the second turbine, and two 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 comprises: a second heat exchanger and a gas-liquid separator, 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.

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 fan.

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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