Aero-engine system based on wet regeneration regenerative eddy-current hybrid combined cycle

Abstract

The invention relates to the technical field of engines, and provides an aero-engine system based on wet regeneration regenerative eddy-current hybrid combined cycle, which comprises an air compression unit, a solid oxide fuel cell, a combustion chamber and a reforming unit, the gas compression unit is connected with the solid oxide fuel cell, the solid oxide fuel cell is connected with the combustion chamber, and the reforming unit is selectively connected with the solid oxide fuel cell and the combustion chamber; the solid oxide fuel cell is used for converting chemical energy of the hydrogen-rich gas-phase fuel mixture into electric energy through electrochemical reaction, and high-pressure gas and the hydrogen-rich gas-phase fuel mixture which is not completely reacted are combusted in the combustion chamber. According to the aero-engine system based on the wet regeneration regenerative eddy-current hybrid combined cycle, chemical energy is converted into electric energy through the solid oxide fuel cell, the loss generated when the chemical energy is converted into heat energy is remarkably reduced, and the upper limit of Carnot efficiency is broken upwards; unreacted materials carry electrochemical reaction waste heat to enter the combustion chamber to participate in combustion, and the fuel utilization rate is increased.

Description

Technical Field

[0001] The present invention relates to the field of engine technology, and in particular to an aviation engine system based on a wet regeneration heat recovery turbo-electric hybrid combined cycle. Background Art

[0002] High-efficiency aviation propulsion technology is the key to increasing the range of military and civilian aircraft and reducing fuel consumption. Traditional aviation turbines are built around a single Brayton cycle, which mainly uses high-temperature thermal energy from fuel gas to do work, but the low-temperature waste heat from fuel gas is not fully utilized. A large amount of unused heat energy is directly discharged with the exhaust gas, resulting in significant exergy losses. At the same time, the irreversibility of the combustion process, the power consumption of the cooling gas compression of the hot end components, and the loss of the impeller will further lead to exergy losses and affect the thermal efficiency of the entire machine. Therefore, reducing exergy losses is one of the core ideas for future high-efficiency aviation propulsion.

[0003] Solid oxide fuel cells can directly convert the chemical energy contained in the fuel into electrical energy with a higher energy grade. Compared with the method of converting chemical energy into heat energy through direct combustion, the exergy loss in the chemical energy release stage is greatly reduced, which is one of the key ideas for future aviation power technology to break through the efficiency limit of the Carnot cycle. How to combine solid oxide fuel cells with aviation gas engines to form a hybrid combined cycle, which can fully utilize the unreacted fuel and waste heat after the electrochemical reaction to participate in combustion while generating electricity, and then generate high-temperature gas to drive the turbine to further work has become one of the problems that need to be solved in the industry. Summary of the invention

[0004] The present invention provides an aviation engine system based on a wet regeneration heat recovery turbo-electric hybrid combined cycle, which is used to realize efficient waste heat recovery and regenerative cooling of hot end components while realizing a combined cycle formed by combining a solid oxide fuel cell and an aviation gas engine, thereby achieving a leap in the thermal efficiency of the combined cycle.

[0005] The present invention provides an aviation engine system based on a wet regeneration recuperative turbo-electric hybrid combined cycle, comprising: a compressor unit, a solid oxide fuel cell, a combustion chamber and a reforming unit; the compressor unit is connected to the solid oxide fuel cell, the solid oxide fuel cell is connected to the combustion chamber, and the reforming unit is selectively connected to the solid oxide fuel cell and the combustion chamber; the compressor unit comprises a compressor and a turbine, the compressor is connected to the turbine, the compressor is used to compress air to form high-pressure gas, the reforming unit is used to generate a hydrogen-rich gas-phase fuel mixture by a reforming reaction, the solid oxide fuel cell is used to convert the chemical energy of the hydrogen-rich gas-phase fuel mixture into electrical energy by an electrochemical reaction, the high-pressure gas and the incompletely reacted hydrogen-rich gas-phase fuel mixture are burned in the combustion chamber to generate combustion gas, which drives the turbine to rotate; when the aircraft is in a cruise mode, the reforming unit is connected to the solid oxide fuel cell and the combustion chamber, and when the aircraft is in a take-off mode, a climb mode and an approach mode, the reforming unit is connected to the combustion chamber.

[0006] According to the present invention, an aircraft engine system based on a wet regeneration heat recovery turbo-electric hybrid combined cycle also includes: a steam generator and a mixer; the steam generator is connected to the turbine to utilize the combustion gas generated in the combustion chamber to heat the circulating working 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; liquid kerosene is filled in the mixer, and the liquid kerosene evaporates into gaseous kerosene using the heat of the superheated steam, and the gaseous kerosene and the superheated steam form a mixed gas, and the mixer is connected to the reforming unit, and the mixed gas undergoes a reforming reaction in the reforming unit, and absorbs the heat of the mixed gas during the reforming reaction to reduce the temperature of the mixed gas, and the cooled mixed gas enters the flame tube cooling interlayer of the combustion chamber to cool the flame tube cooling interlayer.

[0007] According to an aircraft engine system based on a wet regeneration heat-recovery turbo-electric hybrid combined cycle provided by the present invention, the compression unit includes: a first compressor, a second compressor, a first turbine, a second turbine and a first heat exchanger; the first compressor is connected to the first turbine, the second compressor is connected to the second turbine, the first compressor, the first heat exchanger and the second compressor are connected in sequence, the second compressor is connected to the combustion chamber, and the second turbine is connected to the reforming unit.

[0008] According to an aircraft engine system based on a wet regeneration and recuperation turbo-electric hybrid combined cycle 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 layer of the combustion chamber.

[0009] According to an aircraft engine system based on a wet regeneration heat recovery turbo-electric hybrid combined cycle 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, the first end of the third reforming reactor is connected to the flame tube cooling interlayer of the combustion chamber, and the second end of the third reforming reactor is selectively connected to the solid oxide fuel cell and the combustion chamber.

[0010] According to the present invention, an aircraft engine system based on a wet regeneration heat recovery turbo-electric hybrid combined cycle also includes: a gas-liquid separation unit and a cooling unit, the gas-liquid separation unit is connected to the steam generator, and the cooling unit is connected to the gas-liquid separation unit; the gas-liquid separation unit is used to exchange heat with the fuel gas to condense the water vapor in the fuel gas into liquid, and separate the liquid, and the liquid cools the electrical equipment under the action of the cooling unit and then flows into the first heat exchanger.

[0011] According to an aircraft engine system based on a wet regeneration heat recovery turbo-electric hybrid combined cycle 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 cooling unit.

[0012] According to an aircraft engine system based on a wet regeneration heat recovery turbo-electric hybrid combined cycle provided by the present invention, the cooling unit 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] According to the present invention, an aircraft engine system based on a wet regeneration heat recovery turbo-electric hybrid combined cycle also includes: a third turbine, a generator, a motor and a fan, the third turbine is connected to the combustion chamber; the third turbine is connected to the generator, the generator is connected to the motor, and the motor is connected to the fan.

[0014] An aircraft engine system based on a wet regeneration turbo-electric hybrid combined cycle provided by the present invention also includes: a fuel tank and a second pump, wherein the fuel tank is connected to the mixer via the second pump.

[0015] The aircraft engine system based on wet regeneration heat recovery turbo-electric hybrid combined cycle provided by the present invention is provided with a solid oxide fuel cell. When the aircraft is in cruise mode, the solid oxide fuel cell directly converts chemical energy into electrical energy for use by other electrical equipment, significantly reducing the exergy loss when chemical energy is converted into thermal energy, improving energy utilization efficiency, and helping the combined cruise cycle to break through the Carnot efficiency limit; the unreacted materials carry the residual heat of the electrochemical reaction into the combustion chamber to participate in combustion to produce high-temperature combustion gas with work-doing capacity, and further utilize the energy contained in the remaining fuel. . 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 It is a schematic structural diagram of an aero-engine system based on a wet regeneration heat-recovery turbo-electric hybrid combined cycle provided by the present invention.

[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; 90. Solid oxide fuel cell; 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 an aircraft engine system based on a wet regeneration turbo-electric hybrid combined cycle.

[0021] like Figure 1 As shown, in an embodiment of the present invention, an aircraft engine system based on a wet regeneration heat recovery turbo-electric hybrid combined cycle includes: a compressor unit, a solid oxide fuel cell 90, a combustion chamber 14, and a reformer unit. The compressor unit is connected to the solid oxide fuel cell 90, the solid oxide fuel cell 90 is connected to the combustion chamber 14, and the reformer unit is selectively connected to the solid oxide fuel cell 90 and the combustion chamber 14.

[0022] The air compression unit includes a compressor and a turbine, and the compressor is coaxially connected to the turbine. The compressor is used to compress air to form high-pressure gas. The reforming unit is used to generate a hydrogen-rich gas-phase fuel mixture by reforming reaction. The solid oxide fuel cell 90 converts the chemical energy of the hydrogen-rich gas-phase fuel mixture into electrical energy through electrochemical reaction for use by electrical equipment; at the same time, the high-pressure gas and the incompletely reacted hydrogen-rich gas-phase fuel mixture enter the combustion chamber 14 and burn to generate high-temperature combustion gas, which drives the turbine to rotate, and the turbine drives the compressor to rotate. In this embodiment, the hydrogen-rich gas-phase fuel mixture refers to: a mixture of H2, CO, CO2, water and small molecular hydrocarbons. The hydrogen-rich gas-phase fuel mixture flows in different directions when the aircraft is in different modes; since the solid oxide fuel cell 90 has poor dynamic influence characteristics, it is suitable for operating under stable conditions such as cruising to provide high thermal efficiency, and is not suitable for coping with conditions with a large rate of change in operating conditions. Therefore, when the aircraft is in cruising mode, most of the hydrogen-rich gas-phase fuel mixture of the reforming unit is supplied to the solid oxide fuel cell 90, and only a small part is supplied to the combustion chamber 14 for supplementary combustion; when the aircraft is in take-off, climb and approach modes, the hydrogen-rich gas-phase fuel mixture of the reforming unit is all supplied to the combustion chamber 14 for combustion and energy release.

[0023] In this embodiment, the solid oxide fuel cell 90 is combined with the aviation gas engine to form a combined cycle. While generating electricity, the solid oxide fuel cell 90 fully utilizes the unreacted fuel and waste heat after the electrochemical reaction to participate in combustion in the combustion chamber 14, generating high-temperature combustion gas to drive the turbine to work, and the turbine drives the compressor to operate, thereby achieving continuous generation of combustion gas and continuous generation of electricity.

[0024] The aero-engine system based on the wet regeneration heat recovery turbo-electric hybrid combined cycle provided by the embodiment of the present invention, by providing a solid oxide fuel cell, when the aircraft is in cruise mode, the solid oxide fuel cell directly converts chemical energy into electrical energy for use by other electrical equipment, significantly reducing the exergy loss when chemical energy is converted into thermal energy, and breaking through the Carnot efficiency upper limit; the unreacted materials carry the waste heat of the electrochemical reaction into the combustion chamber to participate in the combustion, further improving the fuel utilization rate.

[0025] like Figure 1 As shown, in an embodiment of the present invention, the aircraft engine system based on the wet regeneration heat recovery turbo-electric hybrid combined cycle further includes: a steam generator 20 and a mixer 40. The steam generator 20 is connected to the turbine, and the high-temperature combustion gas generated by the combustion chamber 14 enters the steam generator 20. The high-temperature combustion gas serves as a heat source for steam generation, and heats and evaporates the circulating working fluid in the steam generator 20 to obtain superheated steam, and the superheated steam enters the mixer 40. The mixer 40 is filled with liquid kerosene, which is heated by superheated steam and vaporized to form 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 to generate a hydrogen-rich gaseous fuel mixture. During the reforming reaction, a large amount of heat is absorbed from the mixed gas, which reduces the temperature of the mixed gas. In this process, the heat energy absorbed by the reaction is converted into additional chemical energy of the mixed gas, thereby providing additional chemical heat sinks. It can be understood that the mixed gas here includes both gaseous kerosene and water vapor, and also includes the kerosene water vapor reforming product, that is, a hydrogen-rich gaseous fuel mixture. The mixed gas enters the flame tube cooling interlayer 141 of the flame tube of the combustion chamber 14 to cool the flame tube cooling interlayer 141.

[0026] like Figure 1 As shown, in an embodiment of the present invention, the air compression unit includes: a plurality of compressors and a plurality of turbines, each compressor being connected to a turbine. Specifically, the air compression unit includes: a first compressor 11, a second compressor 13, a first turbine 15, and a second turbine 16. The first compressor 11 is coaxially connected to the first turbine 15, and the second compressor 13 is coaxially connected to the second turbine 16. The air compression unit also includes a first heat exchanger 12, and the first compressor 11, the first heat exchanger 12, the second compressor 13, and the combustion chamber 14 are connected in sequence.

[0027] Specifically, 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 power consumption 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 aircraft engine system based on the wet regeneration heat recovery turbo-electric hybrid combined cycle also includes: a third turbine 71, a generator 72, a motor 73 and a fan 74. An air intake passage 100 is provided outside the aircraft engine system, and a fan 74 is provided inside the aircraft engine system. The 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 of which enters the outer duct; the other enters the first compressor 11 from 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] In an embodiment of the present invention, an aircraft engine system based on a wet regeneration heat recovery turbo-electric hybrid combined cycle further includes: a gas-liquid separation unit and a cooling unit. The gas-liquid separation unit is connected to the steam generator 20, and the cooling unit is connected to the gas-liquid separation unit. The high-temperature combustion gas generated by the combustion chamber 14 passes through multiple turbines and enters the steam generator 20, heating and evaporating the condensed water in the steam generator 20 into superheated steam. After that, the heat-absorbed combustion gas enters the gas-liquid separation unit, exchanges heat with the air in the gas-liquid separation unit, and reduces the temperature of the combustion gas to below the condensation temperature. The water vapor in the combustion gas is condensed into condensed water, and the two-phase exhaust gas containing liquid water is separated into gas and liquid in the gas-liquid separation unit. The condensed water is pumped to the electrical equipment 63 by the cooling unit, and after cooling the electrical equipment 63, it enters the first heat exchanger 12, absorbs part of the heat in the compressed air at the outlet of the first compressor 11, and reduces the compression power consumption of the second compressor 13 by reducing the air temperature.

[0030] Furthermore, 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 connected to the steam generator 20 and the gas-liquid separator 32 respectively, and the gas-liquid separator 32 is connected to the cooling unit.

[0031] 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 is used as a circulating working fluid to cool the electrical equipment 63 under the action of the cooling unit, and then enters the first heat exchanger 12 to recover 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.

[0032] 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, and additional thrust is generated.

[0033] Furthermore, the cooling unit 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.

[0034] 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, 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 purpose of reducing the compression power consumption of the second compressor 13 is achieved. 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.

[0035] The aviation engine system based on the wet regeneration heat recovery turbo-electric hybrid combined cycle 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 increases the proportion of chemical energy directly converted into electrical energy, thereby reducing the exergy loss generated at the combustion end from the source; using the core engine fuel gas condensate as the core thermal management working fluid, the system's waste heat recovery capacity is maximized through multi-path, multi-mode efficient coupling between cold and heat sources.

[0036] 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.

[0037] 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 air) compressed by the second compressor 13 needs to be used as cooling gas to cool the guide vane of the second turbine 16. This part of the cooling gas (compressed air) does not participate in the combustion of the combustion chamber 14, but needs to be compressed by the first compressor 11 and the second compressor 13, resulting in additional compression power consumption of the first compressor 11 and the second compressor 13. In this embodiment, the gas (compressed air) compressed by the first compressor 11 and the second compressor 13 does not need to participate in turbine cooling, and can all participate in combustion, thereby avoiding the additional cooling gas compression power consumption of the compression system and reducing the system exergy loss.

[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, the first end of the third reforming reactor 53 is connected to the flame tube cooling interlayer 141 of the combustion chamber 14, and the second end of the third reforming reactor 53 is selectively connected to the solid oxide fuel cell 90 and the combustion chamber 14.

[0039] 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 heat absorption of the reforming reaction will reduce the temperature of the reformed fuel mixture, providing an additional heat sink for cooling the flame tube cooling interlayer 141 of the combustion chamber 14. The reformed fuel mixture enters the combustion chamber flame tube cooling interlayer 141 to cool the flame tube cooling interlayer 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 high hydrogen-rich gas phase fuel mixture with hydrogen as the main component. When the aircraft is in cruise mode, most of the hydrogen-rich gas phase fuel mixture of the reforming unit is supplied to the solid oxide fuel cell 90, and only a small part is supplied to the combustion chamber 14 to participate in supplementary combustion to meet the turbine cycle temperature requirements; when the aircraft is in take-off, climb and other modes, the hydrogen-rich gas phase fuel mixture generated by the reforming unit is all supplied to the combustion chamber 14 for combustion and energy release. When the hydrogen-rich gas phase fuel mixture enters the combustion chamber 14 to participate in the combustion, the hydrogen-rich gas phase fuel mixture is fully mixed with the high-pressure air at the head of the combustion chamber 14 and burns in a humidified gas phase combustion mode. Compared with the traditional kerosene liquid mist combustion organization, it greatly accelerates the air-fuel mixing speed, can effectively inhibit the generation of combustion hot spots and avoid nozzle coking, and can significantly reduce carbon smoke emissions and nitrogen oxide emissions. The high-temperature and high-humidity combustion gas generated by the combustion further enters each turbine to expand and do work, completing the entire cycle.

[0040] Furthermore, the aircraft engine system based on the wet regeneration heat recovery turbo-electric hybrid combined cycle 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 vaporized 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.

[0041] The aero-engine system based on the wet regeneration heat recovery turbo-electric hybrid combined cycle provided by the embodiment of the present invention obtains the heat recovery cycle core working fluid water by condensing and recovering the exhaust gas from the core engine, and then transports it to various parts of the engine for waste heat recovery for fuel reforming and water vapor heating. Finally, the reformed fuel carrying a large amount of chemical energy and thermal energy is injected back into the fuel cell and the combustion chamber to complete the low exergy loss release of energy, realize physical and chemical dual-dimensional regeneration and heat recovery, and achieve the purpose of cascade recovery and utilization of energy; after fuel reforming, kerosene is converted into hydrogen-rich gas phase fuel suitable for fuel cells, and electricity is efficiently generated by directly converting chemical energy into electrical energy, reducing the exergy loss caused by the conversion of fuel chemical energy into thermal energy, so that the thermal efficiency of the combined cycle system can break through the efficiency limit of the Carnot heat engine. During the combustion process, the complex kerosene mist combustion is transformed into gas phase fuel humidification combustion, which increases the air / fuel mixing speed, helps suppress combustion hot spots, and basically eliminates possible carbon smoke emissions. Hot spot suppression and the addition of water vapor also help reduce nitrogen oxide emissions. The water vapor carries the recovered energy and is injected back into the fuel cell and 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 sink of the water vapor and fuel mixture is used to efficiently cool the turbine guide vanes and the combustion chamber flame tube cooling interlayer, so that the system no longer relies on the high-pressure compressor bleed air as Cooling air greatly reduces the compression work demand of the compressor; the aviation engine system based on the wet regeneration heat recovery turbo-electric hybrid combined cycle provided by the embodiment of the present invention has an integrated chemical reaction core with kerosene-water vapor fuel reforming reaction, solid oxide fuel cell electrochemical reaction, and combustion reaction chemistry. It realizes the reinjection of energy and circulating working fluid while completing the low-exergy loss utilization of fuel chemical energy, fully tapping the physical and chemical heat recovery capacity of water, and efficiently connecting the entire combined cycle system in series with a single bottom circulating 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.

[0042] 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. An aircraft engine system based on a wet regeneration turbo-electric hybrid combined cycle, characterized in that: include: Gas compression unit, solid oxide fuel cell, combustion chamber and reforming unit; The gas compression unit is connected to the solid oxide fuel cell, the solid oxide fuel cell is connected to the combustion chamber, and the reforming unit is selectively connected to the solid oxide fuel cell and the combustion chamber; The air compression unit includes a compressor and a turbine, wherein the compressor is connected to the turbine, the compressor is used to compress air to form high-pressure gas, the reforming unit is used to generate a hydrogen-rich gas-phase fuel mixture by a reforming reaction, the solid oxide fuel cell is used to convert the chemical energy of the hydrogen-rich gas-phase fuel mixture into electrical energy by an electrochemical reaction, and the high-pressure gas and the incompletely reacted hydrogen-rich gas-phase fuel mixture are burned in the combustion chamber to generate combustion gas to drive the turbine to rotate; When the aircraft is in a cruise mode, the reforming unit is connected to the solid oxide fuel cell and the combustion chamber. When the aircraft is in a take-off mode, a climb mode, and an approach mode, the reforming unit is connected to the combustion chamber.

2. The aircraft engine system based on the wet regeneration turbo-electric hybrid combined cycle according to claim 1, characterized in that: Also includes: Steam generators and mixers; The steam generator is connected to the turbine to heat the circulating medium in the steam generator into superheated steam using the gas generated in the combustion chamber, and the steam generator is connected to the mixer to pass the superheated steam into the mixer; The mixer is filled with liquid kerosene, which evaporates into gaseous kerosene using the heat of superheated steam. The gaseous kerosene and the superheated steam 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 cooled mixed gas enters the flame tube cooling interlayer of the combustion chamber to cool the flame tube cooling interlayer.

3. The aircraft engine system based on the wet regeneration turbo-electric hybrid combined cycle according to claim 2 is characterized in that: The air compression unit comprises: a first compressor, a second compressor, a first turbine, a second turbine and a first heat exchanger; The first compressor is connected to the first turbine, the second compressor is connected to the second turbine, the first compressor, the first heat exchanger and the second compressor are connected in sequence, the second compressor is connected to the combustion chamber, and the second turbine is connected to the reforming unit.

4. The aircraft engine system based on wet regeneration and recuperation turbo-electric hybrid combined cycle according to claim 3 is 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.

5. The aircraft engine system based on wet regeneration turbo-electric hybrid combined cycle according to claim 4, 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, the first end of the third reforming reactor is connected to the flame tube cooling interlayer of the combustion chamber, and the second end of the third reforming reactor is selectively connected to the solid oxide fuel cell and the combustion chamber.

6. The aircraft engine system based on wet regeneration turbo-electric hybrid combined cycle according to claim 3, characterized in that: It also includes: a gas-liquid separation unit and a cooling unit, wherein the gas-liquid separation unit is connected to the steam generator, and the cooling unit is connected to 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. After the liquid cools the electrical equipment under the action of the cooling unit, it flows into the first heat exchanger.

7. The aircraft engine system based on wet regeneration turbo-electric hybrid combined cycle according to claim 6, 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 cooling unit.

8. The aircraft engine system based on wet regeneration turbo-electric hybrid combined cycle according to claim 7, characterized in that: The cooling unit 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 the electrical equipment to cool the electrical equipment, and the cooled liquid enters the first heat exchanger.

9. The aircraft engine system based on wet regeneration turbo-electric hybrid combined cycle 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 combustion chamber; 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 aircraft engine system based on wet regeneration turbo-electric hybrid combined cycle according to claim 2, 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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