Aero-engine system based on wet regeneration combined cycle of back-heat electric vortex hybrid

Abstract

The application relates to the technical field of engines and provides an aviation engine system based on a wet regeneration heat regenerative vortex electric hybrid combined cycle, which comprises a compression unit, a solid oxide fuel cell, a combustion chamber and a reforming unit; the 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 a hydrogen-rich gas phase fuel mixture into electric energy through an 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. The aviation engine system based on the wet regeneration heat regenerative vortex electric hybrid combined cycle, the solid oxide fuel cell converts chemical energy into electric energy, significantly reduces the exergy loss when chemical energy is converted into heat energy, and breaks through the upper limit of Carnot efficiency; the unreacted materials carry electrochemical reaction waste heat into the combustion chamber to participate in combustion, and the fuel utilization rate is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of engines, and particularly relates to an aviation engine system based on a wet regeneration heat recovery turbo-electric hybrid combined cycle. BACKGROUND

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

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

[0004] The present application provides an aviation engine system based on a wet regeneration heat recovery turbo-electric hybrid combined cycle, which can realize the combination of solid oxide fuel cells and aviation gas engines to form a combined cycle, and realize efficient waste heat recovery and hot end component regeneration cooling, thereby achieving a leap in the thermal efficiency of the combined cycle.

[0005] The application provides an aero-engine system based on a wet regeneration heat regenerative electric hybrid combined cycle, which comprises a compression unit, a solid oxide fuel cell, a combustion chamber and a reforming unit; the 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 compression unit comprises a compressor and a turbine, the compressor is connected with the turbine, the compressor is used for compressing air to form high-pressure gas, the reforming unit is used for generating a hydrogen-rich gas phase fuel mixture through a reforming reaction, the solid oxide fuel cell is used for converting chemical energy of the hydrogen-rich gas phase fuel mixture into electric energy through an electrochemical reaction, and the high-pressure gas and the hydrogen-rich gas phase fuel mixture which is not fully reacted are combusted in the combustion chamber to generate combustion gas for driving the turbine to rotate; when the aircraft is in a cruising mode, the reforming unit is connected with 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 with the combustion chamber.

[0006] The aero-engine system based on the wet regeneration heat regenerative electric hybrid combined cycle further comprises a steam generator and a mixer; the steam generator is connected with the turbine to heat circulating working medium in the steam generator into superheated steam by using the combustion gas generated by the combustion chamber, and the steam generator is connected with the mixer to pass the superheated steam into the mixer; liquid phase kerosene is injected into the mixer, the liquid phase kerosene is evaporated into gas phase kerosene by using the heat of the superheated steam, the gas phase kerosene and the superheated steam form mixed gas, the mixer is connected with the reforming unit, the mixed gas is subjected to a reforming reaction in the reforming unit, and the reforming reaction absorbs the heat of the mixed gas to reduce the temperature of the mixed gas during the reforming reaction, and the mixed gas after temperature reduction enters a flame tube cooling layer of the combustion chamber to cool the flame tube cooling layer.

[0007] The aero-engine system based on the wet regeneration heat regenerative electric hybrid combined cycle further comprises a steam generator and a mixer; the steam generator is connected with the turbine to heat circulating working medium in the steam generator into superheated steam by using the combustion gas generated by the combustion chamber, and the steam generator is connected with the mixer to pass the superheated steam into the mixer; liquid phase kerosene is injected into the mixer, the liquid phase kerosene is evaporated into gas phase kerosene by using the heat of the superheated steam, the gas phase kerosene and the superheated steam form mixed gas, the mixer is connected with the reforming unit, the mixed gas is subjected to a reforming reaction in the reforming unit, and the reforming reaction absorbs the heat of the mixed gas to reduce the temperature of the mixed gas during the reforming reaction, and the mixed gas after temperature reduction enters a flame tube cooling layer of the combustion chamber to cool the flame tube cooling layer.

[0008] The application provides an aviation engine system based on a wet regeneration heat recovery vortex electric hybrid combined cycle, wherein the reforming unit comprises a first reforming reactor, the first reforming reactor is arranged in the second turbine, and two ends of the first reforming reactor are connected with the mixer and the flame tube cooling interlayer of the combustion chamber respectively.

[0009] The application provides an aviation engine system based on a wet regeneration heat recovery vortex electric hybrid combined cycle, wherein the reforming unit further comprises a second reforming reactor and a third reforming reactor, two ends of the second reforming reactor are connected with the first reforming reactor and the flame tube cooling interlayer of the combustion chamber respectively, the first end of the third reforming reactor is connected with the flame tube cooling interlayer of the combustion chamber, and the second end of the third reforming reactor is selectively connected with the solid oxide fuel cell and the combustion chamber.

[0010] The application provides an aviation engine system based on a wet regeneration heat recovery vortex electric hybrid combined cycle, further comprising a gas-liquid separation unit and a cooling unit, the gas-liquid separation unit is connected with the steam generator, and the cooling unit is connected with the gas-liquid separation unit; the gas-liquid separation unit is used for heat exchange with the fuel gas, so that water vapor in the fuel gas is condensed into liquid, and the liquid is separated out, and the liquid flows into the first heat exchanger after cooling the electrical equipment under the action of the cooling unit.

[0011] The application provides an aviation engine system based on a wet regeneration heat recovery vortex electric hybrid combined cycle, wherein the gas-liquid separation unit comprises a second heat exchanger and a gas-liquid separator, two ends of the second heat exchanger are connected with the steam generator and the gas-liquid separator respectively, and the gas-liquid separator is connected with the cooling unit.

[0012] The application provides an aviation engine system based on a wet regeneration heat recovery vortex electric hybrid combined cycle, wherein the cooling unit comprises a liquid storage tank and a first pump, the liquid storage tank is connected with the gas-liquid separator, the first pump is connected with the liquid storage tank, the first pump is used for pumping the liquid to the electrical equipment to cool the electrical equipment, and the cooled liquid enters the first heat exchanger.

[0013] The application provides an aviation engine system based on a wet regeneration heat recovery vortex electric hybrid combined cycle, further comprising a third turbine, a generator, an electric machine and a fan, the third turbine is connected with the combustion chamber, the third turbine is connected with the generator, the generator is connected with the electric machine, and the electric machine is connected with the fan.

[0014] The aviation engine system based on the wet regeneration heat regenerative vortex electric hybrid combined cycle provided by the application further comprises a fuel tank and a second pump, and the fuel tank is connected with the mixer through the second pump.

[0015] The aviation engine system based on the wet regeneration heat regenerative vortex electric hybrid combined cycle provided by the application can directly convert chemical energy into electric energy by the solid oxide fuel cell when the aircraft is in a cruising mode, significantly reduces the heat loss when chemical energy is converted into heat energy, improves the energy utilization efficiency, and helps to break through the Carnot efficiency limit of the combined cruising. BRIEF DESCRIPTION OF DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the application or prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative labor.

[0017] Figure 1 FIG. 1 is a structural schematic diagram of the aviation engine system based on the wet regeneration heat regenerative vortex electric hybrid combined cycle provided by the application.

[0018] Reference signs:

[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; 90, solid oxide fuel cell; 100, air inlet channel; 141, flame tube cooling interlayer. DETAILED DESCRIPTION

[0020] In order to make the objects, technical solutions and advantages of the application clearer, the technical solutions in the application will be clearly and completely described below in combination with the drawings in the application. Obviously, the described embodiments are some embodiments of the application, rather than all the embodiments. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the application.

[0021] The application is described below Figure 1 An aviation engine system based on a wet regeneration heat recovery combined cycle of a hybrid combined cycle is described.

[0022] As Figure 1 shown, in an embodiment of the application, the aviation engine system based on a wet regeneration heat recovery combined cycle of a hybrid combined cycle includes a compression unit, a solid oxide fuel cell 90, a combustion chamber 14, and a reforming unit. The compression 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 reforming unit is selectively connected to the solid oxide fuel cell 90 and the combustion chamber 14.

[0023] The compression unit includes a compressor and a turbine, which are coaxially connected. 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 90 converts the chemical energy of the hydrogen-rich gas phase fuel mixture into electrical energy through an electrochemical reaction for use by electrical equipment. At the same time, the high-pressure gas and the unreacted hydrogen-rich gas phase fuel mixture enter the combustion chamber 14 to burn and produce high-temperature 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-molecule hydrocarbons. The flow direction of the hydrogen-rich gas phase fuel mixture is different when the aircraft is in different modes. Due to the poor dynamic influence characteristics of the solid oxide fuel cell 90, it is suitable for operating in stable conditions such as cruising to provide high thermal efficiency, and is not suitable for conditions with large operating condition change rates. Therefore, when the aircraft is in cruising mode, most of the hydrogen-rich gas phase fuel mixture from the reforming unit is supplied to the solid oxide fuel cell 90, and only a small amount is supplied to the combustion chamber 14 for afterburning; when the aircraft is in take-off, climb, and approach modes, the hydrogen-rich gas phase fuel mixture from the reforming unit is all supplied to the combustion chamber 14 for combustion and energy release.

[0024] In this embodiment, the solid oxide fuel cell 90 is combined with the aviation gas engine to form a combined cycle. The solid oxide fuel cell 90 generates electricity while fully utilizing the unreacted fuel after the electrochemical reaction and the waste heat in the combustion chamber 14 to participate in combustion, generating high-temperature gas to drive the turbine to do work, and the turbine drives the compressor to operate, realizing continuous gas generation and continuous power generation.

[0025] The embodiment of the present invention provides an aviation engine system based on a wet regeneration heat-recovery turbo-electric hybrid combined cycle. By setting 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 converting chemical energy 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 combustion, further improving the fuel utilization rate.

[0026] like Figure 1 As shown, in an embodiment of the present invention, the aircraft engine system based on the wet regenerative turbo-electric hybrid combined cycle further includes a steam generator 20 and a mixer 40. The steam generator 20 is connected to the turbine. High-temperature combustion gas generated by combustion in the combustion chamber 14 enters the steam generator 20. The high-temperature combustion gas serves as a heat source for steam generation, heating and evaporating the circulating working fluid in the steam generator 20 to produce superheated steam, which then 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 superheated steam are thoroughly mixed in the mixer 40 to form a mixture of gaseous fuel oil and water vapor. The mixed gas enters the reforming unit, undergoing a reforming reaction to produce a hydrogen-rich gaseous fuel mixture. During the reforming reaction, a large amount of heat is absorbed from the mixed gas, lowering the temperature of the mixed gas. During this process, the heat absorbed by the reaction is converted into additional chemical energy for the mixed gas, thereby providing additional chemical heat sink. It can be understood that the mixed gas here includes both gaseous kerosene and water vapor, as well as the kerosene water vapor reforming product, i.e., the hydrogen-rich gaseous fuel mixture. The mixed gas enters the flame tube cooling layer 141 of the flame tube of the combustion chamber 14, cooling the flame tube cooling layer 141.

[0027] like Figure 1 As shown, in an embodiment of the present invention, the compression unit includes: multiple compressors and multiple turbines, each compressor connected to a turbine. Specifically, the 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 compression unit also includes a first heat exchanger 12. The first compressor 11, the first heat exchanger 12, the second compressor 13, and the combustion chamber 14 are sequentially connected.

[0028] Specifically, the air is compressed by the first compressor 11, enters the first heat exchanger 12, 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, and 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 gas. The high-temperature gas enters the first turbine 15 and the second turbine 16 in turn, and the internal energy is converted into mechanical energy through expansion work to drive the first turbine 15 and the second turbine 16 to rotate, thereby driving the first compressor 11 and the second compressor 13 to rotate.

[0029] Further, the aviation engine system based on the wet regeneration heat recovery turbo-electric hybrid combined cycle further comprises a third turbine 71, a generator 72, a motor 73 and a fan 74. An air inlet passage 100 is arranged outside the aviation engine system, and the fan 74 is arranged in the aviation engine system. Air enters the aviation engine system through the air inlet passage 100, and under the action of the fan 74, the air is divided into two air flows, one of which enters the outer duct, and the other enters the first compressor 11 from the inner duct. The high-temperature gas generated during combustion enters the third turbine 71 to drive the third turbine 71 to rotate, the third turbine 71 is connected with 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.

[0030] In the embodiment of the present application, the aviation engine system based on the wet regeneration heat recovery turbo-electric hybrid combined cycle further comprises a gas-liquid separation unit and a cooling unit. The gas-liquid separation unit is connected with the steam generator 20, and the cooling unit is connected with the gas-liquid separation unit. The high-temperature gas generated by the combustion of the combustion chamber 14 enters the steam generator 20 after passing through multiple turbines, heats and evaporates the condensed water in the steam generator 20 into superheated steam, and then the gas absorbed by heat enters the gas-liquid separation unit and exchanges heat with the air in the gas-liquid separation unit, so that the temperature of the gas is reduced to below the condensation temperature, the water vapor in the gas is condensed into condensed water, and the two-phase exhaust containing liquid water is separated in the gas-liquid separation unit. The condensed water is pumped to the electrical equipment 63 by the cooling unit, the electrical equipment 63 is cooled, and then enters the first heat exchanger 12 to absorb part of the heat in the compressed air at the outlet of the first compressor 11, thereby reducing the temperature of the air and reducing the power consumption of the second compressor 13.

[0031] Further, the gas-liquid separation unit comprises a second heat exchanger 31 and a gas-liquid separator 32, and the two ends of the second heat exchanger 31 are respectively connected with the steam generator 20 and the gas-liquid separator 32, and the gas-liquid separator 32 is connected with the cooling unit.

[0032] Specifically, the high-temperature combustion gas enters the steam generator 20 to heat and evaporate 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 to exchange heat with the outer duct air, and the temperature of the gas is reduced to below the condensation temperature, and the water vapor in the gas is condensed to form condensed water, and at the same time, the temperature of the outer duct air is increased, and the volume flow of the air is increased, thereby generating additional thrust. In the second heat exchanger 31, the water in the gas is gradually condensed, and the two-phase exhaust containing liquid water is separated from the liquid condensed water in the gas-liquid separator 32. The condensed water is used as a circulating working medium and is cooled by the cooling unit to cool the electrical equipment 63, 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.

[0033] Further, according to the foregoing, the air enters the aircraft engine system through the air inlet channel 100, and under the action of the fan 74, the air is divided into two air flows. One air flow enters the outer duct and is sprayed out after being heated by the second heat exchanger 31 to directly generate thrust. The gas flows through the steam generator 20 and then enters the second heat exchanger 31 again to exchange heat with the outer duct air, thereby increasing the temperature of the outer duct air and increasing the volume flow of the air to generate additional thrust.

[0034] Further, 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, and 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 generation, such as batteries, motors, and electronic control systems.

[0035] In this embodiment, the heat sink of the condensed water uses the principle of cascade utilization of cold energy, that is, the matching of cold and hot sources. The circulating condensed water is first used to cool the electrical equipment 63, absorbs waste heat, 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 reducing the temperature of the air, the purpose of reducing the compression power consumption of the second compressor 13 is achieved. The circulating condensed water that is further heated enters the steam generator 20 to recover the waste heat in the core engine gas by using the latent heat of vaporization and the heat capacity.

[0036] The aircraft engine system based on the wet regeneration heat recovery turbo-electric hybrid combined cycle provided in the embodiment of the application fully utilizes the turbine hot end components as a heat source, converts low-energy grade heat 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; the core heat management working medium is the condensed water of the core engine gas, and the multi-path and multi-mode efficient coupling between the cold and hot sources is achieved, thereby maximizing the waste heat recovery capacity of the system.

[0037] As Figure 1 shown, in the embodiment of the present application, the reforming unit comprises a first reforming reactor 51, which is arranged in the second turbine 16, and the two ends of the first reforming reactor 51 are connected with the mixer 40 and the flame tube cooling interlayer 141 of the combustion chamber 14 respectively.

[0038] Specifically, the gaseous fuel / water vapor mixture enters the first reforming reactor 51 arranged inside the guide vane of the second turbine 16, and the mixture is cooled while driving the kerosene water vapor reforming reaction by using the obtained heat, and then the flame tube cooling interlayer 141 of the combustion chamber 14 is cooled. In the prior art, part of the gas (compressed air) compressed by the second compressor 13 is needed as cooling gas to cool the guide vane of the second turbine 16, and the 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, causing additional compression power consumption of the first compressor 11 and the second compressor 13. In the present embodiment, the gas (compressed air) compressed by the first compressor 11 and the second compressor 13 does not need to participate in the turbine cooling, and can all participate in the combustion, avoiding the additional cooling gas compression power consumption of the compression system and reducing the system㶲 loss.

[0039] Further, the reforming unit further comprises a second reforming reactor 52 and a third reforming reactor 53. The two ends of the second reforming reactor 52 are connected with the first reforming reactor 51 and the flame tube cooling interlayer 141 of the combustion chamber 14 respectively, and the first end of the third reforming reactor 53 is connected with the flame tube cooling interlayer 141 of the combustion chamber 14, and the second end of the third reforming reactor 53 is selectively connected with the solid oxide fuel cell 90 and the combustion chamber 14.

[0040] Specifically, the fuel that has been preliminarily reformed in the first reforming reactor 51 enters the second reforming reactor 52, and further promotes the reforming reaction process by using the residual heat carried by itself. The endothermic reforming reaction lowers the temperature of the reforming fuel mixture, and provides an additional heat sink for cooling the flame tube cooling jacket 141 of the combustion chamber 14. The reforming fuel mixture enters the flame tube cooling jacket 141 of the combustion chamber 14 to cool the flame tube cooling jacket 141. Then, the reforming fuel mixture enters the third reforming reactor 53 to further promote the reforming reaction process, reach the upper limit of the reaction process, and finally obtain a high hydrogen-rich gas phase fuel mixture mainly composed of hydrogen. When the aircraft is in a cruising mode, most of the hydrogen-rich gas phase fuel mixture produced by 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 the afterburning to meet the turbine cycle temperature requirement; when the aircraft is in a take-off, climbing and other modes, the hydrogen-rich gas phase fuel mixture produced 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 is all supplied to the combustion chamber 14 for combustion, the hydrogen-rich gas phase fuel mixture is fully mixed with high-pressure air at the head of the combustion chamber 14, and is combusted in a humid gas phase combustion manner. Compared with the traditional kerosene liquid mist combustion organization, the air-fuel mixing speed is greatly accelerated, the generation of hot spots and the coking of nozzles can be effectively inhibited, and the carbon smoke and nitrogen oxide emissions can be significantly reduced. The high-temperature and high-humidity combustion gas produced by combustion further enters each turbine for expansion and work, completing the entire cycle.

[0041] Further, the wet regeneration regenerative turbo-electric hybrid combined cycle-based aircraft engine system further comprises a fuel tank 81 and a second pump 82. The fuel tank 81 stores liquid phase fuel, and the liquid phase fuel is pumped to the mixer 40 by the second pump 82 to be uniformly sprayed into the superheated steam in the form of fuel liquid mist. The fuel is gasified by the high temperature of the superheated steam and fully mixed with the superheated steam according to a certain proportion to generate a gas phase fuel / water vapor mixture.

[0042] The aviation engine system based on the wet regenerative heat recovery turbo-electric hybrid combined cycle provided by the embodiment of the present application obtains the heat recovery cycle core working medium water through condensation recovery in the core engine exhaust, and then is transported to various parts of the engine for waste heat recovery, is used for fuel reforming and water vapor heating, and finally is injected into the fuel cell and the combustion chamber by carrying a large amount of chemical energy and heat energy, so as to complete the low-enthalpy energy release, realize the physical and chemical dual-dimension regenerative heat recovery, and achieve the purpose of energy cascade recovery and utilization; through fuel reforming, the kerosene is converted into a hydrogen-rich gas phase fuel suitable for the fuel cell, so as to generate electricity in the form of direct chemical energy to electric energy, reduce the enthalpy loss in the process of converting fuel chemical energy into heat energy, and make the combined cycle system thermal efficiency break through the limitation of Carnot heat engine efficiency. In the combustion process, the complex kerosene liquid mist combustion is changed into gas phase fuel humidification combustion, the air / fuel mixing speed is improved, the combustion hot spot is suppressed, the possible soot emission is basically eliminated, the hot spot suppression and the addition of water vapor also help to reduce the nitrogen oxide emission, the energy carried by the water vapor is recovered and injected into the fuel cell and the combustion chamber through the reforming architecture, the mass flow and heat capacity of the fuel gas are greatly improved, and the work capacity of the fuel gas is significantly improved; the physical and chemical double heat sink of water vapor and fuel mixture is used to efficiently cool the cooling layer of the turbine guide vane and the combustion chamber flame tube, so that the system no longer relies on the high-pressure compressor bleed air as the cooling gas, and the compressor compression power demand is greatly reduced; the aviation engine system based on the wet regenerative heat recovery turbo-electric hybrid combined cycle provided by the embodiment of the present application uses the chemical reaction core composed of kerosene water vapor fuel reforming reaction, solid oxide fuel cell electrochemical reaction and combustion reaction to realize the low-enthalpy loss utilization of fuel chemical energy and the injection of energy and cycle working medium, fully excavate the physical and chemical heat recovery capacity of water, efficiently connect the entire combined cycle system with a single bottom cycle working medium, and improve the system integration; through the cascade recovery of waste heat, efficient cold and heat interaction is achieved, and the overall thermal efficiency is effectively improved.

[0043] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, but not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement to part of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. An aircraft engine system based on a wet regenerative turbo-electric hybrid combined cycle, characterized in that: include: Compression unit, solid oxide fuel cell, combustor, reformer unit, steam generator and mixer; 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 compression unit includes a compressor and a turbine, wherein the compressor is connected to the turbine, and is used to compress air to form high-pressure gas. The reforming unit is used to generate a hydrogen-rich gaseous fuel mixture by a reforming reaction. The solid oxide fuel cell is used to convert the chemical energy of the hydrogen-rich gaseous fuel mixture into electrical energy by an electrochemical reaction. The high-pressure gas and the incompletely reacted hydrogen-rich gaseous 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 takeoff mode, a climb mode, and an approach mode, the reforming unit is connected to the combustion chamber; 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 is evaporated into gaseous kerosene by utilizing the heat of the superheated steam. The gaseous kerosene and the superheated steam form a mixed gas. The mixer is connected to the reforming unit. The mixed gas undergoes a reforming reaction in the reforming unit. The heat of the mixed gas is absorbed during the reforming reaction, thereby reducing 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. The compression unit includes a second turbine, and the reforming unit includes a first reforming reactor. The first reforming reactor is arranged in the second turbine, and both ends of the first reforming reactor are respectively connected to the mixer and the flame tube cooling layer of 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: The air compression unit further comprises: a first compressor, a second compressor, a first 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.

3. The aircraft engine system based on the wet regeneration turbo-electric hybrid combined cycle according to claim 1, 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.

4. The aircraft engine system based on the wet regeneration turbo-electric hybrid combined cycle according to claim 2, characterized in that: The device further comprises: 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.

5. The aircraft engine system based on the wet regeneration turbo-electric hybrid combined cycle according to claim 4, 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 cooling unit.

6. The aircraft engine system based on the wet regeneration turbo-electric hybrid combined cycle according to claim 5, 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.

7. The aircraft engine system based on the 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 wind turbine.

8. The aircraft engine system based on the wet regeneration turbo-electric hybrid combined cycle 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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