Fuel cell and gas turbine hybrid cycle power generation system and working method

Abstract

The invention belongs to the field of aviation power of clean energy, and discloses a fuel cell and gas turbine hybrid cycle power generation system which comprises a fuel tank, a gas turbine subsystem, a fuel cell subsystem, a control subsystem and an electric energy system. In the first working mode, fuel in a fuel tank enters the gas turbine subsystem, and the gas turbine subsystem converts energy generated after fuel combustion into electric energy to be stored in the electric energy system. In the second working mode, fuel of the fuel tank enters the fuel cell subsystem, the fuel cell subsystem converts chemical energy of the fuel into electric energy to be stored in the electric energy system, the remaining anode waste and cathode waste enter the gas turbine subsystem to be combusted, and energy generated after fuel combustion is converted into electric energy to be stored in the electric energy system; and the control subsystem is used for switching the two working modes. Compared with a traditional gas turbine engine system, the fuel utilization rate of the power generation system architecture is increased by 43% or above, the fuel consumption is reduced by 75% under the same power generation requirement, matched electric power can be directly output according to the power supply requirement needed by airborne equipment, and the requirement for adjusting large-amplitude fluctuation of the electric load of an aircraft in real time is met.

Description

Technical Field

[0001] The present invention belongs to the field of clean energy aviation power, and relates to an aviation hybrid cycle power generation system, and in particular to a fuel cell and gas engine hybrid cycle power generation system and a working method. Background Art

[0002] With the rise of clean energy, "green aviation" is gaining increasing attention worldwide, particularly with the International Air Transport Association's (IATA) "Carbon Emissions Roadmap," which calls for achieving zero carbon emissions by 2050. All-electric aircraft place greater demands on the power generation capabilities of aviation gas turbine engines. Traditional gas turbine engines powered by jet fuel have low thermal efficiency and cannot meet green and environmental requirements. While there are currently concepts for aircraft powered by liquid hydrogen, the storage requirements of liquid hydrogen are challenging, making it difficult to design an environment onboard that can accommodate these requirements.

[0003] Some have proposed using fuel cells to generate electricity and improve fuel efficiency. However, fuel cell power systems have slow startup times and low power-to-weight ratios. While this improves fuel efficiency, the increased fuel consumption due to the added weight typically outweighs the fuel savings from the increased fuel efficiency. Preliminary proposals based on hybrid fuel cell and gas turbine engine cycles have been developed for use in oil refineries and thermal power plants. However, these systems are complex, bulky, and have a single power rating, making them unsuitable for aviation propulsion.

[0004] The hybrid power generation system proposed in CN202110988387.6 uses a low-temperature fuel cell operating at 160-200°C. The fuel cell has a complex internal structure, including a fuel dehydrogenation device. Only oxygen and hydrogen undergo an electrochemical reaction inside the fuel cell. The exhaust gas at the fuel cell outlet has a temperature of 80-100°C and contains many components, including methylcyclohexane gasoline, diesel dehydrogenation products, residual hydrogen, oxygen, and water vapor. Due to its low efficiency, it cannot provide sufficient energy to drive aircraft equipment.

[0005] The pressurized fuel cell-internal combustion engine hybrid system proposed in CN201910439432.5 adopts an internal combustion engine mode, with a crankshaft connecting rod structure connected to the generator through a gearbox. The conversion efficiency is low and it is only suitable for small power generation. It is obviously not suitable for use in all-electric aircraft.

[0006] The hydrogen fuel system provided by CN201810664951.7 has an engine that emits a large amount of waste heat, and the exhaust contains a large amount of pollutants, which does not meet the requirements of all-electric aircraft; and the structure is complex and the power-to-weight ratio is low. Summary of the Invention

[0007] In order to solve the above problems, a new dual-mode system architecture with high power-to-weight ratio, high thermoelectric efficiency and low pollution is provided. It has a better flight envelope and can operate stably and efficiently in high and low temperature and high altitude environments.

[0008] The technical solutions of the present invention are as follows:

[0009] A fuel cell and gas turbine hybrid cycle power generation system comprises a fuel tank, a gas turbine subsystem, a fuel cell subsystem, a control subsystem and an electric energy system; in a first operating mode, fuel in the fuel tank enters the gas turbine subsystem, and the gas turbine subsystem converts the energy after the fuel is burned into electrical energy and stores it in the electric energy system; in a second operating mode, fuel in the fuel tank enters the fuel cell subsystem, and the fuel cell subsystem converts the chemical energy of the fuel into electrical energy and stores it in the electric energy system, and the remaining anode waste and cathode waste then enter the gas turbine subsystem for combustion, and the energy after the fuel is burned is converted into electrical energy and stored in the electric energy system; the control subsystem switches between the two operating modes.

[0010] Furthermore, the gas turbine subsystem includes a combustion chamber, a compressor, a starter / generator and a turbine. The inlet of the combustion chamber is respectively connected to the fuel tank, the cathode outlet of the fuel cell subsystem and the anode outlet of the fuel cell subsystem. The outlet of the combustion chamber is connected to the turbine. The turbine is connected to and drives the compressor and the starter / generator to operate. The high-pressure air generated by the compressor enters the combustion chamber or the cathode inlet of the fuel cell subsystem after being selected by the control subsystem. The starter / generator is connected to the power system.

[0011] Furthermore, it also includes a primary heat exchanger. The exhaust gas discharged from the rear end of the turbine passes through the hot end of the primary heat exchanger, and the high-pressure air generated by the compressor passes through the cold end of the primary heat exchanger before entering the control subsystem.

[0012] Furthermore, the control subsystem includes a controller, an auxiliary fuel control valve and a bypass control valve. The controller connects and controls the auxiliary fuel control valve, the bypass control valve, the starter / generator and the electric energy system. The auxiliary fuel control valve is arranged on the fuel passage between the fuel tank and the combustion chamber. The bypass control valve selects the compressor and the combustion chamber, or the compressor and the cathode inlet of the fuel cell subsystem.

[0013] Furthermore, the fuel cell subsystem includes a reformer, a solid oxide fuel cell, a high-temperature pump, and a secondary heat exchanger. The fuel tank is connected to the cold end of the reformer, and the cold end of the reformer is connected to the inlet of the high-temperature pump. The outlet of the high-temperature pump is connected to the anode inlet of the solid oxide fuel cell. The compressor selects the cathode inlet of the solid oxide fuel cell through the control subsystem. The power generation end of the solid oxide fuel cell is connected to the power system. The anode outlet of the solid oxide fuel cell passes through the hot end of the reformer and the hot end of the secondary heat exchanger and is connected to the combustion chamber. The cathode outlet of the solid oxide fuel cell is directly connected to the combustion chamber.

[0014] Furthermore, a pressure swing adsorption molecular sieve is provided in the cold end of the secondary heat exchanger to separate nitrogen and oxygen in the air, wherein the nitrogen is discharged into the surrounding atmosphere and the oxygen is connected to the cathode inlet of the solid oxide fuel cell.

[0015] Furthermore, a catalyst is provided in the cold end of the reformer. The catalyst is a high-temperature fuel catalyst that catalyzes the fuel into a mixed gas of hydrogen and other combustible gases.

[0016] Furthermore, the fuel is one or more of aviation kerosene, natural gas, methanol, and ethanol.

[0017] A method for operating a fuel cell and gas turbine hybrid cycle power generation system, using the above-mentioned fuel cell and gas turbine hybrid cycle power generation system, when a single gas turbine engine is started and operating in a stable mode, it enters a first operating mode, a controller sends a start signal to the starter / generator, simultaneously controls the bypass control valve to connect the combustion chamber and the compressor, and sends a signal to open the auxiliary fuel control valve. At this time, the gas turbine engine subsystem starts, the compressor inlet draws in air, and the starter / generator is cooled by the suction effect. At the same time, the compressed air at the compressor outlet is heated and directly enters the combustion chamber to be mixed with the fuel, ignited and burned. The high-temperature and high-pressure gas drives the turbine to perform work, and the rotor speed increases rapidly. When the rotor speed reaches the cut-off speed, the controller sends a control signal to disconnect the power input switch of the starter / generator, thereby disconnecting the output torque of the starter / generator; the gas turbine engine speed continues to increase to the idle speed, the controller sends a starter / generator load signal, and the starter / generator begins to output electrical energy to the power system; at the same time, the high-temperature exhaust gas discharged from the turbine is cooled and discharged into the surrounding atmosphere.

[0018] A method for operating a fuel cell and gas turbine hybrid cycle power generation system, using the above-mentioned fuel cell and gas turbine hybrid cycle power generation system, when the fuel cell and gas turbine engine hybrid cycle power generation system is operating in a stable mode, it enters a second operating mode, a controller sends a signal to control the bypass control valve to select the compressor and fuel cell subsystem, and at the same time closes the auxiliary fuel control valve; at this time, the gas turbine engine subsystem inhales air from the compressor inlet, dissipates heat to the starter / generator through the suction effect, and at the same time, the compressed air at the compressor outlet is heated and enters the pressure swing adsorption molecular sieve in the secondary heat exchanger to achieve nitrogen and oxygen separation in the air, and the nitrogen is discharged into the surrounding atmosphere. Oxygen is connected to the cathode inlet of the solid oxide fuel cell, and generates electrical energy through electrochemical reaction with the fuel connected to the anode inlet, which is stored in the power system; the residual oxygen at the cathode outlet of the solid oxide fuel cell and the residual fuel at the anode outlet of the solid oxide fuel cell are directly sent into the combustion chamber for combustion after heat exchange in the reformer and secondary heat exchanger. The high-temperature and high-pressure combustion gas generated drives the turbine of the gas turbine engine to rotate, driving the coaxial compressor and starter generator to work. The controller sends a starter / generator load loading signal, and the starter / generator starts to output electrical energy and stores it in the power system; and the exhaust gas at the turbine outlet of the gas turbine engine is discharged into the surrounding atmosphere after cooling.

[0019] The beneficial effects of the present invention are as follows:

[0020] 1. The fuel utilization rate of the novel dual-mode fuel cell and gas turbine engine hybrid cycle power generation system architecture involved in the present invention is increased by more than 43% compared with the traditional gas turbine engine system, and the fuel consumption is saved by 75% under the same power generation demand.

[0021] 2. The novel dual-mode fuel cell and gas turbine engine hybrid cycle power generation system architecture of the present invention is equipped with a fuel reformer, a power conditioner, and a battery. It can directly output matching power according to the power supply requirements of the onboard equipment and meet the needs of real-time regulation of large fluctuations in the aircraft's electrical load.

[0022] 3. The novel dual-mode fuel cell and gas turbine engine hybrid cycle power generation system architecture of the present invention includes a control system and a regulating mechanism that matches the system architecture, which can realize dual-mode operation of the system and meet the power requirements of high-altitude flight and ground maintenance.

[0023] 4. This invention offers exceptional economic value and significant energy savings and emission reduction benefits for applications requiring high power in harsh operating conditions, particularly for all-electric aircraft, which require significant power for high-altitude flight and minimal power for ground maintenance. Furthermore, this solution can also be applied to other energy generation systems, demonstrating excellent versatility, cost-effectiveness, and environmental friendliness.

[0024] 5. Relative to CN202110988387.6, the present invention adopts a high-temperature solid oxide fuel cell, the internal stack reaction temperature of the fuel cell is (1000-1200)°C, and the residual gas discharged from the fuel cell outlet contains only hydrogen, oxygen and water vapor, with a temperature of (600-800)°C, which has extremely high thermal efficiency. Relative to CN201910439432.5, the power generation power of the present invention is extremely high, and the thermal energy utilization rate is also higher. The engine of the present invention is a gas turbine structure, and the compressor, turbine and generator are coaxial and compact in structure. Relative to CN201810664951.7, the exhaust waste heat of the present invention can heat the fuel and compressed air, and the exhaust is discharged only after heat exchange; only hydrogen is burned in the engine, and the product is only water vapor, without pollutants. Relative to the above-mentioned scheme, the present invention can enable the energy system to operate in different modes by switching between different working modes, adapt to different electricity demands and energy reserves, and provide support for different flight demand modes of all-electric aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only show certain embodiments of the present invention and should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without creative work.

[0026] Figure 1 This is a schematic diagram of the architecture of the novel dual-mode fuel cell and gas turbine engine hybrid cycle power generation system of the present invention;

[0027] Among them, 1-fuel tank, 2-fuel pump, 3-reformer, 4-auxiliary fuel control valve, 5-primary heat exchanger, 6-turbine, 7-high temperature pump, 8-solid oxide fuel cell, 9-secondary heat exchanger, 10-combustion chamber, 11-power conditioner, 12-battery, 13-starter / generator, 14-compressor, 15-controller, 16-bypass control valve. DETAILED DESCRIPTION

[0028] This section is an embodiment of the present invention, which is used to explain and illustrate the technical solution of the present invention. In the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.

[0029] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate directions or positional relationships for the purposes of the accompanying drawings, and are intended only to facilitate the description of the present invention and simplify the description, rather than to indicate or imply that the device or case referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention. In addition, the terms "first", "second" and the like are used for descriptive purposes only, and should not be understood as indicating or implying relative importance or implying the number of technical features indicated. Thus, features defined as "first", "second" and the like may explicitly or implicitly include more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0030] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be interpreted broadly. For example, they may refer to fixed, detachable, or integrated connections; mechanical or point connections; direct or indirect connections through an intermediary; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0031] Example 1:

[0032] A novel dual-mode fuel cell and gas turbine engine hybrid cycle power generation system is characterized by comprising a fuel tank 1, a fuel pump 2, a reformer 3, an auxiliary fuel control valve 4, a primary heat exchanger 5, a turbine 6, a high-temperature pump 7, a solid oxide fuel cell 8, a secondary heat exchanger 9, a combustion chamber 10, a power conditioner 11, a battery 12, a starter / generator 13, a compressor 14, a controller 15, and a bypass control valve 16. The turbine 6, starter / generator 13, and compressor 14 rotate coaxially at high speed. The high-pressure air output by the compressor 14 is heated by the primary heat exchanger 5 and then divided into two paths through the bypass control valve: one path is supplied to the combustion chamber, and the other path is heated by the secondary heat exchanger 9 and then supplied to the solid oxide fuel cell 8. The secondary heat exchanger 9 contains a multi-layer pressure swing adsorption molecular sieve to separate oxygen and nitrogen in the compressed air to produce high-purity oxygen (O2).

[0033] Solid oxide fuel cells (SOFCs) 8 operate at temperatures between 800°C and 900°C, requiring preheating to this temperature for effective operation. High-temperature pumps 7 are powered by battery power and operate after the system is started and the battery reaches the required energy reserve, ensuring that the fuel entering the SOFC reaches its operating temperature.

[0034] The secondary exchanger 9 contains multiple layers of honeycomb-shaped pressure swing adsorption molecular sieves to separate oxygen and nitrogen in the compressed air to produce high-purity oxygen O2 to supply the solid oxide fuel cell 8.

[0035] The present invention has two modes: a single gas turbine engine starting and stable operation mode, and a fuel cell and gas turbine engine mixed cycle power generation system stable operation mode.

[0036] The turbine 6, the starter / generator 13, and the compressor 14 are coaxial; the starter / generator 13 is located at the front end of the compressor 14, and can effectively utilize the air suction effect of the compressor 14 during intake to cool and dissipate heat for the starter / generator 13.

[0037] When the system starts, the controller 15 sends a start signal to the starter / generator 13 and an opening signal to the auxiliary fuel control valve 4. When the gas turbine engine speed reaches the ignition speed, the combustion chamber 10 sprays fuel for ignition and combustion, and the high-temperature and high-pressure gas drives the turbine 6 to do work. The speed increases rapidly. When the speed reaches the cut-off speed, the controller 15 sends a control signal to disconnect the power input switch of the starter / generator 13; the gas turbine engine speed continues to increase to the idle speed, and the controller sends a loading signal to the starter / generator 13 to start generating electricity and supply it to the battery 12; at the same time, the high-temperature exhaust gas discharged after the turbine 6 is heated by the compressed air inside the primary heat exchanger 5 and the outlet of the compressor 14, further reducing the exhaust gas temperature.

[0038] When the internal temperature of the solid oxide fuel cell 8 reaches 800° C.-900° C. and the energy is balanced, the controller 13 sends a control signal to close the auxiliary fuel control valve 4 , cutting off the fuel output channel from the reformer 3 to the combustion chamber 10 .

[0039] The system operates stably. The residual H2 and CO in the exhaust gas at the anode outlet have a temperature of approximately 800°C. After mixing, cooling, and reforming in the reformer 3, the temperature reaches approximately 600°C. The exhaust gas then enters the combustion chamber 10 of the gas turbine engine GT, where it is mixed with the compressed air at the outlet of the compressor 14 and the cathode exhaust gas, i.e., residual O2, from the solid oxide fuel cell 8. The high-temperature, high-pressure exhaust gas propels the turbine 6 to produce work, and the generator 13 outputs electrical energy to the battery 12. Simultaneously, the controller 15 converts the voltage of the electrical energy generated by the solid oxide fuel cell 8 through the power conditioner 11 and outputs it to the battery 12. The high-temperature exhaust gas from the gas turbine engine passes through the primary heat exchanger 5 to heat the compressed air at the outlet of the compressor 14, further reducing its temperature before being discharged.

[0040] Example 2:

[0041] A novel fuel cell and gas turbine engine hybrid cycle power generation system, wherein an aircraft fuel system provides fuel to the fuel cell and gas turbine engine hybrid cycle power generation system, and the fuel cell and gas turbine engine hybrid cycle power generation system provides electrical energy to the aircraft load system. The system is characterized in that the system includes a gas turbine engine subsystem, a fuel cell subsystem, and a control and energy storage system;

[0042] The gas turbine engine subsystem includes a starter / generator 13, a compressor 14, a combustor 10, and a turbine 6;

[0043] The fuel cell subsystem includes a solid oxide fuel cell 8, a reformer 3, and a high-temperature pump 7;

[0044] The control and energy storage system includes an auxiliary fuel control valve 4, a controller 15, a battery 12, and a power conditioner 11;

[0045] The starter / generator 13, the compressor 14, and the turbine 6 are coaxially arranged in sequence; the inlet of the compressor 14 is connected to the atmosphere, and the outlet of the compressor 14 is connected to the cold air inlet of the primary heat exchanger 5. After passing through the bypass control valve 16, one path enters the combustion chamber 10 to participate in combustion, and the other path is connected to the secondary heat exchanger 9 to separate the oxygen O2 through the molecular sieve and is connected to the cathode of the solid oxide fuel cell 8. When the fuel cell and gas turbine mixed cycle power generation system is working, the compressor 14 inhales air from the inlet, generates compressed air and supplies it to the solid oxide fuel cell 8; the anode inlet of the solid oxide fuel cell 8 is connected to the supply pipeline of the high-temperature pump 7, the anode outlet of the solid oxide fuel cell 8 is connected to the fuel pipeline of the reformer 3, and the cathode outlet of the solid oxide fuel cell 8 is connected to the fuel pipeline of the reformer 3. The outlet of the combustion chamber 10 is connected to the gas path of the combustion chamber 10; the outlet of the combustion chamber 10 is connected to the turbine 6; the fuel cell and gas turbine engine mixed cycle power generation system includes two power generation units, a starter / generator 13 and a solid oxide fuel cell 8, and the two power generation units are connected to the power conditioner 11. The electric energy is converted into the voltage and current required by the airborne equipment by the power conditioner 11 and stored in the airborne battery 12; a fuel pump 2 is provided between the airborne fuel system and the fuel cell subsystem, and an auxiliary fuel control valve 4 is provided between the airborne fuel system and the combustion chamber 10; the controller 15 is connected to the auxiliary fuel valve 4 by a cable, and the controller 15 can adjust the opening of the fuel valve 16 and the auxiliary fuel valve 4 to adjust the fuel supply amount of the fuel cell subsystem and the combustion chamber 10.

[0046] The fuel cell and gas turbine engine mixed cycle power generation system is provided with a reformer 3, a primary heat exchanger 5, and a secondary heat exchanger 9 for heat exchange; when the fuel cell and gas turbine engine mixed cycle power generation system uses kerosene, natural gas, methanol, ethanol, etc. as fuel, a reforming device is provided between the fuel pump 2 and the solid oxide fuel cell 8, and the fuel is reformed to produce hydrogen by the reformer 3 and then supplied to the solid oxide fuel cell 8 through the high-temperature pump 7; in order to ensure the stable working temperature of the solid oxide fuel cell 8, the compressor 14 compresses the air and preheats it to a specific temperature through the primary heat exchanger 5 and the secondary heat exchanger 9 before entering the fuel cell.

[0047] The fuel cell and gas turbine engine hybrid cycle power generation system is also equipped with a bypass control valve 16 and an auxiliary fuel control valve 4. A controller 15 uses control signals to open and close the bypass control valve 16 and the auxiliary fuel control valve 4, thereby controlling the fuel cell and gas turbine engine hybrid cycle power generation system's stable mode and the standalone gas turbine engine's startup and stable mode.

[0048] When a single gas turbine engine is started and operating in a stable mode, the controller 15 sends a start signal to the starter / generator 13. At the same time, the controller 15 sends a signal to open the valve connecting the bypass control valve 16 and the combustion chamber 10, and sends a signal to open the valve connecting the auxiliary fuel control valve 4 and the combustion chamber 10), and directly connects the pressure-regulated fuel to the combustion chamber 10 through the fuel pipeline; at this time, the gas turbine engine subsystem starts, and the compressor 14 inlet inhales air, and the starter / generator 13 is cooled by the suction effect. At the same time, the compressed air at the outlet of the compressor 14 is heated by the primary heat exchanger 5, and directly enters the combustion chamber 10 after passing through the bypass control valve 16. The fuel is mixed, ignited and burned, and the high-temperature and high-pressure gas drives the turbine 6 to do work. The rotor speed increases rapidly. When the rotor speed reaches the cut-off speed, the controller 15 sends a control signal to disconnect the power input switch of the starter / generator 13, thereby disconnecting the output torque of the starter / generator 13. The gas turbine engine speed continues to increase to the idle speed, and the controller 15 sends a load loading signal to the starter / generator 13. The starter / generator 13 starts to output electrical energy to the power conditioner 11, which is then stored in the battery 12 after power conditioning and conversion. At the same time, the high-temperature exhaust gas discharged from the turbine 6 passes through the primary heat exchanger 5 to heat the compressed air at the outlet of the compressor 14, and then is discharged into the surrounding atmosphere.

[0049] When the fuel cell and gas turbine engine hybrid cycle power generation system is operating in a stable mode, the controller 15 sends a signal to close the valve connecting the bypass control valve 16 and the combustion chamber 10, and at the same time closes the valve connecting the auxiliary fuel control valve 4 and the combustion chamber 10); at this time, the gas turbine engine subsystem inhales air from the inlet of the compressor 14, and dissipates heat to the starter / generator 13 through the suction effect. At the same time, the compressed air at the outlet of the compressor 14 is heated by the primary heat exchanger 5, and enters the pressure swing adsorption molecular sieve in the secondary heat exchanger 9 after passing through the bypass control valve 16, so as to realize the separation of nitrogen N2 and oxygen O2 in the air, and the nitrogen N2 is discharged into the surrounding atmosphere, while the oxygen O2 is connected to the cathode inlet of the solid oxide fuel cell 8, and reacts with the fuel connected to the anode inlet through an electrochemical reaction. Electric energy is generated and stored in the battery 12 after voltage regulation and conversion by the power conditioner 11; the residual oxygen O2 at the cathode outlet of the solid oxide fuel cell 8 and the residual fuel at the anode outlet of the solid oxide fuel cell 8 are directly entered into the combustion chamber 10 for combustion after being reformed by the reformer 3 and heat exchanged by the secondary heat exchanger 9. The high-temperature and high-pressure combustion gas generated drives the turbine 6 of the gas turbine engine to rotate, driving the coaxial compressor 14 and the starter generator 13 to work. The controller 15 sends a load loading signal to the starter / generator 13, and the starter / generator 13 starts to output electric energy to the power conditioner 11, which is stored in the battery 12 after power regulation and conversion; and the exhaust gas at the outlet of the turbine 6 of the gas turbine engine is cooled by the primary heat exchanger 5 and discharged into the surrounding atmosphere.

[0050] The electric energy output by the starter / generator 13 and the solid oxide fuel cell 8 is converted into ±270V DC by the power regulator 11 and supplied to the electrical equipment of the aircraft;

[0051] Example 3:

[0052] A novel fuel cell and gas turbine engine hybrid cycle power generation system, wherein an onboard fuel system provides fuel to the fuel cell and gas turbine engine hybrid cycle power generation system, and the fuel cell and gas turbine engine hybrid cycle power generation system provides energy for all-electric or multi-electric aircraft load systems. The system is characterized in that the system includes a gas turbine subsystem, a fuel cell subsystem, and a control and energy storage system;

[0053] The gas turbine engine subsystem includes a starter / generator 13, a compressor 14, a combustor 10, and a turbine 6;

[0054] The fuel cell subsystem includes a solid oxide fuel cell 8, a reformer 3, and a high-temperature pump 7;

[0055] The control and energy storage system includes an auxiliary fuel control valve 4, a controller 15, a battery 12, and a power conditioner 11;

[0056] The starter / generator 13, the compressor 14, and the turbine 6 are coaxially arranged in sequence; the inlet of the compressor 14 is connected to the atmosphere, and the outlet of the compressor 14 is connected to the cold air inlet of the primary heat exchanger 5. After passing through the bypass control valve 16, one path enters the combustion chamber 10 to participate in combustion, and the other path is connected to the secondary heat exchanger 9 to separate the oxygen O2 through the molecular sieve and is connected to the cathode of the solid oxide fuel cell 8. When the fuel cell and gas turbine mixed cycle power generation system is working, the compressor 14 inhales air from the inlet, generates compressed air and supplies it to the solid oxide fuel cell 8; the anode inlet of the solid oxide fuel cell 8 is connected to the supply pipeline of the high-temperature pump 7, the anode outlet of the solid oxide fuel cell 8 is connected to the fuel pipeline of the reformer 3, and the cathode outlet of the solid oxide fuel cell 8 is connected to the fuel pipeline of the reformer 3. The outlet of the combustion chamber 10 is connected to the gas path of the combustion chamber 10; the outlet of the combustion chamber 10 is connected to the turbine 6; the fuel cell and gas turbine engine mixed cycle power generation system includes two power generation units, a starter / generator 13 and a solid oxide fuel cell 8, and the two power generation units are connected to the power conditioner 11. The electric energy is converted into the voltage and current required by the airborne equipment by the power conditioner 11 and stored in the airborne battery 12; a fuel pump 2 is provided between the airborne fuel system and the fuel cell subsystem, and an auxiliary fuel control valve 4 is provided between the airborne fuel system and the combustion chamber 10; the controller 15 is connected to the auxiliary fuel valve 4 by a cable, and the controller 15 can adjust the opening of the fuel valve 16 and the auxiliary fuel valve 4 to adjust the fuel supply amount of the fuel cell subsystem and the combustion chamber 10.

[0057] The fuel cell and gas turbine engine mixed cycle power generation system is provided with a reformer 3, a primary heat exchanger 5, and a secondary heat exchanger 9 for heat exchange; when the fuel cell and gas turbine engine mixed cycle power generation system uses kerosene as fuel, a reforming device is provided between the fuel pump 2 and the solid oxide fuel cell 8. The fuel is reformed to produce hydrogen by the reformer 3 and then supplied to the solid oxide fuel cell 8 through the high-temperature pump 7; to ensure the stable operating temperature of the solid oxide fuel cell 8, the compressor 14 compresses the air and preheats it to a specific temperature through the primary heat exchanger 5 and the secondary heat exchanger 9 before entering the fuel cell.

[0058] The fuel cell and gas turbine engine hybrid cycle power generation system is also equipped with a bypass control valve 16 and an auxiliary fuel control valve 4. A controller 15 uses control signals to open and close the bypass control valve 16 and the auxiliary fuel control valve 4, thereby controlling the fuel cell and gas turbine engine hybrid cycle power generation system in a stable operating mode and the gas turbine engine startup and stable operating mode.

[0059] When a separate gas turbine engine is started and in stable working mode, the controller 15 sends a start signal to the starter / generator 13. At the same time, the controller 15 sends a signal to open the valve connecting the bypass control valve 16 and the combustion chamber 10, and sends a signal to open the valve connecting the auxiliary fuel control valve 4 and the combustion chamber 10), and directly connects the pressure-regulated fuel to the combustion chamber 10 through the fuel pipeline; at this time, the gas turbine engine subsystem is started, and the compressor 14 inlet inhales air, and the starter / generator 13 is cooled by the suction effect. At the same time, the compressed air at the outlet of the compressor 14 is heated by the primary heat exchanger 5, and directly enters the combustion chamber 10 after passing through the bypass control valve 16. The fuel is mixed, ignited and burned, and the high-temperature and high-pressure gas drives the turbine 6 to do work. The rotor speed increases rapidly. When the rotor speed reaches the cut-off speed, the controller 15 sends a control signal to disconnect the power input switch of the starter / generator 13, thereby disconnecting the output torque of the starter / generator 13. The gas turbine engine speed continues to increase to the idle speed, and the controller 15 sends a load loading signal to the starter / generator 13. The starter / generator 13 starts to output electrical energy to the power conditioner 11, which is then stored in the battery 12 after power conditioning and conversion. At the same time, the high-temperature exhaust gas discharged from the turbine 6 passes through the primary heat exchanger 5 to heat the compressed air at the outlet of the compressor 14, and then is discharged into the surrounding atmosphere.

[0060] When the fuel cell and gas turbine engine hybrid cycle power generation system is in a stable working mode, the controller 15 sends a signal to close the valve connecting the bypass control valve 16 and the combustion chamber 10, and at the same time closes the valve connecting the auxiliary fuel control valve 4 and the combustion chamber 10); at this time, the gas turbine engine subsystem inhales air from the inlet of the compressor 14, and dissipates heat to the starter / generator 13 through the suction effect. At the same time, the compressed air at the outlet of the compressor 14 is heated by the primary heat exchanger 5, and enters the pressure swing adsorption molecular sieve in the secondary heat exchanger 9 after passing through the bypass control valve 16, so as to realize the separation of nitrogen N2 and oxygen O2 in the air, and the nitrogen N2 is discharged into the surrounding atmosphere, while the oxygen O2 is connected to the cathode inlet of the solid oxide fuel cell 8, and reacts with the fuel connected to the anode inlet through electrochemical reaction. Electric energy is generated and stored in the battery 12 after voltage regulation and conversion by the power conditioner 11; the residual oxygen O2 at the cathode outlet of the solid oxide fuel cell 8 and the residual fuel at the anode outlet of the solid oxide fuel cell 8 are directly entered into the combustion chamber 10 for combustion after being reformed by the reformer 3 and heat exchanged by the secondary heat exchanger 9. The high-temperature and high-pressure combustion gas generated drives the turbine 6 of the gas turbine engine to rotate, driving the coaxial compressor 14 and the starter generator 13 to work. The controller 15 sends a load loading signal to the starter / generator 13, and the starter / generator 13 starts to output electric energy to the power conditioner 11, which is stored in the battery 12 after power regulation and conversion; and the exhaust gas at the outlet of the turbine 6 of the gas turbine engine is cooled by the primary heat exchanger 5 and discharged into the surrounding atmosphere.

[0061] The electric energy output by the starter / generator 13 and the solid oxide fuel cell 8 is converted into ±270V DC by the power regulator 11 and supplied to the electrical equipment of the aircraft;

[0062] The present invention relates to a novel dual-mode fuel cell and gas turbine engine hybrid cycle power generation system, comprising a gas turbine subsystem, a fuel cell subsystem, and a control and energy storage system. The system operates in two modes: a standalone gas turbine engine startup and stabilization mode, and a fuel cell-gas turbine engine hybrid cycle power generation system stabilization mode.

[0063] See also Figure 1 , single gas turbine engine start-up and stabilization mode. The fuel cell subsystem requires specific temperature, pressure, and fuel supply conditions for stable operation. Under special conditions such as system startup and shutdown, the system can only operate in single gas turbine engine start-up and stabilization mode.

[0064] During the startup process, when a single gas turbine engine is started and operating in the stable mode, the controller 15 sends a start signal to the starter / generator 13. At the same time, the controller 15 sends a signal to open the valve connecting the bypass control valve 16 and the combustion chamber 10, and sends a signal to open the valve connecting the auxiliary fuel control valve 4 and the combustion chamber 10), and directly connects the pressure-regulated fuel to the combustion chamber 10 through the fuel pipeline; at this time, the gas turbine engine subsystem starts, and the compressor 14 inlet inhales air, dissipating heat to the starter / generator 13 through the suction effect. At the same time, the compressed air at the outlet of the compressor 14 is heated by the primary heat exchanger 5 and directly enters the combustion chamber 10 after passing through the bypass control valve 16. ) is mixed with the fuel, ignited and burned, and the high-temperature and high-pressure combustion gas drives the turbine 6 to do work, and the rotor speed increases rapidly. When the rotor speed reaches the cut-off speed, the controller 15 gives a control signal to disconnect the power input switch of the starter / generator 13, and disconnects the output torque of the starter / generator 13; the gas turbine engine speed continues to increase to the slow speed, and the controller 15 sends a load loading signal to the starter / generator 13, and the starter / generator 13 starts to output electrical energy to the power conditioner 11, which is stored in the battery 12 after power regulation and conversion; at the same time, the high-temperature exhaust gas discharged from the turbine 6 passes through the primary heat exchanger 5 to heat the compressed air at the outlet of the compressor 14 and then is discharged into the surrounding atmosphere.

[0065] See also Figure 1When the fuel cell and gas turbine engine hybrid cycle power generation system operates in stable mode, the controller 15 sends a signal to close the valve connecting the bypass control valve 16 and the combustion chamber 10, and at the same time closes the valve connecting the auxiliary fuel control valve 4 and the combustion chamber 10); at this time, the gas turbine engine subsystem inhales air from the inlet of the compressor 14, and dissipates heat to the starter / generator 13 through the suction effect. At the same time, the compressed air at the outlet of the compressor 14 is heated by the primary heat exchanger 5, and enters the pressure swing adsorption molecular sieve in the secondary heat exchanger 9 after passing through the bypass control valve 16, so as to realize the separation of nitrogen N2 and oxygen O2 in the air. The nitrogen N2 is discharged into the surrounding atmosphere, while the oxygen O2 is connected to the cathode inlet of the solid oxide fuel cell 8 and is electrochemically reacted with the fuel connected to the anode inlet. Electric energy should be generated, which is stored in the battery 12 after voltage regulation and conversion by the power conditioner 11; the residual oxygen O2 at the cathode outlet of the solid oxide fuel cell 8 and the residual fuel at the anode outlet of the solid oxide fuel cell 8 are directly entered into the combustion chamber 10 for combustion after being reformed by the reformer 3 and heat exchanged by the secondary heat exchanger 9. The high-temperature and high-pressure combustion gas generated drives the turbine 6 of the gas turbine engine to rotate, driving the coaxial compressor 14 and the starter generator 13 to work, and the controller 15 sends a load loading signal to the starter / generator 13, and the starter / generator 13 starts to output electric energy to the power conditioner 11, which is stored in the battery 12 after power regulation and conversion; and the exhaust gas at the outlet of the turbine 6 of the gas turbine engine is cooled by the primary heat exchanger 5 and discharged into the surrounding atmosphere.

[0066] The above description is merely a detailed description of specific embodiments of the present invention. Any unspecified portions are conventional techniques. However, the scope of the present invention is not limited thereto. Any changes or substitutions that can be readily conceived by a person skilled in the art within the technical scope disclosed in the present invention are intended to be encompassed within the scope of the present invention. The scope of the present invention shall be determined by the scope of the claims.

Claims

1. A fuel cell and gas turbine hybrid cycle power generation system, characterized in that: The invention comprises a fuel tank (1), a gas turbine subsystem, a fuel cell subsystem, a control subsystem and an electric energy system; in a first working mode, the fuel in the fuel tank (1) enters the gas turbine subsystem, and the gas turbine subsystem converts the energy after the fuel is burned into electric energy and stores it in the electric energy system; in a second working mode, the fuel in the fuel tank (1) enters the fuel cell subsystem, and the fuel cell subsystem converts the chemical energy of the fuel into electric energy and stores it in the electric energy system, and the remaining anode waste and cathode waste enter the gas turbine subsystem for combustion, and the energy after the fuel is burned is converted into electric energy and stored in the electric energy system; the control subsystem switches between the two working modes.

2. A fuel cell and gas turbine hybrid cycle power generation system according to claim 1, characterized in that: The gas turbine subsystem comprises a combustion chamber (10), a compressor (14), a starter / generator (13) and a turbine (6). The inlet of the combustion chamber (10) is respectively connected to a fuel tank (1), a cathode outlet of a fuel cell subsystem and an anode outlet of the fuel cell subsystem. The outlet of the combustion chamber (10) is connected to a turbine (6). The turbine (6) is connected to and drives the compressor (14) and the starter / generator (13) to operate. The high-pressure air generated by the compressor (14) enters the cathode inlet of the combustion chamber or the fuel cell subsystem after being selected by the control subsystem. The starter / generator (13) is connected to an electric energy system.

3. A fuel cell and gas turbine hybrid cycle power generation system according to claim 2, characterized in that: It also includes a primary heat exchanger (5), the exhaust gas discharged from the rear end of the turbine (6) passes through the hot end of the primary heat exchanger (5), and the high-pressure air generated by the compressor (14) passes through the cold end of the primary heat exchanger (5) and then enters the fuel cell subsystem.

4. A fuel cell and gas turbine hybrid cycle power generation system according to claim 2, characterized in that: The control subsystem includes a controller (15), an auxiliary fuel control valve (4) and a bypass control valve (16). The controller (15) is connected to and controls the auxiliary fuel control valve (4), the bypass control valve (16), the starter / generator (13) and the electric energy system. The auxiliary fuel control valve (4) is arranged on the fuel passage between the fuel tank (1) and the combustion chamber (10). The bypass control valve (16) selects the compressor (14) and the combustion chamber (10), or the compressor (14) and the cathode inlet of the fuel cell subsystem.

5. A fuel cell and gas turbine hybrid cycle power generation system according to claim 4, characterized in that: The fuel cell subsystem comprises a reformer (3), a solid oxide fuel cell (8), a high temperature pump (7), and a secondary heat exchanger (9); the fuel tank (1) is connected to the cold end of the reformer (3); the cold end of the reformer (3) is connected to the inlet of the high temperature pump (7); the outlet of the high temperature pump (7) is connected to the anode inlet of the solid oxide fuel cell (8); the compressor (14) selects the cathode inlet of the solid oxide fuel cell (8) through the control subsystem; the power generation end of the solid oxide fuel cell (8) is connected to the power system; the anode outlet of the solid oxide fuel cell (8) passes through the hot end of the reformer (3) and the hot end of the secondary heat exchanger (9) in turn and is connected to the combustion chamber (10); the cathode outlet of the solid oxide fuel cell (8) is directly connected to the combustion chamber (10).

6. A fuel cell and gas turbine hybrid cycle power generation system according to claim 5, characterized in that: A pressure swing adsorption molecular sieve is arranged in the cold end of the secondary heat exchanger (9) to separate nitrogen and oxygen in the air, wherein the nitrogen is discharged into the surrounding atmosphere and the oxygen is connected to the cathode inlet of the solid oxide fuel cell (8).

7. A fuel cell and gas turbine hybrid cycle power generation system according to claim 5, characterized in that: A catalyst is arranged in the cold end of the reformer (3), and the catalyst is a high-temperature fuel catalyst, which catalyzes the fuel into a mixed gas of hydrogen and other combustible gases.

8. A fuel cell and gas turbine hybrid cycle power generation system according to claim 7, characterized in that: The fuel is one or more of aviation kerosene, natural gas, methanol and ethanol.

9. A working method of a fuel cell and gas turbine hybrid cycle power generation system, characterized in that: A fuel cell and gas turbine hybrid cycle power generation system as described in any one of claims 4 to 8 is used, characterized in that when a single gas turbine engine is started and works in a stable mode, it enters a first working mode, the controller sends a start signal to the starter / generator, and at the same time controls the bypass control valve to connect the combustion chamber and the compressor, and sends a signal to open the auxiliary fuel control valve. At this time, the gas turbine engine subsystem starts, the compressor inlet inhales air, and the starter / generator is cooled by the suction effect. At the same time, the compressed air at the compressor outlet is directly heated and enters the combustion chamber to be mixed with the fuel, ignited and burned, and the high-temperature and high-pressure gas drives the turbine to work, and the rotor speed increases rapidly. When the rotor speed reaches the cut-off speed, the controller sends a control signal to disconnect the power input switch of the starter / generator and disconnect the output torque of the starter / generator; the gas turbine engine speed continues to increase to the slow speed, the controller sends a starter / generator load loading signal, and the starter / generator starts to output electrical energy to the power system; at the same time, the high-temperature exhaust gas discharged after the turbine is discharged into the surrounding atmosphere after cooling.

10. A method for operating a fuel cell and gas turbine hybrid cycle power generation system, characterized in that: A fuel cell and gas turbine hybrid cycle power generation system as described in any one of claims 5 to 8 is used, characterized in that when the fuel cell and gas turbine engine hybrid cycle power generation system operates in a stable mode, it enters a second operating mode, and the controller sends a signal to control the bypass control valve to select the compressor and the fuel cell subsystem, and closes the auxiliary fuel control valve at the same time; at this time, the gas turbine engine subsystem inhales air from the compressor inlet, and dissipates heat for the starter / generator through the suction effect, and at the same time, the compressed air at the compressor outlet is heated and then enters the secondary heat exchanger for heat exchange, and then is connected to the cathode inlet of the solid oxide fuel cell. The fuel connected to the anode inlet generates electrical energy through electrochemical reaction and is stored in the electrical energy system; the residual oxygen at the cathode outlet of the solid oxide fuel cell and the residual fuel at the anode outlet of the solid oxide fuel cell directly enter the combustion chamber for combustion after heat exchange through the reformer and the secondary heat exchanger, and the high-temperature and high-pressure combustion gas generated drives the turbine of the gas turbine engine to rotate, driving the coaxial compressor and the starter generator to work, the controller sends a starter / generator load loading signal, and the starter / generator starts to output electrical energy and stores it in the electrical energy system; and the exhaust gas at the turbine outlet of the gas turbine engine is discharged into the surrounding atmosphere after cooling.

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