Gas turbine-fuel cell hybrid power system and double-working-medium circulation method thereof

Abstract

The invention discloses a hybrid power system of a gas turbine-fuel cell and a double-working-medium circulation method of the hybrid power system, and belongs to the field of novel hybrid power of gas turbine engines, the system comprises a carbon-free fuel storage tank, a solid oxide fuel cell and a gas turbine engine, the carbon-free fuel storage tank is respectively connected with the solid oxide fuel cell, the gas turbine engine and the heat exchanger so as to carry out heat exchange on the carbon-free fuel and respectively supply the obtained high-temperature carbon-free fuel into the solid oxide fuel cell and the gas turbine engine for reaction; the gas turbine engine is connected with the solid oxide fuel cell so as to provide an oxidizing agent for the reaction process of the solid oxide fuel cell, and reaction products of the solid oxide fuel cell are supplied into the gas turbine engine to be subjected to dual-fuel combustion with aviation kerosene. The system utilizes the cooling medium to strengthen cooling heat exchange and prevent coking, and improves the combined cycle heat efficiency and propulsive efficiency of the engine.

Description

Technical Field

[0001] The present invention relates to the technical field of novel hybrid power of gas turbine engines, and in particular to a hybrid power system of a gas turbine-fuel cell based on carbon-free fuel and a dual-working-fluid circulation method thereof. Background Art

[0002] Future multi-electric power systems face multiple technical challenges, including high incoming flow velocity, high temperature rise combustion, and high power extraction. Especially for high-performance engines that fly at high speeds, improving the Brayton cycle efficiency is an important means to improve engine performance. Among the relevant technologies, the best solution to improve the efficiency of the Brayton cycle is to use intercooling, heat recovery and other solutions to improve the efficiency of the cycle itself, and these solutions have been widely used in actual systems. However, the above solutions are unlikely to achieve greater efficiency improvements.

[0003] Increasing turbine inlet temperature is also a key means of improving engine efficiency. Therefore, thermal management solutions such as turbine cooling and cooling the cooling air temperature are essential for increasing turbine inlet temperature. For long-range UAVs, the vehicle's power performance is primarily reflected in high thrust, low fuel consumption, and high power extraction. Improving the power system's power supply can provide sufficient power support for future advanced avionics systems and weapon systems (such as laser weapons). However, current thermal management systems and power generation systems generally fail to meet these requirements.

[0004] Because existing gas turbine engines often use aviation kerosene (Jet Kerosene) or natural gas as fuel, it has also been frequently used as a cooling medium for air-to-oil heat exchange in recent years. However, JET Kerosene is prone to coking at high temperatures, which in turn causes coke product accumulation, increasing flow resistance and ultimately leading to reduced heat transfer capacity within the pipes and even pipe blockage. Furthermore, JET Kerosene also has the problem of high carbon emissions. Therefore, finding a clean cooling medium that can replace JET Kerosene, with high heat sink, flammability, low or even zero carbon emissions, and high heat transfer capacity, has become a key issue in improving engine performance.

[0005] Furthermore, the primary source of power for gas turbine engines is the shaft work generated by turbine expansion, which is primarily used to propel the compressor, though some shaft work can also be extracted for use in the aircraft's remaining power generation systems. Therefore, introducing alternative hybrid propulsion modes and developing combined-cycle propulsion systems to extract more electrical energy and improve Brayton cycle efficiency are key approaches to improving overall aircraft engine performance.

[0006] The power technology using aviation kerosene as cooling medium and fuel mainly has the following problems:

[0007] (1) The efficiency of the Brayton cycle is relatively low. Existing methods such as intercooling and heat recovery are unlikely to significantly improve the cycle efficiency. In addition, existing aerospace heat management and power extraction equipment are unable to meet the development requirements of high-energy-consuming equipment such as future laser weapons.

[0008] (2) The physical heat sink of aviation kerosene is limited, and the utilization of chemical heat sink is limited by the problem of aviation kerosene coking. The pipeline resistance caused by aviation kerosene coking increases sharply and even causes flow blockage. This problem is particularly obvious in microchannel heat exchangers, where coking is easy to occur and difficult to suppress;

[0009] (3) As a hydrocarbon fuel, aviation kerosene has a high carbon emission content and is highly polluting. Its use as a fuel for civil aviation is not conducive to emission reduction. Summary of the Invention

[0010] The present invention provides a gas turbine-fuel cell hybrid power system and a dual-working fluid circulation method thereof, which solves the problems that existing methods for improving the efficiency of the Brayton cycle, such as intercooling and heat recovery, are difficult to substantially improve the cycle efficiency, and that the physical heat of existing aviation kerosene is limited, while the utilization of chemical heat sinks is limited by the coking problem of aviation kerosene, and the pipeline resistance caused by the coking of aviation kerosene increases sharply and may even cause flow blockage.

[0011] A first embodiment of the present invention provides a gas turbine-fuel cell hybrid system, comprising: a carbon-free fuel storage tank, a solid oxide fuel cell, and a gas turbine engine, wherein:

[0012] The carbon-free fuel storage tank is connected to the gas turbine engine via a cooling air path, and is connected to the solid oxide fuel cell via a carbon-free fuel working medium flow path. Heat exchangers are provided on the cooling air path and the carbon-free fuel working medium flow path to perform heat exchange on all carbon-free fuels to obtain a first high-temperature carbon-free fuel and a second high-temperature carbon-free fuel. The first high-temperature carbon-free fuel and the second high-temperature carbon-free fuel are respectively supplied to the solid oxide fuel cell and the gas turbine engine for reaction.

[0013] The gas turbine engine is connected to the solid oxide fuel cell through a fuel cell reaction air path and a reaction product channel to provide an oxidant for the reaction process of the solid oxide fuel cell, and to supply the reaction products of the solid oxide fuel cell to the gas turbine engine for dual-fuel combustion with aviation kerosene.

[0014] Optionally, the carbon-free fuel storage tank supplies the carbon-free fuel to the carbon-free fuel working medium flow path and the cooling air path respectively according to preset distribution requirements.

[0015] Optionally, the heat exchanger exchanges heat with the carbon-free fuel in the carbon-free fuel working medium flow path through high-temperature air from the air inlet or compressor outlet of the gas turbine engine to obtain a first high-temperature carbon-free fuel.

[0016] Optionally, the cooling air path connects the carbon-free fuel storage tank to the air inlet or compressor outlet of the gas turbine engine, and the carbon-free fuel in the cooling air path is heat exchanged through the heat exchanger to obtain a second high-temperature carbon-free fuel, while cooling the high-temperature air at the air inlet or compressor outlet of the gas turbine engine to obtain cooling air.

[0017] Optionally, the cooling air path supplies the cooling air into the gas turbine engine to cool turbine blades and combustion chamber walls of the gas turbine engine.

[0018] Optionally, the reaction product channel supplies the reaction product to a combustion chamber or an afterburner in the gas turbine engine to perform dual-fuel combustion with aviation kerosene as an engine auxiliary fuel.

[0019] The second aspect of the present invention provides a dual-fluid circulation method for a hybrid power system of a gas turbine-fuel cell, comprising the following steps: supplying carbon-free fuel to the carbon-free fuel working fluid flow path and the cooling air path respectively according to preset distribution requirements, and using a heat exchanger to exchange heat with the carbon-free fuel in the carbon-free fuel working fluid flow path and the cooling air path respectively to obtain a first high-temperature carbon-free fuel and a second high-temperature carbon-free fuel; supplying the first high-temperature carbon-free fuel and the second high-temperature carbon-free fuel to a solid oxide fuel cell and a gas turbine engine respectively for reaction, and using the fuel cell reaction air path to provide an oxidant for the solid oxide fuel cell reaction process; introducing the reaction product of the solid oxide fuel cell into the gas turbine engine through a reaction product channel for dual-fuel combustion with aviation kerosene.

[0020] A third aspect of the present invention provides an electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the dual-fluid circulation method of the gas turbine-fuel cell hybrid power system as described in the above embodiment.

[0021] A fourth embodiment of the present invention provides a computer program product, which, when executed by a processor, implements the dual-fluid circulation method of the gas turbine-fuel cell hybrid system as described above.

[0022] A fifth aspect of the present invention provides a non-temporary computer-readable storage medium having a computer program stored thereon. When the computer program is executed by a processor, the dual-fluid circulation method of the gas turbine-fuel cell hybrid power system as described in the above embodiment is implemented.

[0023] The gas turbine-fuel cell hybrid system and dual-medium circulation method thereof according to the embodiments of the present invention achieve at least the following beneficial technical effects:

[0024] Carbon-free fuel is used as a cooling medium and fuel, combined with solid oxide fuel cells. The carbon-free fuel is used as a cooling medium to cool the high-temperature air at the compressor outlet. The high-temperature air at the compressor outlet can be used as cooling air for the subsequent turbine. By lowering the temperature of the cooling air, the amount of cold air used is reduced, and the amount of air available for propulsion is increased. The high-temperature carbon-free fuel that absorbs heat and heats up is used as the reaction raw material of the solid oxide fuel cell to form a hybrid electric propulsion system. The products of the high-temperature carbon-free fuel after decomposition by the solid oxide fuel cell can be used as fuel for the engine, realizing the gas turbine-fuel cell gas power cycle;

[0025] The use of carbon-free fuel can overcome the disadvantage of aviation kerosene coking and reduce pollutants and carbon emissions in terms of combustion;

[0026] The efficiency of the solid oxide fuel cell used can be as high as over 60%. After its introduction, it can improve the overall propulsion efficiency of the system. Combined with the Brayton cycle, it can improve the overall efficiency of the engine cycle and achieve the goal of comprehensive and efficient energy utilization.

[0027] Additional aspects and advantages of the present invention will be set forth in part in the description which follows and, in part, will be obvious from the description which follows, or may be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0029] Figure 1 A schematic structural diagram of a gas turbine-fuel cell hybrid system according to one embodiment of the present invention;

[0030] Figure 2 PV diagram of a Boleiden cycle based on ammonia heat exchange and power extraction cancellation according to one embodiment of the present invention;

[0031] Figure 3 is an enthalpy-temperature diagram based on a solid oxide fuel cell according to one embodiment of the present invention;

[0032] Figure 4A flow chart of a dual-working medium circulation method for a gas turbine-fuel cell hybrid system according to one embodiment of the present invention;

[0033] Figure 5 FIG. 1 is a schematic structural diagram of an electronic device according to an embodiment of the present invention.

[0034] Description of reference numerals:

[0035] 100 - carbon-free fuel storage tank, 200 - solid oxide fuel cell, 300 - gas turbine engine, 400 - heat exchanger, memory 501 , processor 502 and communication interface 503 . DETAILED DESCRIPTION

[0036] The following describes embodiments of the present invention in detail. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present invention, but are not to be construed as limiting the present invention.

[0037] Figure 1 The figure is a schematic structural diagram of a gas turbine-fuel cell hybrid power system provided according to an embodiment of the present invention.

[0038] like Figure 1 As shown, the gas turbine-fuel cell hybrid system includes a carbon-free fuel storage tank 100 , a solid oxide fuel cell 200 and a gas turbine engine 300 .

[0039] The carbon-free fuel storage tank 100 is connected to the gas turbine engine 300 via a cooling air path and to the solid oxide fuel cell 200 via carbon-free fuel working medium flow paths. Heat exchangers 400 are provided in the cooling air path and the carbon-free fuel working medium flow paths to exchange heat with the entire carbon-free fuel, producing a first high-temperature carbon-free fuel and a second high-temperature carbon-free fuel. The first high-temperature carbon-free fuel and the second high-temperature carbon-free fuel are then fed into the solid oxide fuel cell 200 and the gas turbine engine 300, respectively, for reaction. The gas turbine engine 300 is connected to the solid oxide fuel cell 200 via a fuel cell reaction air path and a reaction product channel to provide an oxidant for the reaction process of the solid oxide fuel cell 200. The reaction products of the solid oxide fuel cell 200 are then fed into the gas turbine engine 300 for dual-fuel combustion with aviation kerosene.

[0040] In some embodiments, the carbon-free fuel stored in the carbon-free fuel storage tank 100 may include, but is not limited to, ammonia, hydrogen, and other fuels. Ammonia, hydrogen, and other fuels, when used as both the system's cooling fluid and fuel, have higher physical heat sinks and latent heats of phase change than jet fuel, are free of coking issues, and represent a new type of clean fuel. For example, ammonia reacts and decomposes in a fuel cell, ultimately producing nitrogen and hydrogen. Under sufficiently high reaction temperatures, essentially no nitrogen oxides are generated. Therefore, a power system using carbon-free fuels as both the cooling fluid and fuel can achieve essentially zero carbon emissions. Therefore, carbon-free fuels are more suitable as a medium for gas turbine heat exchangers than traditional jet fuel.

[0041] Therefore, for cooling, the present invention uses carbon-free fuel as the cooling medium, overcoming the coking disadvantage of existing aviation kerosene heat exchange. Furthermore, it reduces pollutants and carbon emissions. Furthermore, for safety, if ammonia is used as a new fuel, decomposed hydrogen can be used as fuel, avoiding the need to directly carry hydrogen.

[0042] In some embodiments, the solid oxide fuel cell SOFC used in the embodiments of the present invention has a power generation efficiency of more than 60%, which can provide auxiliary energy for other electronic equipment of the aircraft or serve as electric propulsion cruise, and ultimately ensure that the shaft work of the turbine is mainly used to provide power and thrust for the compressor, and a variety of fuels can also be used as anode reactants. For example, the SOFC using ammonia as fuel can react after decomposition at the anode, reducing the complexity of the system; in addition, the ammonia SOFC is easy to use with the engine, and the density of liquid ammonia is the same as that of aviation kerosene, which is easy to carry and can significantly reduce weight compared to the battery system. Therefore, the heat exchange and power generation system using carbon-free fuel as the medium is suitable for multi-electric high-speed power requirements.

[0043] Furthermore, the embodiments of the present invention construct a high-efficiency thermal management and power system by coupling the efficient heat exchange capability of carbon-free fuels and the efficient power generation capability of solid oxide fuel cells. This can develop thermal management and power generation control strategies under multiple operating conditions, thereby solving the cooling and power extraction problems of multi-electric power systems.

[0044] In some embodiments, the carbon-free fuel storage tank 100 divides the carbon-free fuel into a first carbon-free fuel and a second carbon-free fuel according to preset distribution requirements, supplies the first carbon-free fuel into the carbon-free fuel working fluid flow path, and supplies the second carbon-free fuel into the cooling air path.

[0045] Furthermore, the heat exchanger 400 exchanges heat with the first carbon-free fuel in the carbon-free fuel working fluid flow path through the high-temperature air of the air inlet or compressor outlet of the gas turbine engine 300 to obtain the first high-temperature carbon-free fuel; the cooling air path connects the carbon-free fuel storage tank 100 with the air inlet or compressor outlet of the gas turbine engine 300, and exchanges heat with the second carbon-free fuel in the cooling air path through the heat exchanger 400 to obtain the second high-temperature carbon-free fuel, while cooling the high-temperature air of the air inlet or compressor outlet of the gas turbine engine 300 to obtain cooling air.

[0046] It should be noted that after the high-temperature air from the air inlet or compressor outlet of the gas turbine engine 300 is heat exchanged with the second carbon-free fuel, the cooling air obtained after the heat exchange is supplied to the gas turbine engine 300 through the cooling air path to cool the turbine blades and combustion chamber walls of the gas turbine engine 300. By lowering the temperature of the cooling air, the purpose of reducing the amount of cold air used and increasing the amount of air available for propulsion is achieved.

[0047] Furthermore, after obtaining the first high-temperature carbon-free fuel and the second high-temperature carbon-free fuel, the first high-temperature carbon-free fuel is supplied to the solid oxide fuel cell 200 for chemical reaction. At the same time, the fuel cell reaction air path obtains an oxidant from the incoming air of the gas turbine engine 300 and supplies it to the solid oxide fuel cell 200 to assist the chemical reaction process of the solid oxide fuel cell 200 and supply the second high-temperature carbon-free fuel to the gas turbine engine 300 for combustion.

[0048] In some embodiments, the reaction product channel supplies the reaction products of the solid oxide fuel cell 200 to a combustion chamber or an afterburner in the gas turbine engine 300 to perform dual-fuel combustion with aviation kerosene as an engine auxiliary fuel.

[0049] The following is a detailed description of the working process of the gas turbine-fuel cell hybrid system proposed in the embodiment of the present invention.

[0050] The carbon-free fuel in the carbon-free fuel storage tank 100 is used as a cooling medium and fuel. A portion of the carbon-free fuel passes through the heat exchanger 400 and the cooling air path to cool the air outlet of the gas turbine engine 300 or the high-temperature air outlet of the cooling compressor, and the high-temperature carbon-free fuel that absorbs heat and heats up is obtained as a combustion raw material for the product after the fuel cell reaction. The other portion of the carbon-free fuel passes through the heat exchanger 400 and the carbon-free fuel working medium flow path to obtain the high-temperature carbon-free fuel that absorbs heat and heats up, and the high-temperature carbon-free fuel that absorbs heat and heats up is supplied to the solid oxide fuel cell 200 for reaction. During the reaction process of the solid oxide fuel cell 200, the fuel cell reaction air path The corresponding air is obtained from the gas turbine engine 300 to provide it with an oxidant, and then the reaction product channel supplies the reaction product of the solid oxide fuel cell 200 to the gas turbine engine 300 for dual-fuel combustion with aviation kerosene, thereby realizing the gas power cycle of the gas turbine-fuel cell. Since the efficiency of the solid oxide fuel cell can be as high as 60% or more, combined with the Brayton cycle, the efficiency of the engine cycle can be improved as a whole, achieving the goal of comprehensive and efficient utilization of energy. In addition, the introduction of the solid oxide fuel cell can improve the propulsion efficiency of the system as a whole and provide power for other avionics equipment of the aircraft.

[0051] The effect of the gas turbine-fuel cell hybrid power system proposed in the present invention will be further described below through a specific embodiment.

[0052] Ammonia is chosen as the carbon-free fuel. The system mainly consists of two cycles. The first is a Brayton cycle based on the air flowing from the engine, and the second is an air cycle based on the solid oxide fuel cell.

[0053] Air Brayton cycle: The incoming air is compressed by isentropic compression in the aircraft engine ( Figure 2 0-3), isobaric heat absorption, that is, combustion process ( Figure 2 3-4). Then the air engine expands isoentropically ( Figure 2 4-9).

[0054] During the air cycle, at the high-pressure compressor outlet, a portion of the total air is extracted as cooling air. This portion of air is cooled by 150-200K by the ammonia working fluid. Due to the improvement effect of the cooling bleed air temperature drop and the increase in the turbine inlet temperature Tt4, the effective work and thermal efficiency of the cycle are significantly improved.

[0055] Fuel cell air circulation: Figure 3 As shown, its purpose is to use fan bleed air and ammonia as reaction gas, and discharge the hydrogen-containing tail gas after the fuel cell reaction into the combustion chamber as fuel for combustion. The thermodynamic process is described as follows: Figure 3As shown, point 1 is the reactant inlet. After absorbing heat, its temperature and enthalpy increase to reach the desired reaction state (heat absorption is DH0), which is point 2. The process from points 2 to 3 is a chemical reaction. The total enthalpy difference during this process is DH1 (used for internal fuel cell thermal management) + DH2 (used for power generation). These two components can be considered the total energy released by the reaction. This reaction is approximately isothermal, so the enthalpy decreases, but the temperatures at points 2 and 3 remain unchanged.

[0056] In summary, the gas turbine-fuel cell hybrid system of the embodiment of the present invention uses a fuel cell as an important source of electrical energy for the aircraft, maximizing the application of the engine turbine's shaft power to the aircraft propulsion system. The hybrid propulsion system can achieve a performance improvement of approximately 2.5% in thrust, approximately 4% in thermal efficiency, and approximately 5% in fuel consumption compared to the original fuel-fueled turbofan engine system. New fuels (ammonia, hydrogen, etc.) are used as cooling media for the high-temperature air at the gas turbine engine airway outlet or the cooling compressor outlet. The heat transfer performance of ammonia or hydrogen is better than that of aviation kerosene. Using this new fuel as a cooling medium is beneficial for improving the compactness of the heat exchanger and avoiding the coking problem of aviation kerosene. If ammonia is used as the new fuel, the hydrogen produced after the reaction in the solid oxide fuel cell can be burned as fuel. Hydrogen has the advantages of high calorific value and easy combustion, but it itself has the risks of low safety and easy leakage. This can avoid the problems of low safety and easy leakage caused by directly carrying hydrogen.

[0057] Next, a dual-medium circulation method of a gas turbine-fuel cell hybrid power system according to an embodiment of the present invention will be described with reference to the accompanying drawings.

[0058] Figure 4 The present invention provides a flow chart of a dual-working medium circulation method for a gas turbine-fuel cell hybrid power system according to an embodiment of the present invention.

[0059] like Figure 4 As shown, the dual-working medium cycle method of the gas turbine-fuel cell hybrid system includes the following steps:

[0060] In step S401, the carbon-free fuel is supplied to the carbon-free fuel working fluid flow path and the cooling air path respectively according to the preset distribution requirements, and the carbon-free fuel in the carbon-free fuel working fluid flow path and the cooling air path is heat exchanged by a heat exchanger to obtain a first high-temperature carbon-free fuel and a second high-temperature carbon-free fuel.

[0061] In step S402, the first high-temperature carbon-free fuel and the second high-temperature carbon-free fuel are respectively fed into the solid oxide fuel cell and the gas turbine engine for reaction, and the fuel cell reaction air path is used to provide an oxidant for the solid oxide fuel cell reaction process.

[0062] In step S403, the reaction product of the solid oxide fuel cell is introduced into the gas turbine engine through the reaction product channel to perform dual-fuel combustion with aviation kerosene.

[0063] It should be noted that the aforementioned explanation of the embodiment of the gas turbine-fuel cell hybrid system is also applicable to the dual-working medium circulation method of the gas turbine-fuel cell hybrid system of this embodiment, and will not be repeated here.

[0064] The dual-fluid circulation method of the gas turbine-fuel cell hybrid power system of the embodiment of the present invention uses carbon-free fuel as the cooling medium and combustion medium, and combines the gas turbine and fuel cell circulation. The carbon-free fuel is used as the cooling medium to enhance cooling heat exchange and prevent coking, thereby improving the ultimate goal of improving the thermal efficiency and propulsion efficiency of the engine combined cycle. It has positive significance for aviation engine thermal management, comprehensive energy utilization, and reduction of emission pollution.

[0065] Figure 5 This is a schematic diagram of the structure of an electronic device provided by an embodiment of the present invention. The electronic device may include:

[0066] Memory 501 , processor 502 , and computer programs stored in the memory 501 and executable on the processor 502 .

[0067] When the processor 502 executes the program, the dual-working medium cycle method of the gas turbine-fuel cell hybrid system provided in the above embodiment is implemented.

[0068] Furthermore, the electronic device further includes:

[0069] The communication interface 503 is used for communication between the memory 501 and the processor 502 .

[0070] The memory 501 is used to store computer programs that can be run on the processor 502 .

[0071] The memory 501 may include a high-speed RAM memory, and may also include a non-volatile memory (non-volatile memory), such as at least one disk memory.

[0072] If the memory 501, processor 502, and communication interface 503 are implemented independently, the communication interface 503, memory 501, and processor 502 can be connected to each other via a bus and communicate with each other. The bus can be an Industry Standard Architecture (ISA) bus, a Peripheral Component Interconnect (PCI) bus, or an Extended Industry Standard Architecture (EISA) bus. The bus can be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 5 Only one thick line is used in the diagram, but this does not mean that there is only one bus or one type of bus.

[0073] Optionally, in a specific implementation, if the memory 501, the processor 502 and the communication interface 503 are integrated on a chip, the memory 501, the processor 502 and the communication interface 503 can communicate with each other through an internal interface.

[0074] The processor 502 may be a central processing unit (CPU), an application specific integrated circuit (ASIC), or one or more integrated circuits configured to implement the embodiments of the present invention.

[0075] An embodiment of the present invention further provides a computer program product, which, when executed by a processor, implements the dual-working-fluid cycle method of the gas turbine-fuel cell hybrid power system.

[0076] An embodiment of the present invention further provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the dual-medium circulation method of the gas turbine-fuel cell hybrid power system as described above.

[0077] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or N embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples without contradiction.

[0078] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of technical features indicated. Thus, a feature specified as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "N" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0079] Any process or method description in a flowchart or otherwise described herein may be understood to represent a module, segment or portion of code comprising one or N executable instructions for implementing a custom logical function or step of a process, and the scope of the preferred embodiments of the present invention includes alternative implementations in which functions may be performed out of the order shown or discussed, including performing functions in a substantially simultaneous manner or in the reverse order depending on the functions involved, which should be understood by those skilled in the art to which the embodiments of the present invention pertain.

[0080] The logic and / or steps represented in the flowcharts or otherwise described herein, for example, can be considered as a sequenced list of executable instructions for implementing the logical functions, and can be embodied in any computer-readable medium for use by, or in conjunction with, an instruction execution system, apparatus, or device (e.g., a computer-based system, a system including a processor, or other system that can fetch and execute instructions from an instruction execution system, apparatus, or device). For purposes of this specification, a "computer-readable medium" can be any device that can contain, store, communicate, propagate, or transport a program for use by, or in conjunction with, an instruction execution system, apparatus, or device. More specific examples (a non-exhaustive list) of computer-readable media include the following: an electrical connection with one or N wires (electronic devices), a portable computer disk cartridge (magnetic device), random access memory (RAM), read-only memory (ROM), erasable and programmable read-only memory (EPROM or flash memory), fiber optic devices, and a portable compact disc read-only memory (CDROM). In addition, the computer-readable medium may even be paper or other suitable medium on which the program is printed, since the program can be obtained electronically by optically scanning the paper or other medium and then editing, interpreting or processing it in other suitable ways as necessary, and then storing it in a computer memory.

[0081] It should be understood that various parts of the present invention can be implemented using hardware, software, firmware, or a combination thereof. In the above embodiment, the N steps or methods can be implemented using software or firmware stored in a memory and executed by a suitable instruction execution system. If implemented using hardware, as in another embodiment, any one of the following technologies known in the art or a combination thereof can be used: a discrete logic circuit having logic gate circuits for implementing logic functions on data signals, an application-specific integrated circuit having suitable combinational logic gate circuits, a programmable gate array (PGA), a field programmable gate array (FPGA), etc.

[0082] Those skilled in the art will understand that all or part of the steps in the method of the above embodiment can be completed by instructing related hardware through a program, and the program can be stored in a computer-readable storage medium. When the program is executed, it includes one or a combination of the steps of the method embodiment.

[0083] In addition, the functional units in the various embodiments of the present invention may be integrated into a single processing module, or each unit may exist physically separately, or two or more units may be integrated into a single module. The aforementioned integrated modules may be implemented in the form of hardware or in the form of software functional modules. If the integrated modules are implemented in the form of software functional modules and sold or used as independent products, they may also be stored in a computer-readable storage medium.

[0084] The storage medium mentioned above may be a read-only memory, a magnetic disk, or an optical disk, etc. Although the embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and are not to be construed as limiting the present invention. Persons skilled in the art may make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

Claims

1. A gas turbine-fuel cell hybrid system, characterized in that: include: Carbon-free fuel storage tanks, solid oxide fuel cells, and gas turbine engines, among others. The carbon-free fuel storage tank is connected to the gas turbine engine via a cooling air path, and is connected to the solid oxide fuel cell via a carbon-free fuel working medium flow path. Heat exchangers are provided on the cooling air path and the carbon-free fuel working medium flow path to perform heat exchange on all carbon-free fuels to obtain a first high-temperature carbon-free fuel and a second high-temperature carbon-free fuel. The first high-temperature carbon-free fuel and the second high-temperature carbon-free fuel are respectively supplied to the solid oxide fuel cell and the gas turbine engine for reaction. The gas turbine engine is connected to the solid oxide fuel cell through a fuel cell reaction air path and a reaction product channel to provide an oxidant for the reaction process of the solid oxide fuel cell, and to supply the reaction products of the solid oxide fuel cell to the gas turbine engine for dual-fuel combustion with aviation kerosene.

2. The gas turbine-fuel cell hybrid system according to claim 1, characterized in that: The carbon-free fuel storage tank supplies the carbon-free fuel to the carbon-free fuel working medium flow path and the cooling air path respectively according to preset distribution requirements.

3. The gas turbine-fuel cell hybrid system according to claim 1, characterized in that: The heat exchanger exchanges heat with the carbon-free fuel in the carbon-free fuel working medium flow path through the high-temperature air from the air inlet or the compressor outlet of the gas turbine engine to obtain a first high-temperature carbon-free fuel.

4. The gas turbine-fuel cell hybrid system according to claim 1, characterized in that: The cooling air path connects the carbon-free fuel storage tank with the air inlet or compressor outlet of the gas turbine engine, and the carbon-free fuel in the cooling air path is heat exchanged through the heat exchanger to obtain a second high-temperature carbon-free fuel, while the high-temperature air at the air inlet or compressor outlet of the gas turbine engine is cooled to obtain cooling air.

5. The gas turbine-fuel cell hybrid system according to claim 4, characterized in that: The cooling air path supplies the cooling air into the gas turbine engine to cool turbine blades and combustion chamber walls of the gas turbine engine.

6. The gas turbine-fuel cell hybrid system according to claim 1, characterized in that: The reaction product channel supplies the reaction product to a combustion chamber or an afterburner in the gas turbine engine so as to be used as an engine auxiliary fuel for dual fuel combustion with aviation kerosene.

7. A dual-medium circulation method for a gas turbine-fuel cell hybrid system, characterized in that: A gas turbine-fuel cell hybrid system according to any one of claims 1 to 6 comprises the following steps: Supplying the carbon-free fuel into the carbon-free fuel working medium flow path and the cooling air path respectively according to a preset distribution requirement, and using a heat exchanger to exchange heat with the carbon-free fuel in the carbon-free fuel working medium flow path and the cooling air path respectively to obtain a first high-temperature carbon-free fuel and a second high-temperature carbon-free fuel; Supplying the first high-temperature carbon-free fuel and the second high-temperature carbon-free fuel to a solid oxide fuel cell and a gas turbine engine respectively for reaction, and utilizing the fuel cell reaction air path to provide an oxidant for the solid oxide fuel cell reaction process; The reaction product of the solid oxide fuel cell is introduced into the gas turbine engine through a reaction product channel to perform dual fuel combustion with aviation kerosene.

8. An electronic device, characterized in that: The invention comprises a memory, a processor and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the dual-working medium circulation method of the hybrid power system of the gas turbine-fuel cell as claimed in claim 7 is implemented.

9. A computer program product, characterized in that When the computer program / instruction is executed by a processor, the dual-working medium cycle method of the gas turbine-fuel cell hybrid system according to claim 7 is implemented.

10. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the dual-medium cycle method of the gas turbine-fuel cell hybrid system according to claim 7 is implemented.

Images