CN110608108B - Non-turbine jet engine integrated with solid oxide fuel cell - Google Patents
Non-turbine jet engine integrated with solid oxide fuel cell Download PDFInfo
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- CN110608108B CN110608108B CN201810614227.3A CN201810614227A CN110608108B CN 110608108 B CN110608108 B CN 110608108B CN 201810614227 A CN201810614227 A CN 201810614227A CN 110608108 B CN110608108 B CN 110608108B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/06—Combination of fuel cells with means for production of reactants or for treatment of residues
- H01M8/0606—Combination of fuel cells with means for production of reactants or for treatment of residues with means for production of gaseous reactants
- H01M8/0612—Combination of fuel cells with means for production of reactants or for treatment of residues with means for production of gaseous reactants from carbon-containing material
- H01M8/0618—Reforming processes, e.g. autothermal, partial oxidation or steam reforming
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/30—Hydrogen technology
- Y02E60/50—Fuel cells
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Abstract
The invention provides a non-turbine jet engine integrated with a solid oxide fuel cell, which comprises a partial oxidation reformer, a solid oxide fuel cell system and an airplane propulsion system, wherein a direct current motor drives a gas compressor through a connecting shaft, the partial oxidation reformer is arranged behind the direct current motor, and the solid oxide fuel cell system, a combustion chamber and a spray pipe are sequentially connected. The invention utilizes the solid oxide fuel cell to generate electricity to drive the direct current motor, and then the direct current motor is connected with the shaft to drive the gas compressor to work, thereby canceling the traditional turbine and solving the problems of difficult matching between the gas compressor and the turbine, poor performance under variable working conditions and the like; after the turbine is eliminated, the pressure ratio and the temperature ratio of the engine are not limited by the power distribution of the turbine and the temperature before the turbine, so that the power of the engine is improved. The invention also solves the problems of high fuel consumption rate and high air pollutant emission content of the traditional aircraft engine by utilizing the advantages of high thermal efficiency and less pollutant gas emission of the solid oxide fuel cell.
Description
Technical Field
The invention relates to a jet engine, in particular to a non-turbine jet engine integrated with a solid oxide fuel cell, and belongs to the technical field of aircraft propulsion systems.
Background
At present, the propulsion system of the airplane has lower thermal efficiency, high oil consumption, higher nitrogen oxide emission and more serious pollution to the environment, so that the development of new energy and the design of a new propulsion system are more important contents at present.
The traditional gas turbine aeroengine converts the chemical energy of fuel into mechanical energy to generate propulsive work, so that the energy loss is great, and the efficiency is only about 35%; the solid oxide fuel cell has the efficiency of about 50 percent, can convert the chemical energy of the fuel into electric energy, improves the efficiency of the system, is very environment-friendly, and has important significance for the current waste gas pollution. Hydrogen is a very friendly fuel, which has high energy and does not pollute the environment, but has great problems in wide use due to low volume energy density and inconvenient carrying. Therefore, considering both the advantages of high hydrogen energy and no environmental pollution and the problem of sources, the idea of using the partial oxidation reformer to catalytically reform the fuel to generate reformed gas mainly comprising hydrogen for the solid oxide fuel cell is one way to solve the problem, and the way is more economical for long-endurance aircraft.
When a traditional gas turbine aircraft engine works normally, two thirds of the power of the turbine is used for driving the gas compressor, the other one third of the power is output power, and the gas compressor needs to be driven by the turbine to do work. The two are mutually influenced and restricted in the working process, the matching is difficult, the performance of the engine is influenced to a great extent, the performance of variable working conditions is poor easily, and the energy consumption is high.
Disclosure of Invention
The invention aims to solve the problems that when a traditional gas turbine aircraft engine works normally, two thirds of the power of a turbine is used for driving a gas compressor, the other one third of the power is output power, the gas compressor needs to be driven by the work of the turbine, the two are mutually influenced and restricted in the working process, the matching is difficult, the performance of the engine is influenced to a great extent, the performance of variable working conditions is poor, and the energy consumption is high; the pressure ratio and the temperature ratio of the engine are limited by the power distribution of the turbine and the temperature before the turbine, so that the power of the engine is not high, the fuel consumption rate of the traditional aircraft engine is high, and the emission content of air pollutants is high.
To achieve the purpose, the invention provides a non-turbine jet engine integrated with a solid oxide fuel cell, which comprises an air inlet channel, a fuel delivery pump, a partial oxidation reformer, a solid oxide fuel cell system, an aircraft propulsion system, an air delivery passage and a fuel delivery passage, wherein the aircraft propulsion system comprises an air compressor, a combustion chamber, a direct current motor, a connecting shaft and a spray pipe;
the gas inlet channel is arranged on the upper side and the lower side of the front end of the gas compressor, the direct current motor drives the gas compressor through a connecting shaft, the partial oxidation reformer is arranged behind the direct current motor, and the solid oxide fuel cell system, the combustion chamber and the spray pipe are sequentially connected; the air conveying passage is formed by that air enters through an air inlet channel, is compressed by an air compressor and then is divided into two parts, one part is sent to the partial oxidation reformer, and the other part flows from the outside of the partial oxidation reformer and enters the solid oxide fuel cell system; the fuel oil conveying passage is used for conveying the fuel oil to the partial oxidation reformer to perform reforming reaction with air in the partial oxidation reformer by flowing through the outer wall of the direct current motor through the fuel oil conveying pump.
Preferably, the air inlet channel is arranged on the periphery of the front end of the compressor.
Preferably, the fuel delivery pump is located above the connecting shaft, the direct current motor needs to be cooled in a working state, and fuel flows through the direct current motor shell through the fuel delivery pump to reduce the temperature of the direct current motor in working.
Preferably, the solid oxide fuel cell system generates electrochemical reaction, outputs direct current and supplies electric energy to the direct current motor through an electric wire.
Preferably, the solid oxide fuel cell system is formed by combining a plurality of cell stacks, the cells in each cell stack are combined in series, and air and reformed gas enter the solid oxide fuel cell system and are distributed to each cell to generate electrochemical reaction to generate direct current.
Preferably, the partial oxidation reformer comprises an air inlet, a fuel inlet, a catalyst and a reformed gas outlet, the partial oxidation reformer adopts a tubular reactor, the front end of the partial oxidation reformer is provided with the fuel inlet and the air inlet, the air inlet is positioned at the outer ring of the fuel inlet, the middle part of the partial oxidation reformer is filled with the nickel-based catalyst, and the rear end of the partial oxidation reformer is provided with the reformed gas outlet.
Preferably, the solid oxide fuel cell system includes a cathode inlet, an anode inlet, and an anode-electrolyte-cathode assembly, the anode-electrolyte-cathode assembly penetrates the entire solid oxide fuel cell system in a circular tube shape, the anode inlet is located inside the anode-electrolyte-cathode assembly, and the cathode inlet is located at the outer circumference of the anode-electrolyte-cathode assembly.
Preferably, the reformed gas outlet is collected and transported to an anode inlet of the solid oxide fuel cell system through a pipeline.
Preferably, the air conveying passage is divided into two parts after air enters the compressor through an air inlet channel and is compressed, one part is sent to an air inlet of the partial oxidation reformer, and the other part flows from the outside of the partial oxidation reformer to a cathode inlet of the solid oxide fuel cell system.
Preferably, the fuel delivery path is formed by the way that fuel flows through the shell of the direct current motor through the fuel delivery pump, the temperature of the fuel is increased, and the fuel is sent to the fuel inlet of the partial oxidation reformer to perform reforming reaction with air in the partial oxidation reformer.
The operating principle of the non-turbine jet engine integrated with the solid oxide fuel cell is as follows:
the invention does not adopt the traditional turbine to drive the compressor to work, but utilizes the electric energy of the fuel cell to directly drive the compressor to work through the motor, so that the compressor and the turbine are decoupled, and the complex matching process is changed; meanwhile, the traditional aircraft engine mainly adopts turbine expansion to convert internal energy of gas into mechanical energy, then generates thrust to the gas through a tail nozzle or outputs work through a power turbine to realize the propulsion of an airplane, and for the engine generating the thrust by jet, the tail nozzle and the turbine can provide the same function to a certain extent in the aspect of propulsion, so that when the driving problem of a gas compressor is solved, the turbine can be considered to be completely removed, and the tail nozzle is used as a part generating the power to realize the acceleration of air flow to generate the thrust, thereby improving the total efficiency of the system.
The non-turbine jet engine integrated with the solid oxide fuel cell has the beneficial effects that:
(1) compared with the traditional gas turbine aircraft engine, the invention structurally cancels the turbine, thereby changing the mode that the turbine drives the compressor to work. Direct current generated by a fuel cell drives a direct current motor, the direct current motor is directly connected with a compressor through a connecting shaft to work, and the compressor only needs to be changed by the motor when in a working state, so that decoupling of the compressor and the turbine is realized, the problem of difficult matching of the compressor and the turbine is solved, the working process is more flexible, and the efficiency is improved.
(2) The invention has the advantages that the structure of the invention cancels the turbine, the direct current motor is used for driving the air compressor, the pressure ratio and the temperature ratio of the engine are not limited by the power distribution of the turbine and the temperature in front of the turbine, and the power of the engine is improved.
(3) The invention solves the problems of high fuel consumption rate and high air pollutant emission content of the traditional aircraft engine by utilizing the advantages of high thermal efficiency and less pollutant gas emission of the solid oxide fuel cell.
(4) The invention reforms macromolecular fuel by partial oxidation reforming to obtain hydrogen-based micromolecular hydrocarbon, realizes the obtaining of reaction gas for fuel cells on an airplane, and solves the difficulty of directly carrying hydrogen. Meanwhile, a partial oxidation reforming mode is adopted on the airplane, and the volume and the mass are greatly reduced because extra water is not required to be carried; the method is an exothermic reaction, does not need to heat the reaction, saves additional equipment, reduces occupied space, has quick partial oxidation reforming reaction, can meet the demand of a fuel cell for reformed gas, and solves the problems of difficult installation and the like caused by compact space of an airplane.
(5) The jet pipe is used as a main part for generating thrust, the jet pipe is directly used for accelerating high-temperature gas, the aircraft is propelled by utilizing the reaction force of airflow, the combination form of a turbine and a tail jet pipe is cancelled, the weight is reduced, and the problem that the working processes of the tail jet pipe and the turbine are mutually influenced is solved.
Drawings
Fig. 1 is a schematic diagram of a non-turbine jet engine integrated with a solid oxide fuel cell according to the present invention;
FIG. 2 is a schematic diagram of the operating principle of the partial oxidation reformer according to the present invention;
FIG. 3 is a schematic diagram of the operating principle of the solid oxide fuel cell according to the present invention;
in the figure: 1-an air inlet channel; 2, an air compressor; 3-connecting the shaft; 4-a fuel delivery pump; 5-a direct current motor; 6-partial oxidation reformer; 7-solid oxide fuel cells; 8-a combustion chamber; 9-a spray pipe; 10-an electrical wire; 11-an air inlet; 12-a fuel inlet; 13-a catalyst; 14-cathode inlet; 15-anode inlet; 16-anode-electrolyte-cathode assembly.
Detailed Description
The following detailed description of embodiments of the invention is provided in conjunction with the appended drawings:
the first embodiment is as follows: the present embodiment is explained with reference to fig. 1 to 3. The non-turbine jet engine integrated with the solid oxide fuel cell in the embodiment comprises a partial oxidation reformer 6, a solid oxide fuel cell system 7, an aircraft propulsion system, an air delivery passage and a fuel delivery passage, wherein the aircraft propulsion system comprises a gas compressor 2, a combustion chamber 8, a direct current motor 5, a connecting shaft 3 and a spray pipe 9;
the direct current motor 5 drives the compressor 2 through the connecting shaft 3, the partial oxidation reformer 6 is arranged behind the direct current motor 5, and the solid oxide fuel cell system 7, the combustion chamber 8 and the spray pipe 9 are sequentially connected; the air conveying passage is formed by that air enters through an air inlet channel 1, is compressed by an air compressor 2 and then is divided into two parts, one part is sent to a partial oxidation reformer 6, and the other part flows from the outside of the partial oxidation reformer 6 and enters a solid oxide fuel cell system 7; the fuel oil conveying path is that the fuel oil flows through the outer wall of the direct current motor 5 through the fuel oil conveying pump 4, is sent to the partial oxidation reformer 6 and carries out reforming reaction with air in the partial oxidation reformer 6.
The direct current motor 5 is connected with the compressor 2 through the connecting shaft 3, directly drives the compressor 2 to work, and structurally cancels a turbine, so that the compressor 2 works more flexibly.
And tail gas and unreacted gas of the solid oxide fuel cell 7 enter a combustion chamber 8 for combustion, generated high-temperature fuel gas enters a spray pipe 9, is accelerated in the spray pipe 9 to generate thrust to push the airplane to move forward, and finally the tail gas is discharged into the atmosphere.
The air inlet channel 1 is arranged on the periphery of the front end of the air compressor 2.
The air inlet channel 1 belongs to an air conveying passage and is used for the inlet of air at the front end of a fuel cell propulsion system.
The fuel oil delivery pump 4 is positioned above the connecting shaft 3, the direct current motor 5 needs to be cooled in a working state, and fuel oil flows through the shell of the direct current motor 5 through the fuel oil delivery pump 4 to lower the temperature of the direct current motor 5 in working.
The solid oxide fuel cell system 7 generates electrochemical reaction, outputs direct current to supply electric energy to the direct current motor 5 through the electric wire 10, and the direct current motor 5 converts the electric energy from the solid oxide fuel cell 7 into mechanical energy.
The solid oxide fuel cell system 7 is formed by combining a plurality of cell stacks, the cells in each cell stack are combined in series, air and reformed gas enter the solid oxide fuel cell system 7 and are distributed to each cell, electrochemical reaction is carried out to generate direct current, and a high-power generation system can be obtained by connecting the cell stacks in series.
The partial oxidation reformer 6 comprises an air inlet 11, a fuel inlet 12, a catalyst 13 and a reformed gas outlet, the partial oxidation reformer 6 adopts a tubular reactor, the front end of the partial oxidation reformer 6 is provided with the fuel inlet 12 and the air inlet 11, the air inlet 11 is positioned at the outer ring of the fuel inlet 12, the middle part of the partial oxidation reformer 6 is provided with the nickel-based catalyst 13, and the rear end of the partial oxidation reformer 6 is provided with the reformed gas outlet.
The solid oxide fuel cell system 7 comprises a cathode inlet 14, an anode inlet 15 and an anode-electrolyte-cathode assembly 16, wherein the anode-electrolyte-cathode assembly 16 penetrates through the solid oxide fuel cell system 7 in a circular tube shape, the anode inlet 15 is positioned inside the anode-electrolyte-cathode assembly 16, and the cathode inlet 14 is positioned on the periphery of the anode-electrolyte-cathode assembly 16.
The solid oxide fuel cell 7 has a tubular structure, and uses an anode-electrolyte-cathode assembly 16 as a structure for reaction, wherein the inner layer of the anode-electrolyte-cathode assembly 16 is an anode, and the outer layer is a cathode. The anode inlet 15 of the solid oxide fuel cell 7 is fed with the reformed gas from the partial oxidation reformer 6, and the cathode inlet 14 of the solid oxide fuel cell 7 is fed with the air compressed by the compressor 2.
The reformate gas outlet is piped to the anode inlet 15 of the solid oxide fuel cell system 7.
The air conveying path is divided into two parts after air enters the compressor 2 through the air inlet 1 and is compressed, one part is sent to the air inlet 11 of the partial oxidation reformer 6, and the other part flows through the cathode inlet 14 of the partial oxidation reformer 6 and enters the solid oxide fuel cell system 7, and electrochemical reaction is carried out between the air conveying path and reformed gas in the solid oxide fuel cell 7.
The fuel oil is conveyed through the shell of the direct current motor 5 by the fuel oil conveying pump 4, the temperature of the fuel oil is increased, and the fuel oil is conveyed to the fuel oil inlet 12 of the partial oxidation reformer 6 to carry out reforming reaction with air in the partial oxidation reformer 6.
After the fuel oil passes through the fuel transfer pump 4 and the outer wall of the direct current motor 5 to be cooled, the temperature of the fuel oil is increased and is sent to a fuel oil inlet 12 of the partial oxidation reformer 6, the fuel oil is uniformly mixed with air in the reformer 6 and then carries out reforming reaction under the action of a catalyst 13, macromolecular fuel is reformed into reformed gas mainly comprising hydrogen and is sent to an anode inlet of the solid oxide fuel cell 7, and electrochemical reaction is carried out in the solid oxide fuel cell 7 to generate current.
The specific operation process and the working principle of the non-turbine jet engine integrated with the solid oxide fuel cell are as follows:
air from the atmosphere enters an air inlet channel 1, is compressed by an air compressor 2 and then is divided into two parts, wherein one part of air is sent to an air inlet of a partial oxidation reformer 6, and the other part of air flows through the outer wall of the partial oxidation reformer 6 and enters a cathode inlet 14 of a solid oxide fuel cell 7; fuel oil from the oil storage tank is firstly sent to the outer wall of the direct current motor 5 through the fuel transfer pump 4, the direct current motor 5 is cooled and then sent to the fuel oil inlet 12 of the partial oxidation reformer 6, the fuel oil and air in the reformer 6 are uniformly mixed and then carry out reforming reaction under the action of the catalyst 13, macromolecule fuel is reformed into reformed gas taking hydrogen as the main part, and the reformed gas is transferred to the anode inlet 15 of the solid oxide fuel cell 7 from the reformed gas outlet of the partial oxidation reformer 6. At this time, the solid oxide fuel cell 7 takes a cathode reactant as reformed gas and an anode reactant as air to perform an electrochemical reaction, generates electron transfer to generate direct current, and transmits the direct current to the direct current motor 5 through the wire 10, so that the direct current can work and convert electric energy into mechanical energy. The direct current motor 5 is connected with the air compressor 2 through the connecting shaft 3 to drive the air compressor 2 to work, so that air compression is realized. The tail gas discharged from the anode-electrolyte-cathode assembly 16 of the solid oxide fuel cell 7 contains gas which is not completely reacted, the tail gas is introduced into the combustion chamber 8 to be combusted, high-temperature and high-pressure fuel gas is generated, the fuel gas is conveyed to the spray pipe 9 and accelerated in the spray pipe 9, high-speed airflow is discharged to the atmosphere, and finally the aircraft is propelled by the reaction force generated by the airflow.
The above-mentioned embodiments further explain the objects, technical solutions and advantages of the present invention in detail. It should be understood that the above-mentioned embodiments are only examples of the present invention, and are not intended to limit the present invention, and that the reasonable combination of the features described in the above-mentioned embodiments can be made, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A non-turbine jet engine integrated with a solid oxide fuel cell, characterized by comprising a partial oxidation reformer (6), a solid oxide fuel cell system (7), an aircraft propulsion system, an air delivery path and a fuel delivery path, the aircraft propulsion system comprising a compressor (2), a combustion chamber (8), a direct current motor (5), a connecting shaft (3) and a jet pipe (9);
the direct current motor (5) drives the compressor (2) through the connecting shaft (3), the partial oxidation reformer (6) is arranged behind the direct current motor (5), and the solid oxide fuel cell system (7), the combustion chamber (8) and the spray pipe (9) are sequentially connected; the air conveying passage is formed by that air enters through an air inlet channel (1), is compressed by a compressor (2) and then is divided into two parts, one part is sent to a partial oxidation reformer (6), and the other part flows from the outside of the partial oxidation reformer (6) and enters a solid oxide fuel cell system (7); the fuel oil conveying passage is characterized in that fuel oil flows through the outer wall of the direct current motor (5) through a fuel conveying pump (4) and is conveyed to the partial oxidation reformer (6) to perform reforming reaction with air in the partial oxidation reformer (6);
the fuel delivery pump (4) is positioned above the connecting shaft (3), the direct current motor (5) needs to be cooled in a working state, and fuel flows through a shell of the direct current motor (5) through the fuel delivery pump (4) to lower the temperature of the direct current motor (5) in working;
the partial oxidation reformer (6) comprises an air inlet (11), a fuel inlet (12), a catalyst (13) and a reformed gas outlet, the partial oxidation reformer (6) adopts a tubular reactor, the front end of the partial oxidation reformer (6) is provided with the fuel inlet (12) and the air inlet (11), the air inlet (11) is positioned on the outer ring of the fuel inlet (12), the middle part of the partial oxidation reformer (6) is provided with the nickel-based catalyst (13), and the rear end of the partial oxidation reformer (6) is provided with the reformed gas outlet;
the solid oxide fuel cell system (7) comprises a cathode inlet (14), an anode inlet (15) and an anode-electrolyte-cathode assembly (16), wherein the anode-electrolyte-cathode assembly (16) penetrates through the solid oxide fuel cell system (7) in a circular tube shape, the anode inlet (15) is positioned inside the anode-electrolyte-cathode assembly (16), and the cathode inlet (14) is positioned on the periphery of the anode-electrolyte-cathode assembly (16);
the air conveying passage is divided into two parts after air enters the compressor (2) through the air inlet channel (1) to be compressed, one part of the air is sent to an air inlet (11) of the partial oxidation reformer (6), and the other part of the air flows through the outside of the partial oxidation reformer (6) to enter a cathode inlet (14) of the solid oxide fuel cell system (7);
the fuel oil conveying path is that the fuel oil flows through the shell of the direct current motor (5) through the fuel oil conveying pump (4), the temperature of the fuel oil is increased, and the fuel oil is sent to the fuel oil inlet (12) of the partial oxidation reformer (6) to carry out reforming reaction with air inside the partial oxidation reformer (6).
2. The turboless jet engine integrated with a solid oxide fuel cell according to claim 1, characterized in that the air intake duct (1) is provided at the periphery of the front end of the compressor (2).
3. The solid oxide fuel cell integrated turboless jet engine according to claim 1, characterized in that the solid oxide fuel cell system (7) generates electrochemical reactions outputting direct current to supply electric power to the direct current motor (5) through electric wires (10).
4. The solid oxide fuel cell integrated turboless jet engine of claim 1, wherein the solid oxide fuel cell system (7) is assembled from a plurality of cell stacks, the cells in each cell stack being assembled in series, air and reformate gas entering the solid oxide fuel cell system (7) being distributed to each cell, and electrochemical reaction taking place to generate direct current.
5. The turboless jet engine integrated with a solid oxide fuel cell according to claim 1, characterized in that the reformed gas outlet is piped for delivery to the anode inlet (15) of the solid oxide fuel cell system (7).
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| US6641084B1 (en) * | 2002-06-21 | 2003-11-04 | The Boeing Company | Solid oxide fuel cell as auxiliary power source installation in transport aircraft |
| US8394552B2 (en) * | 2006-09-19 | 2013-03-12 | Hamilton Sundstrand Corporation | Jet fuel based high pressure solid oxide fuel cell system |
| CN103597643B (en) * | 2011-04-21 | 2016-06-08 | 空中客车德国运营有限责任公司 | Drive unit, for providing the method for power and drive the utilization of unit |
| JP5836044B2 (en) * | 2011-10-05 | 2015-12-24 | 三菱日立パワーシステムズ株式会社 | Gas turbine combined power generation system having high temperature fuel cell and operation method of gas turbine combined power generation system having high temperature fuel cell |
| EP2759689B8 (en) * | 2013-01-28 | 2016-09-21 | General Electric Technology GmbH | Emergency power supply system comprising a hydrogen fueled fuel cell |
| CN107842442B (en) * | 2017-11-10 | 2020-09-18 | 中国空气动力研究与发展中心计算空气动力研究所 | Aircraft engine |
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