A novel SOFC-GT-LTSEPS system architecture low-temperature superconducting electric propulsion system and working method

Abstract

The application belongs to the field of clean energy aviation power, and provides a novel SOFC-GT-LTSEPS system architecture low-temperature superconducting electric propulsion system and a working method, which has low-temperature superconducting power generation and electric propulsion functions, generates gaseous hydrogen by heating liquid hydrogen fuel, and provides the anode of the SOFC after compression and pressurization; air is pressurized by the compressor of the GT, heated by a preheating exchanger, and high-temperature and high-pressure oxygen is obtained, which is provided to the cathode of the SOFC. Chemical reaction occurs in the SOFC to generate water vapor, and the remaining hydrogen in the anode is transported to the combustion chamber of the GT to be mixed and burned with the remaining oxygen in the cathode, the generated high-temperature and high-pressure gas drives the turbine to do work, drives the generator to output power, and at the same time, the LTSEPS system provides power to the aircraft. The system architecture scheme has the advantages of fast start, low-temperature superconducting, high energy utilization rate, high power-to-weight ratio and electric propulsion, and has the low-temperature superconducting function, fully utilizes the low-temperature characteristics of liquid hydrogen and the characteristics of high-temperature electrochemical reaction.

Description

Technical Field

[0001] This invention belongs to the field of clean energy aviation propulsion, and relates to a propulsion system and method using SOFC-GT architecture, specifically to a novel SOFC-GT-LTSEPS system architecture cryogenic superconducting propulsion system and its working method. Background Technology

[0002] With the rise of clean energy, "green aviation" is receiving increasing attention worldwide, especially given the International Air Transport Association's (IATA) "Carbon Emissions Roadmap," which aims to achieve zero carbon emissions by 2050. All-electric aircraft place higher demands on the power generation capacity of aviation gas turbine engines. Traditional gas turbine engines, which use aviation kerosene, have low thermoelectric efficiency and cannot meet the requirements for green and environmentally friendly systems. While fuel cell power generation systems have high power generation efficiency, they suffer from slow start-up, low power-to-weight ratio, and fuel utilization of only about 50%. Fully utilizing the gas turbine engine (GT) to supplement the combustion of remaining fuel, and combining the cryogenic and superconducting properties of liquid hydrogen, can improve the efficiency and power output of the electric propulsion system. An integrated system solution based on solid oxide fuel cells (SOFC), gas turbine engines (GT), and cryogenic superconducting propulsion systems (LTSEPS) has seen initial applications in all-electric aircraft (such as UAVs and commercial regional jets), but the technology is still immature, with relatively high weight and cost. Summary of the Invention

[0003] To address the aforementioned issues, this invention provides a novel SOFC-GT-LTSEPS system architecture cryogenic superconducting propulsion system and its operating method. This system features a novel dual-mode cryogenic superconducting, high thermoelectric efficiency, and low-pollution electric propulsion system architecture with a superior flight envelope. It can operate stably and efficiently in high and low temperatures and in near-space at a range of 11km-25km.

[0004] The technical solution of this invention is:

[0005] A novel SOFC-GT-LTSEPS system architecture for a cryogenic superconducting propulsion system includes a liquid hydrogen storage tank connected to a compressor via a first channel valve. The compressor outlet is connected to the inlet of a first three-way valve. One outlet of the first three-way valve is connected to a primary heat exchanger, which is connected to the anode inlet of the SOFC. The other outlet of the first three-way valve is connected to a hydrogen circulation system, which provides a superconducting cryogenic operating environment for the cryogenic superconducting starter / generator and cryogenic superconducting motor system. The hydrogen circulation system then enters the other inlet of the first channel valve and the combustion chamber via a fourth three-way valve. The exhaust gases from the SOFC anode and cathode pass through the primary and secondary heat exchangers before entering the combustion chamber for combustion. The combustion chamber drives a turbine, which is coaxially connected to the cryogenic superconducting starter / generator and compressor. The compressor provides oxygen to the combustion chamber and the SOFC cathode. The electrical energy output from the SOFC and the cryogenic superconducting starter / generator powers the cryogenic superconducting motor system, which in turn drives the thrust fan system.

[0006] Furthermore, the cryogenic superconducting motor system includes a first cryogenic superconducting motor and a second cryogenic superconducting motor, and the thrust fan system includes a first thrust fan and a second thrust fan. The first cryogenic superconducting motor drives the first thrust fan, and the second cryogenic superconducting motor drives the second thrust fan. The first cryogenic superconducting motor is powered by a cryogenic superconducting starter / generator, and the second cryogenic superconducting motor is powered by an SOFC.

[0007] Furthermore, the cryogenic superconducting starter / generator is connected to the first cryogenic superconducting motor via a first DC / AC converter and a first DC boost converter; the electrical outlet of the SOFC is connected to the second cryogenic superconducting motor via a second DC / AC converter and a second DC boost converter.

[0008] Furthermore, the hydrogen cycle system includes: a first three-way valve connected to the hot end inlet of the first heat exchanger and the inlet of the second channel valve, wherein the second channel valve is a double-inlet and double-outlet valve; the flow path of the first three-way valve and the first heat exchanger is provided by a cryogenic superconducting starter / generator; the hot end outlet of the first heat exchanger is connected to the second three-way valve; the outlet of the second channel valve is connected to the second three-way valve through the cold end of the secondary heat exchanger and the primary heat exchanger; the last outlet of the second three-way valve is connected to the inlet of the second channel valve; and the outlet of the second channel valve is connected to the fourth three-way valve.

[0009] Furthermore, the hot exhaust gas emitted after the turbine passes through the hot ends of the secondary heat exchanger and the primary heat exchanger before being discharged outside the engine.

[0010] Furthermore, the hydrogen cycle system also includes: a first three-way valve connected to inlet one of a third channel valve, the third channel valve being a dual-inlet, dual-outlet valve, outlet one of the third channel valve connected to inlet two of a second channel valve, outlet two of the third channel valve connected to the cold end inlet of the first heat exchanger and the cold end inlet of the second heat exchanger respectively; the cold end outlet of the first heat exchanger provides a low-temperature environment for the first cryogenic superconducting motor and then connects to the inlet of a fourth three-way valve; the cold end outlet of the second heat exchanger provides a low-temperature environment for the second cryogenic superconducting motor and then connects to the hot end inlet of the second heat exchanger, the hot end outlet of the second heat exchanger connected to inlet two of the third channel valve.

[0011] A novel SOFC-GT-LTSEPS system architecture operating method for a cryogenic superconducting propulsion system, comprising the aforementioned novel SOFC-GT-LTSEPS system architecture cryogenic superconducting propulsion system, including GT-LTSEPS mode:

[0012] The liquid hydrogen storage tank is connected to the combustion chamber, and the compressor is also connected to the combustion chamber. The cryogenic superconducting starter / generator acts as a starter, driving the turbine and compressor to run, raising the turbine to the ignition speed. Then, combustion occurs in the combustion chamber, and the high-temperature gas drives the turbine to rotate. When the turbine reaches the cut-off speed, the cryogenic superconducting starter / generator acts as a generator. The hydrogen cycle system provides liquid hydrogen to provide superconducting cryogenic conditions for the cryogenic superconducting starter / generator, the first cryogenic superconducting motor, and the second cryogenic superconducting motor. The cryogenic superconducting starter / generator provides electrical energy to the first cryogenic superconducting motor, and the battery provides electrical energy to the second cryogenic superconducting motor.

[0013] Furthermore, it also includes the SOFC-GT-LTSEPS mode:

[0014] After the GT-LTSEPS mode is operating stably, when the SOFC stack temperature reaches the required level, the path from the compressor to the SOFC cathode is selected, and the path from the compressor to the SOFC anode is selected. At the same time, the hydrogen input channel from the liquid hydrogen tank to the combustion chamber and the air input channel from the compressor to the combustion chamber are cut off. The SOFC anode outlet exhaust gas and cathode outlet exhaust gas are cooled by passing through the primary heat exchanger and then enter the combustion chamber for mixing and combustion. The SOFC provides power to the second cryogenic superconducting motor. The hydrogen cycle system provides liquid hydrogen to provide superconducting cryogenic conditions for the cryogenic starter / generator, the first cryogenic superconducting motor, and the second cryogenic superconducting motor. The cryogenic superconducting starter / generator provides power to the first cryogenic superconducting motor.

[0015] The beneficial effects of this invention are:

[0016] 1. The present invention relates to a novel SOFC-GT-LTSEPS system solution that improves upon traditional gas turbine engine systems by more than 90%, and reduces fuel consumption by 80% for the same power generation requirements. The novel SOFC-GT-LTSEPS system architecture includes a gas turbine engine subsystem, a fuel cell subsystem, and a cryogenic superconducting propulsion subsystem. It can directly output matching power according to the power requirements of the all-electric aircraft's onboard equipment and meet the real-time power requirements of the cryogenic superconducting propulsion system, thereby enabling the control of flight attitude and speed within the flight envelope of the all-electric aircraft.

[0017] 2. The novel SOFC-GT-LTSEPS system involved can achieve dual-mode operation, meeting the power requirements of electric and cryogenic superconducting propulsion for high-altitude flight and ground maintenance. This invention offers high economic and environmental performance for applications with harsh working conditions and high power demands, especially for all-electric aircraft with ultra-high power requirements for high-altitude flight and lower power requirements for ground maintenance, with virtually no emissions.

[0018] 3. In addition, this scheme has high practical value for the energy generation of laser weapons, and also has good versatility, economy and environmental friendliness for small business jets and drones. Attached Figure Description

[0019] To more clearly illustrate the technical solutions of the embodiments of this invention, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this invention and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained from these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of a novel SOFC-GT-LTSEPS system architecture scheme according to the present invention;

[0021] Wherein, 1—liquid hydrogen storage tank, 2—first channel valve, 3—compressor, 4—first three-way valve, 5—primary heat exchanger, 6—SOFC, 7—secondary heat exchanger, 8—combustion chamber, 9—turbine, 10—cryogenic superconducting starter / generator, 11—compressor, 12—second channel valve, 13—secondary heat exchanger, 14—primary heat exchanger, 15—second three-way valve, 16—first heat exchanger, 17—first thrust fan, 18—first cryogenic superconducting motor, 19—first DC / AC converter, 20—first DC booster, 21—second DC / AC converter, 22—second DC booster, 23—second cryogenic superconducting motor, 24—second thrust fan, 25—second heat exchanger, 26—channel valve, 27—third three-way valve, 28—fourth three-way valve. Detailed Implementation

[0022] This section describes embodiments of the present invention, used to explain and illustrate the technical solutions of the present invention. Unless otherwise specified, the embodiments and features described herein can be combined with each other.

[0023] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating directions or positional relationships, are based on the orientation or positional relationships in the accompanying drawings and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or case referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include more than one of those features. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0024] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integrated connections; they can refer to mechanical connections or point connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0025] Example 1:

[0026] A novel SOFC-GT-LTSEPS system architecture for a cryogenic superconducting propulsion system includes a liquid hydrogen storage tank 1 connected to a compressor 3 via a first channel valve 2. The outlet of compressor 3 is connected to the inlet of a first three-way valve 4. One outlet of the first three-way valve 4 is connected to a primary heat exchanger 5, which is connected to the anode inlet of an SOFC 6. The other outlet of the first three-way valve 4 is connected to a hydrogen circulation system, which provides a superconducting cryogenic operating environment for the cryogenic superconducting starter / generator 10 and the cryogenic superconducting motor system. The hydrogen circulation system then connects to a fourth three-way valve 28... The exhaust gas from the anode and cathode of SOFC6 enters the combustion chamber 8 through the primary heat exchanger 5 and the secondary heat exchanger 7. The combustion chamber 8 drives the turbine 9 to operate. The turbine 9 is coaxially connected to the cryogenic superconducting starter / generator 10 and the compressor 11. The compressor 11 provides oxygen to the combustion chamber 8 and the cathode of SOFC6. The electrical energy output from SOFC6 and cryogenic superconducting starter / generator 10 powers the cryogenic superconducting motor system, which in turn drives the thrust fan system.

[0027] Furthermore, the cryogenic superconducting motor system includes a first cryogenic superconducting motor 18 and a second cryogenic superconducting motor 23, and the thrust fan system includes a first thrust fan 17 and a second thrust fan 24. The first cryogenic superconducting motor 18 drives the first thrust fan 17, and the second cryogenic superconducting motor 23 drives the second thrust fan 24. The first cryogenic superconducting motor 18 is powered by a cryogenic superconducting starter / generator 10, and the second cryogenic superconducting motor 23 is powered by SOFC6.

[0028] Furthermore, the cryogenic superconducting starter / generator 10 is connected to the first cryogenic superconducting motor 18 via the first DC / AC converter 19 and the first DC boost converter 20; the power outlet of SOFC6 is connected to the second cryogenic superconducting motor 23 via the second DC / AC converter 21 and the second DC boost converter 22.

[0029] Furthermore, the hydrogen cycle system includes: a first three-way valve 4 connected to the hot end inlet of the first heat exchanger 16 and the inlet 1 of the second channel valve 12, wherein the second channel valve 12 is a double-inlet and double-outlet valve; the flow path of the first three-way valve 4 and the first heat exchanger 16 passes through the cryogenic superconducting starter / generator 10 to provide a cryogenic environment; the hot end outlet of the first heat exchanger 16 is connected to the second three-way valve 15; the outlet 1 of the second channel valve 12 is connected to the second three-way valve 15 successively through the cold end of the secondary heat exchanger 13 and the primary heat exchanger 14; the last outlet of the second three-way valve 15 is connected to the inlet 2 of the second channel valve 12; and the outlet 2 of the second channel valve 12 is connected to the fourth three-way valve 28.

[0030] Furthermore, the hot exhaust gas emitted after turbine 9 passes through the hot ends of the secondary heat exchanger 13 and the primary heat exchanger 14 before being discharged outside the machine.

[0031] Furthermore, the hydrogen cycle system also includes: a first three-way valve 4 is connected to the inlet 1 of a third channel valve 26, the third channel valve 26 is a double-inlet and double-outlet valve, the outlet 1 of the third channel valve 26 is connected to the inlet 2 of a second channel valve 12, and the outlet 2 of the third channel valve 26 is connected to the cold end inlet of the first heat exchanger 16 and the cold end inlet of the second heat exchanger 25 respectively; the cold end outlet of the first heat exchanger 16 provides a low-temperature environment for the first cryogenic superconducting motor 18 and then connects to the inlet of a fourth three-way valve 28; the cold end outlet of the second heat exchanger 25 provides a low-temperature environment for the second cryogenic superconducting motor 23 and then connects to the hot end inlet of the second heat exchanger 25, and the hot end outlet of the second heat exchanger 25 is connected to the inlet 2 of the third channel valve 26.

[0032] A novel SOFC-GT-LTSEPS system architecture operating method for a cryogenic superconducting propulsion system, comprising the aforementioned novel SOFC-GT-LTSEPS system architecture cryogenic superconducting propulsion system, including GT-LTSEPS mode:

[0033] The liquid hydrogen storage tank 1 is connected to the combustion chamber 8, and the compressor 11 is connected to the combustion chamber 8. The cryogenic superconducting starter / generator 10 starts as a starter, driving the turbine 9 and the compressor 11 to run, causing the turbine 9 to rise to the ignition speed. Then, the combustion chamber 8 is ignited and combusted. The high-temperature gas drives the turbine 9 to rotate. When the turbine 9 reaches the cut-off speed, the cryogenic superconducting starter / generator 10 works as a generator. The hydrogen circulation system provides liquid hydrogen to provide superconducting cryogenic conditions for the cryogenic superconducting starter / generator 10, the first cryogenic superconducting motor 18, and the second cryogenic superconducting motor 23. The cryogenic superconducting starter / generator 10 provides electrical energy to the first cryogenic superconducting motor 18, and the battery provides electrical energy to the second cryogenic superconducting motor 23.

[0034] Furthermore, it also includes the SOFC-GT-LTSEPS mode:

[0035] After the GT-LTSEPS mode is operating stably, when the stack temperature of SOFC6 reaches the required level, the cathode path from compressor 11 to SOFC6 and the anode path from compressor 3 to SOFC6 are selected. At the same time, the hydrogen input channel from the liquid hydrogen tank to the combustion chamber 8 is cut off, and the air input channel from compressor 11 to the combustion chamber 8 is also cut off. The exhaust gas from the anode outlet and the exhaust gas from the cathode outlet of SOFC6 are cooled by passing through the primary heat exchanger 5 and the primary heat exchanger 7 respectively before entering the combustion chamber 8 for mixing and combustion. SOFC6 provides power to the second cryogenic superconducting motor 23. The hydrogen circulation system provides liquid hydrogen to provide superconducting cryogenic conditions for the cryogenic superconducting starter / generator 10, the first cryogenic superconducting motor 18, and the second cryogenic superconducting motor 23. The cryogenic superconducting starter / generator 10 provides power to the first cryogenic superconducting motor 18.

[0036] Example 2:

[0037] A novel SOFC-GT-LTSEPS system is disclosed, in which the aircraft uses liquid hydrogen to fuel the SOFC-GT system and utilizes the low-temperature characteristics of liquid hydrogen (-254°C) to provide low-temperature cooling for the low-temperature superconducting electric motor and the low-temperature superconducting starter / generator, thereby achieving the purpose of low-temperature superconductivity and providing electrical energy for the aircraft's electric propulsion system. The system is characterized by comprising a gas turbine engine subsystem, a fuel cell subsystem, and a low-temperature superconducting propulsion subsystem.

[0038] The gas turbine engine subsystem includes an 8-combustion chamber, a 9-turbine, a 10-cryosuperconducting starter / generator, an 11-compressor, and a 27-three-way valve. The 11-compressor, 10-cryosuperconducting starter / generator, and 9-turbine are arranged coaxially in sequence. The inlet of the 11-compressor is connected to the atmosphere, and the outlet is connected to the inlet of the 27-three-way valve. The bypass is connected to the inlet gas pipeline of the 8-combustion chamber. Compressed air enters the 8-combustion chamber and mixes with hydrogen for combustion. The outlet of the 8-combustion chamber is connected to the inlet pipeline of the 9-turbine. The high-temperature exhaust gas impacts the 9-turbine to do work, driving the coaxial 10-cryosuperconducting starter / generator and 11-compressor to rotate, outputting electrical energy and compressed air. The coolant inlet of the 10 cryogenic superconducting starter / generator is connected to one outlet pipe of the 4 three-way valve, and the outlet is connected to the hot inlet pipe of the 16 heat exchanger. The "start", "shutdown" or "load" of the 10 cryogenic superconducting starter / generator is controlled by the aircraft electromechanical control system. When a "start" signal is received, the starting circuit of the 10 cryogenic superconducting starter / generator is turned on, the onboard battery provides power, and the 10 cryogenic superconducting starter / generator starts to work. When a "shutdown" signal is received, the starting circuit is turned off, and the 10 cryogenic superconducting starter / generator stops working. When a "load" signal is received, the output circuit of the 10 cryogenic superconducting starter / generator is turned on, and the output circuit interface is connected to the input circuit interface of the 20 DC booster.

[0039] The fuel cell subsystem includes: 1. a liquid hydrogen storage tank; 2. a channel valve; 3. a compressor; 4. a three-way valve; 5. a primary heat exchanger; 6. a SOFC (Sodium Hydrogen Fuel Cell); 7. a secondary heat exchanger; and 28. a three-way valve. The 2-channel valve, 3. the compressor, 4. the three-way valve, and 28. the three-way valve are all controlled by the aircraft's electromechanical control system to "open / close." When the aircraft's electromechanical control system receives a "start" signal, the 2-channel valve opens, the starting circuit of the 3rd compressor is activated, and the electric compressor begins to work. When a "close" signal is received, the starting circuit is disconnected, and the electric compressor stops working. Both the primary heat exchanger (5-stage) and the secondary heat exchanger (7-stage) have hot-end and cold-end interfaces. The hot-end interfaces are divided into two: a hydrogen interface and an oxygen interface. The secondary heat exchanger (7-stage) contains a multi-layered spiral mesh molecular sieve, which can separate oxygen (O2) and nitrogen (N2) from the air input at the cold-end inlet. The nitrogen (N2) is directly discharged outside the machine. The oxygen (O2) cold-end outlet of the secondary heat exchanger (7-stage) is connected to the cathode inlet of the SOFC (Solid Oxygen Fuel Cell) (6-stage), and the hydrogen (H2) cold-end outlet of the primary heat exchanger (5-stage) is connected to the anode inlet of the SOFC (Solid Oxygen Fuel Cell). The anode outlet of the SOFC (Solid Oxygen Fuel Cell) is connected to the hot-end hydrogen interface of the primary heat exchanger (5-stage), and the cathode outlet of the SOFC (Solid Oxygen Fuel Cell) is connected to the hot-end oxygen interface of the primary heat exchanger (5-stage).

[0040] The cryogenic superconducting propulsion subsystem comprises: a 12-channel valve, a 13-stage heat exchanger, a 14-stage primary heat exchanger, a 15-three-way valve, a 16-stage heat exchanger, a 17-stage thrust fan, an 18-stage cryogenic superconducting electric motor, a 19-stage DC / AC converter, a 20-stage DC booster, a 21-stage DC / AC converter, a 22-stage DC booster, a 23-stage cryogenic superconducting electric motor, a 24-stage thrust fan, a 25-stage heat exchanger, and a 26-channel valve. The 12-channel valve, 15-stage three-way valve, 18-stage cryogenic superconducting electric motor, 23-stage cryogenic superconducting electric motor, and 26-channel valve are controlled by the aircraft's electromechanical control system. Upon receiving an "open" signal, these five components activate. Cryogenic liquid hydrogen in the pipeline cools the cryogenic superconducting propulsion subsystem to achieve cryogenic superconductivity. Simultaneously, through multiple heat exchanges, the temperature of the liquid hydrogen at the pipeline outlet rises, and some of the liquid hydrogen vaporizes to generate hydrogen gas, which connects to the main pipeline of the 28-stage three-way valve of the fuel cell subsystem.

[0041] The SOFC-GT-LTSEPS system has two operating modes: GT-LTSEPS mode and SOFC-GT-LTSEPS mode.

[0042] GT-LTSEPS mode: When the aircraft electromechanical control system receives the "start" signal, it connects the starting circuit of the 10 cryogenic superconducting starter / generator, and simultaneously sends "open" signals to the 2-channel valve and the 4-way three-way valve, as well as connects the starting circuit of the 3 compressor's electric starter. When the GT rotor speed reaches the ignition speed, hydrogen is injected into the 8 combustion chamber and ignited, generating high-temperature and high-pressure gas to drive the 9 turbine to do work. The GT rotor speed increases rapidly. When the speed reaches the cut-off speed, the aircraft electromechanical control system sends a control signal to disconnect the starting circuit of the 10 cryogenic superconducting starter / generator. The GT speed continues to increase to idle speed, and the aircraft electromechanical control system sends a "load" signal to the 10 cryogenic superconducting starter / generator and a "start" signal to the 18 cryogenic superconducting motor. The electrical energy output by the 10 cryogenic superconducting starter / generator is connected to the 18 cryogenic superconducting motor through the 20 DC boost converter and the 19 DC / AC converter to drive the 17 thrust fan.

[0043] SOFC-GT-LTSEPS Mode: First, the aircraft electromechanical control system activates the GT-LTSEPS mode. After GT-LTSEPS stabilizes, when the stack temperature of the 8SOFC reaches 800℃-900℃ and internal energy balance is achieved, the aircraft electromechanical control system closes the bypass passages of three-way valves 27 and 28, cutting off the hydrogen input channel from liquid hydrogen tank 1 to combustion chamber 8, and simultaneously cutting off the air input channel from compressor 11 to combustion chamber 8. The residual H2 and water vapor in the exhaust gas at the anode outlet of the 8SOFC and the residual O2 discharged at the cathode outlet have a temperature of approximately 800℃. After being cooled by the primary heat exchangers 5 and 7, and the temperature drops to approximately 600°C, the gas enters the combustion chamber 8 for mixed combustion. The high-temperature, high-pressure gas drives the turbine 9 to perform work, which in turn drives the coaxial cryogenic superconducting starter / generator 10 and compressor 11. The electrical energy output from the cryogenic superconducting starter / generator 10 passes through the DC boost converter 20 and the DC / AC converter 19, and is then connected to the cryogenic superconducting motor 18, which drives the thrust fan 17. At the same time, the electrical energy generated by the SOFC 8 passes through the DC boost converter 21 and the DC / AC converter 22, and is then connected to the cryogenic superconducting motor 23, which drives the thrust fan 24.

[0044] Example 3:

[0045] A novel SOFC-GT-LTSEPS system is disclosed, in which the aircraft's electromechanical control system controls the system's "start-up" and "disconnection," as well as the start-up timing and switching between two operating modes. The novel SOFC-GT-LTSEPS system includes a gas turbine engine subsystem, a fuel cell subsystem, and a cryogenic superconducting propulsion subsystem.

[0046] The gas turbine engine subsystem includes an 8-combustion chamber, a 9-turbine, a 10-cryosuperconducting starter / generator, an 11-compressor, and a 27-three-way valve. The 11-compressor, 10-cryosuperconducting starter / generator, and 9-turbine are arranged coaxially in sequence. The inlet of the 11-compressor is connected to the atmosphere, and the outlet is connected to the inlet of the 27-three-way valve. The bypass is connected to the inlet gas pipeline of the 8-combustion chamber. Compressed air enters the 8-combustion chamber and mixes with hydrogen for combustion. The outlet of the 8-combustion chamber is connected to the inlet pipeline of the 9-turbine. The high-temperature exhaust gas impacts the 9-turbine to do work, driving the coaxial 10-cryosuperconducting starter / generator and 11-compressor to rotate, outputting electrical energy and compressed air. The coolant inlet of the 10 cryogenic superconducting starter / generator is connected to one outlet pipe of the 4 three-way valve, and the outlet is connected to the hot inlet pipe of the 16 heat exchanger. The "start", "shutdown" or "load" of the 10 cryogenic superconducting starter / generator is controlled by the aircraft electromechanical control system. When a "start" signal is received, the starting circuit of the 10 cryogenic superconducting starter / generator is turned on, the onboard battery provides power, and the 10 cryogenic superconducting starter / generator starts to work. When a "shutdown" signal is received, the starting circuit is turned off, and the 10 cryogenic superconducting starter / generator stops working. When a "load" signal is received, the output circuit of the 10 cryogenic superconducting starter / generator is turned on, and the output circuit interface is connected to the input circuit interface of the 20 DC booster.

[0047] The fuel cell subsystem includes: 1. a liquid hydrogen storage tank; 2. a channel valve; 3. a compressor; 4. a three-way valve; 5. a primary heat exchanger; 6. a SOFC (Sodium Hydrogen Fuel Cell); 7. a secondary heat exchanger; and 28. a three-way valve. The 2-channel valve, 3. the compressor, 4. the three-way valve, and 28. the three-way valve are all controlled by the aircraft's electromechanical control system to "open / close." When the aircraft's electromechanical control system receives a "start" signal, the 2-channel valve opens, the starting circuit of the 3rd compressor is activated, and the electric compressor begins to work. When a "close" signal is received, the starting circuit is disconnected, and the electric compressor stops working. Both the primary heat exchanger (5-stage) and the secondary heat exchanger (7-stage) have hot-end and cold-end interfaces. The hot-end interfaces are divided into two: a hydrogen interface and an oxygen interface. The secondary heat exchanger (7-stage) contains a multi-layered spiral mesh molecular sieve, which can separate oxygen (O2) and nitrogen (N2) from the air input at the cold-end inlet. The nitrogen (N2) is directly discharged outside the machine. The oxygen (O2) cold-end outlet of the secondary heat exchanger (7-stage) is connected to the cathode inlet of the SOFC (Solid Oxygen Fuel Cell) (6-stage), and the hydrogen (H2) cold-end outlet of the primary heat exchanger (5-stage) is connected to the anode inlet of the SOFC (Solid Oxygen Fuel Cell). The anode outlet of the SOFC (Solid Oxygen Fuel Cell) is connected to the hot-end hydrogen interface of the primary heat exchanger (5-stage), and the cathode outlet of the SOFC (Solid Oxygen Fuel Cell) is connected to the hot-end oxygen interface of the primary heat exchanger (5-stage).

[0048] The cryogenic superconducting propulsion subsystem comprises: a 12-channel valve, a 13-stage heat exchanger, a 14-stage primary heat exchanger, a 15-three-way valve, a 16-stage heat exchanger, a 17-stage thrust fan, an 18-stage cryogenic superconducting electric motor, a 19-stage DC / AC converter, a 20-stage DC booster, a 21-stage DC / AC converter, a 22-stage DC booster, a 23-stage cryogenic superconducting electric motor, a 24-stage thrust fan, a 25-stage heat exchanger, and a 26-channel valve. The 12-channel valve, 15-stage three-way valve, 18-stage cryogenic superconducting electric motor, 23-stage cryogenic superconducting electric motor, and 26-channel valve are controlled by the aircraft's electromechanical control system. Upon receiving an "open" signal, these five components activate. Cryogenic liquid hydrogen in the pipeline cools the cryogenic superconducting propulsion subsystem to achieve cryogenic superconductivity. Simultaneously, through multiple heat exchanges, the temperature of the liquid hydrogen at the pipeline outlet rises, and some of the liquid hydrogen vaporizes to generate hydrogen gas, which connects to the main pipeline of the 28-stage three-way valve of the fuel cell subsystem.

[0049] The SOFC-GT-LTSEPS system has two operating modes: GT-LTSEPS mode and SOFC-GT-LTSEPS mode. (Reference) Figure 1 :

[0050] In GT-LTSEPS mode, when the aircraft electromechanical control system receives the "start" signal, it activates the starting circuit of the 10 cryogenic superconducting starter / generator, simultaneously sends "open" signals to the 2-channel valve and the 4-way three-way valve, and activates the starting circuit of the 3 compressor's electric starter. When the GT rotor speed reaches the ignition speed, hydrogen is injected into the 8 combustion chamber and ignited, generating high-temperature, high-pressure gas to drive the 9 turbine to do work, and the GT rotor speed increases rapidly. When the speed reaches the cut-off speed, the aircraft electromechanical control system sends a control signal to disconnect the starting circuit of the 10 cryogenic superconducting starter / generator. As the GT speed continues to increase to idle speed, the aircraft electromechanical control system sends a "load" signal to the 10 cryogenic superconducting starter / generator and a "start" signal to the 18 cryogenic superconducting motor. The electrical energy output from the 10 cryogenic superconducting starter / generator is connected to the 18 cryogenic superconducting motor through the 20 DC boost converter and the 19 DC / AC converter to drive the 17 thrust fan.

[0051] In SOFC-GT-LTSEPS mode, the aircraft's electromechanical control system first activates GT-LTSEPS mode. GT-LTSEPS operates stably. When the stack temperature of SOFC 8 reaches 800℃-900℃ and internal energy balance is achieved, the aircraft's electromechanical control system closes the bypass passages of three-way valves 27 and 28, cutting off the hydrogen input channel from liquid hydrogen tank 1 to combustion chamber 8, and simultaneously cutting off the air input channel from compressor 11 to combustion chamber 8. The residual H2 and water vapor in the exhaust gas at the anode outlet of SOFC 8 and the residual O2 discharged from the cathode outlet have a temperature of approximately 800℃. After being cooled by the primary heat exchangers 5 and 7, and the temperature drops to approximately 600°C, the gas enters the combustion chamber 8 for mixed combustion. The high-temperature, high-pressure gas drives the turbine 9 to perform work, which in turn drives the coaxial cryogenic superconducting starter / generator 10 and compressor 11. The electrical energy output from the cryogenic superconducting starter / generator 10 passes through the DC boost converter 20 and the DC / AC converter 19, and is then connected to the cryogenic superconducting motor 18, which drives the thrust fan 17. At the same time, the electrical energy generated by the SOFC 8 passes through the DC boost converter 21 and the DC / AC converter 22, and is then connected to the cryogenic superconducting motor 23, which drives the thrust fan 24.

[0052] Please see Figure 1 The fuel cell subsystem requires specific temperature, pressure, and fuel supply conditions to operate stably. Under special conditions such as system start-up and shutdown, the system can only operate in standalone gas turbine start-up and standby mode.

[0053] During startup, when the gas turbine engine is operating in standalone startup and stable mode, controller 15 sends a startup signal to starter / generator 13. Simultaneously, controller 15 signals to open the bypass control valve 16 connecting to combustion chamber 10, and signals to open the auxiliary fuel control valve 4 connecting to combustion chamber 10, allowing pressurized fuel to be directly introduced into combustion chamber 10 via fuel lines. At this time, the gas turbine engine subsystem starts, and air is drawn into compressor 14. The suction effect cools starter / generator 13, while the compressed air from compressor 14 outlet is heated by primary heat exchanger 5 and then directly enters combustion chamber 10 after passing through bypass control valve 16. The gas turbine engine mixes with fuel and ignites for combustion. The high-temperature, high-pressure 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 sends a control signal to disconnect the power input switch of the starter / generator 13, thus disconnecting the output torque of the starter / generator 13. The speed of the gas turbine engine 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 begins to output electrical energy to the power regulator 11, which is then stored in the battery 12 after power regulation and conversion. At the same time, the high-temperature exhaust gas discharged from the turbine 6 is heated by the primary heat exchanger 5 to the compressed air at the outlet of the compressor 14 before being discharged into the surrounding atmosphere.

[0054] Please see Figure 1When the fuel cell and gas turbine engine hybrid cycle power generation system is operating 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 simultaneously closes the valve connecting the auxiliary fuel control valve 4 and the combustion chamber 10. At this time, the gas turbine engine subsystem draws in air from the compressor 14 inlet, using the suction effect to cool the starter / generator 13. Simultaneously, the compressed air from the compressor 14 outlet is heated by the primary heat exchanger 5, and after passing through the bypass control valve 16, it enters the pressure swing adsorption molecular sieve in the secondary heat exchanger 9, achieving the separation of nitrogen (N2) and oxygen (O2) from 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, where it reacts electrochemically with the fuel connected to the anode inlet. The generated electrical energy is stored in the battery 12 after being regulated and converted by the power regulator 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 reformed by the reformer 3 and heat-exchanged by the secondary heat exchanger 9 before directly entering the combustion chamber 10 for combustion. The generated high-temperature and high-pressure gas drives the turbine 6 of the gas turbine engine to rotate, which drives the coaxial compressor 14 and the starter generator 13 to work. The controller 15 sends a load signal to the starter / generator 13, and the starter / generator 13 starts to output electrical energy to the power regulator 11. After being regulated and converted by the power regulator, the electrical energy is stored in the battery 12. The exhaust gas at the outlet of the turbine 6 of the gas turbine engine is cooled by the primary heat exchanger 5 and then discharged into the surrounding atmosphere.

[0055] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should be covered within the protection scope of the present invention.

Claims

1. A novel SOFC-GT-LTSEPS system architecture cryogenic superconducting propulsion system, characterized in that, The liquid hydrogen storage tank (1) is connected to the compressor (3) through the first channel valve (2). The outlet of the compressor (3) is connected to the inlet of the first three-way valve (4). One outlet of the first three-way valve (4) is connected to the primary heat exchanger (5), and the primary heat exchanger (5) is connected to the anode inlet of the SOFC (6). The other outlet of the first three-way valve (4) is connected to the hydrogen circulation system, which provides a superconducting cryogenic working environment for the cryogenic superconducting starter / generator (10) and the cryogenic superconducting motor system. The hydrogen circulation system then enters the other inlet of the first channel valve (2) and the other inlet of the first three-way valve (28) through the fourth three-way valve (28). Combustion chamber (8); exhaust gases from the anode and cathode of SOFC (6) enter combustion chamber (8) through primary heat exchanger (5) and secondary heat exchanger (7) for combustion; combustion chamber (8) drives turbine (9) to run, turbine (9) is coaxially connected to cryogenic superconducting starter / generator (10) and compressor (11), compressor (11) provides oxygen to combustion chamber (8) and the cathode of SOFC (6); the electrical energy output by SOFC (6) and cryogenic superconducting starter / generator (10) respectively powers cryogenic superconducting motor system, cryogenic superconducting motor system drives thrust fan system.

2. The novel SOFC-GT-LTSEPS system architecture cryogenic superconducting propulsion system according to claim 1, characterized in that, The cryogenic superconducting motor system includes a first cryogenic superconducting motor (18) and a second cryogenic superconducting motor (23), and the thrust fan system includes a first thrust fan (17) and a second thrust fan (24). The first cryogenic superconducting motor (18) drives the first thrust fan (17), and the second cryogenic superconducting motor (23) drives the second thrust fan (24). The first cryogenic superconducting motor (18) is powered by a cryogenic superconducting starter / generator (10), and the second cryogenic superconducting motor (23) is powered by an SOFC (6).

3. The novel SOFC-GT-LTSEPS system architecture cryogenic superconducting propulsion system according to claim 2, characterized in that, The cryogenic superconducting starter / generator (10) is connected to the first cryogenic superconducting motor (18) through the first DC / AC converter (19) and the first DC booster (20); the electrical outlet of the SOFC (6) is connected to the second cryogenic superconducting motor (23) through the second DC / AC converter (21) and the second DC booster (22).

4. The novel SOFC-GT-LTSEPS system architecture cryogenic superconducting propulsion system according to claim 2, characterized in that, The hydrogen cycle system includes: a first three-way valve (4) connected to the hot end inlet of the first heat exchanger (16) and the inlet of the second channel valve (12), wherein the second channel valve (12) is a double-inlet and double-outlet valve. The flow path of the first three-way valve (4) and the first heat exchanger (16) passes through the low-temperature superconducting starter / generator (10) and provides a low-temperature environment. The hot end outlet of the first heat exchanger (16) is connected to the second three-way valve (15). The outlet of the second channel valve (12) is connected to the second three-way valve (15) through the cold end of the secondary heat exchanger (13) and the primary heat exchanger (14). The last outlet of the second three-way valve (15) is connected to the inlet of the second channel valve (12). The outlet of the second channel valve (12) is connected to the fourth three-way valve (28).

5. A novel SOFC-GT-LTSEPS system architecture cryogenic superconducting propulsion system according to claim 4, characterized in that, The hot exhaust gas emitted after the turbine (9) passes through the hot ends of the secondary heat exchanger (13) and the primary heat exchanger (14) before being discharged outside the machine.

6. The novel SOFC-GT-LTSEPS system architecture cryogenic superconducting propulsion system according to claim 4, characterized in that, The hydrogen cycle system also includes: a first three-way valve (4) is also connected to the inlet of the third channel valve (26), the third channel valve (26) is a double-inlet and double-outlet valve, the outlet of the third channel valve (26) is connected to the inlet of the second channel valve (12), the outlet of the third channel valve (26) is connected to the cold end inlet of the first heat exchanger (16) and the cold end inlet of the second heat exchanger (25); the cold end outlet of the first heat exchanger (16) provides a low-temperature environment for the first low-temperature superconducting motor (18) and then connects to the inlet of the fourth three-way valve (28); the cold end outlet of the second heat exchanger (25) provides a low-temperature environment for the second low-temperature superconducting motor (23) and then connects to the hot end inlet of the second heat exchanger (25), the hot end outlet of the second heat exchanger (25) is connected to the inlet of the third channel valve (26).

7. A method for operating a novel SOFC-GT-LTSEPS system architecture cryogenic superconducting propulsion system, using the novel SOFC-GT-LTSEPS system architecture cryogenic superconducting propulsion system as described in claim 6, characterized in that, Including GT-LTSEPS mode: The liquid hydrogen storage tank (1) is connected to the combustion chamber (8), and the compressor (11) is connected to the combustion chamber (8). The start-up of the cryogenic superconducting starter / generator (10) works as a starter, driving the turbine (9) and the compressor (11) to run, so that the turbine (9) rises to the ignition speed. Then the combustion chamber (8) is ignited and burned. The high-temperature gas drives the turbine (9) to rotate. When the turbine (9) reaches the cut-off speed, the cryogenic superconducting starter / generator (10) works as a generator. The hydrogen circulation system provides liquid hydrogen to provide superconducting cryogenic conditions for the cryogenic superconducting starter / generator (10), the first cryogenic superconducting motor (18), and the second cryogenic superconducting motor (23). The cryogenic superconducting starter / generator (10) provides electrical energy to the first cryogenic superconducting motor (18), and the battery provides electrical energy to the second cryogenic superconducting motor (23).

8. The operating method of a novel SOFC-GT-LTSEPS system architecture cryogenic superconducting propulsion system according to claim 7, characterized in that, Also includes SOFC-GT-LTSEPS mode: After the GT-LTSEPS mode is working stably, when the stack temperature of SOFC (6) reaches the required level, the cathode path from compressor (11) to SOFC (6) is selected, the anode path from compressor (3) to SOFC (6) is selected, and the hydrogen input channel from liquid hydrogen tank to combustion chamber (8) is cut off. The air input channel from compressor (11) to combustion chamber (8) is also cut off. The exhaust gas from the anode outlet of SOFC (6) and the exhaust gas from the cathode outlet pass through the primary heat exchanger (5) and the primary heat exchanger (7) respectively to cool down before entering the combustion chamber (8) for mixing and combustion. SOFC (6) provides power to the second low-temperature superconducting motor (23). The hydrogen circulation system provides liquid hydrogen to provide superconducting low-temperature conditions for the low-temperature superconducting starter / generator (10), the first low-temperature superconducting motor (18) and the second low-temperature superconducting motor (23). The low-temperature superconducting starter / generator (10) provides power to the first low-temperature superconducting motor (18).

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