Liquid hydrogen fuel energy power system and airplane

Abstract

The utility model discloses a liquid hydrogen fuel energy power system and an airplane, and belongs to the technical field of liquid hydrogen airplane power device system integration. The system comprises a liquid hydrogen tank, a liquid hydrogen pipeline, a gas hydrogen pipeline, a heat conduction liquid circulation pipeline, an air pipeline, a hydrogen turbine engine power device, a fuel cell, a heating device, a primary heat exchanger, a secondary heat exchanger, a starter and an onboard power supply and distribution network. According to the system, liquid-gas-hydrogen conversion is realized through absorption of waste heat of the fuel cell and exhaust waste heat of the exhaust nozzle of the engine, and the problem of vaporization of liquid hydrogen fuel on the engine is effectively solved. Pressurized air is provided for the fuel cell through air entraining of an engine air compressor, waste heat of the fuel cell is absorbed through a first-stage heat exchanger, and the air side supply and heat dissipation functions of the fuel cell are achieved. A two-stage heat exchange device is formed through the fuel cell heat dissipation heat exchanger and the exhaust nozzle heat regenerator, and fuel vaporization heating of different hydrogen fuel flow supply requirements is achieved according to the starting process and the stable operation process.

Description

TECHNICAL FIELD

[0001] The utility model belongs to liquid hydrogen aircraft power device system integration technical field especially relates to a kind of liquid hydrogen fuel energy power system and aircraft. BACKGROUND

[0002] With the continuous improvement of environmental protection requirements of civil aviation transport industry, there is an urgent demand for disruptive civil aircraft products that can reduce pollutant emissions. The main technical route of the foreseeable new energy civil aircraft product for reducing pollution emissions includes: sustainable fuel SAF and hydrogen energy route. Among them, hydrogen fuel, as an ideal clean energy to replace existing aircraft fuel (aviation kerosene), has an energy density ratio of three times that of existing fuel, and hydrogen energy is expected to increase the effective payload and range of aircraft. For solving environmental problems, since the hydrogen combustion product is only water, it can achieve true zero carbon emission, and reduce the environmental impact by 50% to 90% in flight state. Combined with its high energy density, hydrogen energy has become an important energy for reducing emissions in future new energy aircraft.

[0003] The volume energy density of low-temperature liquid hydrogen storage is about 3 times that of 35MPa high-pressure gas hydrogen storage and 1.8 times that of 70MPa high-pressure gas hydrogen storage, so for future long-range branch and trunk aircraft, liquid hydrogen storage will be a more feasible form of on-board fuel storage. At the same time, the high heat sink property of liquid hydrogen can improve the energy utilization efficiency of the power system and reduce fuel consumption. The application form of hydrogen fuel on hydrogen energy aircraft is mainly to provide energy for hydrogen turbine engine power or hydrogen fuel cell power. Hydrogen turbine engine is a power device that directly burns hydrogen fuel and converts the internal energy of fuel into mechanical energy. Fuel cell is an energy conversion device that converts fuel chemical energy directly into electrical energy through chemical reaction. Based on the current technical status, fuel cell is limited by specific power and heat, and it is difficult to expand to higher power application scenarios in the short term. Therefore, for branch, trunk and long-range aircraft, hydrogen turbine engine as the main power and fuel cell as the auxiliary power will be the feasible power system architecture form in the future.

[0004] With the technical breakthrough of liquid hydrogen storage and hydrogen power system, hydrogen energy branch, trunk and long-range aircraft will be expected to be successfully developed. For the existing liquid hydrogen fuel energy power system scheme, it involves independent working mode of system, and fails to fully utilize liquid hydrogen cold energy for heat management, so the system has low comprehensive energy utilization efficiency, system functional components are not reasonably utilized, the system is relatively complex, and the problems of heat source required for engine starting when using liquid hydrogen as fuel and power system starting are not considered. UTILITY MODEL CONTENTS

[0005] Therefore, the utility model discloses a kind of liquid hydrogen fuel energy power system and aircraft.

[0006] The utility model discloses adopt the following technical scheme:

[0007] A liquid hydrogen fuel energy power system, the system includes: liquid hydrogen tank, liquid hydrogen pipeline, primary heat exchanger, gas hydrogen pipeline, heat conduction liquid circulation pipeline, air pipeline, hydrogen turbine engine power device, fuel cell, heating device, starter, airborne power supply and distribution network;

[0008] The hydrogen turbine engine power device includes compressor, combustion chamber, turbine and tail nozzle, and the compressor, the combustion chamber, the turbine and the tail nozzle are sequentially arranged.

[0009] The outlet of the liquid hydrogen tank is connected with the liquid hydrogen inlet of the primary heat exchanger through the liquid hydrogen pipeline, and a liquid hydrogen pump is arranged on the liquid hydrogen pipeline.

[0010] The first branch of the gas hydrogen outlet of the primary heat exchanger is connected with the fuel inlet of the fuel cell through the gas hydrogen pipeline, and a temperature sensor and an adjusting valve are arranged at the position of the fuel inlet of the fuel cell.

[0011] The second branch of the gas hydrogen outlet of the primary heat exchanger is connected with the fuel inlet of the combustion chamber through the gas hydrogen pipeline, and a temperature sensor and an adjusting valve are arranged at the position of the fuel inlet of the combustion chamber.

[0012] The heating device is arranged on the heat conduction liquid circulation pipeline, and the heat conduction liquid circulation pipeline flows through the fuel cell and the primary heat exchanger.

[0013] The air pipeline includes the pipeline of the engine main flow channel air flow path and the pipeline connecting the bleed air port of the compressor and the air input port of the fuel cell.

[0014] The airborne power supply and distribution network is connected with the fuel cell and the starter respectively, and the starter is connected with the turbine engine.

[0015] Further, the system includes a secondary heat exchanger, the gas hydrogen outlet of the primary heat exchanger further includes a third branch, the third branch is connected with the gas hydrogen inlet of the secondary heat exchanger through the gas hydrogen pipeline, the gas hydrogen outlet of the secondary heat exchanger is connected with the fuel inlet of the combustion chamber through the gas hydrogen pipeline, a temperature sensor and an adjusting valve are arranged at the position of the fuel inlet of the combustion chamber, and the secondary heat exchanger is arranged at the position of the tail nozzle.

[0016] Further, the gas hydrogen pipeline includes a first gas hydrogen pipeline, a second gas hydrogen pipeline and a third gas hydrogen pipeline.

[0017] The first gas hydrogen pipeline includes the inlet of the first three-way valve, the first outlet of the first three-way valve, the fuel inlet of the fuel cell, which are sequentially connected with the primary heat exchanger, the first adjusting valve and the first three-way valve, and a temperature sensor is arranged between the first adjusting valve and the fuel inlet of the fuel cell.

[0018] The second hydrogen gas pipeline comprises: sequentially connecting the primary heat exchanger, the inlet of the first three-way valve, the second outlet of the first three-way valve, the inlet of the second three-way valve, the first outlet of the second three-way valve, the second regulating valve and the fuel inlet of the combustion chamber;

[0019] The third hydrogen gas pipeline comprises: sequentially connecting the second outlet of the second three-way valve, the secondary heat exchanger, the one-way valve, the second regulating valve and the fuel inlet of the combustion chamber; a temperature sensor is arranged between the second regulating valve and the fuel inlet of the combustion chamber.

[0020] Further, the heat-conducting liquid circulation pipeline comprises a first circulation pipeline and a second circulation pipeline;

[0021] The first circulation pipeline comprises: sequentially connecting the heat-conducting liquid output port of the fuel cell, the heat-conducting liquid circulation pump, the inlet of the third three-way valve, the first outlet of the third three-way valve, the heating device and the heat-conducting liquid input port of the fuel cell;

[0022] The second circulation pipeline comprises: sequentially connecting the heat-conducting liquid output port of the fuel cell, the heat-conducting liquid circulation pump, the inlet of the third three-way valve, the second outlet of the third three-way valve, the primary heat exchanger and the heat-conducting liquid input port.

[0023] Further, a stop valve is arranged at the liquid hydrogen tank outlet position.

[0024] Further, the on-board power supply and distribution network is connected with on-board equipment.

[0025] Further, the starter is connected with the hydrogen turbine engine power device through a transmission mechanism.

[0026] Further, one end of the transmission shaft is provided with a propelling device.

[0027] An airplane is provided with the above-mentioned liquid hydrogen fuel energy power system.

[0028] Further, the hydrogen storage tank is arranged at the rear half of the fuselage, and the fuel cell is arranged at the tail end of the fuselage.

[0029] The beneficial effects of the utility model are as follows:

[0030] (1) The liquid gas hydrogen conversion is realized by absorbing the waste heat of the fuel cell and the exhaust waste heat of the engine tail nozzle, the liquid hydrogen fuel vaporization problem on the airplane is effectively solved, the fuel cell heat dissipation energy consumption is saved, the engine fuel supply temperature and enthalpy value are improved, the fuel consumption is reduced, and the system energy comprehensive utilization efficiency is improved.

[0031] (2) The fuel cell heating device not only provides the initial ambient temperature for starting the fuel cell, but also realizes liquid-gas hydrogen conversion as an initial heat source, and provides a heat source function. The engine compressor bleed air is used to provide pressurized air for the fuel cell, and the first heat exchanger is used to absorb the waste heat of the fuel cell, so as to realize the air supply and heat dissipation functions of the fuel cell, without the need to equip a separate air inlet pressurizing device and heat dissipation device, thereby realizing the functional reuse of system components, reducing system equipment, and reducing system complexity.

[0032] (3) A two-stage heat exchange device is adopted, that is, a two-stage heat exchange device is formed by the fuel cell heat dissipation heat exchanger and the tail nozzle heat exchanger, so as to realize fuel vaporization heating with different hydrogen fuel flow supply requirements for the starting process and the stable operation process, and the supply has large adjustable margin and flexible adjustment. Under the condition of small flow hydrogen fuel supply in the starting process, the liquid hydrogen fuel does not need to pass through the second heat exchanger, so as to reduce the fuel flow path, reduce the pressure loss along the path, and improve the fuel supply quality.

[0033] (4) A system starting method is provided to solve the problem of the heat source of the system starting, and realize the joint starting of the main power device and the auxiliary power device. BRIEF DESCRIPTION OF DRAWINGS

[0034] In order to more clearly illustrate the technical scheme of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiments. Obviously, the drawings described in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.

[0035] Figure 1 is a schematic diagram of a liquid hydrogen fuel energy power system of the present application;

[0036] Figure 2 is a schematic diagram of a liquid hydrogen fuel energy power system of the present application.

[0037] Illustration: Figure 1 The line marked with "1" represents a liquid hydrogen pipeline, the line marked with "2" represents a gaseous hydrogen pipeline, and the line marked with "3" represents a heat-conducting liquid circulation pipeline. DETAILED DESCRIPTION

[0038] In order to better understand the technical scheme of the present application, the following will describe the embodiments of the present application in detail in combination with the drawings.

[0039] It should be clear that the described embodiments are only some embodiments of the present application, not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0040] Embodiment 1

[0041] As Figure 1 shown, Figure 1 "three-way valve 1" is the first three-way valve of the embodiment, "three-way valve 2" is the second three-way valve of the embodiment, and "three-way valve 3" is the third three-way valve of the embodiment. Figure 1 "regulating valve 1" is the first regulating valve of the embodiment, and "regulating valve 2" is the second regulating valve of the embodiment.

[0042] A liquid hydrogen fuel energy power system, the system comprising: a liquid hydrogen tank, a primary heat exchanger, a liquid hydrogen pipeline, a gaseous hydrogen pipeline, a heat-conducting liquid circulation pipeline, an air pipeline, a hydrogen turbine engine power device, a fuel cell, a heating device, a starter, an on-board power supply and distribution network; the output shaft power of the hydrogen turbine power device is used to drive a propulsion device or a power generation device to generate electric energy.

[0043] The hydrogen turbine engine power device comprises a compressor, a combustion chamber, a turbine and an exhaust nozzle; the compressor, the combustion chamber, the turbine and the exhaust nozzle are sequentially arranged;

[0044] The outlet of the liquid hydrogen tank is connected with the liquid hydrogen inlet of the primary heat exchanger through the liquid hydrogen pipeline, and a liquid hydrogen pump is arranged on the liquid hydrogen pipeline;

[0045] The first branch of the gaseous hydrogen outlet of the primary heat exchanger is connected with the fuel inlet of the fuel cell through the gaseous hydrogen pipeline, and a temperature sensor and a regulating valve are arranged at the position of the fuel inlet of the fuel cell;

[0046] The second branch of the gaseous hydrogen outlet of the primary heat exchanger is connected with the fuel inlet of the combustion chamber through the gaseous hydrogen pipeline, and a temperature sensor and a regulating valve are arranged at the position of the fuel inlet of the combustion chamber;

[0047] The heat-conducting liquid circulation pipeline is provided with the heating device, and the heat-conducting liquid circulation pipeline flows through the fuel cell and the primary heat exchanger;

[0048] The air pipeline comprises: a pipeline of an engine main flow passage air flow path, and a pipeline connecting the bleed air port of the compressor and the air input port of the fuel cell;

[0049] The on-board power supply and distribution network is connected with the fuel cell and the starter respectively, and the starter is connected with the turbine engine.

[0050] Further, the system comprises a secondary heat exchanger, the hydrogen gas outlet of the primary heat exchanger further comprises a third branch, the third branch is connected with the hydrogen gas inlet of the secondary heat exchanger through a hydrogen gas pipeline, the hydrogen gas outlet of the secondary heat exchanger is connected with the fuel inlet of the combustion chamber through a hydrogen gas pipeline, the fuel inlet of the combustion chamber is provided with a temperature sensor and a regulating valve; the secondary heat exchanger is arranged at the position of the tail nozzle.

[0051] Further, the hydrogen gas pipeline comprises a first hydrogen gas pipeline, a second hydrogen gas pipeline and a third hydrogen gas pipeline.

[0052] The first hydrogen gas pipeline comprises: the primary heat exchanger, the inlet of the first three-way valve, the first outlet of the first three-way valve, the first regulating valve, the fuel inlet of the fuel cell connected in sequence; a temperature sensor is arranged between the first regulating valve and the fuel inlet of the fuel cell.

[0053] The second hydrogen gas pipeline comprises: the primary heat exchanger, the inlet of the first three-way valve, the second outlet of the first three-way valve, the inlet of the second three-way valve, the first outlet of the second three-way valve, the second regulating valve and the fuel inlet of the combustion chamber connected in sequence.

[0054] The third hydrogen gas pipeline comprises: the second outlet of the second three-way valve, the secondary heat exchanger, the one-way valve, the second regulating valve and the fuel inlet of the combustion chamber connected in sequence; a temperature sensor is arranged between the second regulating valve and the fuel inlet of the combustion chamber.

[0055] Further, the heat-conducting liquid circulation pipeline comprises a first circulation pipeline and a second circulation pipeline.

[0056] The first circulation pipeline comprises: the heat-conducting liquid output port of the fuel cell, the heat-conducting liquid circulation pump, the inlet of the third three-way valve, the first outlet of the third three-way valve, the heating device and the heat-conducting liquid input port of the fuel cell connected in sequence.

[0057] The second circulation pipeline comprises: the heat-conducting liquid output port of the fuel cell, the heat-conducting liquid circulation pump, the inlet of the third three-way valve, the second outlet of the third three-way valve, the primary heat exchanger and the heat-conducting liquid input port connected in sequence.

[0058] Further, the liquid hydrogen tank outlet is provided with a stop valve.

[0059] Further, the on-board power supply and distribution network is connected with on-board equipment.

[0060] Further, the starter is connected with the hydrogen turbine engine power device through a transmission mechanism.

[0061] Further, one end of the transmission shaft is provided with a propelling device.

[0062] An aircraft is provided with the above-mentioned liquid hydrogen fuel energy power system.

[0063] Further, the hydrogen storage tank is arranged at the rear half of the fuselage, and the fuel cell is arranged at the tail end of the fuselage. Figure 2

[0064] Embodiment 2

[0065] A full-machine liquid hydrogen energy power system uses liquid hydrogen as fuel, a hydrogen turbine engine as the main propulsion power, and a fuel cell as auxiliary power, and is suitable for branch line and trunk line long-range aircraft. In the system, the problems of comprehensive utilization of energy, functional reuse of system components, flexible adjustment of fuel supply, system starting heat source and starting method are mainly considered, the efficient utilization of liquid hydrogen fuel from the low-temperature hydrogen storage device to the hydrogen power is realized, the system energy utilization efficiency is improved, the system equipment is reduced, the system complexity is reduced, and the fuel supply adjustable margin is improved.

[0066] A liquid hydrogen fuel energy power system includes a hydrogen turbine engine power device, a fuel cell auxiliary power device (mainly including a fuel cell), a hydrogen storage device (mainly including a liquid hydrogen tank), a two-stage heat exchange device (mainly including a first-stage heat exchanger and a second-stage heat exchanger), an energy storage battery, a starter, and an airborne power supply and distribution network.

[0067] The hydrogen turbine engine power device includes a compressor, a combustion chamber, a turbine, and a tail nozzle. The hydrogen turbine power device outputs shaft power to drive a propulsion device or a power generation device to generate electric energy.

[0068] The fuel cell auxiliary power device includes a fuel cell, a heating device, a heat-conducting liquid circulating pump, a first-stage heat exchanger, and heat-conducting liquid for heat management. The air intake system includes hydrogen gas intake and high-pressure air intake. The fuel cell auxiliary power device outputs electric energy to the airborne power supply and distribution network.

[0069] The hydrogen storage device is a low-temperature liquid hydrogen storage tank, which is equipped with a liquid hydrogen filling port, a liquid hydrogen discharge port, a sensor installation interface, safety valves, pressure regulating valves, and other valve interfaces. The shape of the storage tank can be a conventional sphere, a cylinder, or a special shape.

[0070] The two-stage heat exchange device is located downstream of the hydrogen storage device and at the tail nozzle of the engine. The first-stage heat exchanger is used to realize heat flow transfer between fuel cell heat production and liquid hydrogen fuel, and the second-stage heat exchanger is used to realize heat flow transfer between tail nozzle exhaust waste heat and hydrogen fuel. The first-stage heat exchanger completes the vaporization of liquid hydrogen fuel, and the second-stage heat exchanger realizes the required fuel temperature rise under the demand of large-flow fuel supply of the engine.

[0071] Embodiment 3

[0072] As shown in Figure 1 ​As shown, Figure 1 In this embodiment, "three-way valve 1" refers to the first three-way valve, "three-way valve 2" refers to the second three-way valve, and "three-way valve 3" refers to the third three-way valve. Figure 1 In this embodiment, "regulating valve 1" refers to the first regulating valve and "regulating valve 2" refers to the second regulating valve.

[0073] A liquid hydrogen fuel cell power system includes a hydrogen turbine engine power unit, a fuel cell auxiliary power unit, a hydrogen storage device, a two-stage heat exchange device, an energy storage battery, a starter, an onboard power supply and distribution network, onboard equipment, a shut-off valve, a liquid hydrogen pump, a heat transfer fluid circulation pump, a three-way valve, a regulating valve, liquid hydrogen pipelines, gaseous hydrogen pipelines, air pipelines, and heat transfer fluid circulation pipelines. The liquid hydrogen fuel cell power system scheme includes:

[0074] The liquid hydrogen pipeline is connected in sequence to a liquid hydrogen storage tank, a shut-off valve, a liquid hydrogen pump, and a first-stage heat exchanger. It is used to pressurize the output liquid hydrogen to the required pressure, and after being vaporized by the first-stage heat exchanger, it is transported downstream for use by fuel cells and hydrogen turbine engines.

[0075] The gaseous hydrogen pipeline is divided into three lines: the first, second, and third gaseous hydrogen pipelines. The first gaseous hydrogen pipeline connects sequentially to the primary heat exchanger, the inlet of the first three-way valve, the first outlet of the first three-way valve, the first regulating valve, and the hydrogen input port of the fuel cell, supplying gaseous hydrogen to the hydrogen inlet side of the fuel cell for chemical reaction. The second gaseous hydrogen pipeline connects sequentially to the primary heat exchanger, the inlet of the first three-way valve, the second outlet of the first three-way valve, the inlet of the second three-way valve, the first outlet of the second three-way valve, the second regulating valve, and the fuel inlet of the combustion chamber, delivering gaseous hydrogen to the combustion chamber of the hydrogen turbine engine for combustion. The third gaseous hydrogen pipeline connects sequentially to the second outlet of the second three-way valve, the secondary heat exchanger, the check valve, the second regulating valve, and the fuel inlet of the combustion chamber, further heating the gaseous hydrogen before delivering it to the combustion chamber of the hydrogen turbine engine for combustion. Figure 1 As shown in the figure, the line marked "1" represents the liquid hydrogen pipeline, the line marked "2" represents the gaseous hydrogen pipeline, and the line marked "3" represents the heat transfer fluid circulation pipeline.

[0076] The two-stage heat exchange system is located downstream of the hydrogen storage unit and at the exhaust nozzle, respectively. The two-stage heat exchange system includes a primary heat exchanger and a secondary heat exchanger. The primary heat exchanger has two heat exchange channels: a liquid hydrogen fuel channel and a heat transfer fluid channel. The heat transfer fluid carries away the waste heat generated by the fuel cell and transfers it to the liquid hydrogen fuel through the primary heat exchanger, achieving liquid-to-gas hydrogen conversion and fuel cell cooling. The secondary heat exchanger also has two heat exchange channels: a gaseous hydrogen fuel channel and an engine exhaust nozzle channel. The secondary heat exchanger transfers the exhaust waste heat from the exhaust nozzle to the gaseous hydrogen fuel, further warming the gaseous hydrogen fuel to meet the minimum combustion temperature requirements of the combustion chamber.

[0077] The air pipeline is divided into two routes. One route is connected with the air port of the compressor and the air input port of the fuel cell, and high-pressure air generated by the compressor is used to provide air for the fuel cell, so as to realize the reuse of the compressor function. The other route is the air flow path of the main flow path of the engine, which sequentially completes the compression of the compressor, the combustion in the combustion chamber, the work of the turbine, and the exhaust of the tail nozzle. The exhaust heat is absorbed by the low-temperature hydrogen, and the waste heat is recovered.

[0078] The heat-conducting liquid circulation pipeline is divided into two routes, i.e., a first circulation pipeline and a second circulation pipeline. The first circulation pipeline is connected with the fuel cell heat-conducting liquid output port, the heat-conducting liquid circulation pump, the third three-way valve first outlet, the heating device, and the heat-conducting liquid input port in sequence, and is used to realize the high-efficiency operation environment required for cold start of the fuel cell. The fuel cell heating is to maintain the normal working temperature of the battery and prevent the performance of the battery from being reduced or unable to work normally in a low-temperature environment. When the fuel cell is cold started, the heating device is turned on to heat the heat-conducting liquid, and after the internal temperature of the fuel cell reaches the most suitable working temperature, the heating device is turned off. The heat-conducting liquid is used to maintain the internal temperature of the fuel cell at the most suitable working temperature.

[0079] The second circulation pipeline is connected with the fuel cell heat-conducting liquid output port, the heat-conducting liquid circulation pump, the third three-way valve second outlet, the primary heat exchanger, and the heat-conducting liquid input port in sequence, and is used to transfer the waste heat generated by the operation of the fuel cell to the liquid hydrogen fuel, so as to realize the conversion of liquid and gaseous hydrogen and the heat dissipation of the fuel cell. The fuel cell uses liquid cooling, and liquid cooling is widely used in high-power fuel cell stacks because the heat transfer coefficient of liquid flow is higher than that of air flow, and it is more convenient to realize high-efficiency heat recovery.

[0080] In addition, the starter is connected to the on-board power supply network, and the starting power of the starter is provided by the on-board energy storage battery. The hydrogen turbine engine is started by the starter, and the on-board high-power density energy storage battery drives the starter and is connected with the engine shaft through a transmission mechanism. The fuel cell and the energy storage battery output electric energy to the on-board power supply network, which is used for the power use of the starter and on-board equipment. At the same time, the fuel cell can charge the energy storage battery.

[0081] The secondary heat exchanger is integrated with the hydrogen turbine engine to fully use the heat source of the engine for heat exchange, and to use the high heat sink property of liquid hydrogen to improve the performance of the engine. In the embodiment, an integrated arrangement scheme of the heat exchanger and the tail nozzle is proposed to use the exhaust heat of the tail nozzle to improve the energy utilization efficiency. In addition, other forms of integrated schemes can also be used to use the cooling capacity of liquid hydrogen. The engine thermodynamic cycle established by considering the use of the cooling capacity of liquid hydrogen is generally referred to as an unconventional thermodynamic cycle, including an intercooling cycle, a hydrogen-cooled turbine cycle, and a regenerative cycle. Among them, the intercooling cycle refers to using liquid hydrogen to cool the inlet air flow of the compressor to reduce the work of the compressor and improve the cycle efficiency; the hydrogen-cooled turbine cycle refers to using liquid hydrogen to cool the turbine cooling gas to improve the cooling capacity of the cooling gas, thereby increasing the temperature before the turbine and improving the cycle efficiency; the regenerative cycle refers to using liquid hydrogen to absorb the high-temperature exhaust heat of the engine to increase the temperature and enthalpy of the fuel and reduce fuel consumption.

[0082] Liquid hydrogen consumes energy during preparation. In order to compensate for this part of the energy consumption in advance, the cooling capacity carried by liquid hydrogen should be fully utilized during the use of liquid hydrogen for energy power system energy comprehensive management. On the one hand, the fuel cell cooling circuit is connected with the primary heat exchanger, and the cooling capacity of liquid hydrogen is used to cool the fuel cell, and the waste heat generated by the fuel cell is used to heat the low-temperature fuel; on the other hand, the exhaust of the engine tail nozzle is connected with the secondary heat exchanger, and the exhaust heat is used to heat the low-temperature fuel. Both methods increase the enthalpy of the fuel and reduce the fuel consumption, thereby improving the energy comprehensive utilization efficiency of the system.

[0083] The fuel cell heating device provides the initial environment required for starting the fuel cell, and the heat source is also used to realize the initial conversion of liquid and gaseous hydrogen required for starting the system, effectively solving the problem of heat source for starting the system, and no separate liquid hydrogen vaporization heating device is needed. In addition, the engine compressor bleed air is used to provide pressurized air for the fuel cell, and the primary heat exchanger is used to absorb the waste heat of the fuel cell to realize the air supply and heat dissipation functions of the fuel cell, and no separate air inlet pressurization device and heat dissipation device is needed. Through the above-mentioned methods, the function multiplexing of system components is realized, and the system equipment is reduced, thereby reducing the complexity of the system.

[0084] The hydrogen fuel is regulated by the two-stage heat exchanger. When the system is in a starting process or a slow vehicle state, the fuel flow demand is small, and the required heating amount of the low-temperature fuel is small. At this time, the gaseous hydrogen fuel does not need to pass through the second-stage heat exchanger, directly enters the combustion chamber through the second gaseous hydrogen pipeline to participate in combustion, reduces the fuel flow path, reduces the pressure loss along the path, and improves the fuel supply quality. When the system is in a take-off climb and cruise state, the fuel flow demand is large, and the required heating amount of the low-temperature fuel is large. At this time, the gaseous hydrogen fuel needs to pass through the second-stage heat exchanger to further absorb heat, so as to realize the minimum temperature requirement of the hydrogen fuel combustion under large flow. The fuel is regulated by the two-stage heat exchanger, so as to realize the fuel vaporization and heating under different hydrogen fuel flow supply requirements, and the regulation is flexible with large adjustable margin.

[0085] The fuel cell is used in a flight process, serves as an airborne energy output, reduces the demand of the aircraft on the engine power extraction, and improves the working performance of the engine.

[0086] The utility model also provides a kind of liquid hydrogen fuel energy power system combined starting method, specifically as follows:

[0087] (1) start fuel cell self-heating device and heat-conducting liquid circulating pump, open third three-way valve inlet and first outlet, heat-conducting liquid is continuously heated until the temperature in fuel cell reaches suitable working temperature;

[0088] (2) close the first outlet of the third three-way valve, open the second outlet, and the heat-conducting liquid circulating pump pumps the heat-conducting liquid into the first heat exchanger;

[0089] (3) start starter, and the starter drives the hydrogen turbine engine to start by transmission mechanism;

[0090] (4) start liquid hydrogen pump, and the liquid hydrogen is vaporized by heat exchange with the heat-conducting liquid in the first heat exchanger. Open the inlet of the first three-way valve and the second outlet, the inlet of the second three-way valve and the first outlet, and monitor the fuel inlet temperature of the combustion chamber simultaneously;

[0091] (5) change the flow of the heat-conducting liquid by adjusting the opening of the third three-way valve, and then affect the heat exchange amount of the first heat exchanger, so as to achieve the purpose of regulating the fuel inlet temperature of the combustion chamber. When the temperature of the gaseous hydrogen reaches the minimum requirement of combustion, ignite, and the hydrogen turbine engine continues to run, gradually enters the ground slow vehicle state, and completes starting;

[0092] (6) the engine compressor runs, and part of the high-pressure air from the compressor is used as the air source of the fuel cell, and the gaseous hydrogen temperature at the inlet of the first three-way valve is monitored;

[0093] (7) when the gaseous hydrogen temperature at the inlet of the first three-way valve reaches the required hydrogen temperature of the fuel cell, open the first outlet of the first three-way valve, and the gaseous hydrogen enters the fuel cell to react chemically, and the fuel cell completes starting.

[0094] As Figure 1 shown, Figure 1 In the figure, "three-way valve 1" is the first three-way valve of the embodiment, "three-way valve 2" is the second three-way valve of the embodiment, and "three-way valve 3" is the third three-way valve of the embodiment. Figure 1 In the figure, "regulating valve 1" is the first regulating valve of the embodiment, and "regulating valve 2" is the second regulating valve of the embodiment.

[0095] The system comprises a hydrogen turbine power device and a fuel cell auxiliary power device, and the hydrogen turbine power device and the fuel cell auxiliary power device are jointly started by using liquid hydrogen as fuel; the fuel cell cooling circuit is communicated with the first heat exchanger, the fuel cell is cooled by using the cold energy of the liquid hydrogen, and the waste heat generated by the fuel cell is used for heating low-temperature fuel; the engine tail nozzle exhaust is communicated with the second heat exchanger, and the exhaust waste heat is used for heating low-temperature fuel. Both the two modes increase the fuel enthalpy value, reduce fuel consumption, and improve the energy comprehensive utilization efficiency of the system; the fuel cell heating device provides the initial environment required for starting the fuel cell, and the heat source generated by the fuel cell heating device is also used for realizing the initial conversion of liquid and gaseous hydrogen required for starting the system, thereby providing a starting heat source for the system, and a separate liquid hydrogen vaporization heating device is not required. The booster air for the fuel cell is provided by using the engine compressor bleed air, the waste heat of the fuel cell is absorbed by using the first heat exchanger, the air supply and heat dissipation functions of the fuel cell are realized, and a separate air inlet booster device and heat dissipation device are not required. The system component function reuse is realized, and the system additional equipment is reduced; for fuel vaporization heating under different hydrogen fuel flow supply requirements in the starting process and the stable running process, the first or second heating mode can be used, the fuel supply adjustment margin is large, and the adjustment is flexible.

[0096] The above embodiment of the utility model is described in detail, the principle and implementation mode of the utility model are described by applying specific examples in the paper, and the above embodiment is only used to help understand the method and core idea of the utility model; meanwhile, for the general technical personnel in the field, according to the idea of the utility model, the specific implementation mode and application range will be changed, and the above is described, and the content of the specification should not be understood as the limitation of the utility model.

Claims

1. A liquid hydrogen fuel energy power system, characterized by, The system comprises a liquid hydrogen tank, a liquid hydrogen pipeline, a primary heat exchanger, a gaseous hydrogen pipeline, a heat-conducting liquid circulation pipeline, an air pipeline, a hydrogen turbine engine power device, a fuel cell, a heating device, a starter, an airborne power supply and distribution network; The hydrogen turbine engine power device comprises a compressor, a combustion chamber, a turbine and a tail nozzle; the compressor, the combustion chamber, the turbine and the tail nozzle are sequentially arranged; An outlet of the liquid hydrogen tank is connected with a liquid hydrogen inlet of the primary heat exchanger through the liquid hydrogen pipeline, and a liquid hydrogen pump is arranged on the liquid hydrogen pipeline; A first branch of a gaseous hydrogen outlet of the primary heat exchanger is connected with a fuel inlet of the fuel cell through the gaseous hydrogen pipeline, and a temperature sensor and a regulating valve are arranged at the fuel inlet of the fuel cell; A second branch of the gaseous hydrogen outlet of the primary heat exchanger is connected with a fuel inlet of the combustion chamber through the gaseous hydrogen pipeline; and a temperature sensor and a regulating valve are arranged at the fuel inlet of the combustion chamber; The heat-conducting liquid circulation pipeline passes through the fuel cell and the primary heat exchanger and is provided with the heating device; The air pipeline comprises a pipeline of an engine main flow channel air flow path and a pipeline connecting a bleed air port of the compressor and an air input port of the fuel cell; The airborne power supply and distribution network is connected with the fuel cell and the starter respectively, and the starter is connected with the turbine engine.

2. The power system of claim 1, wherein, The system comprises a secondary heat exchanger, the gaseous hydrogen outlet of the primary heat exchanger further comprises a third branch, the third branch is connected with a gaseous hydrogen inlet of the secondary heat exchanger through a gaseous hydrogen pipeline, a gaseous hydrogen outlet of the secondary heat exchanger is connected with a fuel inlet of the combustion chamber through a gaseous hydrogen pipeline, and a temperature sensor and a regulating valve are arranged at the fuel inlet of the combustion chamber; and the secondary heat exchanger is arranged at a position of the tail nozzle.

3. The power system of claim 2, wherein, The gaseous hydrogen pipeline comprises a first gaseous hydrogen pipeline, a second gaseous hydrogen pipeline and a third gaseous hydrogen pipeline; The first gaseous hydrogen pipeline comprises a first three-way valve, a first regulating valve, a fuel inlet of the fuel cell, an inlet of the first three-way valve, the primary heat exchanger, and a first outlet of the first three-way valve in sequence; and a temperature sensor is arranged between the first regulating valve and the fuel inlet of the fuel cell; The second gaseous hydrogen pipeline comprises a second three-way valve, a second regulating valve, a fuel inlet of the combustion chamber, a second outlet of the first three-way valve, an inlet of the second three-way valve, the primary heat exchanger, and a first outlet of the second three-way valve in sequence; The third gaseous hydrogen pipeline comprises a second outlet of the second three-way valve, the secondary heat exchanger, a one-way valve, the second regulating valve, and the fuel inlet of the combustion chamber in sequence; and a temperature sensor is arranged between the second regulating valve and the fuel inlet of the combustion chamber.

4. The power system of claim 1, wherein, The heat-conducting liquid circulation pipeline comprises a first circulation pipeline and a second circulation pipeline; The first circulation pipeline comprises a heat-conducting liquid output port of the fuel cell, a heat-conducting liquid circulation pump, an inlet of a third three-way valve, a first outlet of the third three-way valve, the heating device, and a heat-conducting liquid input port of the fuel cell in sequence. The second circulation pipeline comprises, in sequence, the fuel cell heat conducting liquid output port, the heat conducting liquid circulation pump, the third three-way valve inlet, the third three-way valve second outlet, the first heat exchanger and the heat conducting liquid input port.

5. The power system of claim 1, wherein, The liquid hydrogen tank outlet position is provided with a stop valve.

6. The power system of claim 1, wherein, The onboard power supply and distribution network is connected with onboard equipment.

7. The power system of claim 1, wherein, The starter is connected with the hydrogen turbine engine power device through a transmission shaft.

8. The power system of claim 7, wherein, One end of the transmission shaft is provided with a propulsion device.

9. An aircraft, characterized in that The aircraft is provided with the liquid hydrogen fuel energy power system as claimed in any one of claims 1-8.

10. The aircraft of claim 9, wherein, The liquid hydrogen tank is arranged at the rear half of the fuselage, and the fuel cell is arranged at the tail end of the fuselage.

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