Low-pollution aircraft energy system of hydrogen gas turbine and hydrogen fuel cell hybrid power APU and operation method of low-pollution aircraft energy system

Abstract

The invention belongs to the technical field of aviation hydrogen energy power systems, and discloses a hydrogen gas turbine and hydrogen fuel cell hybrid power APU low-pollution aircraft energy system which comprises a main engine, an APU, a water evaporation system, a valve set, a liquid hydrogen vaporization system and a controller, and the APU comprises a hydrogen gas turbine and a hydrogen fuel cell; the liquid hydrogen vaporizing system is connected with the main engine and the APU, the liquid hydrogen vaporizing system supplies vaporized hydrogen to the main engine and the APU, and the APU supplies a heat source for vaporizing the liquid hydrogen to the liquid hydrogen vaporizing system; the water evaporation system is connected with the main engine and the APU, the water evaporation system receives water of the hydrogen fuel cell, pressurizes and evaporates the water and then injects water vapor to the hydrogen gas turbine and the main engine, and exhaust gas of the main engine and exhaust gas of the hydrogen gas turbine provide heat sources for water vapor evaporation of the water evaporation system; the controller is connected with and controls the valve set, and the controller adjusts the operation state of the energy system by controlling the opening degree of the valve set. According to the method, an aircraft RAT system is omitted, the APU of the aircraft can be started at any height, and the energy efficiency of a main engine can be improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aviation hydrogen power systems, and relates to an aircraft hydrogen energy system and an operating method thereof, and specifically to a low-pollution aircraft energy system having a hydrogen gas turbine and a hydrogen fuel cell hybrid APU and a hydrogen combustion engine and an operating method thereof. Background Art

[0002] Traditional aircraft fueled by aviation kerosene have too much pollution and do not meet the goal of net zero carbon emissions. Clean fuels must be used instead. Hydrogen fuel is an important means of decarbonizing aviation. The amount of carbon dioxide produced by the hydrogen power system of aircraft is zero, and the main pollutants emitted are nitrogen oxides. Nitrogen oxides can damage the ozone layer, form acid rain, etc., and are harmful to the environment and human body.

[0003] The auxiliary power system of traditional aircraft, namely APU, can only provide auxiliary starting function below 12,000 meters. Above 12,000 meters, it cannot work due to insufficient ambient air intake. The aircraft needs to be equipped with RAT system to provide emergency power. The function of aircraft APU is limited by altitude, and the aircraft needs to be equipped with APU and RAT at the same time, which makes the system complex and heavy.

[0004] The high-temperature and high-pressure gases exhausted by the main engines and APU of traditional aircraft are directly discharged outside the aircraft, wasting a lot of heat.

[0005] To address these issues, it is necessary to develop an aircraft energy system that is low-pollution, high-efficiency, and light in weight.

[0006] Previous hydrogen-powered aircraft have used hydrogen as a single main propulsion energy source, and also needed to balance electrical power. However, this technology is not mature, which affects the operating efficiency of the main engine. Summary of the invention

[0007] In order to solve the above problems, the present invention proposes a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU and its operation method, which solves the problems of heavy weight of existing aircraft, height restrictions on APU operation, and high pollutant emissions, and provides the aircraft with the main power and auxiliary power required for flight. The system can start the engine on the ground, provide auxiliary power for the aircraft at any flight altitude on the ground and in the air, and complete the air auxiliary starting task when the main engine is turned off in the air. This makes it unnecessary to equip the aircraft with a RAT system, achieving the goals of low pollution, low fuel consumption, high efficiency and weight reduction for the aircraft.

[0008] The technical solution of the present invention is as follows:

[0009] A low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU comprises a main engine, an APU, a water evaporation system, a valve group, a liquid hydrogen vaporization system and a controller, wherein the APU comprises a hydrogen gas turbine and a hydrogen fuel cell; the liquid hydrogen vaporization system is connected to the main engine and the APU, the liquid hydrogen vaporization system supplies vaporized hydrogen to the main engine and the APU, and the APU supplies a heat source for vaporizing liquid hydrogen to the liquid hydrogen vaporization system; the water evaporation system is connected to the main engine and the APU, the water evaporation system receives water from the hydrogen fuel cell and pressurizes and evaporates the water, and then sprays the water vapor to the hydrogen gas turbine and the main engine, and the exhaust of the main engine and the hydrogen gas turbine provide a heat source for the evaporation of water vapor in the water evaporation system; the controller is connected to and controls the valve group, and the controller adjusts the operating state of the energy system by controlling the opening of the valve group; the valve group is all the valves arranged at each structural connection node of the energy system.

[0010] Furthermore, the liquid hydrogen vaporization system includes a hydraulic storage tank, a liquid hydrogen pump, a heat exchanger and a hydrogen storage tank. The liquid hydrogen enters the heat exchanger from the hydraulic storage tank through the liquid hydrogen pump, and enters the hydrogen storage tank after heat exchange with the high-temperature and high-pressure gas of the hydrogen gas turbine of the APU, or enters the hydrogen storage tank after heat exchange with the high-temperature and high-pressure gas from the main engine, and is then distributed to the main engine, hydrogen gas turbine and hydrogen fuel cell respectively by controlling three valves.

[0011] Furthermore, the water evaporation system includes a condenser, a water storage device, a water pump and an evaporator. The water from the hydrogen fuel cell of the APU enters the water storage device after heat exchange in the condenser, and enters the evaporator through the water pump. The water exchanges heat with the exhaust gas of the hydrogen gas turbine of the APU in the evaporator and is then sprayed into the hydrogen gas turbine of the APU. Alternatively, the water exchanges heat with the exhaust gas of the main engine in the evaporator and is then sprayed into the main engine.

[0012] Furthermore, the hydrogen gas turbine of the APU includes a compressor, a combustion chamber, and a turbine. The hydrogen gas turbine of the APU is connected to the hydrogen fuel cell, the water evaporation system, and the liquid hydrogen vaporization system of the APU; the hydrogen fuel cell of the APU includes a fuel cell, a battery, a PMAD, and a motor. The hydrogen fuel cell of the APU is connected to the main engine, the hydrogen gas turbine of the APU, the water evaporation system, and the liquid hydrogen vaporization system; in the ground auxiliary state and the ground starting state and the air auxiliary starting state below 12,000 meters, the high-temperature and high-pressure gas from the APU hydrogen gas turbine enters the APU hydrogen fuel cell and reacts chemically with the hydrogen from the liquid hydrogen vaporization system to provide electrical energy for the aircraft. The excess electrical energy is stored in the battery, and the electrical energy in the battery is distributed through the PMAD to the motor drive load; in the air working state, the high-temperature and high-pressure gas from the main engine enters the APU hydrogen fuel cell and reacts chemically with the hydrogen from the liquid hydrogen vaporization system to provide electrical energy for the aircraft. The excess electrical energy is stored in the battery, and the electrical energy in the battery is distributed through the PMAD to the motor drive load.

[0013] A method for operating a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU. When the aircraft is on the ground and the main engine is not working, the APU works to provide auxiliary electric power for the aircraft. At this time, ambient air passes through the hydrogen gas turbine to obtain high-temperature and high-pressure gas, which is divided into three paths. The first path of high-temperature and high-pressure gas enters a liquid hydrogen vaporization system to perform heat exchange in the liquid hydrogen vaporization system, and the second path of high-temperature and high-pressure gas enters the APU hydrogen fuel cell to chemically react with hydrogen from the liquid hydrogen vaporization system to provide electric energy for the aircraft. After being discharged from the liquid hydrogen vaporization system, the first path of high-temperature and high-pressure gas burns with the third path of high-temperature and high-pressure gas and hydrogen in the hydrogen gas turbine to perform work, providing shaft power for starting the main engine of the aircraft. Water generated by the hydrogen fuel cell exchanges heat with the high-temperature and high-pressure exhaust gas at the outlet of the hydrogen gas turbine in the water evaporation system to generate water vapor. The water vapor is sprayed into the hydrogen gas turbine.

[0014] A method for operating a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU. When the aircraft is on the ground and the main engine is working, the hydrogen fuel cell of the APU works to provide electrical power for the aircraft. At this time, ambient air enters the main engine to generate high-temperature and high-pressure gas. The high-temperature and high-pressure gas is divided into three paths. The first path of high-temperature and high-pressure gas of the main engine enters a liquid hydrogen vaporization system to perform heat exchange in the liquid hydrogen vaporization system. The second path of high-temperature and high-pressure gas enters the APU hydrogen fuel cell to perform a chemical reaction with hydrogen to provide electrical energy for the aircraft. After the first path of high-temperature and high-pressure gas is discharged from the liquid hydrogen vaporization system, it is burned with the third path of high-temperature and high-pressure gas and hydrogen from the liquid hydrogen vaporization system in a combustion chamber of the main engine to perform work to provide power for the aircraft. Ambient air enters the main engine to generate high-temperature and high-pressure exhaust gas. The exhaust gas and water generated by the APU hydrogen fuel cell perform heat exchange in a water evaporation system to generate water vapor. The water vapor is sprayed into the combustion chamber of the main engine.

[0015] A method for operating a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU. When the aircraft is at any flight altitude and the main engine is working normally, the hydrogen fuel cell of the APU is working, and at this time, ambient air enters the main engine to obtain high-temperature and high-pressure gas, which is divided into three paths. The first path of high-temperature and high-pressure gas of the main engine enters a liquid hydrogen vaporization system for heat exchange, and the second path of high-temperature and high-pressure gas enters the APU hydrogen fuel cell to chemically react with hydrogen from the liquid hydrogen vaporization system to provide electrical energy for the aircraft. After the first path of high-temperature and high-pressure gas is discharged from the liquid hydrogen vaporization system, it is burned and expanded in the main engine with the third path of high-temperature and high-pressure gas and the hydrogen from the liquid hydrogen vaporization system to provide power for the aircraft. The high-temperature and high-pressure exhaust gas discharged from the main engine and the water generated by the APU hydrogen fuel cell are heat exchanged in a water evaporation system to generate water vapor; the water vapor is sprayed into the combustion chamber of the main engine.

[0016] A method for operating a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU. When an aircraft flies at an altitude of 12,000 meters and the main engine is stopped, the hydrogen gas turbine and the hydrogen fuel cell of the APU work simultaneously to assist in starting the main engine. At this time, the ambient air passes through the hydrogen gas turbine to obtain high-temperature and high-pressure gas, which is divided into three paths. The first path of high-temperature and high-pressure gas enters a liquid hydrogen vaporization system to perform heat exchange in the liquid hydrogen vaporization system, and the second path of high-temperature and high-pressure gas enters the APU hydrogen fuel cell to chemically react with the hydrogen from the liquid hydrogen vaporization system to provide electrical energy for the aircraft. The first path of high-temperature and high-pressure gas enters the APU hydrogen fuel cell to chemically react with the hydrogen from the liquid hydrogen vaporization system to provide electrical energy for the aircraft. After being discharged from the liquid hydrogen vaporization system, the high-temperature and high-pressure gas is burned with the third high-temperature and high-pressure gas and hydrogen in the hydrogen gas turbine to produce work, providing the aircraft with shaft power for starting the main engine; the water produced by the hydrogen fuel cell exchanges heat with the high-temperature and high-pressure exhaust gas at the outlet of the hydrogen gas turbine in the water evaporation system to produce water vapor; the water vapor is sprayed into the hydrogen gas turbine; after the main engine is started successfully, the APU operates under the conditions of any flight altitude of the aircraft and when the main engine is working normally; if the main engine fails to start, the aircraft uses the APU's hydrogen gas turbine and hydrogen fuel cell to provide power to maintain operation at the same time, and the aircraft makes an emergency landing on the ground.

[0017] A method for operating a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU. When the aircraft is above an altitude of 12,000 meters and the main engine is stopped, the hydrogen fuel cell of the APU works to provide electrical energy for the aircraft; the ambient atmosphere and hydrogen stored in a liquid hydrogen vaporization system undergo a chemical reaction in the hydrogen fuel cell of the APU to generate electrical energy, and the electrical energy generated by the chemical reaction and the electrical energy stored in the battery together provide power for the aircraft until the aircraft descends below 12,000 meters; when the aircraft descends below 12,000 meters, it operates in the same manner as when the aircraft is flying at an altitude of 12,000 meters with the main engine stopped.

[0018] The beneficial effects of the present invention are as follows:

[0019] 1Any flight altitude available, minus aircraft RAT systems

[0020] When an engine failure occurs at an altitude of more than 12,000 meters, the traditional APU cannot restart the engine due to insufficient air intake. The aircraft needs to use RAT to provide emergency energy, and then restart the engine by APU when the aircraft descends below 12,000 meters. The hydrogen fuel cell in this hybrid APU can generate electricity at an altitude of more than 12,000 meters. When the aircraft has an engine failure, this electricity and the electricity stored in the battery can be used to maintain operation. When the aircraft descends below 12,000 meters, the hydrogen turbine in the APU starts working and the APU restarts the engine. This hybrid APU can provide power for engine restart at any altitude, and the aircraft can remove the RAT system.

[0021] 2. Improve the energy efficiency of the main engine

[0022] The APU's hydrogen fuel cell works throughout the flight to provide electricity for the aircraft. The main engine does not need to provide electricity for the aircraft, but only provides the thrust required by the aircraft. The fuel utilization efficiency of the main engine is improved, and the efficiency is improved.

[0023] 3. Low-pollution energy system

[0024] When hydrogen fuel is burned, the combustion temperature is high and it is easy to produce excessive nitrogen oxide pollutants. By injecting water vapor in the combustion chamber, the temperature of the main combustion zone of the combustion chamber is reduced, which greatly reduces nitrogen oxide emissions. This system not only achieves zero carbon emissions, but also greatly reduces nitrogen oxide emissions.

[0025] 4Energy system with low fuel consumption

[0026] Injecting water vapor into the hydrogen gas turbine combustion chamber of the main engine and APU makes combustion more complete, increases engine thrust, and reduces fuel consumption. (Water vapor comes from the reaction product of hydrogen fuel cells)

[0027] 5APU high reliability

[0028] In the event of a failure of either the hydrogen gas turbine or the hydrogen fuel cell, the APU can continue to operate and provide auxiliary power.

[0029] 6Simplify system cooling structure

[0030] The heat exchanger uses liquid hydrogen cooling energy as the cooling source, replacing the traditional lubricating oil cooling, greatly simplifying the system cooling structure. The evaporator uses turbine exhaust waste heat as the heat source, improving the system's thermal energy utilization efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the technical solution of the implementation method of the patent of the present invention, the following is a brief introduction to the drawings required for use in the implementation method. It should be understood that the following drawings only show certain embodiments of the patent of the present invention and should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying creative work.

[0032] Figure 1 It is a structural schematic diagram of a low-pollution aircraft hydrogen energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU of the present invention;

[0033] Among them, 1 to 12 are valves in different positions. DETAILED DESCRIPTION

[0034] This section is an embodiment of the present invention, which is used to explain and illustrate the technical solution of the present invention. In the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.

[0035] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate directions or positional relationships as given in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or case referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", etc. are used only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implying the number of technical features indicated. Thus, features defined as "first", "second", etc. may explicitly or implicitly include more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0036] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected" and "connected" should be interpreted in a broad sense, for example, it can be a fixed connection, a detachable connection or an integrated connection; it can be a mechanical connection or a point connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0037] Embodiment 1:

[0038] A low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU comprises a main engine, an APU, a water evaporation system, a valve group, a liquid hydrogen vaporization system and a controller, wherein the APU comprises a hydrogen gas turbine and a hydrogen fuel cell; the liquid hydrogen vaporization system is connected to the main engine and the APU, the liquid hydrogen vaporization system supplies vaporized hydrogen to the main engine and the APU, and the APU supplies a heat source for vaporizing liquid hydrogen to the liquid hydrogen vaporization system; the water evaporation system is connected to the main engine and the APU, the water evaporation system receives water from the hydrogen fuel cell and pressurizes and evaporates the water, and then sprays the water vapor to the hydrogen gas turbine and the main engine, and the exhaust of the main engine and the hydrogen gas turbine provide a heat source for the evaporation of water vapor in the water evaporation system; the controller is connected to and controls the valve group, and the controller adjusts the operating state of the energy system by controlling the opening of the valve group; the valve group is all the valves arranged at each structural connection node of the energy system.

[0039] The liquid hydrogen vaporization system includes a hydraulic storage tank, a liquid hydrogen pump, a heat exchanger and a hydrogen storage tank. The liquid hydrogen enters the heat exchanger from the hydraulic storage tank through the liquid hydrogen pump, and enters the hydrogen storage tank after heat exchange with the high-temperature and high-pressure gas of the APU's hydrogen gas turbine, or enters the hydrogen storage tank after heat exchange with the high-temperature and high-pressure gas from the main engine, and is then distributed to the main engine, hydrogen gas turbine and hydrogen fuel cell respectively by controlling three valves.

[0040] It is characterized in that the water evaporation system includes a condenser, a water storage device, a water pump and an evaporator. The water from the hydrogen fuel cell of the APU enters the water storage device after heat exchange in the condenser, and enters the evaporator through the water pump. The water exchanges heat with the exhaust gas of the hydrogen gas turbine of the APU in the evaporator and then is sprayed into the hydrogen gas turbine of the APU, or the water exchanges heat with the exhaust gas of the main engine in the evaporator and then is sprayed into the main engine.

[0041] The hydrogen gas turbine of the APU includes a compressor, a combustion chamber, and a turbine. The hydrogen gas turbine of the APU is connected to the hydrogen fuel cell, the water evaporation system, and the liquid hydrogen vaporization system of the APU; the hydrogen fuel cell of the APU includes a fuel cell, a battery, a PMAD, and a motor. The hydrogen fuel cell of the APU is connected to the main engine, the hydrogen gas turbine of the APU, the water evaporation system, and the liquid hydrogen vaporization system; in the ground auxiliary state, the ground starting state, and the air auxiliary starting state below 12,000 meters, the high-temperature and high-pressure gas from the APU hydrogen gas turbine enters the APU hydrogen fuel cell and reacts chemically with the hydrogen from the liquid hydrogen vaporization system to provide electrical energy for the aircraft. The excess electrical energy is stored in the battery, and the electrical energy in the battery is distributed through the PMAD to the motor drive load; in the air working state, the high-temperature and high-pressure gas from the main engine enters the APU hydrogen fuel cell and reacts chemically with the hydrogen from the liquid hydrogen vaporization system to provide electrical energy for the aircraft. The excess electrical energy is stored in the battery, and the electrical energy in the battery is distributed through the PMAD to the motor drive load.

[0042] Description: PMAD is a power management and distribution device.

[0043] A method for operating a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU. When the aircraft is on the ground and the main engine is not working, the APU works to provide auxiliary electric power for the aircraft. At this time, ambient air passes through the hydrogen gas turbine to obtain high-temperature and high-pressure gas, which is divided into three paths. The first path of high-temperature and high-pressure gas enters a liquid hydrogen vaporization system to perform heat exchange in the liquid hydrogen vaporization system, and the second path of high-temperature and high-pressure gas enters the APU hydrogen fuel cell to chemically react with hydrogen from the liquid hydrogen vaporization system to provide electric energy for the aircraft. After being discharged from the liquid hydrogen vaporization system, the first path of high-temperature and high-pressure gas burns with the third path of high-temperature and high-pressure gas and hydrogen in the hydrogen gas turbine to perform work, providing shaft power for starting the main engine of the aircraft. Water generated by the hydrogen fuel cell exchanges heat with the high-temperature and high-pressure exhaust gas at the outlet of the hydrogen gas turbine in the water evaporation system to generate water vapor. The water vapor is sprayed into the hydrogen gas turbine.

[0044] When the aircraft is on the ground and the main engine is working, the APU's hydrogen fuel cell works to provide electrical power for the aircraft. At this time, ambient air enters the main engine to generate high-temperature and high-pressure gas, which is divided into three paths. The first path of high-temperature and high-pressure gas from the main engine enters the liquid hydrogen vaporization system and exchanges heat in the liquid hydrogen vaporization system. The second path of high-temperature and high-pressure gas enters the APU hydrogen fuel cell to react chemically with hydrogen to provide electrical energy for the aircraft. After the first path of high-temperature and high-pressure gas is discharged from the liquid hydrogen vaporization system, it is burned with the third path of high-temperature and high-pressure gas and hydrogen from the liquid hydrogen vaporization system in the combustion chamber of the main engine to provide power for the aircraft. Ambient air enters the main engine to generate high-temperature and high-pressure exhaust gas, which exchanges heat with the water generated by the APU hydrogen fuel cell in the water evaporation system to generate water vapor; the water vapor is sprayed into the combustion chamber of the main engine.

[0045] When the aircraft is at any flight altitude and the main engine is working normally, the hydrogen fuel cell of the APU is working. At this time, ambient air enters the main engine to obtain high-temperature and high-pressure gas. The high-temperature and high-pressure gas is divided into three paths. The first high-temperature and high-pressure gas of the main engine enters the liquid hydrogen vaporization system for heat exchange, and the second high-temperature and high-pressure gas enters the APU hydrogen fuel cell to react chemically with the hydrogen from the liquid hydrogen vaporization system to provide electrical energy for the aircraft. After the first high-temperature and high-pressure gas is discharged from the liquid hydrogen vaporization system, it burns and expands with the third high-temperature and high-pressure gas and the hydrogen from the liquid hydrogen vaporization system in the main engine to provide power for the aircraft; the high-temperature and high-pressure exhaust gas discharged from the main engine and the water generated by the APU hydrogen fuel cell exchange heat in the water evaporation system to generate water vapor; the water vapor is sprayed into the combustion chamber of the main engine.

[0046] When the aircraft is flying at an altitude of 12,000 meters and the main engine is stopped, the hydrogen gas turbine and hydrogen fuel cell of the APU work simultaneously to assist in starting the main engine; at this time, the ambient air passes through the hydrogen gas turbine to obtain high-temperature and high-pressure gas, which is divided into three paths. The first path of high-temperature and high-pressure gas enters the liquid hydrogen vaporization system and performs heat exchange in the liquid hydrogen vaporization system. The second path of high-temperature and high-pressure gas enters the APU hydrogen fuel cell to react chemically with the hydrogen from the liquid hydrogen vaporization system to provide electrical energy for the aircraft; the first path of high-temperature and high-pressure gas is discharged from the liquid hydrogen vaporization system and burns with the third path of high-temperature and high-pressure gas and hydrogen in the hydrogen gas turbine to provide shaft power for starting the main engine of the aircraft; the water generated by the hydrogen fuel cell exchanges heat with the high-temperature and high-pressure exhaust gas at the outlet of the hydrogen gas turbine in the water evaporation system to generate water vapor; the water vapor is sprayed into the hydrogen gas turbine; after the main engine is successfully started, the APU operates in the state of any flight altitude of the aircraft and when the main engine is working normally; if the main engine fails to start, the aircraft uses the hydrogen gas turbine and hydrogen fuel cell of the APU to provide power to maintain operation at the same time, and the aircraft makes an emergency landing on the ground.

[0047] When the aircraft is above 12,000 meters and the main engine is shut down, the APU's hydrogen fuel cell works to provide electrical energy for the aircraft; the ambient atmosphere and the hydrogen stored in the liquid hydrogen vaporization system react chemically in the APU's hydrogen fuel cell to generate electrical energy, and the electrical energy generated by the chemical reaction and the electrical energy stored in the battery together provide power for the aircraft until the aircraft descends below 12,000 meters; when the aircraft descends below 12,000 meters, it operates in the same manner as when the aircraft is flying at an altitude of 12,000 meters with the main engine shut down.

[0048] Embodiment 2:

[0049] Combination Figure 1 :

[0050] (1) Ground assistance status

[0051] In the ground state, when the main engine is not working, the APU works to provide auxiliary electric power for the aircraft, valves 1, 2, 6, 7, 8, 11 are opened, and valves 3, 4, 5, 9, 10 are closed. After the ambient air passes through the APU hydrogen gas turbine, high-temperature and high-pressure gas is obtained, and the high-temperature and high-pressure gas is divided into three paths. The first high-temperature and high-pressure gas enters the liquid hydrogen vaporization system, where heat is exchanged. The liquid hydrogen is vaporized into hydrogen and stored in the hydrogen storage tank of the liquid hydrogen vaporization system. The second high-temperature and high-pressure gas enters the APU hydrogen fuel cell and reacts chemically with hydrogen to provide electrical energy for the aircraft, and the reaction produces water. After the first high-temperature and high-pressure gas comes out of the liquid hydrogen vaporization system, it is burned with the third high-temperature and high-pressure gas and hydrogen in the APU hydrogen gas turbine to provide shaft power for the aircraft. The APU hydrogen gas turbine produces high-temperature and high-pressure exhaust gas. The water produced by the APU hydrogen fuel cell exchanges heat with the high-temperature and high-pressure exhaust gas produced by the APU hydrogen gas turbine in the water evaporation system to produce water vapor. The water vapor is sprayed into the APU hydrogen gas turbine.

[0052] (2) Ground start status

[0053] In the ground start state, when the main engine is working, the APU works to provide auxiliary electric power for the aircraft, valves 1, 2, 3, 4, 8, 9, 11 are opened, and valves 5, 6, 7, 10 are closed. Ambient air enters the main engine, passes through the low-pressure compressor and the high-pressure compressor to obtain high-temperature and high-pressure gas, which is divided into three paths. The first path of high-temperature and high-pressure gas from the main engine enters the liquid hydrogen vaporization system, where heat is exchanged. Liquid hydrogen is vaporized into hydrogen and stored in the hydrogen storage tank of the liquid hydrogen vaporization system. The second path of high-temperature and high-pressure gas enters the APU hydrogen fuel cell to react chemically with hydrogen to provide electrical energy for the aircraft, and the reaction produces water. After the first path of high-temperature and high-pressure gas comes out of the liquid hydrogen vaporization system, it is burned with the third path of high-temperature and high-pressure gas and hydrogen in the APU hydrogen gas turbine to provide shaft power for the aircraft. The main engine and the APU hydrogen gas turbine produce high-temperature and high-pressure exhaust gas, which is heat-exchanged with the water produced by the APU hydrogen fuel cell in the water evaporation system to produce water vapor. Water vapor is injected into the combustion chambers of the APU hydrogen gas turbine and the main engine respectively.

[0054] (3) Air working status

[0055] At any flight altitude, when the main engine is working normally, the hydrogen fuel cell of the APU is working, and the hydrogen-fueled hydrogen turbine is not working. Valves 1, 2, 3, 4, 5, 8, and 9 are open, and valves 6, 7, 10, and 11 are closed. Ambient air enters the main engine, and after passing through the low-pressure compressor and the high-pressure compressor, high-temperature and high-pressure gas is obtained. The high-temperature and high-pressure gas is divided into three paths. The first high-temperature and high-pressure gas of the main engine enters the liquid hydrogen vaporization system, where heat is exchanged. The liquid hydrogen is vaporized into hydrogen and stored in the hydrogen storage tank of the liquid hydrogen vaporization system. The second high-temperature and high-pressure gas enters the APU hydrogen fuel cell and reacts chemically with hydrogen to provide electrical energy for the aircraft, and the reaction produces water. After the first high-temperature and high-pressure gas comes out of the liquid hydrogen vaporization system, it works with the third high-temperature and high-pressure gas and hydrogen in the main engine to provide shaft power for the aircraft. The high-temperature and high-pressure exhaust gas discharged by the main engine and the water produced by the APU hydrogen fuel cell are heat-exchanged in the water evaporation system to produce water vapor. The water vapor is sprayed into the combustion chamber of the main engine.

[0056] (4) At altitudes below 12,000 meters, main generator failure

[0057] At an altitude of 12,000 meters, when the main engine stops, the APU works to assist in starting the main engine. Valves 1, 2, 6, 7, 8, and 11 are opened, and valves 3, 4, 5, 9, and 10 are closed. After the ambient air passes through the APU hydrogen gas turbine, high-temperature and high-pressure gas is obtained, and the high-temperature and high-pressure gas is divided into three paths. The first high-temperature and high-pressure gas enters the liquid hydrogen vaporization system, where heat is exchanged. The liquid hydrogen is vaporized into hydrogen and stored in the hydrogen storage tank of the liquid hydrogen vaporization system. The second high-temperature and high-pressure gas enters the APU hydrogen fuel cell and reacts chemically with hydrogen to provide electrical energy for the aircraft, and the reaction produces water. After the first high-temperature and high-pressure gas comes out of the liquid hydrogen vaporization system, it burns with the third high-temperature and high-pressure gas and hydrogen in the APU hydrogen gas turbine to provide shaft power for the aircraft. The APU hydrogen gas turbine produces high-temperature and high-pressure exhaust gas. The water produced by the APU hydrogen fuel cell exchanges heat with the high-temperature and high-pressure exhaust gas produced by the APU hydrogen gas turbine in the water evaporation system to produce water vapor. The water vapor is sprayed into the APU hydrogen gas turbine. The APU starts the main engine and continues to operate according to (3) if the start is successful. If the main engine fails to start, the aircraft uses the power provided by the APU to maintain operation and the aircraft makes an emergency landing.

[0058] (5) At an altitude of 12,000 meters or above, the main generator fails

[0059] When the main engine stops at an altitude of more than 12,000 meters, the APU's hydrogen fuel cell works to provide electrical energy for the aircraft. The ambient atmosphere and the hydrogen stored in the liquid hydrogen vaporization system react chemically in the APU's fuel cell to provide electrical energy for the aircraft. This part of the electrical energy, together with the electrical energy stored in the battery, powers the aircraft until the aircraft descends below 12,000 meters. When the aircraft descends to an altitude of 12,000 meters, the APU works to assist in starting the main engine. After the start is successful, it continues to work according to (3). If the main engine fails to start, the aircraft uses the power provided by the APU to maintain operation and the aircraft makes an emergency landing on the ground.

[0060] The above is only a specific embodiment of the present invention, and the present invention is described in detail. The unexplained part is a conventional technology. However, the protection scope of the present invention is not limited to this. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention should be included in the protection scope of the present invention. The protection scope of the present invention shall be based on the protection scope of the claims.

Claims

1. A low-pollution aircraft energy system with a hydrogen gas turbine and hydrogen fuel cell hybrid APU, It is characterized in that It includes a main engine, an APU, a water evaporation system, a valve group, a liquid hydrogen vaporization system and a controller, wherein the APU includes a hydrogen gas turbine and a hydrogen fuel cell; the liquid hydrogen vaporization system is connected to the main engine and the APU, the liquid hydrogen vaporization system supplies vaporized hydrogen to the main engine and the APU, and the APU provides a heat source for liquid hydrogen vaporization to the liquid hydrogen vaporization system; the water evaporation system is connected to the main engine and the APU, the water evaporation system receives water from the hydrogen fuel cell and pressurizes and evaporates the water, and then sprays the water vapor to the hydrogen gas turbine and the main engine, and the exhaust of the main engine and the hydrogen gas turbine provide a heat source for the evaporation of water vapor in the water evaporation system; the controller is connected to and controls the valve group, and the controller adjusts the operating state of the energy system by controlling the opening of the valve group; the valve group is all the valves arranged at each structural connection node of the energy system.

2. A low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU according to claim 1, It is characterized in that The liquid hydrogen vaporization system includes a hydraulic storage tank, a liquid hydrogen pump, a heat exchanger and a hydrogen storage tank. The liquid hydrogen enters the heat exchanger from the hydraulic storage tank through the liquid hydrogen pump, and enters the hydrogen storage tank after heat exchange with the high-temperature and high-pressure gas of the APU's hydrogen gas turbine, or enters the hydrogen storage tank after heat exchange with the high-temperature and high-pressure gas from the main engine, and is then distributed to the main engine, hydrogen gas turbine and hydrogen fuel cell respectively by controlling three valves.

3. A low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU according to claim 1, It is characterized in that The water evaporation system includes a condenser, a water storage device, a water pump and an evaporator. The water from the hydrogen fuel cell of the APU enters the water storage device after heat exchange in the condenser, and enters the evaporator through the water pump. The water exchanges heat with the exhaust gas of the hydrogen gas turbine of the APU in the evaporator and is then sprayed into the hydrogen gas turbine of the APU. Alternatively, the water exchanges heat with the exhaust gas of the main engine in the evaporator and is then sprayed into the main engine.

4. A low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU according to claim 1, It is characterized in that The hydrogen gas turbine of the APU includes a compressor, a combustion chamber, and a turbine. The hydrogen gas turbine of the APU is connected to the hydrogen fuel cell, the water evaporation system, and the liquid hydrogen vaporization system of the APU; the hydrogen fuel cell of the APU includes a fuel cell, a battery, a PMAD, and a motor. The hydrogen fuel cell of the APU is connected to the main engine, the hydrogen gas turbine of the APU, the water evaporation system, and the liquid hydrogen vaporization system; in the ground auxiliary state, the ground starting state, and the air auxiliary starting state below 12,000 meters, the high-temperature and high-pressure gas from the APU hydrogen gas turbine enters the APU hydrogen fuel cell and reacts chemically with the hydrogen from the liquid hydrogen vaporization system to provide electrical energy for the aircraft. The excess electrical energy is stored in the battery, and the electrical energy in the battery is distributed through the PMAD to the motor drive load; in the air working state, the high-temperature and high-pressure gas from the main engine enters the APU hydrogen fuel cell and reacts chemically with the hydrogen from the liquid hydrogen vaporization system to provide electrical energy for the aircraft. The excess electrical energy is stored in the battery, and the electrical energy in the battery is distributed through the PMAD to the motor drive load.

5. A method for operating a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU, using a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU as claimed in any one of claims 1 to 4, It is characterized in that When the aircraft is on the ground and the main engine is not working, the APU works to provide auxiliary electric power for the aircraft. At this time, the ambient air passes through the hydrogen gas turbine to obtain high-temperature and high-pressure gas, which is divided into three paths. The first path of high-temperature and high-pressure gas enters the liquid hydrogen vaporization system and exchanges heat in the liquid hydrogen vaporization system. The second path of high-temperature and high-pressure gas enters the APU hydrogen fuel cell to react chemically with the hydrogen from the liquid hydrogen vaporization system to provide electric energy for the aircraft. After the first path of high-temperature and high-pressure gas is discharged from the liquid hydrogen vaporization system, it burns with the third path of high-temperature and high-pressure gas and hydrogen in the hydrogen gas turbine to provide shaft power for starting the main engine of the aircraft. The water generated by the hydrogen fuel cell exchanges heat with the high-temperature and high-pressure exhaust gas at the outlet of the hydrogen gas turbine in the water evaporation system to generate water vapor. The water vapor is sprayed into the hydrogen gas turbine.

6. A method for operating a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU, using a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU as claimed in any one of claims 1 to 4, It is characterized in that When the aircraft is on the ground and the main engine is working, the APU's hydrogen fuel cell works to provide electrical power for the aircraft. At this time, ambient air enters the main engine to generate high-temperature and high-pressure gas, which is divided into three paths. The first path of high-temperature and high-pressure gas from the main engine enters the liquid hydrogen vaporization system and exchanges heat in the liquid hydrogen vaporization system. The second path of high-temperature and high-pressure gas enters the APU hydrogen fuel cell to react chemically with hydrogen to provide electrical energy for the aircraft. After the first path of high-temperature and high-pressure gas is discharged from the liquid hydrogen vaporization system, it is burned with the third path of high-temperature and high-pressure gas and hydrogen from the liquid hydrogen vaporization system in the combustion chamber of the main engine to provide power for the aircraft. Ambient air enters the main engine to generate high-temperature and high-pressure exhaust gas, which exchanges heat with the water generated by the APU hydrogen fuel cell in the water evaporation system to generate water vapor; the water vapor is sprayed into the combustion chamber of the main engine.

7. A method for operating a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU, using a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU as claimed in any one of claims 1 to 4, It is characterized in that When the aircraft is at any flight altitude and the main engine is working normally, the hydrogen fuel cell of the APU is working. At this time, ambient air enters the main engine to obtain high-temperature and high-pressure gas. The high-temperature and high-pressure gas is divided into three paths. The first high-temperature and high-pressure gas of the main engine enters the liquid hydrogen vaporization system for heat exchange, and the second high-temperature and high-pressure gas enters the APU hydrogen fuel cell to react chemically with the hydrogen from the liquid hydrogen vaporization system to provide electrical energy for the aircraft. After the first high-temperature and high-pressure gas is discharged from the liquid hydrogen vaporization system, it burns and expands with the third high-temperature and high-pressure gas and the hydrogen from the liquid hydrogen vaporization system in the main engine to provide power for the aircraft; the high-temperature and high-pressure exhaust gas discharged from the main engine and the water generated by the APU hydrogen fuel cell exchange heat in the water evaporation system to generate water vapor; the water vapor is sprayed into the combustion chamber of the main engine.

8. A method for operating a low-pollution aircraft energy system of a hydrogen gas turbine and a hydrogen fuel cell hybrid APU according to claim 7, It is characterized in that When the aircraft is flying at an altitude of 12,000 meters and the main engine is stopped, the hydrogen gas turbine and hydrogen fuel cell of the APU work simultaneously to assist in starting the main engine; at this time, the ambient air passes through the hydrogen gas turbine to obtain high-temperature and high-pressure gas, which is divided into three paths. The first path of high-temperature and high-pressure gas enters the liquid hydrogen vaporization system and performs heat exchange in the liquid hydrogen vaporization system. The second path of high-temperature and high-pressure gas enters the APU hydrogen fuel cell to react chemically with the hydrogen from the liquid hydrogen vaporization system to provide electrical energy for the aircraft; the first path of high-temperature and high-pressure gas is discharged from the liquid hydrogen vaporization system and burns with the third path of high-temperature and high-pressure gas and hydrogen in the hydrogen gas turbine to provide shaft power for starting the main engine of the aircraft; the water generated by the hydrogen fuel cell exchanges heat with the high-temperature and high-pressure exhaust gas at the outlet of the hydrogen gas turbine in the water evaporation system to generate water vapor; the water vapor is sprayed into the hydrogen gas turbine; after the main engine is successfully started, the APU operates in the state of any flight altitude of the aircraft and when the main engine is working normally; if the main engine fails to start, the aircraft uses the hydrogen gas turbine and hydrogen fuel cell of the APU to provide power to maintain operation at the same time, and the aircraft makes an emergency landing on the ground.

9. A low-pollution aircraft with a hydrogen gas turbine and hydrogen fuel cell hybrid APU according to claim 8 Energy system operation methods, It is characterized in that When the aircraft is above 12,000 meters and the main engine is shut down, the APU's hydrogen fuel cell works to provide electrical energy for the aircraft; the ambient atmosphere and the hydrogen stored in the liquid hydrogen vaporization system react chemically in the APU's hydrogen fuel cell to generate electrical energy, and the electrical energy generated by the chemical reaction and the electrical energy stored in the battery together provide power for the aircraft until the aircraft descends below 12,000 meters; when the aircraft descends below 12,000 meters, it operates in the same manner as when the aircraft is flying at an altitude of 12,000 meters with the main engine shut down.

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