A high-temperature proton exchange membrane fuel cell system

Abstract

The present invention discloses a high-temperature proton exchange membrane fuel cell system, which includes a centrifugal compressor, a high-speed motor, and a plurality of stack units. The centrifugal compressor is coaxially arranged with the high-speed motor; the centrifugal compressor is respectively communicated with each of the stack units through a plurality of tubular diffusers; wherein, the stack units are distributed in a circumferential array around the center line of the high-speed motor; and a first heat dissipation cavity through which cooling air for the stack passes is provided between two adjacent stack units and between the stack unit and the high-speed motor. The present invention can effectively improve the specific power of the fuel cell system and can be applied to aviation fields such as light aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of hydrogen fuel cells, and in particular to a high-temperature proton exchange membrane fuel cell system. Background Art

[0002] Proton exchange membrane fuel cells are power generation devices that convert the chemical energy of fuel directly into electrical energy through electrochemical reactions and generate a certain amount of waste heat. As a new generation of power generation technology, proton exchange membrane fuel cells have the characteristics of high energy conversion efficiency, no mechanical moving parts and environmental friendliness.

[0003] Proton exchange membrane fuel cells can be divided into low-temperature proton exchange membrane fuel cells (normal operating temperature is 60-90°C) and high-temperature proton exchange membrane fuel cells (normal operating temperature is 120-200°C) according to the operating temperature. The thermal power generated during the operation of proton exchange membrane fuel cells is equivalent to the electrical power, which leads to the former usually relying on a liquid-cooled thermal management system to take away a large amount of waste heat in the design of high-power stacks. Although the specific power of the stack itself is relatively high, if auxiliary equipment such as liquid cooling and heat dissipation systems are taken into account, the overall specific power of the system will be greatly reduced. This is also one of the reasons why low-temperature proton exchange membrane fuel cells are difficult to be widely used in the aviation field. If proton exchange membrane fuel cell technology is to be used in aviation fields such as light aircraft, the specific power of the system needs to be further improved.

[0004] In summary, how to further improve the specific power of fuel cell systems so that they can be used in aviation fields such as light aircraft is one of the important issues that need to be urgently addressed in this field. Summary of the invention

[0005] The purpose of the present invention is to provide a high-temperature proton exchange membrane fuel cell system to solve the deficiencies in the prior art. The system can have a higher specific power of the fuel cell system and can be applied to aviation fields such as light aircraft.

[0006] The present invention provides a high-temperature proton exchange membrane fuel cell system, comprising a centrifugal compressor, a high-speed motor and a plurality of fuel cell stack units, wherein the centrifugal compressor is coaxially arranged with the high-speed motor; the centrifugal compressor is connected to each fuel cell stack unit through a plurality of tubular diffusers; wherein:

[0007] The battery stack units are distributed in a circular array around the center line of the high-speed motor; and a first heat dissipation cavity for allowing battery stack cooling air to pass through is provided between two adjacent battery stack units and between the battery stack unit and the high-speed motor.

[0008] The high-temperature proton exchange membrane fuel cell system as described above, optionally, further includes a first heat sink, wherein the first heat sink is formed by extending a plurality of the stack units toward the first heat dissipation cavity.

[0009] The high-temperature proton exchange membrane fuel cell system as described above, wherein, optionally, it further includes a heat insulation screen, and the heat insulation screen is cylindrical; the heat insulation screen is sleeved on the outer periphery of the high-speed motor; the first heat dissipation cavity is an annular grid and is located on the outer periphery of the heat insulation screen.

[0010] The high-temperature proton exchange membrane fuel cell system as described above, wherein, optionally, there is a second heat dissipation cavity between the heat insulation screen and the high-speed motor, and the second heat dissipation cavity is used for the motor cooling air to pass through;

[0011] The second heat dissipation cavity is provided with second heat dissipation fins, and the second heat dissipation fins are used for dissipating heat from the high-speed motor.

[0012] The high-temperature proton exchange membrane fuel cell system as described above, wherein, optionally, it further includes a radial turbine, and the radial turbine is coaxially arranged with the high-speed motor;

[0013] The air inlet of the radial turbine is communicated with the cathode outlet of the stack unit, so that the cathode exhaust gas discharged from the stack unit drives the radial turbine to rotate.

[0014] The high-temperature proton exchange membrane fuel cell system as described above, wherein, optionally, it further includes a plurality of bypass pipes, and the plurality of bypass pipes correspond to the stack units one by one. Both ends of the bypass pipe are respectively communicated with the cathode inlet and the cathode outlet of the corresponding stack unit;

[0015] The bypass pipe is used for conducting when the corresponding stack unit fails.

[0016] The high-temperature proton exchange membrane fuel cell system as described above, wherein, optionally, it further includes a hydrogen circulation pump, and the hydrogen circulation pump is coaxially arranged with the high-speed motor;

[0017] The air inlet of the hydrogen circulation pump is communicated with the anode outlet of each stack unit, and the air outlet of the hydrogen circulation pump is communicated with the anode inlet of each stack unit.

[0018] The high-temperature proton exchange membrane fuel cell system as described above, wherein, optionally, it further includes a combustion chamber. The first air inlet of the combustion chamber is communicated with the centrifugal compressor, the second air inlet of the combustion chamber is communicated with the anode outlet of the stack unit, and the exhaust outlet of the combustion chamber is communicated with the air inlet of the radial turbine.

[0019] The high-temperature proton exchange membrane fuel cell system as described above, wherein, optionally, there are a plurality of combustion chambers, and they correspond to the stack units one by one.

[0020] The high-temperature proton exchange membrane fuel cell system as described above, wherein, optionally, the combustion chamber is an annular tube combustion chamber.

[0021] Compared with the prior art, the present invention has at least the following beneficial effects:

[0022] In the present invention, a plurality of stack units are provided. The stack unit is a high-temperature proton exchange membrane fuel cell stack, and its normal operating temperature is 120 to 200 °C. By arranging the stack units in a circumferential array, the surface area of the stack is effectively increased, and air-cooling heat dissipation can be achieved. It can greatly simplify the thermal management system and reduce the system weight.

[0023] The stack units are arranged in a ring shape, and a first heat dissipation cavity through which the stack cooling air passes is provided therein. When it is applied to the aviation field such as light aircraft, the stack cooling air can pass through the first heat dissipation cavity, and the airflow generated during the flight of the aircraft is used to dissipate heat from the stack units.

[0024] The multiple stack units are arranged in parallel, forming a redundant design in which the multiple stack units are backup to each other, which is beneficial to improving airworthiness safety.

[0025] The high operating temperature of the high-temperature proton exchange membrane fuel cell improves the thermal efficiency of the Brayton cycle composed of the centrifugal compressor and the radial turbine, greatly reduces the system power consumption, and also reduces the size and weight of the high-speed motor, which is beneficial to improving the specific power of the fuel cell system.

[0026] During the startup process of the high-temperature proton exchange membrane fuel cell, the centrifugal compressor can be used to heat the air to rapidly and uniformly increase the temperature of the proton exchange membrane, which is beneficial to shortening the startup time. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 is a schematic structural diagram of Embodiment 1 of the present invention;

[0028] Figure 2 is a schematic structural diagram of Embodiment 2 of the present invention.

[0029] DESCRIPTION OF THE REFERENCE NUMERALS:

[0030] 1 - centrifugal compressor, 2 - high-speed motor, 3 - stack unit, 4 - first heat dissipation cavity, 5 - first heat sink, 6 - heat insulation screen, 7 - second heat dissipation cavity, 8 - second heat sink, 9 - radial turbine, 10 - bypass pipe, 11 - hydrogen circulation pump, 12 - combustion chamber, 13 - magnetic levitation bearing. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0031] The embodiments described below with reference to the drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0032] The present invention aims to solve the problem of how to further improve the specific power of a fuel cell system so that the fuel cell system can be applied to aviation fields such as light aircraft. To this end, the present invention proposes the following embodiments to solve this problem.

[0033] Embodiment 1

[0034] Please refer to Figure 1 and Figure 2 , this embodiment discloses a high-temperature proton exchange membrane fuel cell system, including a centrifugal compressor 1, a high-speed motor 2 and a plurality of stack units 3. The centrifugal compressor 1 and the high-speed motor 2 are coaxially arranged; the centrifugal compressor 1 is communicated with each of the stack units 3 through a plurality of tubular diffusers. The centrifugal compressor 1 is used to compress air and supply it to the stack unit 3, and the high-speed motor 2 is used to drive the centrifugal compressor 1 to rotate. In actual application, the normal operation of the stack unit 3 also requires components such as a hydrogen tank for supplying hydrogen to the stack unit 3. Since the hydrogen supply system of the fuel cell is a prior art and can be realized by those skilled in the art, and it is not the key point of improvement of this solution, it will not be elaborated here. Specifically, during implementation, the number of the tubular diffusers is equal to the number of the stack units 3 and they are in one-to-one correspondence. The centrifugal compressor 1 branches out multiple branches, and each branch is connected to a stack unit 3 through a tubular diffuser.

[0035] During specific implementation, the stack unit 3 is a high-temperature proton exchange membrane fuel cell stack. In this application, the high-temperature proton exchange membrane fuel cell stack refers to a fuel cell stack with an operating temperature of 120°C to 200°C. Compared with a low-temperature proton exchange membrane fuel cell with an operating temperature of 60 to 90°C, the high-temperature proton exchange membrane has a smaller demand for the intensity of heat dissipation, making it possible to dissipate heat by air cooling. Therefore, using a high-temperature proton exchange membrane fuel cell stack is one of the important conditions for the fuel cell system proposed in this embodiment to have a high specific power.

[0036] Specifically, a plurality of the stack units 3 are distributed in a circumferential array around the center line of the high-speed motor 2; and a first heat dissipation cavity 4 for the stack cooling air to pass through is provided between adjacent stack units 3 and between the stack unit 3 and the high-speed motor 2. During specific implementation, a gap is provided between two adjacent stack units 3. By arranging the stack units 3 in a circumferential array, the surface area of the stack unit 3 in contact with the stack cooling air increases, resulting in a larger heat dissipation surface. Since the outer peripheral surface of the first heat dissipation cavity 4 is surrounded by the stack units 3, when the stack cooling air passes through the first heat dissipation cavity 4, the heat on the surface of the stack unit 3 can be taken away, thus achieving the purpose of air cooling.

[0037] In specific use, the first heat dissipation cavity 4 is an annular grille, and its center line should be consistent with the forward direction of the light aircraft to which it is applied. In this way, during operation, the stack cooling air can pass through the first heat dissipation cavity 4 to achieve the purpose of air cooling.

[0038] The high-temperature proton exchange membrane fuel cell system proposed in this embodiment uses air cooling to dissipate heat from the fuel cell system so that it can operate within a more suitable temperature range. Therefore, it is possible to avoid using liquid cooling to dissipate heat from the stack unit. Through air cooling, the thermal management system can be greatly simplified and the weight of auxiliary equipment can be reduced.

[0039] In specific implementation, to further improve the heat dissipation effect, a first heat sink 5 is further included in this embodiment. The first heat sink 5 extends from multiple stack units 3 to the first heat dissipation cavity 4. That is, the first heat sink 5 is used to dissipate heat from the stack unit 3. During use, after adding the first heat sink 5, the contact area with the stack cooling air is increased, which is beneficial to improving the heat dissipation efficiency.

[0040] In specific implementation, the high-speed motor 2 and the centrifugal compressor 1 also generate a lot of heat during operation. Since multiple stack units 3 are evenly distributed around the center line of the high-speed motor 2, during operation, the temperature of the stack unit 3 is higher than the operating temperature of the motor. To prevent the heat of the stack unit 3 from radiating to the high-speed motor 2 and at the same time isolate the two cooling airflows to form inner and outer bypass ducts and reduce the temperature of the cooling air for the motor to ensure a lower temperature of the motor. The following improvements are also made in this embodiment:

[0041] In this embodiment, a heat insulation screen 6 is further included. The heat insulation screen 6 is cylindrical; the heat insulation screen 6 is sleeved on the outer periphery of the high-speed motor 2; the first heat dissipation cavity 4 is an annular grille and is located on the outer periphery of the heat insulation screen 6. After setting the heat insulation screen 6, it can prevent the centrifugal compressor 1 and the high-speed motor 2 from affecting the air cooling of the stack unit 3.

[0042] In specific implementation, the heat insulation screen 6 is a cylindrical structure with openings at both ends. A second heat dissipation cavity 7 is provided between the heat insulation screen 6 and the high-speed motor 2. The second heat dissipation cavity 7 is used for the motor cooling air to pass through. Second heat sinks 8 are provided in the second heat dissipation cavity 7, and the second heat sinks 8 are used to dissipate heat from the high-speed motor 2. Since the centrifugal compressor 1 and the high-speed motor 2 are compact in structure and have a small surface area, direct air cooling will cause uneven internal heat dissipation. In practical applications, an independent liquid cooling system can be designed for cooling. Specifically, the liquid cooling liquid of the centrifugal compressor 1 and the high-speed motor 2 is cooled. The centrifugal compressor 1 and the high-speed motor 2 are compactly arranged within a cylindrical envelope surface, and the waste heat generated during operation is transferred to the cooling liquid through the cooling channels embedded in the casings of each component. The cooling liquid is circulated to the second heat sinks 8 under the drive of a pump to transfer the heat to the motor cooling air.

[0043] In specific implementation, in order to fully recover the compression work of the centrifugal compressor, further improvements are made in this embodiment. It further includes a radial turbine 9, and the radial turbine 9 is coaxially arranged with the high-speed motor 2. The air inlet of the radial turbine 9 is communicated with the cathode outlet of the fuel cell stack unit 3, so that the high-temperature and high-pressure cathode exhaust gas discharged from the fuel cell stack unit 3 drives the radial turbine 9 to rotate. By arranging the radial turbine 9, on the one hand, the centrifugal compressor 1, the cathode flow channel of the fuel cell stack and the radial turbine 9 in the system actually form a Brayton thermodynamic cycle, and its efficiency increases with the increase of the temperature before the turbine. Therefore, in a high-temperature proton exchange membrane fuel cell system, the radial turbine 9 can recover more than 70% of the power of the air compressor, thereby effectively improving the specific power of the system. Further, the radial turbine 9 is coaxially arranged with the high-speed motor 2, and the energy recovered by the turbine is used to drive the coaxial centrifugal compressor 1 to rotate, so as to reduce the power consumption of the high-speed motor 2, which is beneficial to reducing the size of the high-speed motor 2; at the same time, the radial turbine 9 is also located in the heat insulation screen 6 to prevent the heat of the radial turbine 9 from affecting the air-cooled heat dissipation of the fuel cell stack unit 3.

[0044] In specific implementation, a plurality of fuel cell stack units 3 are connected in parallel on the air pipeline. It further includes a plurality of bypass pipes 10, and the plurality of bypass pipes 10 correspond to the fuel cell stack units 3 one by one. Both ends of the bypass pipe 10 are respectively communicated with the cathode inlet and the cathode outlet of the corresponding fuel cell stack unit 3. The bypass pipe 10 is used to conduct when the corresponding fuel cell stack unit 3 fails. That is, in use, the bypass pipe 10 is not conducted when the corresponding fuel cell stack unit 3 is working normally, and is conducted when the corresponding fuel cell stack unit 3 fails. In this way, when one or several fuel cell stack units 3 fail, air can enter the radial turbine 9 through the bypass pipe 10. When the fuel cell stack unit 3 corresponding to the pipeline fails and the air flow needs to be restricted, the valve can be opened, and the compressed air can be directly introduced into the corresponding radial turbine 9 through the bypass pipe 10 to avoid the surge of the centrifugal compressor, so as not to affect the normal operation of other fuel cell stack units 3, the centrifugal compressor 1 and the radial turbine 9.

[0045] In specific implementation, the connection or disconnection of the bypass pipe 10 can be realized by arranging a solenoid valve on the bypass pipe 10. Those skilled in the art can achieve this, and will not be elaborated here.

[0046] Embodiment 2

[0047] This embodiment is a further improvement based on Embodiment 1. The same parts will not be elaborated, and only the differences will be described below.

[0048] Please refer to Figure 1, in specific implementation, when a high-temperature proton exchange membrane fuel cell operates, hydrogen exceeding the chemical reaction equivalent needs to be supplied. After hydrogen and oxygen in the air react in the fuel cell stack unit 3, the hydrogen cannot completely react. For the treatment of the residual hydrogen, this application proposes two treatment methods, that is, recycling the residual hydrogen in this embodiment, and burning the residual hydrogen in Embodiment 3. Specifically, in this embodiment, a hydrogen circulation pump 11 is further included, and the hydrogen circulation pump 11 is coaxially arranged with the high-speed motor 2. That is, the hydrogen circulation pump 11 is driven by the high-speed motor 2. The inlet of the hydrogen circulation pump 11 is communicated with the anode outlet of each fuel cell stack unit 3, and the outlet of the hydrogen circulation pump 11 is communicated with the anode inlet of each fuel cell stack unit 3. That is, the hydrogen circulation pump 11 is used to pump the residual hydrogen into the hydrogen inlet in a cycle to achieve the recycling of hydrogen.

[0049] Embodiment 3

[0050] This embodiment is a further improvement based on Embodiment 1. The same parts will not be described in detail, and only the differences will be described below.

[0051] Please refer to Figure 2 , when a high-temperature proton exchange membrane fuel cell operates, hydrogen exceeding the chemical reaction equivalent needs to be supplied. This embodiment treats the residual hydrogen of the fuel cell system. Different from Embodiment 2, in this embodiment, a combustion chamber 12 is further included. The first air inlet of the combustion chamber 12 is communicated with the centrifugal compressor 1, the second air inlet of the combustion chamber 12 is communicated with the anode outlet of the fuel cell stack unit 3, and the exhaust port of the combustion chamber 12 is communicated with the air inlet of the radial turbine 9.

[0052] There are multiple combustion chambers 12, and they correspond to the fuel cell stack units 3 one by one. Specifically, the high-temperature proton exchange membrane fuel cell system includes multiple branches, and each branch is provided with a fuel cell stack unit 3 and an intake pipe connecting the fuel cell stack unit 3 and the centrifugal compressor 1. During operation, first, the centrifugal compressor 1 sucks in air and does work on the air. Then, the air is equally divided into several parts according to the number of fuel cell stacks, and after being decelerated and expanded by the tubular diffuser, it is sent to the cathode of the fuel cell stack unit 3 to participate in the electrochemical reaction. The cathode products of the electrochemical reaction are collected and converged through the intake pipe of the radial turbine 9 and accelerated to form a swirl, which impacts the impeller of the radial turbine 9; when a certain fuel cell stack unit 3 needs to stop supplying air due to a fault, the air leading to this fuel cell can bypass this fuel cell stack unit 10 through the bypass pipe 10, that is, at this time, the tubular diffuser is directly connected to the intake pipe of the radial turbine 9 through the bypass pipe 10.

[0053] The combustion chamber 12 is an annular combustion chamber. Specifically, the annular combustion chamber should ensure that the axial projection of the pipeline is limited within the range of the plane of each fuel cell stack unit 3, and shall not encroach upon or block the axial projection area of the meridional flow channel. Further, in order to reduce the heat radiation from the combustion chamber to other components, in practical applications, the outer periphery of the annular combustion chamber is sprayed with a heat insulation coating. Specifically, the annular fuel chamber 12 is also circumferentially arrayed around the center line of the high-speed motor 2.

[0054] In the above embodiments, in order to reduce the resistance of the high-speed motor 2 during high-speed rotation, the rotor of the high-speed motor 2 is supported by two magnetic suspension bearings 13, and the magnetic suspension controller 14 for controlling the magnetic suspension bearings 13 is arranged in the heat insulation screen 6. At the same time, the magnetic suspension bearings 13 do not require lubricating oil during high-speed rotation, and can prevent the lubricating oil from polluting and poisoning the catalyst in the fuel cell.

[0055] In specific implementation, the high-speed motor 2 (including the corresponding motor controller), together with the magnetic suspension bearings 13 and the magnetic suspension controller 14 at both ends thereof, is temperature-controlled by an independent liquid cooling system. The liquid cooling system includes a coolant pump (and controller), a coolant storage tank, a temperature sensor, cooling channels integrated in the housing of the high-speed motor 2 and the magnetic suspension bearing, and a radiator. Except for the coolant pump and the coolant storage tank, they are all arranged in the heat insulation screen 6. The radiator is composed of a coolant pipeline and a second heat sink 8, and is arranged in the annular gap (i.e., the second heat dissipation cavity) between the outer shell of the high-speed motor 2 and the heat insulation screen 6, that is, it can be air-cooled by the air in the inner channel.

[0056] Through the above Embodiments 1 to 3, the solutions proposed by the present invention have at least the following beneficial effects:

[0057] In the present invention, a plurality of fuel cell stack units 3 are provided. The fuel cell stack units 3 are high-temperature proton exchange membrane fuel cell stacks, and their normal operating temperature is 120 to 200 °C; by arranging the fuel cell stack units 3 in a circumferential array, the surface area of the fuel cell stack is effectively increased, and air-cooling heat dissipation can be realized. It can greatly simplify the thermal management system and reduce the system weight.

[0058] The fuel cell stack units 3 are arranged in an annular shape, and a first heat dissipation cavity for the fuel cell cooling air to pass through is provided therein. When it is applied to the aviation field such as a light aircraft, the fuel cell cooling air can pass through the first heat dissipation cavity, and the fuel cell stack units can be cooled by the airflow generated during the flight of the aircraft.

[0059] The multiple fuel cell stack units 3 are arranged in parallel, forming a redundant design in which the multiple fuel cell stack units are backed up with each other, which is beneficial to improving the airworthiness safety.

[0060] The high operating temperature of the high-temperature proton exchange membrane fuel cell improves the thermal efficiency of the Brayton cycle composed of a centrifugal compressor and a radial turbine, greatly reduces the parasitic power of the system, and also reduces the size and weight of the high-speed motor, which is beneficial to improving the specific power of the fuel cell system.

[0061] During the startup process of the high-temperature proton exchange membrane fuel cell, the centrifugal compressor can be used to heat the air to rapidly and uniformly increase the temperature of the proton exchange membrane, which is beneficial to shortening the startup time.

[0062] The structure, characteristics, and effects of the present invention have been described in detail based on the embodiments shown in the drawings. The above are only the preferred embodiments of the present invention, but the present invention is not limited to the scope shown in the drawings. Any changes made according to the concept of the present invention, or equivalent embodiments modified into equivalent changes, still within the spirit covered by the description and the drawings, shall be within the protection scope of the present invention.

Claims

1. A high-temperature proton exchange membrane fuel cell system, comprising a centrifugal compressor (1), a high-speed motor (2) and a plurality of stack units (3), wherein the centrifugal compressor (1) is coaxially arranged with the high-speed motor (2); the centrifugal compressor (1) is respectively communicated with each of the stack units (3) through a plurality of tubular diffusers; and it is characterized in that: The stack unit (3) is a high-temperature proton exchange membrane fuel cell stack; The stack units (3) are arranged in a circular array around the center line of the high-speed motor (2); and a first heat dissipation cavity (4) for the cooling air of the stack to pass through is provided between two adjacent stack units (3) and between the stack unit (3) and the high-speed motor (2); further comprising a heat insulation screen (6), the heat insulation screen (6) being cylindrical; the heat insulation screen (6) is sleeved on the outer periphery of the high-speed motor (2); the first heat dissipation cavity (4) is an annular grid and is located on the outer periphery of the heat insulation screen (6).

2. The high-temperature proton exchange membrane fuel cell system according to claim 1, characterized in that: Further comprising first heat dissipation fins (5), the first heat dissipation fins (5) are formed by extending from a plurality of the stack units (3) towards the first heat dissipation cavity (4).

3. The high-temperature proton exchange membrane fuel cell system according to claim 2, characterized in that: A second heat dissipation cavity (7) is provided between the heat insulation screen (6) and the high-speed motor (2), and the second heat dissipation cavity (7) is used for the motor cooling air to pass through; Second heat dissipation fins (8) are provided in the second heat dissipation cavity (7), and the second heat dissipation fins (8) are used for dissipating heat from the high-speed motor (2).

4. The high-temperature proton exchange membrane fuel cell system according to claim 1, characterized in that: Further comprising a radial turbine (9), the radial turbine (9) is coaxially arranged with the high-speed motor (2); The air inlet of the radial turbine (9) is communicated with the cathode outlet of the stack unit (3), so that the cathode exhaust gas discharged from the stack unit (3) drives the radial turbine (9) to rotate.

5. The high-temperature proton exchange membrane fuel cell system according to claim 4, characterized in that: Further comprising a plurality of bypass pipes (10), the plurality of bypass pipes (10) correspond to the stack units (3) one by one, and both ends of the bypass pipe (10) are respectively communicated with the cathode inlet and the cathode outlet of the corresponding stack unit (3); The bypass pipe (10) is used for conducting when the corresponding stack unit (3) fails.

6. The high-temperature proton exchange membrane fuel cell system according to any one of claims 1 to 5, characterized in that: Further comprising a hydrogen circulation pump (11), the hydrogen circulation pump (11) is coaxially arranged with the high-speed motor (2); The air inlet of the hydrogen circulation pump (11) is communicated with the anode outlet of each stack unit (3), and the air outlet of the hydrogen circulation pump (11) is communicated with the anode inlet of each stack unit (3).

7. The high-temperature proton exchange membrane fuel cell system according to claim 4 or 5, characterized in that: Further comprising a combustion chamber (12), the first air inlet of the combustion chamber (12) is communicated with the centrifugal compressor (1), the second air inlet of the combustion chamber (12) is communicated with the anode outlet of the stack unit (3), and the exhaust port of the combustion chamber (12) is communicated with the air inlet of the radial turbine (9).

8. The high-temperature proton exchange membrane fuel cell system according to claim 7, characterized in that: There are a plurality of the combustion chambers (12), and they correspond to the stack units (3) one by one.

9. The high-temperature proton exchange membrane fuel cell system according to claim 7, characterized in that: The combustion chamber (12) is an annular tube combustion chamber.

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