A double-rotor fuel cell air compressor

Abstract

The present invention provides a dual-rotor fuel cell air compressor, which relates to the technical field of air compressors. It includes a driving mechanism, an outer rotor, an inner rotor, a first radial bearing, a first thrust bearing, a second radial bearing and a second thrust bearing. The driving mechanism is drivingly connected to the outer rotor. A first compression impeller and a second compression impeller are respectively arranged at both ends of the outer rotor. The outer side of the outer rotor is movably connected to the first radial bearing and the first thrust bearing respectively, and its inner side is connected to the second radial bearing. A third compression impeller and a turbine are respectively arranged at both ends of the inner rotor. The outer side of the inner rotor is movably connected to the second radial bearing and the second thrust bearing respectively. The dual rotors can correspond to the low-speed stage when the turbine is not working. At this time, the load of the fuel cell system is low and the power generation is small, and there is no need for turbine recovery. The air compressor can switch between two-stage compression and three-stage compression. Compared with two-stage compression, the work done by the motor in three-stage compression is lower, reducing the energy consumption of the air compressor.

Description

Technical Field

[0001] The present invention relates to the technical field of air compressors, and in particular to a dual-rotor fuel cell air compressor. Background Art

[0002] Hydrogen fuel cell vehicles have the advantages of high efficiency, fast hydrogen refueling, strong endurance, and environmental friendliness, and truly achieve the "zero emission" goal. An air compressor is an important component of the cathode air supply system of a vehicle fuel cell, and can provide a gas source for the fuel cell system. By pressurizing the incoming air, the power density and efficiency of the fuel cell can be improved, and the size of the fuel cell system can be reduced. At the same time, the air compressor is a large energy consumer in the system, and its performance directly affects the efficiency of the system. In addition, the external dimensions and weight of the air compressor also directly affect the structural compactness and cost of the system. With the gradual improvement of fuel cell technology and the power gradually entering the high-power range, the motor power will further increase, which increases the difficulty and reduces the reliability for high-speed motors and controllers. Therefore, it is necessary to utilize the residual pressure exhaust gas of the fuel cell to recover energy, reduce the power consumption of electricity, and further improve the overall efficiency of the machine.

[0003] The applicant found that there are at least the following technical problems in the prior art: Currently, for a single-stage centrifugal compressor with energy recovery, a compression impeller and a turbine are respectively arranged on both sides of the motor. The impeller and the turbine are arranged on a single shaft and rotate simultaneously. However, at low speeds, the load of the fuel cell system is low and the power generation is small, and the role of turbine energy recovery is minimal, and even counteracts to do negative work, increasing the system energy consumption. Summary of the Invention

[0004] The purpose of the present invention is to provide a dual-rotor fuel cell air compressor to solve the technical problem that the turbine of the fuel cell air compressor with energy recovery in the prior art is difficult to work efficiently under all working conditions. The preferred technical solutions provided by the present invention can produce many technical effects as described below.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] A dual-rotor fuel cell air compressor includes a driving mechanism, an outer rotor, an inner rotor, a first radial bearing, a first thrust bearing, a second radial bearing, and a second thrust bearing. The driving mechanism is drivingly connected to the outer rotor. A first compression impeller and a second compression impeller are respectively arranged at both ends of the outer rotor. The outer rotor is movably connected to the first radial bearing and the first thrust bearing on the outside and is connected to the second radial bearing on the inside. A third compression impeller and a turbine are respectively arranged at both ends of the inner rotor. The outer side of the inner rotor is movably connected to the second radial bearing and the second thrust bearing.

[0007] Preferably, the first radial bearing, the first thrust bearing, and the second radial bearing are gas bearings, and the second thrust bearing is a double-rotation gas bearing.

[0008] Preferably, the inner rotor further includes an inner rotor shaft and an inner rotor thrust disk. The third compression impeller is connected to one end of the inner rotor shaft, the turbine is connected to the other end of the inner rotor shaft. The inner rotor thrust disk is connected to the inner rotor shaft and is close to the end where the turbine is provided. Both sides of the inner rotor thrust disk are movably connected to one of the second thrust bearings respectively, and the outer side of the inner rotor shaft is movably connected to the second radial bearing.

[0009] Preferably, the third compression impeller is sleeved on the outside of the inner rotor and is detachably connected to the inner rotor through a locking nut. The turbine is sleeved on the outside of the inner rotor and is detachably connected to the inner rotor through a locking nut. The inner rotor thrust disk is sleeved on the outside of the inner rotor and forms an extrusion contact with the end of the turbine away from the locking nut.

[0010] Preferably, the outer rotor further includes an outer rotor shaft and an outer rotor thrust disk. The first compression impeller is connected to one end of the outer rotor shaft, the second compression impeller is connected to the other end of the outer rotor shaft. The outer rotor thrust disk is connected to the outer rotor shaft and is close to the end where the first compression impeller is provided. Both sides of the outer rotor thrust disk are movably connected to one of the first thrust bearings respectively, the outer side of the outer rotor shaft is movably connected to the first radial bearing and its inner side is connected to the second radial bearing.

[0011] Preferably, the first compression impeller is sleeved on the outside of the outer rotor and is detachably connected to the outer rotor through a locking nut. The outer rotor thrust disk is sleeved on the outside of the outer rotor and forms an extrusion contact with the end of the first compression impeller away from the locking nut. The second compression impeller is sleeved on the outside of the outer rotor and is detachably connected to the outer rotor through a locking nut.

[0012] Preferably, the drive mechanism includes a motor stator and a permanent magnet. The permanent magnet is connected to the outer rotor shaft, and the motor stator is located outside the permanent magnet.

[0013] Preferably, a protective sleeve is sleeved on the outer rotor shaft outside the permanent magnet.

[0014] Preferably, the first radial bearing includes a first radial bearing seat, a first radial bearing wave foil, and a first radial bearing top foil that are connected in sequence.

[0015] Preferably, the second radial bearing includes a connected second radial bearing wave foil and a second radial bearing top foil, and the second radial bearing wave foil is connected to the inner side of the outer rotor.

[0016] The beneficial effects of the present invention are as follows: By forming a dual-rotor in which the outer rotor and the inner rotor cooperate, the air compressor can have two operating states, namely, the turbine working state and the turbine non-working state. The operating state when the turbine is not working can correspond to the low-speed stage of the air compressor. At this time, the load of the fuel cell system is low and the power generation is small, and there is no need for turbine recovery. The operating state when the turbine is working can correspond to the high-speed stage of the air compressor. At this time, the load of the fuel cell system is large and the power generation is large, and turbine recovery can be carried out. During the actual operation process, the dual-rotor fuel cell air compressor can flexibly switch between the above two different operating states according to the actual situation;

[0017] When the turbine is not working, the air compressor can form a two-stage compression in series. When the turbine is working, the air compressor can form a three-stage compression in which three compression impellers work in series. Compared with the two-stage compression, the three-stage compression with energy recovery requires less work from the motor under the premise of obtaining the same flow and pressure of exhaust gas, thereby effectively reducing the energy consumption of the air compressor;

[0018] The range of turbine recovery in the full operating range of the fuel cell system is wider, and by using the dual-rotor setting method, it will not have a counterproductive effect, and the control system for full operating range energy recovery is simpler. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0020] Figure 1 It is a sectional view structure diagram of the present invention;

[0021] Figure 2 It is a side view structure diagram of the present invention when the turbine is in the working state;

[0022] Figure 3 It is a sectional view structure diagram of the outer rotor of the present invention;

[0023] Figure 4 It is a sectional view structure diagram of the inner rotor of the present invention;

[0024] In the figure, 1 is a driving mechanism; 11 is a motor stator; 12 is a permanent magnet;

[0025] 2. Outer Rotor; 21. Outer Rotor Shaft; 22. First Compression Impeller; 23. Second Compression Impeller; 24. Outer Rotor Thrust Disk; 25. Protective Sleeve

[0026] 3. Inner Rotor; 31. Inner Rotor Shaft; 32. Third Compression Impeller; 33. Turbine; 34. Inner Rotor Thrust Disk

[0027] 4. First Radial Bearing; 41. First Radial Bearing Housing; 42. First Radial Bearing Wave Foil; 43. First Radial Bearing Top Foil

[0028] 5. First Thrust Bearing

[0029] 6. Second Radial Bearing; 61. Second Radial Bearing Wave Foil; 62. Second Radial Bearing Top Foil

[0030] 7. Second Thrust Bearing Detailed Embodiment

[0031] To make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be described in detail below. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without any creative work fall within the scope of protection of the present invention.

[0032] In the description of the present invention, it should be understood that the terms "center", "lateral", "length", "width", "height", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "side", etc. indicate the orientation or positional relationship based on the Figure 1 orientation or positional relationship shown, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation to the present invention.

[0033] In the description of the present invention, it should also be noted that unless otherwise clearly defined and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0034] Refer to Figures 1 to 4, the present invention provides a dual-rotor fuel cell air compressor, which includes a driving mechanism 1, an outer rotor 2, an inner rotor 3, a first radial bearing 4, a first thrust bearing 5, a second radial bearing 6 and a second thrust bearing 7.

[0035] The outer rotor 2 includes an outer rotor shaft 21, a first compression impeller 22, a second compression impeller 23 and an outer rotor thrust plate 24;

[0036] The first compression impeller 22 is connected to one end of the outer rotor shaft 21, and the second compression impeller 23 is connected to the other end of the outer rotor shaft 21;

[0037] The outer rotor thrust plate 24 is connected to the outer rotor shaft 21 and is close to the end with the first compression impeller 22. Both sides of the outer rotor thrust plate 24 are movably connected to a first thrust bearing 5 respectively;

[0038] In specific connection, the first compression impeller 22 is sleeved outside the outer rotor 2 and is detachably connected to the outer rotor 2 through a locking nut. The second compression impeller 23 is sleeved outside the outer rotor 2 and is detachably connected to the outer rotor 2 through a locking nut. The outer rotor thrust plate 24 is sleeved outside the outer rotor 2 and forms an extrusion contact with the end of the first compression impeller 22 away from the locking nut. The outer rotor thrust plate 24 is fixed to the outer rotor 2 through the extrusion contact force from the first compression impeller 22;

[0039] During the operation process, the outer rotor shaft 21, the first compression impeller 22, the second compression impeller 23 and the outer rotor thrust plate 24 always rotate synchronously;

[0040] The outside of the outer rotor shaft 21 is movably connected to the first radial bearing 4 and its inside is connected to the second radial bearing 6. The number of the first radial bearings 4 is two, and the two first radial bearings 4 are symmetrically arranged relative to the driving mechanism 1. The number of the second radial bearings 6 is two, and the two second radial bearings 6 are symmetrically arranged relative to the driving mechanism 1;

[0041] The outer rotor shaft 21 can be supported by two first radial bearings 4 and two first thrust bearings 5. The two first thrust bearings 5 can limit the axial displacement of the outer rotor shaft 21 by restricting the outer rotor thrust plate 24.

[0042] The inner rotor 3 includes an inner rotor shaft 31, a third compression impeller 32, a turbine 33 and an inner rotor thrust plate 34;

[0043] The third compression impeller 32 is connected to one end of the inner rotor shaft 31, and the turbine 33 is connected to the other end of the inner rotor shaft 31;

[0044] The inner rotor thrust disk 34 is connected to the inner rotor shaft 31 and is close to one end where the turbine 33 is provided. Both sides of the inner rotor thrust disk 34 are movably connected to a second thrust bearing 7 respectively;

[0045] During specific connection, the third compression impeller 32 is sleeved outside the inner rotor 3 and is detachably connected to the inner rotor 3 through a locking nut. The turbine 33 is sleeved outside the inner rotor 3 and is detachably connected to the inner rotor 3 through a locking nut. The inner rotor thrust disk 34 is sleeved outside the inner rotor 3 and forms a pressing contact with one end of the turbine 33 away from the locking nut. The inner rotor thrust disk 34 is fixed to the inner rotor 3 through the pressing contact force from the turbine 33;

[0046] During the operation process, the inner rotor shaft 31, the third compression impeller 32, the turbine 33 and the inner rotor thrust disk 34 always rotate synchronously;

[0047] The outside of the inner rotor shaft 31 is movably connected to the second radial bearing 6. The inner rotor shaft 31 can be supported by two second radial bearings 6 and two second thrust bearings 7. The two second thrust bearings 7 can limit the axial displacement of the inner rotor shaft 31 by restricting the inner rotor thrust disk 34.

[0048] The driving mechanism 1 is drivingly connected to the outer rotor 2. In this embodiment, the driving mechanism 1 preferably includes a motor stator 11 and a permanent magnet 12. The motor stator 11 is fixedly connected to the housing. The outer rotor shaft 21 is provided with a fixing groove at the corresponding position of the permanent magnet 12. The permanent magnet 12 is connected to the fixing groove of the outer rotor shaft 21, and the two can move synchronously. The motor stator 11 is located outside the permanent magnet 12. After being energized, the permanent magnet 12 can rotate relatively, thereby driving the outer rotor shaft 21 to rotate relatively;

[0049] On this basis, in order to protect the permanent magnet 12 to a certain extent, a protective sleeve 25 is preferably sleeved outside the permanent magnet 12 on the outer rotor shaft 21. Both ends of the protective sleeve 25 can cover the outside of the permanent magnet 12, which has a good protective effect on the permanent magnet 12.

[0050] In this embodiment, first of all, the first radial bearing 4, the first thrust bearing 5, the second radial bearing 6 and the second thrust bearing 7 are all preferably gas bearings, and can further be preferably foil gas journal bearings;

[0051] The foil gas journal bearing has small frictional losses, and has a series of advantages such as almost no friction at high speeds, good high-temperature stability, small vibration and no need for lubricating oil. Therefore, it can be widely used in mechanical equipment such as air circulators, air blowers, fuel cell air compressors, micro gas turbines, etc. When applied to this embodiment, it can achieve good application effects;

[0052] Secondly, the second thrust bearing 7 is further preferably a double-rotation-direction foil gas journal bearing. With such a setting, the second thrust bearing 7 can simultaneously have the ability to rotate in the forward direction and the reverse direction. During the operation of the air compressor, when starting up, the second thrust bearing 7 may be subject to reverse frictional force, resulting in reverse rotation of the second thrust bearing 7. If the second thrust bearing 7 does not have the ability to rotate in the reverse direction, there is a possibility of damage. Therefore, by selecting and setting a double-rotation-direction foil gas journal bearing, this technical problem can be effectively solved to ensure the normal operation of the equipment.

[0053] In this embodiment, the first radial bearing 4 preferably includes a first radial bearing housing 41, a first radial bearing wave foil 42, and a first radial bearing top foil 43. The first radial bearing housing 41 is preferably fixedly connected to the machine housing. The first radial bearing housing 41, the first radial bearing wave foil 42, and the first radial bearing top foil 43 are connected in sequence. When the equipment is not started, the first radial bearing top foil 43 can form frictional contact with the outer rotor 2.

[0054] In this embodiment, the second radial bearing 6 preferably includes a second radial bearing wave foil 61 and a second radial bearing top foil 62. The second radial bearing wave foil 61 is connected to the inner side of the outer rotor 2. The second radial bearing wave foil 61 and the second radial bearing top foil 62 are connected. When the equipment is not started, the second radial bearing top foil 62 can form frictional contact with the inner rotor 3.

[0055] The double-rotor fuel cell air compressor mentioned in this embodiment has two different operating states, which respectively correspond to the operating state when the turbine 33 is not working and the operating state when the turbine 33 is working;

[0056] The operating state when the turbine 33 is not working can correspond to the low-speed stage of the air compressor. At this time, the load of the fuel cell system is low and the power generation power is small, and no turbine recovery is required;

[0057] The operating state when the turbine 33 is working can correspond to the high-speed stage of the air compressor. At this time, the load of the fuel cell system is large and the power generation power is large, and turbine recovery can be carried out;

[0058] During the actual operation process, the double-rotor fuel cell air compressor can flexibly switch between the above two different operating states according to the actual situation.

[0059] In this embodiment, the operating principle when the turbine 33 is not working is as follows:

[0060] The two first radial bearings 4 and the two first thrust bearings 5 can support the outer rotor 2, and at the same time are fixedly connected to the external machine housing and remain relatively stationary;

[0061] When the driving mechanism 1 starts, it can drive the outer rotor 2 to rotate, andFigure 2 The effect of the outer rotor rotating clockwise is shown. During the rotation of the outer rotor 2, the second radial bearing 6 rotates synchronously with the outer rotor 2;

[0062] It should be noted that since the second radial bearing 6 can form frictional contact with the inner rotor 3, when the outer rotor 2 starts to rotate, the inner rotor will also rotate clockwise at the beginning based on the frictional force transmitted by the rotation of the two second radial bearings 6. This is different from the counterclockwise rotation shown in the attached drawings. The counterclockwise rotation shown in the attached drawings is the motion effect when the following turbine 33 works;

[0063] As the rotational speed increases, when the rotational speed gradually increases to the take-off speed of the second radial bearing 6, the frictional force between the inner rotor 3 and the two second radial bearings 6 decreases. At the same time, there is a frictional force between the second thrust bearing 7 and the inner rotor 3. Under the action of the reverse frictional force of the second thrust bearing 7, when the frictional force between the inner rotor 3 and the two second radial bearings 6 is less than the frictional force between the second thrust bearing 7 and the inner rotor 3, the inner rotor 3 gradually enters a super-low speed state or a static suspension state;

[0064] When in the above state, due to the characteristics of the gas bearing, the outer rotor 2 is completely in a suspended state supported by the two first radial bearings 4 and the two first thrust bearings 5 and rotates at a high speed. Therefore, the two second radial bearings 6 used to support the inner rotor 3 and connected to the outer rotor 2 are also in a state of high-speed rotation and suspension. Due to the characteristics of the gas bearing and relying on the frictional force provided by the second thrust bearing 7, the inner rotor shaft 31 can be relatively stationary and suspended between the two high-speed rotating second radial bearings 6;

[0065] In this operating state, the first compression impeller 22 and the second compression impeller 23 located at both ends of the outer rotor 2 can form two-stage compression. The gas compressed by the first compression impeller 22 can enter the second compression impeller 23 for further compression, forming a series of two-stage compression.

[0066] In this embodiment, the operating principle when the turbine 33 works is as follows:

[0067] Compared with the above operating principle when the turbine 33 does not work, the difference is only that the turbine 33 switches between rotation and non-rotation. Therefore, when the turbine 33 is not rotating, it is consistent with the above operating principle;

[0068] While the outer rotor 2 is rotating clockwise at a high speed, the turbine 33 is driven by the pressurized exhaust gas from the fuel cell system to start rotating, and its rotation direction is opposite to that of the outer rotor 2, which is Figure 2The counterclockwise rotation shown in [description] is due to the fact that when the turbine 33 is not working, the radial direction of the inner rotor 3 is in a static suspension state. At this time, only when the rotational force brought by the turbine 33 is greater than the frictional force of the second thrust bearing 7 can the whole inner rotor 3 rotate reversely relative to the outer rotor 2. Additionally, due to the structural design of the thrust bearing, the outer diameter of the thrust bearing is large, the linear velocity is high, and the take-off speed is lower than that of the radial bearing. Therefore, only exhaust gas with a relatively low pressure and flow rate is required to drive the rotation of the inner rotor 3;

[0069] Since the rotation directions of the inner rotor 3 and the outer rotor 2 are opposite, there is a large linear velocity difference between the second radial bearing 6 for supporting the inner rotor 3 and the inner rotor 3, which can form a good hydrodynamic pressure effect, and the second radial bearing 6 can also provide a good supporting effect;

[0070] In this operating state, the turbine 33 drives the inner rotor 3 to rotate, driving the third compression impeller 32 to start working. The third compression impeller 32 can cooperate with the first compression impeller 22 and the second compression impeller 23 to form a three-stage compression with three compression impellers working in series;

[0071] Compared with the two-stage compression with energy recovery, under the premise of obtaining the same flow rate and pressure of exhaust gas, the work done by the motor is lower, thus effectively reducing the energy consumption of the air compressor;

[0072] The range of energy recovery by the turbine 33 in the full operating range of the fuel cell system is wider, and there will be no counter-effect, and the control system for full operating range energy recovery is simpler.

[0073] The above is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should all be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A dual-rotor fuel cell air compressor, characterized in that: The invention comprises a driving mechanism (1), an outer rotor (2), an inner rotor (3), a first radial bearing (4), a first thrust bearing (5), a second radial bearing (6) and a second thrust bearing (7), wherein the driving mechanism (1) is drivingly connected to the outer rotor (2), a first compression impeller (22) and a second compression impeller (23) are respectively arranged at two ends of the outer rotor (2), the outer side of the outer rotor (2) is movably connected to the first radial bearing (4) and the first thrust bearing (5) respectively, and the inner side thereof is connected to the second radial bearing (6), the two ends of the inner rotor (3) are respectively arranged with a third compression impeller (32) and a turbine (33), the outer side of the inner rotor (3) is movably connected to the second radial bearing (6) and the second thrust bearing (7), and the driving mechanism (1) comprises a motor stator (11) and a permanent magnet (12), the permanent magnet (12) is connected to the outer rotor (2), and the motor stator (11) is located on the outer side of the permanent magnet (12).

2. The dual-rotor fuel cell air compressor according to claim 1, characterized in that: The first radial bearing (4), the first thrust bearing (5) and the second radial bearing (6) are gas bearings, and the second thrust bearing (7) is a birotational gas bearing.

3. The dual-rotor fuel cell air compressor according to claim 1, characterized in that: The inner rotor (3) further comprises an inner rotor shaft (31) and an inner rotor thrust plate (34); the third compression impeller (32) is connected to one end of the inner rotor shaft (31); the turbine (33) is connected to the other end of the inner rotor shaft (31); the inner rotor thrust plate (34) is connected to the inner rotor shaft (31) and is close to one end where the turbine (33) is provided; both sides of the inner rotor thrust plate (34) are movably connected to one of the second thrust bearings (7); and the outer side of the inner rotor shaft (31) is movably connected to the second radial bearing (6).

4. The dual-rotor fuel cell air compressor according to claim 3, characterized in that: The third compression impeller (32) is sleeved on the outer side of the inner rotor (3) and is detachably connected to the inner rotor (3) via a locking nut; the turbine (33) is sleeved on the outer side of the inner rotor (3) and is detachably connected to the inner rotor (3) via a locking nut; the inner rotor thrust plate (34) is sleeved on the outer side of the inner rotor (3) and is in extrusion contact with an end of the turbine (33) away from the locking nut.

5. The dual-rotor fuel cell air compressor according to claim 1, characterized in that: The outer rotor (2) further comprises an outer rotor shaft (21) and an outer rotor thrust plate (24); the first compression impeller (22) is connected to one end of the outer rotor shaft (21); the second compression impeller (23) is connected to the other end of the outer rotor shaft (21); the outer rotor thrust plate (24) is connected to the outer rotor shaft (21) and is close to the end where the first compression impeller (22) is provided; both sides of the outer rotor thrust plate (24) are movably connected to one of the first thrust bearings (5); the outer side of the outer rotor shaft (21) is movably connected to the first radial bearing (4) and the inner side thereof is connected to the second radial bearing (6).

6. The dual-rotor fuel cell air compressor according to claim 5, characterized in that: The first compression impeller (22) is sleeved on the outer side of the outer rotor (2) and is detachably connected to the outer rotor (2) via a locking nut; the outer rotor thrust plate (24) is sleeved on the outer side of the outer rotor (2) and is in extrusion contact with an end of the first compression impeller (22) away from the locking nut; and the second compression impeller (23) is sleeved on the outer side of the outer rotor (2) and is detachably connected to the outer rotor (2) via a locking nut.

7. The dual-rotor fuel cell air compressor according to claim 5, characterized in that: The permanent magnet (12) is connected to the outer rotor shaft (21), and a protective sleeve (25) is provided on the outer side of the permanent magnet (12) on the outer rotor shaft (21).

8. The dual-rotor fuel cell air compressor according to claim 2, characterized in that: The first radial bearing (4) comprises a first radial bearing seat (41), a first radial bearing wave foil (42) and a first radial bearing top foil (43) which are connected in sequence.

9. The dual-rotor fuel cell air compressor according to claim 2, characterized in that: The second radial bearing (6) comprises a second radial bearing corrugated foil (61) and a second radial bearing top foil (62) which are connected to each other, and the second radial bearing corrugated foil (61) is connected to the inner side of the outer rotor (2).

Images