A high-temperature superconducting magnetic levitation power rotor system and aircraft thereof

Abstract

The present invention discloses a high-temperature superconducting magnetic levitation powered rotor system and an aircraft thereof, and belongs to the technical field of rotorcraft. The present invention solves the problem that the existing rotor system has a compact structure and the internal heat cannot be dissipated. The present invention includes a stator ring and a rotor ring, and a plurality of blades are arranged on the rotor ring; a gap is arranged between the stator ring and the rotor ring, and the gap forms a cooling duct; a high-temperature superconducting magnetic levitation module and a driving module are arranged between the rotor rings; a cooling microchannel structure connected to the cooling duct is arranged on the stator ring or the rotor ring, and the other end of the cooling microchannel structure is connected to the outside world. The present invention maintains the axial and radial gaps together by the high-temperature superconducting magnetic levitation module and the driving module, simplifies the axial and radial support structures, provides sufficient space for air flow, and at the same time, a cooling microchannel structure is arranged to increase the air flow, effectively improving the heat dissipation effect.

Description

Technical Field

[0001] The present invention belongs to the technical field of rotorcraft, and in particular relates to a high-temperature superconducting magnetic levitation powered rotor system and an aircraft thereof. Background Art

[0002] Magnetic levitation relies on electromagnetic force between objects rather than mechanical contact force to balance gravity and achieve contactless coupling between objects, fundamentally eliminating various mechanical wear and mechanical friction resistance. In recent years, with the continuous development of magnetic levitation technology, applying magnetic levitation technology to rotorcraft has become a new design idea for rotorcraft.

[0003] The prior art provides a shaftless electromagnetic rotor with an outer edge support, comprising a circular lower rotor cover and an upper rotor cover; a cavity for placing a rotor ring is reserved between the lower rotor cover and the upper rotor cover; the upper rotor cover and the lower rotor cover are detachably connected as a whole; the rotor ring is made of metal, a plurality of propeller blades are installed on the inner side of the rotor ring, the outer side of the rotor ring is grooved and two permanent magnets are installed in the grooves, and the two permanent magnets are arranged on both sides of the rotor ring opposite to each other; a plurality of armature windings are provided. The circular array is arranged around the rotor ring and installed in the lower rotor cover. The armature winding is connected to an external DC power supply, and the coil of the armature winding faces the center of the circular ring. A vertical base adjustment magnetic induction coil is provided directly below the rotor ring, and the vertical base adjustment magnetic induction coil is installed in the lower rotor cover. A vertical base magnetic induction coil is provided directly above the rotor ring, and the vertical base magnetic induction coil is installed in the upper rotor cover. The vertical base adjustment magnetic induction coil and the vertical base magnetic induction coil are used to provide magnetic levitation force for the rotating rotor ring. However, the device is an encapsulated design in which the outer orbital ring is nested in the rotor ring, and the structure is compact. In addition, the device is driven to rotate by an internal electromagnet, and the heat generated inside cannot be dissipated in time, resulting in demagnetization of the permanent magnet and reducing the working efficiency of the disc motor. Summary of the invention

[0004] In view of the problem in the prior art that the rotor system has a compact structure and the internal heat cannot be dissipated, the present invention provides a high-temperature superconducting magnetic levitation powered rotor system and an aircraft thereof.

[0005] The technical solution adopted by the present invention is as follows:

[0006] A high-temperature superconducting magnetic suspension power rotor system comprises a stator ring and a rotor ring, wherein the rotor ring is provided with a plurality of blades;

[0007] A gap is provided between the stator ring and the rotor ring, and the gap forms a cooling duct;

[0008] A high-temperature superconducting magnetic suspension module and a driving module are arranged between the stator ring and the rotor ring; the high-temperature superconducting magnetic suspension module is used to maintain the axial and radial gaps between the stator ring and the rotor ring; the driving module is used to drive the rotor ring to rotate relative to the stator ring;

[0009] The stator ring or the rotor ring is provided with a cooling micro-channel structure connected with the cooling duct, and the other end of the cooling micro-channel structure is connected with the outside.

[0010] After adopting this technical solution, the present invention maintains the axial gap through the high-temperature superconducting magnetic suspension module and the driving module, and uses the strong pinning effect of high-temperature superconductors to control the radial gap, omitting the radial suspension mechanism, making the structure between the stator ring and the rotor ring simple, ensuring that the size of the cooling duct between the stator ring and the rotor ring is large enough, providing sufficient space for air flow, and effectively improving the heat dissipation effect; on this basis, a cooling microchannel structure is also set up, and the interaction between the cooling duct and the external air is further increased through the cooling microchannel, thereby improving the heat dissipation capacity. The height of one side of the cooling microchannel structure connected to the cooling duct is greater than the height of the other side, which can effectively prevent rainwater from entering the cooling duct from the cooling microchannel structure, thereby avoiding affecting the normal operation of the suspension system.

[0011] Preferably, the stator ring is provided with an annular groove, the rotor ring is arranged in the annular groove, and the cooling microchannel structure is arranged on the stator ring.

[0012] After adopting this technical solution, a ring groove is provided on the stator ring, and the rotor ring is arranged inside the stator ring to form a stator-rotor structure.

[0013] Preferably, a ring groove is provided on one side of the rotor ring, and blades are provided on the other side, the stator ring is provided in the ring groove, and the cooling microchannel structure is provided on the rotor ring.

[0014] After adopting this technical solution, a ring groove is provided on the rotor ring, and the stator ring is arranged inside the rotor ring to form a rotor-stator structure.

[0015] Preferably, there are several rotor rings, the number of the ring grooves is equal to the number of the rotor rings, each of the ring grooves is provided with a high-temperature superconducting magnetic levitation module, a driving module and a cooling duct, and a cooling microchannel structure is provided on the stator ring or the rotor ring corresponding to each cooling duct.

[0016] After adopting this technical solution, the upper limit of the lift required for the rotorcraft to rise can be effectively increased through multi-layer blade drive, thereby enhancing the carrying capacity of the rotorcraft.

[0017] Preferably, three annular grooves are provided, the spacing between two adjacent annular grooves is equal, the angles of attack and the directions of rotation of the blades connected to two adjacent rotor rings are opposite, and the rotation speeds of the blades on the three rotor rings satisfy the following formula:

[0018]

[0019] Where i = 1, 2, 3, indicating the i-th blade; Q i is the resistance moment of the i-th blade, C Qi represents the torque coefficient of the i-th blade, R is the blade radius, ρ is the air density; ω i is the rotation speed of the i-th layer of blades;

[0020] The resistance moment Q on the blade i It will directly act on the rotor ring and eventually on the stator ring. Therefore, a multi-layer blade reverse speed design is adopted to balance the torque of the multi-layer blade rotor ring acting on the stator ring, and the following relationship is obtained:

[0021] Q1+Q3=Q2

[0022] Right now:

[0023]

[0024] Simplified, the rotation speed relationship between the three layers of blades is:

[0025] C Q1 ω1 2 +C Q3 ω3 2 =C Q2 ω2 2 .

[0026] After adopting this technical solution, when the installation angle of the second layer of blades is opposite to that of the other two layers, the blades will obtain lift in the same direction as the other two layers of blades and drag torque in the opposite direction of the other two layers of blades when the rotation speed is applied in the opposite direction, which can achieve the effect of lift superposition and drag torque offset between multiple layers of blades. The present invention provides a calculation formula for the setting parameters of the blades. When the three layers of blades meet the above formula, the sum of the drag torque transmitted to the stator outer ring by the three layers of blades is zero, which inhibits the rotation of the stator outer ring around the axis of the rotorcraft.

[0027] Preferably, the cooling microfluidic channel structure comprises several cooling microfluidic channel groups uniformly arranged in annular direction around the stator ring or the rotor ring, each cooling microfluidic channel group is composed of several cooling microfluidic channels, and the cooling microfluidic channel groups of the cooling microfluidic channel structure on two adjacent stator rings or two adjacent rotor rings are arranged alternately.

[0028] After adopting this technical solution, the staggered arrangement of the cooling microchannel groups of two adjacent cooling microchannel structures can avoid the mutual influence between the cooling microchannel structures, and can further enhance the heat dissipation effect.

[0029] Preferably, the blades are all hollow structures.

[0030] After adopting this technical solution, the lift received by the blades when rotating is distributed in an "inward-concave" shape, and the blade support point is the outer edge. Therefore, although the lift provided by the middle part of the blade is less, the load on the outer edge support position is greater due to its distance from the outer edge support position and the larger lever arm. Setting a hollow blade structure can greatly improve the rotor support strength at the expense of extremely limited lift. At the same time, since there is no need to consider the design of the blade center connector, it is beneficial to reduce weight. The outer edge of the blade allows the blade to be designed with larger geometric dimensions, further increasing the lift.

[0031] Preferably, the high-temperature superconducting magnetic levitation module is arranged at the lower part of the rotor ring, and the driving module is arranged at the upper part of the rotor ring. The high-temperature superconducting magnetic levitation module includes a dewar or a suspended permanent magnet arranged on the stator ring, and the rotor ring is provided with a suspended permanent magnet matched with the dewar or a dewar matched with the suspended permanent magnet, a superconducting magnet is arranged in the dewar, and the dewar is also connected to a low-temperature liquid nitrogen container, and the driving module includes a driving permanent magnet or a driving coil arranged on the stator ring, and the rotor ring is provided with a driving coil matched with the driving permanent magnet or a driving permanent magnet matched with the driving coil.

[0032] After adopting this technical solution, the pinning effect between the superconducting magnet and the permanent magnet track is used to realize the autonomous control of the rotor axial suspension and radial limit, which has high self-stability. By setting the high-temperature superconducting magnetic suspension module at the bottom of the rotor ring and the driving permanent magnet at the top of the rotor ring, the magnetic suspension rotorcraft can achieve frictionless start-up, which means that the rotorcraft does not require physical contact between the rotor and the fuselage during takeoff and landing, reducing wear and energy loss. The magnetic suspension rotor adopts autonomously controlled high-temperature superconducting magnetic suspension technology. The high-temperature superconducting magnetic suspension system can quickly adjust the suspension force to respond to external disturbances without active control. At the same time, during the ascent and descent stages of the rotorcraft, the rotor suspension gap is dynamically adjusted to achieve rapid response to changes in flight status. When the rotorcraft deviates sideways, each suspension gap can still be guaranteed to be within the specified range.

[0033] Preferably, the suspended permanent magnets are arranged according to the Halbach arrangement.

[0034] Preferably, a plurality of anti-collision balls are evenly distributed in an annular direction on the upper top wall and the lower bottom wall of the annular groove.

[0035] After adopting this technical solution, high-temperature superconductors are used to achieve axial suspension. The strong pinning effect of high-temperature superconductors can be used to avoid radial displacement of the rotor ring. Therefore, radial anti-collision balls can be eliminated and the weight of the rotor can be reduced.

[0036] Preferably, a distance sensor is provided between the rotor ring and the stator ring, the distance sensor is electrically connected to a control system, and the control system is electrically connected to a high-temperature superconducting magnetic levitation module and a driving module.

[0037] After adopting this technical solution, the high-temperature superconducting magnetic levitation module and the driving module can be controlled by the spacing data detected by the distance sensor to maintain the gap between the stator ring and the rotor ring.

[0038] A flying vehicle containing a high-temperature superconducting magnetic levitation powered rotor system.

[0039] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0040] 1. The present invention maintains the axial gap through the high-temperature superconducting magnetic suspension module and the driving module, and uses the strong pinning effect of high-temperature superconductivity to control the radial gap, omitting the radial suspension mechanism, making the structure between the stator ring and the rotor ring simple, ensuring that the size of the cooling duct between the stator ring and the rotor ring is large enough, providing sufficient space for air flow, and effectively improving the heat dissipation effect; on this basis, a cooling microchannel structure is also provided, and the interaction between the cooling duct and the external air is further increased through the cooling microchannel, thereby improving the heat dissipation capacity.

[0041] 2. The present invention can effectively increase the upper limit of the lift required for the rotorcraft to rise through multi-layer blade drive, thereby enhancing the carrying capacity of the rotorcraft.

[0042] 3. The present invention sets the blades as hollow structures. This is because the lift received by the blades when rotating is distributed in a "concave" shape, and the blade support point is the outer edge. Therefore, although the lift provided by the middle part of the blade is less, the load on the outer edge support position is greater due to the distance from the outer edge support position and the larger force arm. Setting the blade hollow structure can greatly improve the rotor support strength at the expense of extremely limited lift. At the same time, since there is no need to consider the design of the blade center connector, it is beneficial to reduce weight. The outer edge of the blade allows the blade to be designed with larger geometric dimensions, which further improves the lift.

[0043] 4. The present invention arranges the high-temperature superconducting magnetic levitation module at the bottom of the rotor ring and the driving permanent magnet at the top of the rotor ring so that the magnetic levitation rotorcraft can achieve frictionless starting. This means that the rotorcraft does not need physical contact between the rotor and the body during takeoff and landing, reducing wear and energy loss. The magnetic levitation rotor adopts autonomously controlled high-temperature superconducting magnetic levitation technology. The high-temperature superconducting magnetic levitation system can quickly adjust the suspension force to respond to external disturbances without active control. At the same time, during the ascent and descent stages of the rotorcraft, the rotor suspension gap is dynamically adjusted to achieve rapid response to changes in flight status. When the rotorcraft deviates sideways, each suspension gap can still be guaranteed to be within the specified range.

[0044] 5. The present invention uses high-temperature superconductors to achieve axial suspension, and the strong pinning effect of high-temperature superconductors can be used to avoid radial displacement of the rotor ring, thereby eliminating radial anti-collision balls and reducing the weight of the rotor. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 It is a structural schematic diagram of Example 1;

[0046] Figure 2 It is a structural schematic diagram of Example 3;

[0047] Figure 3 It is a structural schematic diagram of Example 6;

[0048] Among them, 1-blade, 2-stator ring, 3-driving coil, 4-driving permanent magnet, 5-rotor ring, 6-cooling microfluidic structure, 7-cooling duct, 8-anti-collision ball, 9-Dewar, 10-suspended permanent magnet, 11-connector. DETAILED DESCRIPTION

[0049] To make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the technical scheme in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all of the embodiments. The components of the embodiments of the present application generally described and shown in the drawings here can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the application claimed for protection, but merely represents the selected embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without making creative work belong to the scope of protection of the present application.

[0050] In the description of the embodiments of the present application, it should be noted that the terms "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, or are the positions or positional relationships in which the inventive product is usually placed when in use. They are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second", "third", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0051] Example 1

[0052] A high-temperature superconducting magnetic suspension power rotor system, comprising a stator ring 2, wherein a ring groove is arranged in the stator ring 2, a rotor ring 5 is arranged in the ring groove, an opening is arranged on the ring groove, and the rotor ring 5 is connected to a plurality of blades 1 arranged outside the ring groove through the opening;

[0053] A gap is provided between the stator ring 2 and the rotor ring 5, and the gap forms a cooling duct 7. In this embodiment, the width of the cooling duct 7 is 10 mm.

[0054] A high-temperature superconducting magnetic suspension module and a driving module are respectively arranged between the top of the rotor ring 5 and the annular groove wall and between the bottom of the rotor ring 5 and the annular groove wall; the high-temperature superconducting magnetic suspension module is used to maintain the axial and radial gaps between the stator ring 2 and the rotor ring 5; the driving module is used to drive the rotor ring 5 to rotate relative to the stator ring 2;

[0055] A cooling microchannel structure 6 connected to a cooling duct 7 is provided on one side of the stator ring 2 away from the blade 1, and the other end of the cooling microchannel structure 6 is connected to the outside;

[0056] The height of one side of the cooling microchannel structure 6 connected to the cooling duct 7 is greater than the height of the other side. The diameter of each channel in the cooling microchannel structure 6 is 1 to 2 mm and is evenly arranged around the rotation center. When the rotor is running, the air inside the rotor can be exchanged with the outside, thereby improving the heat dissipation capacity of the rotor.

[0057] In this embodiment, the blades 1 are all hollow structures, and six blades 1 are connected to the rotor ring 5. The centers of the six blades 1 are not connected, which reduces the weight of the rotor ring 5, provides more space for the blades 1, and increases the lift generated by the rotor ring 5. During operation, the rotor ring 5 is electromagnetically attracted by the driving coil 2, driving the blades 1 fixed thereon to rotate and generate lift. The rotor ring 5 is made of non-ferromagnetic materials with good thermal conductivity to solve the heat dissipation problem and avoid interfering with the electromagnetic magnetic field.

[0058] In this embodiment, the high-temperature superconducting magnetic suspension module includes a dewar 9 arranged on the stator ring 2, a superconducting magnet is arranged in the dewar 9, and the dewar 9 is also connected to a cryogenic liquid nitrogen container, and a suspended permanent magnet 10 cooperating with the dewar 9 is arranged on the rotor ring 5. The cryogenic liquid nitrogen container can transport a cooling medium, such as liquid nitrogen, into the dewar 9 to make the superconducting magnet reach the required working temperature. The cooling medium is transported between the cryogenic liquid nitrogen container and the dewar 9 through a conveying system. The cryogenic liquid nitrogen container can be arranged on the stator ring 2 or on the frame around the rotor. In this embodiment, it is arranged on the stator ring 2.

[0059] In this embodiment, the suspended permanent magnet 10 is arranged according to the Halbach arrangement. The number of suspended permanent magnets 10 is 100. They are evenly distributed along the circumferential direction, and ferromagnetic materials are used to achieve magnetic isolation between permanent magnets, so that the magnetic field distribution meets the actual application requirements. There are 12 dewars 9, which are evenly distributed at intervals of 30° along the circumferential direction. Through the pinning effect between the superconducting magnet and the suspended permanent magnet 10, the autonomous control of the axial suspension and radial limit of the rotor is achieved, and it has high self-stability. The radial width of the superconducting magnet is 30mm larger than that of the suspended permanent magnet 10 to ensure the stability of the lateral restoring force. The superconducting magnet is placed at a certain height below the suspended permanent magnet 10, which is defined as the field cooling position. The superconducting magnet is in a normal state, and the magnetic field generated by the suspended permanent magnet 10 can be freely penetrated and penetrated, and there will be no force performance. The superconducting magnet is cooled at the field cooling position until it enters the superconducting state, and the magnetic field passing through the inside of the superconducting magnet will be captured by the pinning center. The superconducting magnet will be displaced due to gravity, which will change the magnetic flux inside the superconducting magnet, thereby inducing an electric current. Under the interaction of the electric current and the magnetic field, an electromagnetic force will be generated, which will support the rotor ring 5 without contact, form a frictionless start, and reduce the heat generation between the systems. When the superconducting magnet is displaced axially, the magnetic flux will change inside the superconducting magnet. Due to Lenz's law, its movement will be hindered, so that it will return to the field-cooled position to ensure its stable suspension. When the rotor ring 5 is displaced radially, the transverse magnetic flux in the superconducting magnet changes. According to Lenz's law, an induced current is generated on the surface of the superconducting magnet. This induced current interacts with the magnetic field to generate a transverse Lorentz magnetic force, which is manifested macroscopically as the transverse restoring force of the superconducting magnet.

[0060] In this embodiment, the driving module includes a driving permanent magnet 4 disposed on the upper surface of the rotor ring 5, and the stator ring 2 is provided with a driving coil 3 that cooperates with the driving permanent magnet 4. The driving coil 3 is fixedly connected to the stator ring 2 to form an outer frame of the magnetic suspension rotor, which plays a role in structural support and protection of the rotor ring 5.

[0061] The operation process is:

[0062] During the startup phase, the superconducting magnet in the dewar 9 enters the superconducting state at the field cooling position, interacts with the suspension permanent magnet 10, and generates a suspension force to support the rotor ring 5 to suspend. Then the drive coil 3 of the disc motor is energized to generate an electromagnetic field, which interacts with the drive permanent magnet 4 fixed to the upper surface of the rotor ring 5 to drive the rotor blades 1 to rotate at high speed. Through the pinning effect between the superconducting magnet and the suspension permanent magnet 10, the lateral movement of the rotor ring 5 is limited, which plays a lateral limiting role. The entire system structure is simple and compact, and the system mass is reduced. The magnetic suspension rotor structure adopts the method of wrapping the rotor with the stator, which reduces the volume of the stator ring 2, and the magnet arrangement on the stator ring 2 is more compact, which can effectively reduce the mass of large magnetic suspension rotor aircraft. At the same time, the cooling microchannel 6 and the cooling duct 7 are provided inside the rotor ring 5 to improve the heat dissipation performance of the rotor.

[0063] Example 2

[0064] The embodiment is basically the same as the embodiment 1, except that: in the embodiment, three annular grooves are provided, each of the annular grooves is provided with a rotor ring 5, each of the rotor rings 5 ​​is connected to a plurality of blades 1, and a high-temperature superconducting magnetic suspension module, a driving module, a cooling duct 7 and a cooling microchannel structure 6 are provided between each rotor ring 5 and the annular groove, the spacing between two adjacent annular grooves is equal, and the distances from the two annular grooves on both sides to the outer edge of the stator ring 2 are equal; the blades 1 connected to the rotor rings 5 ​​in two adjacent annular grooves have opposite angles of attack and opposite directions of rotation, and the rotation speeds of the blades 1 on the three rotor rings 5 ​​satisfy the following formula:

[0065]

[0066] Where i = 1, 2, 3, indicating the i-th blade 1; Q i is the resistance moment of the i-th blade 1, C Qi represents the torque coefficient of blade 1 at the i-th layer, R is the radius of blade 1, and ρ is the air density; ω i is the rotation speed of blade 1 at the i-th layer;

[0067] The resistance moment Q of blade 1 is i It will directly act on the rotor ring 5 and finally act on the stator ring 2. Therefore, the design of the reverse speed of the multi-layer blade 1 is adopted to balance the torque of the rotor ring 5 of the multi-layer blade 1 on the stator ring 2, and the following relationship is obtained:

[0068] Q1+Q3=Q2

[0069] Right now:

[0070]

[0071] Simplified, the rotation speed relationship between the three layers of blades 1 is:

[0072] C Q1 ω1 2 +C Q3 ω3 2 =C Q2 ω2 2 .

[0073] In this embodiment, an external stator is used to wrap a three-layer rotor to make the magnetic levitation rotor structure compact; the independent drive form of the three-layer rotor is beneficial to improving the load upper limit of the rotor system and limiting the "reverse twist" phenomenon, thereby providing greater lift and achieving better stability during flight.

[0074] Example 3

[0075] This embodiment is basically the same as embodiment 2, except that: Figure 2 As shown, the cooling micro-channel structure 6 includes several cooling micro-channel groups uniformly arranged in the annular direction around the stator ring 2, each cooling micro-channel group is composed of several cooling micro-channels, and the cooling micro-channel groups of two adjacent cooling micro-channel structures 6 are arranged in a staggered manner. The staggered arrangement of the cooling micro-channel groups of two adjacent cooling micro-channel structures 6 can avoid mutual influence between the cooling micro-channel structures 6, and can further enhance the heat dissipation effect.

[0076] Example 4

[0077] This embodiment is basically the same as any one of the embodiments 1-3, except that: in this embodiment, a plurality of anti-collision balls 8 are evenly arranged in the annular direction on the upper top wall and the lower bottom wall of the annular groove. The upper and lower anti-collision balls 8 are evenly distributed along the circular ring of the driving coil 3 at a spacing of 30°. The anti-collision balls 8 are not completely embedded in the stator ring 2, and a 2mm exposure is retained. The anti-collision balls 8 can rotate freely in the stator ring 2 to play a contact support role.

[0078] Example 5

[0079] This embodiment is basically the same as any one of the embodiments 1-3, except that: a distance sensor is provided between the rotor ring 5 and the stator ring 2, the distance sensor is electrically connected to a control system, and the control system is electrically connected to a high-temperature superconducting magnetic levitation module and a driving module. The high-temperature superconducting magnetic levitation module and the driving module can be controlled by the spacing data detected by the distance sensor to maintain the gap between the stator ring 2 and the rotor ring 5.

[0080] Example 6

[0081] This embodiment is basically the same as embodiment 1, except that: Figure 3As shown, a ring groove is provided on one side of the rotor ring 5, and a blade 1 is provided on the other side. The stator ring 2 is provided in the ring groove. Two adjacent stator rings 2 are connected by a connector 11. There are several connectors, and the connectors are evenly arranged between two adjacent stator rings 2. The cooling micro-channel structure 6 is provided on the side close to the blade 1, and is staggered with the blade 1 to avoid the blade 1 affecting the heat dissipation effect of the cooling micro-channel structure 6. By providing a ring groove on the rotor ring 5, the stator ring 2 is arranged in the rotor ring 5 to form a rotor-stator structure. The dewar 9 is still provided on the stator ring 2.

[0082] Example 7

[0083] An aircraft comprising a rotor system according to any one of embodiments 1-6.

[0084] The above-mentioned embodiments only express the specific implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the protection scope of the present application. It should be pointed out that, for ordinary technicians in this field, several variations and improvements can be made without departing from the technical solution concept of the present application, and these all belong to the protection scope of the present application.

Claims

1. A high temperature superconducting magnetic levitation powered rotor system, characterized in that: It comprises a stator ring (2) and a rotor ring (5), wherein a plurality of blades (1) are arranged on the rotor ring (5); A gap is provided between the stator ring (2) and the rotor ring (5), and the gap forms a cooling duct (7); A high-temperature superconducting magnetic suspension module and a driving module are provided between the stator ring (2) and the rotor ring (5); the high-temperature superconducting magnetic suspension module is used to maintain the axial and radial gaps between the stator ring (2) and the rotor ring (5); the driving module is used to drive the rotor ring (5) to rotate relative to the stator ring (2); The stator ring (2) or the rotor ring (5) is provided with a cooling microchannel structure (6) which is in communication with the cooling duct (7), and the other end of the cooling microchannel structure (6) is in communication with the outside; The stator ring (2) or the rotor ring (5) is provided with an annular groove, wherein three annular grooves are provided, and the spacing between two adjacent annular grooves is equal; the blades (1) connected to two adjacent rotor rings (5) have opposite angles of attack and opposite directions of rotation, and the rotation speeds of the blades (1) on the three rotor rings (5) satisfy the following formula: ， Where, i=1, 2, 3, represents the i-th layer of blades (1); is the resistance moment of the i-th blade (1), represents the torque coefficient of the i-th blade (1), is the radius of the blade (1), is the air density; is the rotation speed of the i-th layer of blades (1); The drag torque on the blade (1) is It will directly act on the rotor ring (5) and ultimately on the stator ring (2), so a design of multi-layer blades (1) with reverse rotation speed is adopted to balance the torque of the rotor ring (5) acting on the stator ring (2), and the following relationship is obtained: ， Right now: ， Simplified, the rotational speed relationship between the three layers of blades (1) is: 。 2. The high temperature superconducting magnetic levitation power rotor system according to claim 1, characterized in that: The stator ring (2) is provided with an annular groove, the rotor ring (5) is arranged in the annular groove, and the cooling micro-channel structure (6) is arranged on the stator ring (2).

3. The high temperature superconducting magnetic levitation power rotor system according to claim 1, characterized in that: A ring groove is provided on one side of the rotor ring (5), and a blade (1) is provided on the other side; the stator ring (2) is arranged in the ring groove; and the cooling microchannel structure (6) is arranged on the rotor ring (5).

4. The high temperature superconducting magnetic levitation power rotor system according to any one of claims 2-3, characterized in that: The rotor ring (2) is provided with a plurality of annular grooves, the number of which is equal to the number of the rotor rings (5), each of which is provided with a high-temperature superconducting magnetic suspension module, a drive module and a cooling duct (7), and a cooling microchannel structure (6) is provided at a position corresponding to each cooling duct (7) on the stator ring (2) or the rotor ring (5).

5. The high temperature superconducting magnetic levitation power rotor system according to claim 4, characterized in that: The cooling micro-channel structure (6) comprises a plurality of cooling micro-channel groups uniformly arranged in a circumferential direction around the stator ring (2) or the rotor ring (5), each cooling micro-channel group being composed of a plurality of cooling micro-channels, and the cooling micro-channel groups of the cooling micro-channel structures (6) on two adjacent stator rings (2) or two adjacent rotor rings (5) are arranged in an alternating manner.

6. The high temperature superconducting magnetic levitation power rotor system according to any one of claims 2-3, characterized in that: The high-temperature superconducting magnetic suspension module is arranged at the lower part of the rotor ring (5), and the driving module is arranged at the upper part of the rotor ring (5). The high-temperature superconducting magnetic suspension module comprises a dewar (9) or a suspended permanent magnet (10) arranged on the stator ring (2); the rotor ring (5) is provided with a suspended permanent magnet (10) matched with the dewar (9) or a dewar (9) matched with the suspended permanent magnet (10); a superconducting magnet is arranged in the dewar (9); the dewar (9) is also connected to a low-temperature liquid nitrogen container; the driving module comprises a driving permanent magnet (4) or a driving coil (3) arranged on the stator ring (2); the rotor ring (5) is provided with a driving coil (3) matched with the driving permanent magnet (4) or a driving permanent magnet (4) matched with the driving coil (3).

7. The high temperature superconducting magnetic levitation power rotor system according to any one of claims 2-3, characterized in that: A plurality of anti-collision balls (8) are evenly distributed in an annular direction on the upper top wall and the lower bottom wall of the annular groove.

8. The high temperature superconducting magnetic levitation power rotor system according to any one of claims 1 to 3, characterized in that: A distance sensor is provided between the rotor ring (5) and the stator ring (2), the distance sensor is electrically connected to a control system, and the control system is electrically connected to a high-temperature superconducting magnetic suspension module and a drive module.

9. An aircraft comprising the high-temperature superconducting magnetic levitation powered rotor system according to any one of claims 1 to 8.

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