131 results about "Critical speed" patented technology

According to the bearing rigidity optimization and vibration reduction design method for the rotor and the bearing system, under the condition that the structural form of the rotor and the bearing system is not subversively adjusted, the elastic bearing and the extrusion oil film damper are arranged and designed, and the bearing rigidity of the rotor and the bearing system is optimized. The fulcrum rigidity is reduced to change the strain energy distribution of the rotor and adjust the critical rotating speed, and the vibration level of the rotor, especially vibration caused by sudden unbalance and transcritical of the multi-fulcrum rotor, is suppressed.

The invention relates to an optimization design method for a multi-fulcrum elastic ring supporting structure of an aero-engine rotor system, and belongs to the technical field of aero-engine vibration control and rotor dynamics simulation. Firstly, a finite element or lumped unit model is adopted to establish a coupling kinetic equation of a rotor and an elastic ring, and fluid-solid coupling factors such as inner and outer oil films of the elastic ring and orifice flow are considered; then, through critical rotating speed and vibration harmonic response analysis, sensitivity evaluation is carried out on rigidity and damping characteristics of different supporting positions, and target vibration reduction modes corresponding to all fulcrums are identified; then, coupling simulation and multi-objective optimization are carried out around the number of bosses of the elastic ring, the height of the bosses, the damping aperture, the thickness of a thin wall and other key structure parameters, and the optimal design meeting the vibration reduction requirement of a rotor system and the strength reliability requirement of the elastic ring is obtained through iteration; and finally, an optimization result is applied to structure manufacturing and assembling. The method can effectively reduce the vibration amplitude of the rotor when the rotor crosses the multi-order critical rotating speed.

The present invention relates to a five-degree-of-freedom ultra-high-speed bearingless permanent magnet motor. Both ends of a cylindrical solid permanent magnet are respectively connected to a rotating shaft. A casing is installed outside the cylindrical solid permanent magnet. A stator core is fixedly installed on the casing. A set of torque windings is embedded in the bottom layer of the stator core, and two sets of suspension windings are embedded in the upper layer of the stator core. End covers are fixedly installed on both sides of the casing. Auxiliary bearings are installed between the end covers and the rotating shaft. Passive permanent magnet bearings are nested on both the end covers and the rotating shaft. The present invention is reasonably designed, integrating a magnetic suspension bearing and a permanent magnet motor into one. While the motor generates an electromagnetic torque capable of driving the rotor to rotate, it can also generate a radial suspension force to overcome the rotor gravity and unilateral magnetic pull force, simplifying the motor structure and shortening the axial length of the motor. The double suspension windings and the axial passive permanent magnet magnetic bearing achieve five-degree-of-freedom control, increasing the rotor stiffness and critical speed of the ultra-high-speed motor, and improving the operation stability and anti-disturbance ability.

The invention relates to the technical field of vibration active control and artificial intelligence, and discloses an aero-engine fan rotor keyless phase virtual dynamic balance method and system based on a finite element method, and the system comprises a modeling and simulation module which is configured to obtain the first-order critical speed and vibration mode of an initial rotor dynamics simulation model; the model calibration module is configured to calibrate the initial rotor dynamics simulation model according to the first actual amplitude to obtain a calibrated rotor dynamics simulation model; the model updating module is configured to update the calibration rotor dynamics simulation model to obtain an updated rotor dynamics simulation model; and the trial weight and counterweight module is configured to substitute the second actual amplitude into particle swarm optimization, calculate the actual total unbalance amount of the rotor system and the trial weight angle difference, and finally add a counterweight and select a direction until the vibration is reduced to realize dynamic balance. According to the invention, the position of the unbalance can be accurately determined only through amplitude analysis.

The invention relates to the technical field of aero-engines, in particular to a boss structure optimization method for an elastic ring type squeeze film damper, which comprises the following steps: acquiring an oil film gap of the damper; corresponding circumferential relative oil film force and radial relative oil film force of the damper under different eccentric ratios are obtained; obtaining multiple groups of optimization parameters; constructing a constraint function and a target function; and obtaining an optimal optimization parameter, and obtaining an optimized boss structure. According to the optimization method, the influence of the boss height and the boss width on the circumferential relative oil film force and the radial relative oil film force is considered, and the purposes of improving the circumferential relative oil film force of the damper and reducing the radial relative oil film force of the damper are taken as targets, so that the optimized boss structure can increase the oil film damping, enhance the vibration reduction characteristic and reduce the oil film rigidity; and the influence of the damper additional rigidity on the critical rotating speed is weakened.

The invention relates to an air suspension high-speed centrifugal compressor applied to the technical field of centrifugal machines, and the air suspension high-speed centrifugal compressor comprises a machine body, a centrifugal rotor, a pneumatic bearing, a magnetic suspension system, an end magnetic disk, a shaft magnet, a brake magnet, a magnetic core, an arc rail groove, a brake module and a steering rib. Vector electromagnetic phase modulation is adopted by the electromagnet, active damping control and gyroscopic effect compensation of the centrifugal rotor are achieved through magnetic field vector synthesis, the centrifugal rotor is accelerated and decelerated through magnetic force, the critical rotation speed acceleration time and deceleration time of the centrifugal rotor are effectively shortened, and the hybrid magnetic locking technology is adopted in the shutdown stage of the centrifugal machine. When the centrifugal rotor is static, the brake module is triggered, magnetic pole reversal of the brake magnet is achieved through a reconstruction mechanism generated by the brake magnet, and the centrifugal rotor is in a stable magnetic attraction brake state through the cooperative magnetic attraction effect of the permanent magnet and the brake magnet.

The application discloses a kind of centrifugal pump shafting critical speed calculation method, including the finite element calculation of radial roller bearing and thrust roller bearing stiffness coefficient curve, the prestressed modal analysis and critical speed calculation of centrifugal pump shafting considering different bearing stiffness coefficient.The setting of constraint condition of this method is in line with actual situation, which can realize the accurate calculation of centrifugal pump shafting critical speed, and help to improve the reliability of safety check of centrifugal pump shafting in design stage, at the same time, the calculation steps are simple, and the engineering application range is wide.

The present invention discloses a parameter optimization design method for a tuned inertia capacitor eddy current damper, which relates to the technical field of damper design and includes the following steps: S01. Determining structural dynamic parameters; S02. Calculating a target effective damping ratio of the structure based on the structural dynamic parameters; S03. Calculating the inertia value, spring stiffness, and linear damping ratio based on the structural dynamic parameters and the target effective damping ratio; S04. Assuming a critical speed; S05. Calculating the peak damping force based on the assumed critical speed, structural dynamic parameters, and linear damping ratio; S06. Determining the conductor material and thickness of the tuned inertia capacitor eddy current damper based on the critical speed, and determining the specifications and quantity of the permanent magnets based on the peak damping force. The present invention establishes, for the first time, a parameter optimization formula for a tuned inertia capacitor eddy current damper, equating the effect of the tuned inertia capacitor eddy current damper to the effective damping ratio of the structure, making it easier for engineering designers to apply.

The invention belongs to the field of rotor design, particularly relates to a high-speed built-in permanent magnet rotor design method, system and equipment based on a stress analysis model, and aims to solve the problem that the structural strength and electromagnetic performance of a high-speed built-in permanent magnet synchronous motor rotor are difficult to collaboratively optimize in the prior art. The method comprises the steps of determining the axial length and the outer diameter of a rotor according to a motor torque demand and an assembly space, and ensuring that a critical rotating speed is higher than a target limit value through dynamic verification; decomposing the rotor into pole shoe, permanent magnet and slotting areas, calculating centrifugal force in different areas, and superposing to obtain a total load; establishing a corresponding stress boundary equation set for a non-magnetic bridge, single / combined magnetic bridge or sheath composite structure; and solving the equation set based on the target rotating speed, and synchronously optimizing the sheath thickness, the magnetic bridge width and the interference magnitude parameter by using the intersection point of the isorotation speed line and the electromagnetic-mechanical characteristic curve. The problem of contradiction between size parameters and performance in traditional design is solved, and calculation efficiency and precision are both considered.

The invention provides a gas-liquid two-phase pump jet propulsion device for an underwater navigation body, and belongs to the technical field of underwater propellers, the gas-liquid two-phase pump jet propulsion device for the underwater navigation body comprises a pump jet assembly, the pump jet assembly is installed in a propeller guide pipe, and the propeller guide pipe is fixedly installed at the rear end of a navigation body shell; the pump jet assembly comprises a paddle shaft, a front stator, a rotor and a rear stator which are sequentially installed in the fluid direction. The gas supply unit comprises a high-pressure gas storage container, the high-pressure gas storage container is communicated with a gas adjusting device through a gas filtering unit, the gas adjusting device is communicated with a gas conveying pipe, the gas conveying pipe is communicated with an annular nozzle, the annular nozzle is connected with an inner cavity of an annular mixing cavity, and the annular mixing cavity is installed in the inner cavity of the annular mixing cavity. The annular mixing cavity is located at the rear end of the pump jet assembly. By fusing the pump spraying momentum transfer principle and the gas-liquid two-phase flow control technology, the thrust can be remarkably improved, and the technical breakthrough of reducing the working noise and improving the cavitation critical speed is synchronously realized.

The invention provides a rail vehicle derailment simulation method and device, electronic equipment and a storage medium, and the method comprises the steps: obtaining a vehicle-rail system which comprises a rail vehicle model, a steel rail model and a rail plate-sleeper-fastener model; performing model verification on at least one of critical speed, operation stability index and axle box vertical vibration acceleration of the vehicle-rail system; obtaining a derailer model, wherein the derailer model comprises a base, a wedge block and a baffle plate; an acceleration sensor is arranged on a vehicle-rail system, simulation is carried out on the rail vehicle under different working conditions according to simulation configuration, simulation data under different working conditions are collected through a speed sensor, and the simulation data comprise wheel impact corresponding values and vehicle speeds; and calculating the relationship between the wheel impact corresponding value and the vehicle speed to obtain a derailment impact simulation result of the railway vehicle. The method has the beneficial effect that the simulation accuracy of the railway vehicle is improved.

This invention provides a dual-end driven long shaft system multi-order torsional vibration test platform and a torsional vibration identification and suppression method, relating to the field of long shaft system variable frequency drive technology. The platform includes two dual-winding drive motors respectively located at both ends of the shaft system, a load motor located in the middle, and a switchable shaft system connection structure, along with a dual-master, dual-slave cooperative control system composed of four drive frequency converters. This method achieves controllable excitation of multi-order torsional vibration by superimposing the load torque step and the frequency excitation source. It utilizes differential amplification and dual-channel filtering in the signal processing module to extract speed fluctuation characteristics, accurately identifying the critical speeds of each order in the system. For the identified torsional vibration phenomenon, a speed differential negative feedback algorithm is used to correct the torque command of the frequency converter, and the torsional vibration energy of the elastic transmission chain is offset by actively enhancing the system's electrical damping. This invention solves the problem of reproducing complex torsional vibration under safe and controllable conditions and verifying suppression strategies in ultra-large generator units.

The invention relates to the technical field of aero-engines, in particular to a rotor supporting structure which comprises a supporting cylinder, a worm gear, a worm and a pressing block. A plurality of strip-shaped holes are formed in the side face of the supporting cylinder, and the strip-shaped holes are distributed in the circumferential side direction of the supporting cylinder. The worm gear rotationally sleeves the supporting cylinder; the worm is meshed with the worm gear; the pressing blocks are fixedly arranged on the inner wall of the worm gear, the pressing blocks correspond to the strip-shaped holes one to one, and the pressing blocks are partially located in the corresponding strip-shaped holes; when the worm gear rotates in the circumferential direction, the pressing blocks can be driven to extrude the side walls of the corresponding strip-shaped holes so as to change the rigidity of the rotor supporting structure. According to the variable-stiffness rotor supporting structure capable of performing active control, when a modern aero-engine operates under variable working conditions, the supporting stiffness can be actively controlled under different working conditions, the effects of being away from the critical rotating speed and reducing the resonance peak value are achieved, rotor vibration response suppression is achieved, and therefore the effect of reducing vibration of the aero-engine is achieved.

The paddle comprises a round hub connected with a mandrel, a plurality of blades are fixedly connected in the circumferential direction of the round hub, the round hub comprises a round pipe, clamping pieces are fixedly connected to the two ends of the round pipe, positioning grooves are formed in the circumferential directions of the clamping pieces, the two ends of the blades are fixedly connected to the positioning grooves, and the outer diameter of the round pipe is smaller than that of the clamping pieces. According to the paddle of the film evaporator, the structure of the circular hub is changed, the overall weight of the paddle is reduced, and the critical rotating speed of the paddle is increased.

A turbomachine engine including an engine core including a high-pressure compressor, which has an exit stage having an exit stage diameter (DCORE), a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, a power turbine in flow communication with the high-pressure turbine, and a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft / sec)1 / 2 and three hundred (ft / sec)1 / 2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft / sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft. The low-pressure shaft has a length (LMSR) defined by an engine core length (LCORE) given by:LCORE=[m(20+m)*n(10+n)](1100)*DCORE+CIS.

The application discloses a multi-bearing segmented flywheel energy storage device, which comprises an upper bearing, a lower bearing, a middle bearing, a shell, a rotating shaft, a first flywheel and a second flywheel. The two flywheels are arranged on the rotating shaft, the shell is arranged outside the flywheels and the rotating shaft, the upper bearing and the lower bearing are arranged at two ends of the rotating shaft, the middle bearing is arranged on the rotating shaft between the two flywheels, and the middle bearing is arranged between the shell and the rotating shaft. The first flywheel is integrally formed with the rotating shaft, and the second flywheel is detachably connected with the rotating shaft. The application is used to solve the problem of excessive radial vibration caused by the first critical speed being too low due to the large axial span of the flywheel. The flywheel body with large thickness is divided into two parts, which is beneficial to the uniformity of the heat treatment of the flywheel body. The radial strength of the rotating shaft of the flywheel body is improved by additionally arranging a bearing between the two flywheel bodies. In order to facilitate the installation of the bearing at the middle position of the flywheel, the segmented flywheel rotating shaft and the matched shell are designed.

A flexible drive shaft (10) for transmitting torque from a motor (4) to a high-speed rotor (2), particularly for a laboratory centrifuge (1), wherein the material of the drive shaft (10) has a defined yield strength and a defined modulus of elasticity. To create a new drive unit, for example for a laboratory centrifuge, that retains the necessary flexibility at critical speeds but exhibits higher strength with respect to bending stresses, it is proposed that a material be used for the drive shaft (10) in which the yield strength of the material is expressed in N / mm². 2 divided by the material's modulus of elasticity in N / mm 2 takes on a value > 0.0045.

The present invention discloses a load compressor configuration, comprising: a rotor assembly, and a first bearing casing and an air intake casing relatively spaced apart and installed on the outer circles at both ends of the rotor assembly. The power input end of the rotor assembly is supported on the first bearing casing through a front bearing, and the power output end of the rotor assembly is supported on the air intake casing through a rear bearing to form an independent rotor support structure. The power input end of the rotor assembly can also be detachably connected to the upstream power input system, and the power output end of the rotor assembly can also be detachably connected to the downstream power output system to ensure the input and output of the load compressor power. The present invention can form an independent rotor system, ensure an independent unit design, and then can be quickly adapted to auxiliary power units of different models and powers, with a wide range of adaptability; the rotor assembly has a short fulcrum span and strong rigidity, ensuring that the rotor system has sufficient critical speed margin.

A turbomachine engine including an engine core including a high-pressure compressor, which has an exit stage having an exit stage diameter (DCORE), a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, a power turbine in flow communication with the high-pressure turbine, and a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft / sec)1 / 2 and three hundred (ft / sec)1 / 2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft / sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft. The low-pressure shaft has a length (LMSR) defined by an engine core length (LCORE) given by:LCORE=[m  (20+m)*n  (10+n)](1100)*DCORE+CIS.

The invention belongs to the field of engine design, and particularly relates to an aero-engine whole machine dynamic structure design parameter optimization method, which utilizes an APDL language of ANSYS software to carry out parametric modeling on an aero-engine whole machine (including a rotor, a support and a stator casing), and applies additional centrifugal force and additional gyroscopic moment generated by maneuvering flight. The stress level of the bearing case, the strain energy distribution of a rotor system and the rotor and stator gap change are obtained through bearing case stress analysis, critical speed analysis and unbalanced response analysis. Based on the analysis results, multi-objective optimization is carried out on complete machine dynamic design parameters, so that the stress level of a force bearing casing is lowest, rotor strain energy distribution meets rotor dynamic design requirements, rotor and stator gap changes are minimum, the rub-impact risk is reduced, optimization of the structural design parameters is completed through software, the design efficiency is improved, and the design cost is reduced. The design period is shortened.

The application discloses a robot friction parameter identification method and device, a terminal and a medium. The method comprises the following steps: acquiring a dynamic speed threshold of a robot joint; identifying a static friction coefficient, a coulomb friction coefficient and a critical speed in a low-speed section where the speed of the robot joint is lower than the dynamic speed threshold; and identifying a viscous friction coefficient in a medium-high speed section where the speed of the robot joint is higher than the dynamic speed threshold, in combination with the obtained static friction coefficient, the coulomb friction coefficient and the critical speed. The application has the advantage that higher-precision robot friction parameters can be obtained, thereby facilitating the construction of a high-precision robot friction model.

The present invention provides a variable frequency compressor. The intermediate plate is provided with a lower exhaust refrigerant passage hole, a groove, a first hole, a rotary valve, a guide vane, a spring hole, an elastic element and a push head; the lower exhaust refrigerant passage hole communicates with the refrigerant passage hole on the first cylinder; the groove is arranged on the first end surface of the intermediate plate, and the groove penetrates the first end surface but does not penetrate the second end surface; the first hole communicates with the second position of the inner cavity of the first cylinder; the rotary valve is rotatable in the first hole; the rotation of the rotary valve is used to control the notch to be in the communication position or the closed position; the guide vane is inclined and installed on the rotary valve; the thrust of the push head on the rotary valve drives the notch to communicate with the second position. When the rotational speed of the variable frequency compressor is less than the critical speed, the variable frequency compressor is in the small capacity mode, the motor speed is relatively high, the efficiency is high, the oil return efficiency of the pump body is high and the overall vibration is reduced; when the rotational speed of the variable frequency compressor is greater than the critical speed, the variable frequency compressor is in the full capacity mode.

The embodiment of the invention provides an aero-engine rotor bending critical rotating speed adjusting method based on a modal shape, and relates to the field of aero-engine high-pressure rotors. The objective of the invention is to improve the problems of complex process and high cost of engine rotor bending critical speed adjustment by changing elastic support rigidity and rotor structure parameters. Comprising the steps that the bending critical rotating speed of the engine rotor is adjusted by adjusting the local mass of a deformation sensitive area of the engine rotor; wherein the deformation sensitive area refers to an area with the maximum bending mode deformation. The bending critical rotation speed of the engine rotor is controllably adjusted by adjusting the mass in a deformation sensitive area of the engine rotor, the bending critical rotation speed can be simply and efficiently adjusted and subjected to test verification through the adjusting mode, and the bending critical rotation speed design margin of the engine can be conveniently obtained.

This invention discloses a turbine testing apparatus, belonging to the technical field of turbine testing equipment. This apparatus uses a limiting unit between mounting bases. Within the limiting unit, a first directional limiting component and a second directional limiting component are mounted via a bracket. The first directional limiting component limits the connecting lug from a first direction, and the second directional limiting component limits the connecting lug from a second direction. This achieves limiting of the turbine test piece from both directions. After the turbine test piece is installed, the first and second directions are perpendicular to the axial direction of the turbine test piece. By limiting the turbine test piece from the second direction, radial vibration of the turbine test piece can be effectively restricted, reducing vibration during testing, increasing the rotor's critical speed, ensuring successful test completion, and reducing the impact of vibration on measurement results. This ensures accurate final measurement results, provides accurate and effective test data for turbine design, reduces wear on the turbine testing apparatus, lowers maintenance costs, and reduces testing risks.

The present application discloses a method, apparatus, device, and medium for determining boundary conditions at an aircraft engine inlet, relating to the field of fluid mechanics. The method comprises: during computational fluid dynamics numerical simulation of an aircraft, collecting air flow rates from each grid surface at the engine inlet boundary to determine the current actual flow rate at the engine inlet; determining a critical specific flow density based on stagnation point information in the current flow field, and determining a target velocity for the grid surface based on the critical specific flow density, target flow rate, and current actual flow rate; determining the local static pressure of the grid surface based on the critical velocity and target velocity, determining whether the gas flow corresponding to each grid surface is supersonic, and determining a target pressure value for the grid surface based on the judgment result and the local static pressure; and determining target density and target velocity component information for the grid surface based on the body center value of the flow field unit to determine the target boundary conditions. The present application can efficiently and accurately determine the boundary conditions of an aircraft engine inlet and improve robustness.

The application discloses an aero-engine rotor and a checking method and checking device for a supporting assembly of the aero-engine rotor, and comprises the following steps: S1: sequentially acquiring a starting typical curve of the aero-engine rotor and rotor vibration mutation time t, and simultaneously acquiring total starting times n during the service life of the aero-engine; S2: installing the aero-engine rotor on the checking device through the rotor supporting assembly, carrying out a debugging test based on the starting typical curve, and acquiring an actual critical speed range of the aero-engine rotor; S3: adjusting the starting typical curve based on the rotor vibration mutation time t and the actual critical speed range to obtain a starting typical adjustment curve; S4: starting the aero-engine to the slow-speed state according to the starting typical adjustment curve, parking the aero-engine, and repeating the process at least n times; and S5: disassembling and checking the aero-engine rotor and the rotor supporting assembly, and judging whether the over-critical performance of the aero-engine rotor and the rotor supporting assembly meets the requirements according to the checking result.

This invention provides a technology that can suppress vibrations of the rotating shaft supported by a magnetic bearing. [Solution] A controller 700 according to one embodiment of the present disclosure includes a coil 412 that generates an electromagnetic force that attracts or repels a rotating shaft 250, and controls the output voltage from the power conversion circuit 460 to the coil 412 by operating a power conversion circuit 460 that outputs power to the coil 412 for a radial magnetic bearing 400 that supports the rotating shaft 250 in a non-contact manner. Specifically, the controller 700 includes an integral element in the transfer function from the current detection value of the coil 412 to the voltage command value Vc1, the amplitude of the open-loop transfer function including the current detection value of the coil 412 has attenuation characteristics in the frequency band above the critical speed of the rotating body RT including the rotating shaft 250, and the phase of the open-loop transfer function including the position detection value of the rotating shaft 250 is in the range of -90 degrees or more and 90 degrees or less at the critical speed of the rotating body RT.

Provided is a technology that can suppress vibration of a rotary shaft to be supported by a magnetic bearing. A controller 700 according to one embodiment of the present disclosure comprises a coil 412 for generating an electromagnetic force that attracts or repels a rotary shaft 250 and, with respect to a radial magnetic bearing 400 for supporting the rotary shaft 250 in a non-contact manner, controls an output voltage from a power conversion circuit 460 to the coil 412 by operating the power conversion circuit 460 that outputs power to the coil 412. Specifically, the controller 700 includes an integral element in a transfer function from a current detection value of the coil 412 to a voltage command value Vc1. The amplitude of an open-loop transfer function including the current detection value of the coil 412 has an attenuation characteristic in a frequency band equal to or higher than a critical speed of a rotor RT including the rotary shaft 250. The phase of the open-loop transfer function including a position detection value of the rotary shaft 250 is in the range of -90 to 90 degrees at the critical speed of the rotor RT.

The utility model provides a check ring rotating assembly which comprises a shaft and a check ring. A groove surrounding the outer wall of the shaft is formed in the end part of the shaft; the check ring is a split ring and is installed in the groove, and in the initial state, the outer circle of the check ring is located on the inner side of the groove or flush with a port of the groove. When the rotating speed of the shaft is larger than the critical rotating speed of unfolding of the check ring, the open end of the check ring is opened, so that the outer circle of the check ring protrudes out of the groove to form an effective dynamic blocking face. The invisible effect of the check ring in the non-working state is achieved, and later overhaul and maintenance of components installed on the inner side of the check ring are facilitated.

The present application provides an active three-degree-of-freedom magnetic bearing and its control method, motor and compressor. The active three-degree-of-freedom magnetic bearing includes a bearing rotor, including a rotor ring body on which a rotating shaft is mounted; a bearing stator, including a first bearing stator assembly and a second bearing stator assembly; the first bearing stator assembly applies a radial magnetic field to the rotor ring body to adjust the radial position of the rotor ring body; the second bearing stator assembly applies an axial magnetic field to the rotor ring body to adjust the axial position of the rotor ring body. The present application sets corresponding bearing stators in the radial and axial directions of the bearing rotor, with a high degree of integration, so that there is no need to assemble a thrust plate separately on the rotating shaft, the structure is more compact, the process is simplified, the bearing volume is effectively reduced, the rotating shaft length is shortened, the critical speed of the rotor is increased, and the operating stability of the magnetic suspension system is improved.