96 results about "Rotordynamics" patented technology

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 invention belongs to the technical field of simulation analysis, and particularly relates to an electric spindle multi-physics field coupling simulation method. The motorized spindle multi-physics field coupling simulation method comprises the following steps that S100, a multi-physics field coupling model is established through finite element software, wherein the steps of geometric model importing, material setting, rotor dynamics module setting, solid heat transfer module setting and grid division are included; and S200, solving through the finite element software: carrying out multi-physics field coupling on the bearing nonlinear restoring force model, the motor unbalanced magnetic pulling force model and the main shaft thermal model with the motorized main shaft rotor model, and solving to obtain the dynamic performance. By using the simulation model for motorized spindle dynamic characteristic research in the technical scheme, the dynamic characteristic research requirement of the motorized spindle under the actual complex working condition can be met.

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 discloses a circumferential pull rod rotor test bench and method. The circumferential pull rod rotor test bench comprises a grooved platform, a driving motor, a load device and a circumferential pull rod rotor, wherein the driving motor and the load device are mounted on the grooved platform; the circumferential pull rod rotor comprises a plurality of gas compressor wheel discs, a plurality of turbine wheel discs and an intermediate shaft; a plurality of gas compressor pull rod bolts penetrate through the gas compressor wheel disc, and the gas compressor wheel disc is connected in a pre-tightening manner through the gas compressor pull rod nuts; a plurality of turbine pull rod bolts penetrate through the turbine wheel disc, and the turbine wheel disc is connected in a pre-tightening mode through turbine pull rod nuts. The test bed further comprises a gas compressor casing and a turbine casing, and the gas compressor casing and the turbine casing are both installed on the grooved platform and are adjustable in position. Dynamic characteristics and various rotor faults of the circumferential pull rod rotor of the gas turbine can be effectively simulated, and the test bench is reliable in structure and stable in operation.

This invention relates to the field of aero-engine maintenance engineering and quality assessment technology, and discloses an aero-engine overhaul assessment method based on a physical information Bayesian neural network. The method includes collecting multi-source heterogeneous data from maintenance and testing sites and converting it into key process indicator scores; extracting rotor dynamics, imbalance transmission, and empirical formula features to construct physical constraint regularization terms; establishing an initial Bayesian neural network containing deterministic and variational Bayesian layers; inputting the key process indicator scores into the network, and optimizing parameters by combining the physical constraint regularization terms with adaptive annealing and early stop mechanisms; performing multiple Monte Carlo samplings on the trained network to calculate the mean distribution of the output results and obtain distribution statistical characteristics; calculating the quality score, confidence interval, and attribution warning information based on the distribution statistical characteristics, and outputting an overhaul assessment report. This invention solves the problem that existing pure data models violate physical laws and cannot quantify confidence levels.

According to the thermal power plant equipment fault early warning method provided by the invention, the array type vibration sensor group and the infrared thermal imaging matrix are deployed to construct the three-dimensional space-time sensing network, and the independent component analysis algorithm is adopted to carry out edge denoising processing, so that the fault feature extraction accuracy under a complex working condition is improved, and the fault early warning efficiency is improved. According to the method, geometric coordinate mapping, rotor dynamics simulation and real-time data indexing are fused based on an equipment digital twinning model, part-level positioning of bearing faults is achieved, twinning derivative parameters are injected through a transfer learning mechanism to predict target equipment, the fault missing report rate of the equipment is reduced, and a safe-economical-sustainable triple gain closed loop is formed.

The application belongs to the technical field of simulation analysis, and particularly relates to a multi-physical field coupling simulation method of an electric spindle. The multi-physical field coupling simulation method of the electric spindle comprises the following steps: S100, a multi-physical field coupling model is established through finite element software, including: importing a geometric model, setting a material, setting a rotor dynamics module, setting a solid heat transfer module and mesh division; S200, solving is performed through the finite element software, including: performing multi-physical field coupling of a bearing nonlinear restoring force model, a motor unbalanced magnetic pull model and a spindle thermal model with the electric spindle rotor model, and obtaining dynamic performance by solving. The simulation model for the dynamic characteristic research of the electric spindle in the technical scheme can meet the demand of the dynamic characteristic research of the electric spindle under actual complex working conditions.

The application provides a magnetic suspension mixed three-degree-of-freedom bearing and an air compressor, wherein the bearing comprises a radial magnetic bearing assembly and an axial magnetic bearing assembly, a permanent magnet capable of providing a bias magnetic field is clamped between the radial magnetic bearing assembly and the axial magnetic bearing assembly, the axial magnetic bearing assembly comprises a first axial stator core and a second axial stator core, the first axial stator core has a first magnetic ring, the radial thickness of the first magnetic ring is la, the second axial stator core has a second magnetic ring, the radial thickness of the second magnetic ring is le, and la < le. The application increases the radial thickness of the side with smaller axial output, thereby improving the axial output of the second axial stator core, making the structures of the first axial stator core and the second axial stator core asymmetric, achieving axial force balance design without increasing the overall volume of the bearing, meeting the axial load demand, and thereby improving the rotor dynamics characteristics.

The application discloses a kind of based on multiple type signal dry vacuum pump working state intelligent diagnosis method and system, specifically related to vacuum pump monitoring technical field, by synchronous acquisition encoder pulse and vibration acceleration signal, equal-angle resampling establishes angular domain sequence, by pulse interval calculation instantaneous angular velocity and angular acceleration and combined with moment of inertia to obtain actual inertia moment, based on screw profile and ideal compression model generates theoretical aerodynamic load moment and difference integration obtains leakage flux index, corrects rotor dynamics aerodynamic term and iteratively inverts unbalance eccentricity, exports health status and fault grade.The application adopts angular domain alignment to make criterion consistent under speed fluctuation and working condition change, constructs leakage flux index by difference integration of aerodynamic load and inertia moment, and iteratively inverts physical unbalance eccentricity with residual error, so that leakage and unbalance have distinguishable physical quantity representation, improve evaluation consistency and traceability.

The invention discloses a gas foil bearing wear high-fidelity modeling method based on a physical neural network, and relates to the technical field of rotor dynamics and fault diagnosis. The method comprises the following steps: firstly, constructing physical models of gas foil bearing wear, wherein the physical models comprise a gas foil bearing structure and lubrication mechanism model and a gas bearing rotor system nonlinear dynamic model; and then building a hybrid modeling framework fusing a physical mechanism and data driving, training a model mismatch item by adopting a neural network, representing an unknown parameter by adopting a Sigmoid function, introducing a displacement compensation factor, and finishing model parameter updating by combining forward calculation and reverse calculation. According to the method, high-fidelity modeling of wear evolution and key parameter collaborative identification can be realized, the model adaptability and the data matching precision under complex working conditions are improved, and technical support is provided for a gas bearing digital twin system and predictive maintenance.

This application belongs to the field of engine modeling technology, specifically relating to a simplified modeling method and apparatus for the dynamics of an interstage elastic support structure in an engine. The method includes: determining the equivalent density of the elastic shaft segment using an equal-volume equivalence method based on the dimensional parameters of the elastic shaft segment of the elastic support structure; determining the equivalent elastic modulus of the elastic shaft segment based on the radial stiffness attenuation coefficient of the elastic support structure; equivalence the elastic shaft segment using equivalent beam elements according to the dimensional parameters of the elastic shaft segment of the elastic support structure, and assigning equivalent density and equivalent elastic modulus parameters to the equivalent beam elements; and establishing a coupling relationship between the established equivalent beam element model and the overall engine dynamics model to complete the establishment of the overall engine rotor dynamics model. This application establishes an equivalent beam element model for circumferentially discontinuous shaft segments suitable for rotor dynamics analysis, ensuring the accuracy of the overall engine rotor dynamics analysis and the rationality of the rotor dynamics structure optimization design direction.

The application discloses a large-length-diameter-ratio rotor structure with a separated turbine, comprising a four-stage fan, a two-stage front turbine, a single-stage rear turbine, four bearing supporting points, a connecting structure and the like. A 1-2-1 four supporting point supporting scheme is adopted, and an intermediate supporting point is additionally arranged at the front turbine to control the bending deformation of the large-length-diameter-ratio rotor. Meanwhile, the two-stage front turbine in the middle section of the rotor is designed as an integrated ring cavity structure, the structure angular rigidity is enhanced, and the overall gyroscopic moment effect is exerted. The front turbine and the rear turbine are connected with the rotor shaft through a large-space double-centering-face stop mouth-toothed sleeve connection, the bending moment bearing capacity is improved, the gyroscopic moment of the wheel disc is fully applied to the shaft section, the rotor resonance speed safety margin is improved, and the bending deformation is controlled. The application is the first rotor structure proposed for a new engine with an inter-stage combustion chamber, and meets the dynamic design requirements of the rotor with the characteristics of the multi-stage separated turbine and the large-length-diameter ratio.

The invention relates to the field of nuclear main pump testing, in particular to a method and a device for testing rigidity and damping of a turbine guide bearing of rotating machinery of a nuclear power plant. According to the method, cold-state gap measurement, static measurement and hot gap measurement are carried out; performing dynamic measurement; based on parameters measured by the sensor, the rigidity and damping of the water lubricated bearing are solved through a rotor dynamic balance equation; constructing a liquid film fluid calculation model of the experiment table water guide bearing, substituting the measured pressure data into the calculation model to obtain axial and circumferential pressure distribution curves of a liquid film of a cylinder of the water guide bearing, and obtaining liquid film forces of the water guide bearing in different states; and comparing the rigidity and damping obtained by the dynamic balance equation of the rotor with the rigidity and damping obtained by the calculation model, eliminating the rigidity and damping with the deviation greater than 5% between the two methods under the same working condition, and averaging the residual values to obtain the final damping and rigidity. The method is high in measurement precision and convenient in measurement.

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 present application relates to an imbalance control method for an electromagnetic bearing rotor system based on the DDPG algorithm, comprising the following steps: establishing a rotor dynamics equation based on rotor dynamics and performing decoupling control; constructing a compensation current, extracting the imbalance coefficient from the compensation current and constructing an adaptive identification equation; constructing a DDPG agent, integrating position error, system response, and control output, and designing a multi-objective reward function through a normalized weighted optimization strategy; using the DDPG agent to optimize the imbalance coefficient identification parameters, dynamically adjusting the compensation current in combination with the rotor speed to offset the unbalanced force disturbance. The present invention identifies the imbalance coefficient reflected at both ends of the rotor by the unbalanced force exerted on the rotor in combination with the deep reinforcement learning algorithm DDPG, thereby improving the identification of the imbalance coefficient and the efficiency of imbalance compensation, and achieving rapid, stable, and efficient compensation of the rotor system.

This invention relates to a dynamic balancing method for a flexible rotor system in an engine, belonging to the technical field of mechanical rotor dynamic balancing. It is applicable to the dynamic balancing of low-pressure rotors or power turbine rotors in turbofan engines when using flexible rotors. The turbofan engine includes a compressor blade disk and a hollow connecting long shaft. The dynamic balancing method includes: S1, inspection of the manufacturing process; S2, dynamic balancing tests on the connecting long shaft and blade disk respectively; S3, assembly and testing of the connecting long shaft and blade disk bearing the first identification on the test bench of the dynamic balancing device according to design requirements; S4, checking whether the dynamic indicators meet the standards; S5, full-range speed vibration testing of the connecting long shaft and blade disk as a whole on the platform of a rotor dynamics experimental apparatus; and S6, verification of the repeatability of assembly parameters and dynamic balancing, thus improving the efficiency of dynamic balancing.

The present invention relates to the field of compressors and bleed air flow path design thereof, and discloses an adaptive bleed air adjustment structure and design method for a multi-operating-condition radial clearance of a compressor. The structure utilizes the pressure change of the compressor rear stage at different compressor speeds to adaptively adjust the bleed air valve position, thereby adaptively adjusting the bleed air flow in a first bleed air cavity at different speeds to heat the compressor disc cavity without the need for pilot operation. The bleed air structure is simple and has little effect on the dynamic characteristics of the compressor rotor. In addition, an analytical model between the control cavity pressure and the speed is constructed to determine the valve control cavity pressure corresponding to different speeds. Under the condition of considering the valve structural parameters, the valve opening timing is controlled and it is ensured that the valve is fully opened at a preset speed, thereby achieving heating of the compressor disc cavity with a maximum bleed air flow through the first bleed air channel at the preset speed.

The invention belongs to the technical field of rotor dynamics, and discloses a blade tip clearance rapid prediction method in a maneuvering flight state. Additional load excitation and additional parametric excitation caused by maneuvering flight are derived based on the beam unit and the concentrated mass. A finite element model of the birotor-bladed disc-cartridge receiver coupling system is established based on a beam-shell hybrid model, additional load excitation and additional parameter excitation caused by maneuvering flight are fused, the finite element model of the birotor-bladed disc-cartridge receiver coupling system in a maneuvering flight state is finally established, and gaps of blade tips are calculated through a numerical integration method. A blade tip gap prediction model is constructed based on an artificial neural network, model training is completed based on a numerical calculation result serving as a training set, and finally rapid gap prediction under different working conditions is achieved. According to the method, the influence of centrifugal deformation of the blade, vibration displacement of the rotor, maneuvering flight deformation and other factors on the blade tip clearance is effectively considered, the morphology of the complex blade is comprehensively considered, and the model generalization ability is high.

The application relates to the technical field of rotor dynamics test, and discloses a device for simulating a misalignment fault of a support point of a rotor system and a foundation loading device. Misalignment loading modules are arranged at the bottoms of each support point bearing of a test rotor, and the first driving unit and the second driving unit of each misalignment loading module are used to realize misalignment or displacement loading of the support point bearing position of the test rotor. Through coordination of the positions of the three driving units, independent control of the support point bearing of the test rotor in three degrees of freedom can be realized, and horizontal direction offset misalignment, vertical direction offset misalignment and overturning direction misalignment of the support point bearing can be realized at the same time. In addition, displacement or rotation angle excitation can be controlled in the three misalignment directions, and a hardware foundation is provided for dynamics test of a rotor system in a real environment.

This application belongs to the field of aero-engine simulation technology, and relates to a method and apparatus for simulating the overall pulsation characteristics of a rotating detonation turbine engine. The method includes: obtaining the given total pressure pulsation characteristics of the rotating detonation combustor; calculating the total outlet pressure of the rotating detonation combustor at the current simulation moment; inputting the total outlet pressure of the rotating detonation combustor into a pre-constructed overall performance model of the turbojet engine in transition state. The overall performance model is formed by coupling various engine components through aerodynamic parameter interfaces in the order of airflow, considering rotor dynamics and volume effects during coupling; solving for independent engine variables and the characteristics of each component under the constraints of overall engine matching conditions of flow balance and power balance until the residuals converge; extracting the total inlet pressure of the rotating detonation combustor and calculating the characteristics of each engine component at the next simulation moment. This application realizes the simulation of the unsteady coupling characteristics of the rotating detonation combustor and the turbojet engine.

The present invention belongs to the technical field of aero-engine vibration control and rotor dynamics simulation, and specifically relates to a method for simulating the rotational inertia excitation response of a multi-row bolted rotor of an aero-engine, which mainly includes: establishing a nonlinear contact model of the rotor; defining mass eccentricity and inertia principal axis tilt in key rotor components, thereby simultaneously applying lateral unbalanced forces and angular inertia moments; using time-domain integration and Newton-Raphson iteration to determine and update the interface conversion between static friction and dynamic friction and the amount of irreversible slip; and finally accurately predicting the dynamic response of the rotor at high speeds, especially in the supercritical range. By coupling the discontinuous characteristics of the interface with the rotational inertia excitation, the present invention can capture the phenomenon of the rotor vibration amplitude continuously increasing, reveal the additional imbalance accumulation mechanism caused by interface looseness or wear, and improve the evaluation accuracy of the aero-engine rotor safety margin and vibration control strategy.

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

This invention discloses a pulse-based vibration reduction control method for the demagnetized rotor of a permanent magnet direct-drive wind turbine, comprising the following steps: based on rotor dynamics theory, the unbalanced magnetic pull generated by the demagnetization of the permanent magnet direct-drive wind turbine is decomposed into terms related to the eccentricity state of the rotor system and fault disturbance terms, thus constructing the dynamic equations of the permanent magnet direct-drive wind turbine rotor system; a pulse control scheme is designed; the terms related to the eccentricity state of the rotor system are linearized using the Lipschitz condition, and the fault disturbance terms are analyzed and processed by constructing peak-to-peak gain; sufficient conditions for the pulse control scheme are derived based on Lyapunov stability theory; and the effectiveness of the designed pulse control scheme is verified through numerical simulation. This invention realizes the analysis and processing of the unbalanced magnetic pull generated by the demagnetization of a permanent magnet direct-drive wind turbine, providing a foundation for the design of a demagnetization vibration controller for permanent magnet direct-drive wind turbines.

The invention belongs to the technical field of rotor dynamics, and discloses a gas turbine multi-disc rotor imbalance fault diagnosis method and a related device. The method comprises the following steps: extracting a feature vector based on acquired abnormal vibration data; on the basis of the feature vectors, a rotor unbalance fault diagnosis model is used for identifying and positioning a fault source, and a multi-disc rotor unbalance fault online identification and tracing result is obtained; the rotor imbalance fault diagnosis model is composed of a low-fidelity model network and a high-fidelity model network, and the low-fidelity model network is used for predicting a low-fidelity result under the condition of given input data after training. And the high-fidelity model network is used for acquiring a high-fidelity prediction result by learning a mapping relationship between the low-fidelity output result and the high-fidelity output result. According to the invention, accurate identification and online traceability of the unbalance fault parameters of the multi-disc rotor are realized.

The invention relates to a rotor system integrated topological optimization design method considering dynamic performance, and belongs to the technical field of high-performance calculation science, and the method comprises the following steps: taking statics and rotor dynamics as constraint conditions for a rotor two-dimensional structure, carrying out two-dimensional topological optimization design, and obtaining a new rotor two-dimensional structure; and on the basis of the new two-dimensional structure of the rotor, three-dimensional topological optimization design is carried out on the sector model of the rotor by taking the rotation period structure frequency and the statics property as constraint conditions, and a new three-dimensional configuration is obtained. According to the method, on the basis of traditional topological optimization which only considers the static performance, the constraint on the dynamic performance is increased, the dynamic performance requirement needed by the rotor system can be met while the maximum rigidity design is completed, the design period can be effectively shortened, and the design efficiency can be effectively improved.

This invention belongs to the field of aero-engine vibration control and rotor dynamics simulation technology, specifically involving a rapid analysis method for the mechanical properties of the rotor-elastic ring oil film in aero-engines. It establishes the rotor-elastic ring coupled dynamic equations; by discretizing the elastic ring using shell elements, deformation features are extracted in polar coordinates; and the inner and outer oil films are modeled in the fluid domain using the Reynolds equation and the orifice throttling equation, thus accurately characterizing the nonlinear dynamics of the oil film under multi-protrusion and porous structures. Based on modal mapping, the normal velocity of the elastic ring wall is projected onto the oil film equation to iteratively solve for the oil film pressure. The pressure is then reflected back to the rotor-elastic ring coupled system to update its displacement field until convergence. This invention efficiently screens and optimizes structural parameters such as the number of protrusions, oil film thickness, and orifice size over a wide speed range, thereby improving the vibration reduction performance and design efficiency of the aero-engine rotor support system.

The present invention discloses a method for designing the robustness of the connection stiffness of a rigid sleeve gear coupling of an engine tie rod rotor and its application, which is used for the dynamic optimization design of a three-point supported slender center tie rod rotor structure in an aircraft engine or a gas turbine. The present invention optimizes the position and structure of the coupling by establishing a finite element model for rotor dynamics analysis, calculating and analyzing the critical speed and strain energy density distribution of the rotor, and combining static and dynamic strength requirements. The method includes the steps of optimizing the fulcrum stiffness and rotor structural parameters, analyzing the positioning reliability of the coupling locating stop, moving the coupling to a low strain energy density and low stress area, and iterative verification and optimization. The present invention improves the robustness of the coupling connection stiffness, optimizes the rotor dynamics performance, and reduces the risk of rotor vibration by optimizing the coupling position and structure. It can be directly applied to the engineering design of aircraft engines and gas turbines and has important engineering application value.

This invention provides a method for tolerance analysis of the inlet ring clearance of a nuclear power plant main pump. By taking the clearance between the main pump impeller inlet ring and the suction duct as the optimization target and constructing a dimensional chain, and combining 3D modeling and tolerance analysis software, the method achieves precise definition of assembly relationships and tolerance parameters. At the same time, it introduces rotor dynamics deflection deformation calculation and conditional assembly logic, which can truly reflect the tolerance accumulation law of the main pump under 3D assembly and operating conditions. This significantly improves the accuracy and reliability of clearance tolerance analysis, effectively avoids the risk of rotor rubbing during operation, reduces testing and assembly costs, and thus ensures the long-term safe and stable operation of the nuclear power plant main pump.

The invention relates to a simulation method for evaluating the dynamics of a rotor of a magnetic suspension blower, which is applied to the field of electronic digital data processing, and comprises the steps of S1, constructing a model, S2, carrying out finite element equivalence, S3, carrying out three-dimensional static simulation, S4, carrying out dynamic modal simulation, S5, carrying out predictive maintenance simulation and S6, completing design. The method can effectively simplify the structure of the integrated rotor of the high-speed permanent magnet motor of the magnetic suspension blower, greatly reduces the time cost of grid processing and calculation, and greatly reduces the calculation difficulty of the electromagnetic coupling field of the integrated rotor of the high-speed permanent magnet motor of the magnetic suspension blower. The maintainability of the high-speed permanent magnet motor integrated rotor of the subsequent magnetic suspension air blower in the actual application process and the operation safety guarantee effect after maintenance can be effectively guaranteed by utilizing a predictive verification mode after fault maintenance in different scenes; and an efficient and feasible scheme is provided for the design of the integrated rotor of the high-speed permanent magnet motor of the magnetic suspension blower.

The invention relates to a high-speed bearing structure matching design method driven by a bearing digital twin model. The method comprises the following steps that S1, structure parameters meeting the bearing capacity, the service life and the reliability of a main bearing are designed according to constraint conditions; s2, combining the structure size according to the structure size type, predicting vibration, rotation precision, power consumption and rigidity in combination with bearing-rotor dynamics, and realizing correlation of structure-dynamics-performance; and S3, according to the performance demand priority, determining a priority combination sequence of various types of structure sizes. The experiment cost can be remarkably reduced, and the experiment period can be shortened. According to the high-speed bearing structure matching design method driven by the bearing digital twin model, the bearing vibration, rotation precision, power consumption and rigidity can be predicted according to the bearing rotor dynamical model to match and design the structural size of the angular contact ball bearing, the cost can be effectively reduced, and the experimental period is shortened.