A temperature distribution simulation analysis method of an air turbine starter

Abstract

The application relates to a temperature distribution simulation analysis method of an air turbine starter, which uses the temperature distribution analysis result of a magnetic gear reducer to analyze the temperature distribution of the air turbine starter and belongs to the technical field of aero-engine starting, and solves the problem of low precision and accuracy of the temperature distribution analysis of the air turbine starter in the prior art. The temperature distribution simulation analysis method considers the magnetic loss and wind friction loss of the magnetic reducer, combines the temperature rise inlet condition caused by turbine end air intake, performs single coupling, comprehensively considers the temperature distribution analysis of various influence factors, simultaneously, the influence of the air gap thickness parameter is introduced, and the accurate measurement of the internal temperature distribution analysis of the magnetic reducer of the turbine starter under complex conditions is realized.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine starting technology, specifically relating to a temperature distribution simulation analysis method for an air turbine starter, and more particularly to a temperature distribution simulation analysis method for a magnetic gear reducer based on fluid dynamics and heat transfer, using the temperature distribution analysis results of the magnetic gear reducer to perform temperature distribution analysis on the air turbine starter. Background Technology

[0002] Magnetic gear reducers are commonly used in turbine starters due to their advantages such as low vibration, low noise, and absence of mechanical friction. However, unlike the mechanical losses caused by planetary gear transmissions, magnetic gear reducers, which transmit torque via a magnetic field, also experience magnetic losses during operation. These losses are converted into heat, heating the magnetic gears and causing a temperature rise in the permanent magnet material. Simultaneously, the friction between the high-speed rotating rotor surface and the air also causes variations in the temperature distribution of the magnetic gear reducer. Since the permanent magnet material in a magnetic gear reducer is highly sensitive to temperature changes, excessively high temperatures can cause demagnetization of the permanent magnet material, significantly impacting the performance and reliability of the reducer, and consequently affecting the starter's performance.

[0003] To avoid the negative impact of high temperatures on the structure and performance of the air turbine starter, it is necessary to analyze the losses of the starter's magnetic reducer, the influence of different operating conditions on temperature distribution, and design a reasonable cooling scheme based on the analysis results. This has an important impact on improving the performance and reliability of the magnetic reducer. Summary of the Invention

[0004] In view of the above problems, the present invention provides a simulation analysis method for temperature distribution of air turbine starters, which solves the problem of low accuracy and precision in the temperature distribution analysis of magnetic gear reducers and air turbine starters in the prior art.

[0005] This invention provides a method for simulating and analyzing the temperature distribution of an air turbine starter. The air turbine starter includes a starter housing and guide assembly, a turbine, and a magnetic gear reducer. The magnetic gear reducer includes an input rotor assembly, a magnetic gear stator assembly, and an output rotor assembly. The method specifically includes the following steps:

[0006] Step 1: Obtain the structural dimensions, operating parameters, and working airflow parameters of the air turbine starter;

[0007] Step 2: Establish a three-dimensional model of the air turbine starter based on its structural dimensional parameters;

[0008] The three-dimensional model of the air turbine starter includes a three-dimensional model of the starter housing and guide, a three-dimensional model of the turbine, a three-dimensional model of the input rotor assembly structure, a three-dimensional model of the magnetic gear stator assembly structure, and a three-dimensional model of the output rotor assembly structure.

[0009] Step 3: Analyze the flow field of the turbine and the magnetic gear reducer based on the three-dimensional model of the air turbine starter;

[0010] The flow field analysis steps for the turbine are as follows:

[0011] Based on the 3D model of the starter housing and guide, and the 3D model of the turbine, the turbine flow channel region is extracted; the turbine flow channel model is obtained based on the turbine flow channel region.

[0012] Mesh the turbine flow channel model;

[0013] The simulated turbine flow field is obtained based on the well-gridped turbine flow channel model;

[0014] The flow field analysis steps for a magnetic gear reducer are as follows:

[0015] Based on the three-dimensional models of the input rotor assembly structure, the magnetic gear stator assembly structure, and the output rotor assembly structure, the flow channel region of the magnetic gear reducer is extracted; the flow channel model of the magnetic gear reducer is obtained based on the internal flow channel region of the magnetic gear reducer.

[0016] Mesh the flow channel model of the magnetic gear reducer;

[0017] The simulated flow field of the magnetic gear reducer was obtained based on the meshed flow channel model of the magnetic gear reducer.

[0018] Step 4: Obtain the magnetic loss value and windage loss value of the magnetic gear reducer;

[0019] Step 5: Analyze the temperature field of the magnetic gear reducer;

[0020] Step 51: Based on the magnetic loss value and windage loss value obtained in Step 4, obtain the heat source and heat flux density of the magnetic gear reducer.

[0021] Step 52: Import the meshed magnetic gear reducer flow channel model from Step 32 into Fluent software. Set the specific heat capacity, thermal conductivity, and density of each component in the magnetic gear reducer flow channel model, and set the equivalent thermal conductivity of the air gap. Based on the heat source and heat flux density of the magnetic gear input rotor assembly structure, magnetic gear output rotor assembly structure, and magnetic gear input rotor assembly structure obtained in Step 51, the simulated turbine flow field and simulated magnetic gear reducer flow field obtained in Step 3, and the coupled energy equation, obtain the temperature distribution results of the gear reducer.

[0022] Optionally, in step 3, the obtained simulated turbine flow field is post-processed to extract various simulation results of the turbine; the static temperature distribution and static pressure distribution of the turbine when it rotates at different operating speeds are obtained, as well as the relationship between the average static temperature change at the turbine outlet when the turbine rotates at different operating speeds.

[0023] Optionally, in step 3, the flow channel region of the magnetic gear reducer is divided into dynamic and static sections.

[0024] Optionally, in step 3, the mesh independence of the turbine flow channel model and the magnetic gear reducer flow channel model with meshed grids is verified, including the following steps: determining the initial total number of grids; gradually increasing the number of grids proportionally; if the error between two adjacent numerical solutions exceeds the maximum error threshold, increasing the number of grids; if the error between two adjacent numerical solutions is between the maximum error threshold and the minimum error threshold, obtaining the corresponding number of grids as the final number of grids for the corresponding flow channel model.

[0025] Optionally, in step 3, when obtaining the simulated turbine flow field based on the meshed turbine flow channel model, the simulation boundary conditions for the simulated turbine flow field are established as follows: the total temperature and total pressure conditions at the airflow inlet are used as the temperature inlet and pressure inlet; the total temperature and total pressure conditions at the airflow outlet are used as the temperature outlet and pressure outlet; based on the simulation boundary conditions, interfaces are set between different mesh regions of the meshed turbine flow channel model to realize the transfer of data such as pressure and temperature; the turbine speed is set; and the simulated turbine flow field is obtained using the pressure-corrected SIMPLE algorithm.

[0026] Optionally, in step 3, when obtaining the simulated flow field of the magnetic gear reducer based on the meshed magnetic gear reducer flow channel model, the simulation boundary conditions for the simulated magnetic gear reducer flow field are established as follows: the airflow velocity and airflow pressure after the turbine in the working state are used as the inlet boundary conditions of the magnetic gear reducer flow field, and the gas pressure at the airflow outlet in the working state is used as the outlet boundary conditions of the magnetic gear reducer flow field; the simulated flow fields of the input rotor assembly structure, the magnetic gear stator assembly structure, and the output rotor assembly structure are obtained based on the simulation boundary conditions.

[0027] Optionally, in step 4, the magnetic loss value of the magnetic gear reducer includes the corresponding magnetic loss values ​​obtained based on the three-dimensional models of the input rotor assembly structure, the magnetic gear stator assembly structure, and the output rotor assembly structure obtained in step 2.

[0028] Optionally, in step 4, the three-dimensional models of the input rotor assembly structure, the magnetic gear stator assembly structure, and the output rotor assembly structure are used to obtain the corresponding magnetic loss values, including the core loss value of the magnetic gear stator assembly structure, the core loss value of the input rotor assembly structure, the core loss value of the output rotor assembly structure, the eddy current loss value of the input rotor assembly structure, and the eddy current loss value of the output rotor assembly structure.

[0029] Compared with the prior art, the present invention has at least the following beneficial effects: The temperature distribution simulation analysis method of the present invention considers the magnetic loss and wind friction loss of the magnetic reducer, and combines the temperature rise inlet conditions caused by the turbine end air intake to perform single-term coupling, comprehensively consider the temperature distribution analysis of multiple influencing factors, and also introduces the influence of the air gap thickness parameter, so as to achieve accurate measurement of the internal temperature distribution analysis of the turbine starter magnetic reducer under complex conditions. Attached Figure Description

[0030] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention.

[0031] Figure 1 This is a flowchart of the temperature distribution simulation analysis method of the present invention.

[0032] Figure 2 This is a schematic diagram of airflow inside the air turbine starter chamber of the present invention. Detailed Implementation

[0033] To better understand the above-described objectives, features, and advantages of the present invention, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other. Furthermore, the present invention can be implemented in other ways different from those described herein; therefore, the scope of protection of the present invention is not limited to the specific embodiments disclosed below.

[0034] A specific embodiment of the present invention, such as Figure 1-2 A simulation analysis method for temperature distribution of an air turbine starter is disclosed. The air turbine starter includes a starter housing and guide assembly, a turbine, and a magnetic gear reducer. The magnetic gear reducer includes an input rotor assembly, a magnetic gear stator assembly, and an output rotor assembly.

[0035] The method of this invention is based on the fluid dynamics domain and heat transfer to perform temperature distribution simulation analysis on a magnetic gear reducer, and the results of the temperature distribution analysis on the magnetic gear reducer are used to perform temperature distribution analysis on an air turbine starter.

[0036] Specifically, the following steps are included:

[0037] Step 1: Obtain the structural dimensions, operating parameters, and working airflow parameters of the air turbine starter;

[0038] Step 11: Obtain the structural dimension parameters of the turbine, input rotor assembly, magnetic gear stator assembly, output rotor assembly, and starter housing and guide assembly.

[0039] Furthermore, the turbine includes a stator vane and a moving vane. The dimensional parameters of the stator vane, the structural dimensional parameters of the moving vane, and the structural dimensional information of the input rotor assembly are acquired to determine the position of the input rotor assembly in the turbine starter flow field, thus obtaining the influence of the input rotor assembly on the flow field. The structural dimensional information of the magnetic gear stator assembly is acquired to determine its position in the turbine starter flow field, thus obtaining the influence of the magnetic gear stator assembly on the flow field. The output rotor assembly includes an output rotor and an output main shaft. The structural dimensional information of the output rotor and the output main shaft is acquired to determine their positions in the turbine starter flow field, thus obtaining the influence of the output rotor assembly on the flow field. The internal structural dimensional parameters of the starter housing and guide assembly are acquired to determine the range of the flow field, the dimensional information of the airflow inlet and outlet, and the position information of the airflow inlet and outlet in the turbine starter flow field.

[0040] Step 12: Obtain the turbine operating temperature, reducer operating temperature, turbine operating speed, reducer operating speed, airflow temperature at the air inlet, and airflow temperature at the air outlet when the air turbine starter is in operation.

[0041] Step 13: Obtain the mass flow rate of the airflow at the air inlet, the airflow velocity at the air inlet, the airflow pressure at the air inlet, the airflow velocity at the air outlet, and the airflow pressure at the air outlet in the air turbine starter.

[0042] Step 2: Create a 3D model of the air turbine starter;

[0043] Based on the internal structural dimensions of the starter housing and guide assembly, a three-dimensional model of the starter housing and guide assembly is established; based on the three-dimensional model of the starter housing and guide assembly, the airflow inlet position and the size and position information of the airflow outlet are determined.

[0044] Based on the dimensions and positions of the turbine, input rotor assembly, magnetic gear stator assembly, and output rotor assembly, three-dimensional models of each assembly are established.

[0045] Step 3: Flow field analysis;

[0046] Step 31: Analyze the flow field of the turbine:

[0047] The specific steps are as follows:

[0048] Step 311: Based on the 3D model of the starter housing, guide vane, and turbine, the turbine flow channel region is extracted using Design Molder software, and the turbine flow channel region is divided into the stationary blade cascade flow channel region and the moving blade cascade flow channel region; the turbine flow channel model is obtained based on the turbine flow channel region.

[0049] Step 312: Use Hypermesh software to mesh the turbine flow channel model;

[0050] Preferably, the mesh independence of the turbine flow channel model is verified to determine the initial total number of meshes. The number of meshes is gradually increased proportionally. If the error between any two consecutive numerical solutions exceeds 10%, it is considered that the mesh has an impact on the result, and the number of meshes is further increased. If the error between two consecutive numerical solutions is between 5% and 10%, it is considered that the impact of the mesh on the result is within an acceptable range, and the corresponding number of meshes is obtained as the final number of meshes for the turbine flow channel model.

[0051] Step 313: Import the meshed turbine flow channel model into Fluent software to obtain the simulated turbine flow field;

[0052] Preferably, the simulation boundary conditions for the turbine flow field are as follows: the total temperature and total pressure conditions at the air inlet are used as the temperature inlet and pressure inlet conditions, respectively, with the total temperature of the airflow at the inlet being 450–470 K and the total pressure of the inlet airflow being 285–295 kPa; the total temperature and total pressure conditions at the air outlet are used as the temperature outlet and pressure outlet conditions, respectively, with the pressure of the airflow at the outlet being standard atmospheric pressure and the temperature of the airflow at the outlet being room temperature; based on the simulation boundary conditions, an interface is set between different grid regions of the meshed turbine flow channel model to realize the transfer of data such as pressure and temperature; the rotational speed of the moving blade cascade is set using the MRF model; and the simulated turbine flow field is obtained using the SIMPLE algorithm based on pressure correction.

[0053] Step 314: Post-process the obtained simulated turbine flow field and extract various simulation results of the turbine, such as pressure and temperature, to obtain the static temperature distribution and static pressure distribution of the turbine when it rotates at different operating speeds, as well as the relationship between the average static temperature change at the turbine outlet when the turbine rotates at different operating speeds.

[0054] Step 32: Analyze the flow field of the magnetic gear reducer;

[0055] Step 321: Based on the three-dimensional models of the input rotor assembly structure, the magnetic gear stator assembly structure, and the output rotor assembly structure, the internal flow channel region of the magnetic gear reducer is extracted using Design Molder software; the flow channel model of the magnetic gear reducer is obtained based on the internal flow channel region of the magnetic gear reducer.

[0056] Preferably, the flow channel region of the magnetic gear reducer is divided into dynamic and static sections; the flow channel model of the magnetic gear reducer is obtained based on the dynamic and static division of the internal flow channel region of the magnetic gear reducer.

[0057] It is understandable that in the flow channel region of a magnetic gear reducer, the rotating area is the moving flow channel region, and the stationary area is the stationary flow channel region.

[0058] Step 322: Use Hypermesh software to mesh the flow channel model of the magnetic gear reducer. Verify the mesh independence of the meshed magnetic gear reducer flow channel model, determine the initial total number of meshes, and gradually increase the number of meshes proportionally. If the error between any two consecutive numerical solutions exceeds 10%, it is considered that the mesh affects the result, and the number of meshes needs to be increased further. If the error between two consecutive numerical solutions is between 5% and 10%, it is considered that the influence of the mesh on the result is within an acceptable range. Obtain the corresponding number of meshes as the final number of meshes for the magnetic gear reducer flow channel model.

[0059] The meshed magnetic gear reducer flow channel model is imported into Fluent software to obtain the simulated magnetic gear reducer flow field. The simulation boundary conditions for the magnetic gear reducer flow field are as follows: the airflow velocity and airflow pressure after the turbine under working conditions are used as the inlet boundary conditions of the magnetic gear reducer flow field, and the gas pressure at the airflow outlet under working conditions is used as the outlet boundary conditions of the magnetic gear reducer flow field. Based on the simulation boundary conditions, the flow field conditions of the input rotor assembly structure, the magnetic gear stator assembly structure, and the output rotor assembly structure are obtained.

[0060] Step 4: Analyze the energy loss of the magnetic gear reducer;

[0061] The energy loss of a magnetic gear reducer includes magnetic loss and windage loss;

[0062] Based on the three-dimensional models of the input rotor assembly structure, magnetic gear stator assembly structure, and output rotor assembly structure obtained in step 2, the corresponding magnetic loss values ​​are obtained respectively.

[0063] The 3D models of the input rotor assembly, magnetic gear stator assembly, and output rotor assembly are imported into the Maxwell electromagnetics calculation platform. The corresponding material electromagnetic parameters of the rotor assembly, magnetic gear stator assembly, and output rotor assembly are input. Mesh the rotor assembly, magnetic gear stator assembly, and output rotor assembly. The rotational domain of the magnetic gear reducer is set. The magnetic loss values ​​of the magnetic gear reducer are obtained, including the core loss of the magnetic gear stator assembly, the core loss of the input rotor assembly, the core loss of the output rotor assembly, the eddy current loss of the input rotor assembly, and the eddy current loss of the output rotor assembly. Based on the 3D models of the magnetic gear stator assembly, input rotor assembly, and output rotor assembly, the corresponding core loss values ​​and eddy current loss values ​​are obtained respectively.

[0064] Preferably, the core loss of the magnetic gear stator assembly is the core loss of the magnetically adjusting stator; the core loss of the input rotor assembly is the core loss of the input rotor magnetic ring; the core loss of the output rotor assembly is the core loss of the output rotor magnetic ring; the eddy current loss of the input rotor assembly is the eddy current loss of the input rotor permanent magnet; and the eddy current loss of the output rotor assembly is the eddy current loss of the input rotor permanent magnet.

[0065] The expression for core loss is:

[0066] p Fe =p h +p e +p a

[0067] =K h fB n +K e f 2 B 2 +K a f 1.5 B 1.5 ;

[0068] Where, p Fe It is the core loss, p h It is hysteresis loss, p e It is eddy current loss, p a It is the additional loss, f is the alternating frequency of the magnetic field, B is the magnetic flux density of the alternating magnetic field, and K is the additional loss. h It is the hysteresis loss coefficient, K e It is the eddy current loss coefficient, K a is the additional loss coefficient; n is the harmonic order.

[0069] Eddy current loss p e The transformed expression is:

[0070]

[0071] Where V is the volume of the permanent magnet, b and h are the width and height of the permanent magnet, ρ is the resistivity of the permanent magnet, and B is the volume of the permanent magnet. n f is the harmonic magnetic flux density amplitude of the nth harmonic. n The relative motion frequency.

[0072] Based on the simulated flow fields of the magnetic gear stator assembly structure, input rotor assembly structure, and output rotor assembly structure obtained in step 3, the corresponding wind speed loss values ​​were obtained.

[0073] The windage loss of a magnetic gear reducer is expressed as:

[0074] P f =ω∫τdS;

[0075] Where k represents the surface roughness coefficient of the rotor; ω is the rotor angular velocity; τ is the shear stress on the wall of the stator-rotor air gap; and S is the wall area corresponding to the shear stress.

[0076] Step 5: Analyze the temperature field of the magnetic gear reducer;

[0077] Step 51: Based on the magnetic loss value and windage loss value obtained in Step 4, obtain the heat source and heat flux density of the magnetic gear input rotor assembly structure, the magnetic gear input rotor assembly structure, and the magnetic gear output rotor assembly structure.

[0078] Magnetic losses form a volumetric heat source, expressed as:

[0079]

[0080] Wind friction loss results in heat flux density, which is calculated using the following formula:

[0081]

[0082] Where S1 is the contact area between the rotor and the air.

[0083] Step 52: Import the meshed magnetic gear reducer flow channel model from Step 32 into Fluent software. Set the specific heat capacity, thermal conductivity, and density of each component in the magnetic gear reducer flow channel model, and set the equivalent thermal conductivity of the air gap. Based on the heat source and heat flux density of the magnetic gear input rotor assembly structure, magnetic gear output rotor assembly structure, and magnetic gear input rotor assembly structure obtained in Step 51, the simulated turbine flow field and simulated magnetic gear reducer flow field obtained in Step 3, and the coupled energy equation, obtain the temperature distribution results of the gear reducer.

[0084] Specifically, the meshed magnetic gear reducer flow channel model from step 32 is imported into Fluent software. The specific heat capacity, thermal conductivity, and density of the materials for the magnetic gear stator assembly, input rotor assembly, and output rotor assembly are set, as is the equivalent thermal conductivity of the air gap. The total temperature and total pressure conditions at the air outlet in the simulated turbine flow field obtained in step 32 are used as the temperature and pressure inlets for the temperature field simulation analysis. The simulated magnetic gear reducer flow field is coupled as the velocity inlet, pressure outlet, and velocity outlet for the temperature field simulation analysis. The heat source and heat flux density generated by the magnetic loss and wind friction loss of the magnetic gear obtained in step 51 are added as additional temperature inlets for the temperature field simulation analysis. Finally, the temperature field simulation analysis is performed to obtain the temperature distribution results of the gear reducer.

[0085] Temperature distribution analysis of the air turbine starter was performed using the results of temperature distribution analysis of the magnetic gear reducer.

[0086] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for simulating and analyzing the temperature distribution of an air turbine starter, the air turbine starter comprising a starter housing and guide assembly, a turbine, and a magnetic gear reducer; the magnetic gear reducer comprising an input rotor assembly, a magnetic gear stator assembly, and an output rotor assembly, characterized in that, Specifically, the following steps are included: Step 1: Obtain the structural dimensions, operating parameters, and working airflow parameters of the air turbine starter; Step 2: Establish a three-dimensional model of the air turbine starter based on its structural dimensional parameters; The three-dimensional model of the air turbine starter includes a three-dimensional model of the starter housing and guide, a three-dimensional model of the turbine, a three-dimensional model of the input rotor assembly structure, a three-dimensional model of the magnetic gear stator assembly structure, and a three-dimensional model of the output rotor assembly structure. Step 3: Analyze the flow field of the turbine and the magnetic gear reducer based on the three-dimensional model of the air turbine starter; The flow field analysis steps for the turbine are as follows: Based on the 3D model of the starter housing and guide, and the 3D model of the turbine, the turbine flow channel region is extracted; the turbine flow channel model is obtained based on the turbine flow channel region. Mesh the turbine flow channel model; The simulated turbine flow field is obtained based on the well-gridped turbine flow channel model; The flow field analysis steps for a magnetic gear reducer are as follows: Based on the three-dimensional models of the input rotor assembly structure, the magnetic gear stator assembly structure, and the output rotor assembly structure, the flow channel region of the magnetic gear reducer is extracted; the flow channel model of the magnetic gear reducer is obtained based on the internal flow channel region of the magnetic gear reducer. Mesh the flow channel model of the magnetic gear reducer; The simulated flow field of the magnetic gear reducer was obtained based on the meshed flow channel model of the magnetic gear reducer. Step 4: Obtain the magnetic loss value and windage loss value of the magnetic gear reducer; Step 5: Analyze the temperature field of the magnetic gear reducer; Step 51: Based on the magnetic loss value and windage loss value obtained in Step 4, obtain the heat source and heat flux density of the magnetic gear reducer. Step 52: Import the meshed magnetic gear reducer flow channel model from Step 32 into Fluent software. Set the specific heat capacity, thermal conductivity, and density of each component in the magnetic gear reducer flow channel model, and set the equivalent thermal conductivity of the air gap. Based on the heat source and heat flux density of the magnetic gear input rotor assembly structure, magnetic gear output rotor assembly structure, and magnetic gear input rotor assembly structure obtained in Step 51, the simulated turbine flow field and simulated magnetic gear reducer flow field obtained in Step 3, and the coupled energy equation, obtain the temperature distribution results of the gear reducer.

2. The temperature distribution simulation analysis method according to claim 1, characterized in that, In step 3, the obtained simulated turbine flow field is post-processed to extract various simulation results of the turbine; the static temperature distribution and static pressure distribution of the turbine when it rotates at different operating speeds are obtained, as well as the relationship between the average static temperature change at the turbine outlet when the turbine rotates at different operating speeds.

3. The temperature distribution simulation analysis method according to claim 1, characterized in that, In step 3, the flow channel area of ​​the magnetic gear reducer is divided into dynamic and static sections.

4. The temperature distribution simulation analysis method according to claim 1, characterized in that, In step 3, the mesh independence of the turbine flow channel model and the magnetic gear reducer flow channel model with meshed grids is verified, including the following steps: determining the initial total number of grids; gradually increasing the number of grids proportionally; if the error between two adjacent numerical solutions exceeds the maximum error threshold, increasing the number of grids; if the error between two adjacent numerical solutions is between the maximum error threshold and the minimum error threshold, obtaining the corresponding number of grids as the final number of grids for the corresponding flow channel model.

5. The temperature distribution simulation analysis method according to claim 1, characterized in that, In step 3, when obtaining the simulated turbine flow field based on the meshed turbine flow channel model, the simulation boundary conditions for the simulated turbine flow field are established as follows: the total temperature and total pressure conditions at the air inlet are used as the temperature inlet and pressure inlet conditions; the total temperature and total pressure conditions at the air outlet are used as the temperature outlet and pressure outlet conditions; based on the simulation boundary conditions, interfaces are set between different mesh regions of the meshed turbine flow channel model to realize the transfer of data such as pressure and temperature; the turbine speed is set; and the simulated turbine flow field is obtained using the pressure-corrected SIMPLE algorithm.

6. The temperature distribution simulation analysis method according to claim 1, characterized in that, In step 3, when obtaining the simulated flow field of the magnetic gear reducer based on the meshed magnetic gear reducer flow channel model, the simulation boundary conditions for the simulated magnetic gear reducer flow field are established as follows: the airflow velocity and airflow pressure after the turbine under working conditions are used as the inlet boundary conditions of the magnetic gear reducer flow field, and the gas pressure at the airflow outlet under working conditions is used as the outlet boundary conditions of the magnetic gear reducer flow field; based on the simulation boundary conditions, the simulated flow fields of the input rotor assembly structure, the magnetic gear stator assembly structure, and the output rotor assembly structure are obtained.

7. The temperature distribution simulation analysis method according to claim 1, characterized in that, In step 4, the magnetic loss value of the magnetic gear reducer is obtained by taking the corresponding magnetic loss values ​​based on the three-dimensional models of the input rotor assembly structure, the magnetic gear stator assembly structure and the output rotor assembly structure obtained in step 2.

8. The temperature distribution simulation analysis method according to claim 7, characterized in that, In step 4, the three-dimensional models of the input rotor assembly structure, the magnetic gear stator assembly structure, and the output rotor assembly structure are used to obtain the corresponding magnetic loss values, including the core loss value of the magnetic gear stator assembly structure, the core loss value of the input rotor assembly structure, the core loss value of the output rotor assembly structure, the eddy current loss value of the input rotor assembly structure, and the eddy current loss value of the output rotor assembly structure.

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