Method for checking stress of bearing, stress checking device, electronic device and medium

Abstract

This invention provides a stress verification method, a stress verification device, an electronic device, and a computer-readable storage medium for bearings. The verification method includes: simplifying the geometry of a flexible gas turbine rotor and determining a model of the flexible gas turbine rotor based on the simplified geometry; wherein the model of the flexible gas turbine rotor has the same mass as the flexible gas turbine rotor; the model of the flexible gas turbine rotor has the same center of mass position as the flexible gas turbine rotor in the same coordinate system; the model of the flexible gas turbine rotor has the same polar moment of inertia as the flexible gas turbine rotor; the model of the flexible gas turbine rotor has the same diametrical moment of inertia as the flexible gas turbine rotor; mounting the bearing model on the model of the flexible gas turbine rotor according to the bearing's installation position on the flexible gas turbine rotor to obtain a rotor-bearing system model; and simulating the rotor-bearing system to obtain the bearing stress.

Description

Technical Field

[0001] This invention relates to the field of mechanical engineering, and in particular to a stress verification method, stress verification device, electronic device, and medium for bearings. Background Technology

[0002] Stress verification of flexible rotor bearings in gas turbines is crucial because it directly affects bearing performance and lifespan, ensures structural integrity and reliability, influences rotor dynamic characteristics and vibration control, and plays a key role in fault diagnosis and prevention. Accurate stress verification allows for the prediction and control of rotor vibration and stability, thereby improving the safety and market competitiveness of gas turbines. However, the complex structure of gas turbines makes typical verification time-consuming and inefficient. Summary of the Invention

[0003] In view of this, the present invention provides a stress verification method, a stress verification device, an electronic device, and a computer-readable storage medium for bearings.

[0004] As a first aspect of the present invention, a stress verification method for a bearing is provided, wherein the bearing is mounted on the flexible rotor of the gas turbine, forming a rotor-bearing system with the flexible rotor of the gas turbine, and the verification method includes:

[0005] The geometry of the aforementioned flexible gas turbine rotor is simplified, and a model of the flexible gas turbine rotor is determined based on the simplified geometry. Specifically, the model of the flexible gas turbine rotor has the same mass as the flexible gas turbine rotor; the model of the flexible gas turbine rotor in the same coordinate system has the same center of mass position as the flexible gas turbine rotor; the model of the flexible gas turbine rotor has the same polar moment of inertia as the flexible gas turbine rotor; and the model of the flexible gas turbine rotor has the same diametrical moment of inertia as the flexible gas turbine rotor.

[0006] Based on the installation position of the bearing on the flexible rotor of the gas turbine, the model of the bearing is installed on the model of the flexible rotor of the gas turbine to obtain the model of the rotor-bearing system.

[0007] The model of the above rotor-bearing system is simulated to directly obtain the stress of the bearing, so as to realize the stress verification of the bearing.

[0008] According to an embodiment of the present invention, after obtaining the model of the rotor-bearing system described above, and before simulating the model of the rotor-bearing system described above, the verification method further includes:

[0009] Multiple boundary conditions are applied to the model of the rotor-bearing system. These boundary conditions include temperature boundary conditions, load boundary conditions, speed boundary conditions, and aerodynamic boundary conditions. The temperature boundary conditions characterize the temperature distribution of the rotor-bearing system model. The load boundary conditions characterize the position and direction of the axial load, unbalanced load, and radial load on the rotor-bearing system model. The contact boundary conditions characterize the lubrication state of the contact interface between the rolling elements and raceways of the bearing. The speed boundary conditions characterize the speed of the rotor-bearing system model. The aerodynamic boundary conditions characterize the aerodynamic forces applied to the rotor-bearing system model.

[0010] According to an embodiment of the present invention, the above-mentioned flexible rotor of the gas turbine includes a multi-stage rotor;

[0011] The geometry of the aforementioned flexible rotor for gas turbines is simplified, including the simplification of the geometry of each stage of the rotor discs.

[0012] According to an embodiment of the present invention, the model of the above-described flexible gas turbine rotor has the same mass as the above-described flexible gas turbine rotor, including:

[0013] The model of the roulette wheel described above has the same mass as the roulette wheel described above;

[0014] The model of the aforementioned flexible gas turbine rotor has the same center of mass position as the aforementioned flexible gas turbine rotor, including:

[0015] The centroid of the roulette wheel model is the same as that of the roulette wheel described above.

[0016] The model of the aforementioned flexible gas turbine rotor has the same polar rotational inertia as the aforementioned flexible gas turbine rotor, including:

[0017] The polar moment of inertia of the above-mentioned roulette wheel model is the same as that of the above-mentioned roulette wheel.

[0018] The model of the aforementioned flexible gas turbine rotor has the same diametrical moment of inertia as the aforementioned flexible gas turbine rotor, including:

[0019] The diameter rotational inertia of the aforementioned wheel model is the same as that of the aforementioned wheel.

[0020] According to an embodiment of the present invention, the model of the roulette wheel obtained from the simplified roulette wheel is configured as a ring structure, and the ring structure includes a ring portion, a first protrusion and a second protrusion in sequence along the radial inward direction of the ring structure.

[0021] The second protrusion protrudes outward along the axial direction of the annular structure, and the first protrusion protrudes outward from the second protrusion along the axial direction.

[0022] According to an embodiment of the present invention, the quality of the above-described roulette wheel model satisfies the following condition:

[0023] The sum of the masses of the first protrusion, the second protrusion, and the annular portion is equal to the mass of the wheel model.

[0024] The sum of the static moments of the first protrusion, the second protrusion, and the annular portion relative to the reference line is equal to the static moment of the roulette wheel model relative to the reference line.

[0025] The sum of the extreme moments of inertia of the first protrusion, the second protrusion, and the annular portion about the same axis of rotation is equal to the extreme moment of inertia of the wheel about the axis of rotation, which is along the axial direction of the annular structure.

[0026] The sum of the diametrical moments of inertia of the first protrusion, the second protrusion, and the annular portion is equal to the diametrical moment of inertia of the disk model.

[0027] According to an embodiment of the present invention, simulation of a rotor-bearing system subjected to multiple boundary conditions yields the following results:

[0028] The three-dimensional dynamic stiffness matrix of the bearing, the load distribution and magnitude of the bearing rollers, the deformation of the gas turbine flexible rotor and the unbalanced response under unbalanced load, the unbalanced response characterizes the vibration state of the gas turbine flexible rotor under the action of the gas turbine flexible rotor.

[0029] As a second aspect of the present invention, a stress verification apparatus is also provided for implementing the above-described stress verification method, the verification apparatus comprising:

[0030] The simplification module is suitable for simplifying the geometry of a gas turbine flexible rotor and determining the model of the gas turbine flexible rotor based on the simplified geometry. The model of the gas turbine flexible rotor has the same mass, the same center of mass, the same polar moment of inertia, and the same diametrical moment of inertia as the gas turbine flexible rotor.

[0031] The assembly module installs the bearing model onto the gas turbine flexible rotor model according to the bearing's installation position on the gas turbine flexible rotor model, thus obtaining a rotor-bearing system model.

[0032] The simulation module is suitable for simulating rotor-bearing system models and directly obtaining bearing stress.

[0033] As a third aspect of the present invention, an electronic device is also provided, comprising:

[0034] One or more processors;

[0035] Memory, used to store one or more computer programs.

[0036] The method is characterized in that the one or more processors execute the one or more computer programs to implement the steps of the method.

[0037] As a fourth aspect of the present invention, a computer-readable storage medium is also provided, on which a computer program or instructions are stored, characterized in that the computer program or instructions, when executed by a processor, implement the steps of the above-described method. Attached Figure Description

[0038] The above and other objects, features and advantages of the present invention will become more apparent from the following description of embodiments of the invention with reference to the accompanying drawings, in which:

[0039] Figure 1 A flowchart of a stress verification method for a bearing provided according to an embodiment of the present invention is shown.

[0040] Figure 2 A schematic diagram illustrating the modeling process of a bearing according to an embodiment of the present invention is shown.

[0041] Figure 3 A model of a roulette wheel according to an embodiment of the present invention is shown.

[0042] Figure 4 A schematic diagram of a rotor-bearing model provided according to an embodiment of the present invention is shown.

[0043] Figure 5 A model of a rotor-bearing system subjected to multiple boundary conditions according to an embodiment of the present invention is shown.

[0044] Figure 6 A load distribution diagram of a cylindrical roller bearing according to an embodiment of the present invention is shown.

[0045] Figure 7 A stress distribution diagram of the inner raceway of a cylindrical ball bearing according to an embodiment of the present invention is shown.

[0046] Figure 8 A mode shape diagram of a flexible rotor according to an embodiment of the present invention is shown.

[0047] Figure 9 A block diagram of a stress verification apparatus according to an embodiment of the present invention is shown.

[0048] Figure 10 A block diagram of an electronic device suitable for implementing a stress verification method according to an embodiment of the present invention is shown. Detailed Implementation

[0049] In the process of realizing this invention, it was found that the method for modeling and strength verification of wind turbine pitch bearing connecting bolts involves using 3D drawing software to construct a 3D geometric model of the relevant components and obtain an assembly. Then, finite element preprocessing software is used to mesh and define the attributes of the assembly before establishing a finite element model for calculation and analysis. However, this verification method is time-consuming to model and requires finite element meshing and calculation, resulting in a slow and inefficient verification process.

[0050] Therefore, this invention proposes a stress verification method for bearings installed on flexible rotors of gas turbines. Through parametric modeling, a three-dimensional model can be quickly generated by inputting rotor and bearing parameters. At the same time, load spectra and operating conditions can be applied quickly, and multiple factors such as temperature, lubrication, and dynamic unbalanced loads can be applied. Moreover, the calculation process does not require finite element meshing, which greatly improves the calculation efficiency.

[0051] Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings. However, it should be understood that these descriptions are exemplary only and are not intended to limit the scope of the invention. In the following detailed description, numerous specific details are set forth to provide a thorough understanding of the embodiments of the invention for ease of explanation. However, it will be apparent that one or more embodiments may be practiced without these specific details. Furthermore, descriptions of well-known structures and techniques are omitted in the following description to avoid unnecessarily obscuring the concept of the invention.

[0052] Figure 1 A flowchart of a stress verification method for a bearing according to an embodiment of the present invention is shown. The bearing is mounted on a flexible rotor of a gas turbine (which can be simply referred to as the rotor), forming a rotor-bearing system with the flexible rotor. The stress verification method includes operations S110 to S130.

[0053] In operation S110, the geometry of the flexible gas turbine rotor is simplified, and the model of the flexible gas turbine rotor is verified based on the simplified geometry. Specifically, the model of the flexible gas turbine rotor has the same mass as the flexible gas turbine rotor; the model of the flexible gas turbine rotor in the same coordinate system has the same center of mass position as the flexible gas turbine rotor; the model of the flexible gas turbine rotor has the same polar moment of inertia as the flexible gas turbine rotor; and the model of the flexible gas turbine rotor has the same diametrical moment of inertia as the flexible gas turbine rotor.

[0054] In operation S120, the bearing model is installed on the model of the flexible gas turbine rotor according to the bearing's installation position on the flexible gas turbine rotor, thus obtaining the rotor-bearing system model.

[0055] Figure 2 A schematic diagram illustrating the modeling process of a bearing according to an embodiment of the present invention is shown.

[0056] like Figure 2 As shown, when modeling a bearing, various geometric, rolling element, assembly, and load-related parameters can be input into the modeling interface. The left area is the bearing parameter input interface, which is divided into multiple groups of parameter input items. The parameter settings for each group are as follows: Bearing external dimension parameters: Input bearing bore diameter 25.000mm, outer diameter 47.000mm, total width 8.000mm, outer ring width 8.000mm, and inner ring width 8.000mm. An input field for outer arc radius and outer fillet radius is also reserved, which can be supplemented according to the actual bearing structure. In addition, the following information can be input on the interface: Ball structure parameters: Input number of balls 12, ball pitch circle diameter 39.900mm, ball diameter 5.000mm, and ball center offset distance 0mm, corresponding to a standard non-offset deep groove ball bearing. The software automatically calculates and outputs ISO standard load data based on the entered bearing geometry, including ISO 281 rated dynamic load of 7202.8 N, ISO 76 rated static load of 4650.8 N, and ISO 281 equivalent load factor of 15.741. It sets the outer ring raceway shoulder diameter to 43.100 mm and the inner ring raceway shoulder diameter to 36.900 mm, with selectable options to set the inner and outer ring shoulder heights to suit rotor journal assembly limit requirements. After inputting all bearing parameters in the modeling interface, the program automatically generates the corresponding 3D cross-sectional model of the bearing on the right. The right-hand 3D model is a half-section structure; the dark blue parts represent the inner and outer rings, and the gold spheres represent the balls. The cross-sectional view clearly shows the mating structure of the inner and outer ring raceways and balls. The model dimensions and structure perfectly match all parameters entered on the left.

[0057] The parameterized bearing model does not require conventional preprocessing operations such as finite element geometric repair, mesh generation, and mesh quality inspection. It can be directly assembled into the equivalent rotor model according to the actual installation position of the bearing on the flexible rotor of the gas turbine to obtain the flexible rotor-bearing system model of the gas turbine, so as to carry out subsequent simulation and verify the bearing stress.

[0058] Figure 2 This invention intuitively demonstrates the parametric modeling method for bearings. By simply entering standardized parameters into the modeling interface, a bearing model can be automatically generated without the need for manual drawing of 3D entities. This simplifies the bearing modeling process, enables the rapid completion of the integrated assembly of the gas turbine flexible rotor and bearing, and provides a model foundation for bearing stress coupling simulation.

[0059] See also Figure 1 By operating S130, the model of the rotor-bearing system is simulated to directly obtain the bearing stress, so as to realize the bearing stress verification.

[0060] According to an embodiment of the present invention, the flexible rotor of a gas turbine comprises multi-stage disks, stepped shafts, and intricate auxiliary structures, resulting in a complex geometric configuration. Direct, complete modeling would generate a large number of redundant geometric features. This embodiment of the present invention, under the conditions of constant total mass, constant centroid coordinates in the same coordinate system, constant polar moment of inertia, and constant diameter moment of inertia, performs an equivalent simplified modeling of the flexible rotor of the gas turbine. The simplified model does not require conventional preprocessing work such as finite element geometric repair, mesh generation, and mesh quality checks, and can be directly used for system coupling simulation. This eliminates the need for finite element mesh solving and subsequent manual extraction of stress data, enabling rapid bearing stress verification and shortening the overall verification cycle.

[0061] According to an embodiment of the present invention, after obtaining the model of the rotor-bearing system and before simulating the model of the rotor-bearing system, the verification method further includes:

[0062] Multiple boundary conditions are applied to the rotor-bearing system model. These boundary conditions include temperature boundary conditions, load boundary conditions, speed boundary conditions, and aerodynamic boundary conditions. The temperature boundary conditions characterize the temperature distribution of the rotor-bearing system model. The load boundary conditions characterize the location and direction of the axial load, unbalanced load, and radial load on the rotor-bearing system model. The contact boundary conditions characterize the lubrication state of the contact interface between the rolling elements and raceways of the bearing. The speed boundary conditions characterize the speed of the rotor-bearing system model. The aerodynamic boundary conditions characterize the aerodynamic forces applied to the rotor-bearing system model.

[0063] Simulation of a rotor-bearing system with multiple boundary conditions can also yield: the three-dimensional dynamic stiffness matrix of the bearing, the load distribution and magnitude of the bearing rollers, the deformation of the flexible rotor of the gas turbine, and the unbalanced response under unbalanced load. The unbalanced response characterizes the vibration state of the flexible rotor of the gas turbine under the action of the flexible rotor.

[0064] According to an embodiment of the present invention, the traditional bearing stress verification method only extracts a local bearing and a small shaft segment to build a simplified model. All kinds of forces are manually applied to the bearing position before bearing stress, load and life calculation are carried out. The model is fragmented and separated from the whole machine operating environment, and cannot reflect the dynamic coupling relationship between the rotor and the bearing. The simulation conditions are far from the actual operating conditions of the unit, the calculated bearing stress values ​​are distorted, and the verification conclusions are not reliable enough.

[0065] This invention relies on a complete rotor-bearing integrated system model, loads physical parameters such as speed and aerodynamic force that can be directly measured during unit operation, and constructs a coupled simulation environment that closely resembles the actual operating state of the whole machine. It fully restores the interaction relationship between the shaft system and the bearing, so that the bearing stress and load data output by the simulation are consistent with the actual service conditions of the equipment, and greatly improves the accuracy and engineering reference value of the bearing stress verification results.

[0066] In this invention, various boundary conditions are set independently and their parameters can be adjusted individually, allowing for separate control of parameters such as temperature field magnitude, rotor speed, aerodynamic load, unbalance, axial / radial load, and lubrication film characteristics. Simulation results can distinguish the contribution percentages of temperature-induced thermal deformation, rotor unbalanced vibration, aerodynamic thrust, shaft axial force, and bearing contact lubrication friction to bearing contact stress. This facilitates engineers in identifying the core causes of excessive bearing stress and fatigue failure, providing clear directions for rotor structure, bearing selection, and lubrication scheme optimization. By inputting measured operating parameters such as unit speed, aerodynamic force, temperature, and combined loads, the internal load and contact stress of the bearing are directly solved using a complete rotor-bearing coupling model, completing bearing strength and fatigue life verification, and guiding bearing selection and structural optimization.

[0067] On the other hand, it can achieve reverse solution: by only inputting the structural parameters of the bearing itself, the six-dimensional support dynamic stiffness matrix of the bearing can be solved in reverse. This stiffness data can be used as a standard and reliable input parameter for rotor dynamics analysis and shaft vibration verification, thus opening up the data link between bearing strength verification and rotor dynamics simulation. One model can realize two types of core analysis work and expand the applicable scenarios of the method.

[0068] According to an embodiment of the present invention, the flexible rotor of the gas turbine includes a multi-stage disk; the geometry of the flexible rotor of the gas turbine is simplified, including the simplification of the geometry of each stage of the disk.

[0069] According to embodiments of the present invention, the model of the flexible gas turbine rotor has the same mass as the flexible gas turbine rotor, including: the model of the disk has the same mass as the disk. The model of the flexible gas turbine rotor has the same center of mass position as the flexible gas turbine rotor, including: the model of the disk has the same center of mass as the disk. The model of the flexible gas turbine rotor has the same polar moment of inertia as the flexible gas turbine rotor, including: the model of the disk has the same polar moment of inertia as the disk. The model of the flexible gas turbine rotor has the same diametrical moment of inertia as the flexible gas turbine rotor, including: the model of the disk has the same diametrical moment of inertia as the disk.

[0070] Existing simplification methods mostly only ensure the conservation of the total mass and moment of inertia of the rotor, allowing arbitrary distribution of the mass and inertia of individual disks. This results in discrepancies between the local stiffness, local centrifugal force, and local imbalance of each disk stage and the actual structure. This invention applies four conservation constraints to each disk stage, ensuring that the mass distribution, rotational inertia, and center of gravity of each disk stage model are completely replicated from the prototype. The centrifugal load, local flexural deformation, and local vibration response of each rotor segment are consistent with the actual rotor, eliminating the dynamic errors caused by simplification at the component level. The calculation results for bearing stress and rotor imbalance response are more accurate.

[0071] The flexible rotor of a gas turbine comprises various components such as multi-stage disks and shaft segments. This invention simplifies the overall geometry of the flexible rotor by not limiting the simplification to individual equivalents of each disk stage, but by disassembling and modeling all independent components of the rotor separately. For each independent component of the rotor (disc stages, segments, etc.), four equivalent constraints are applied: the simplified model mass of a single component equals its actual mass; the center of mass of the simplified model of a single component in the same coordinate system equals its actual center of mass; the polar moment of inertia of the simplified model of a single component equals its actual polar moment of inertia; and the diametrical moment of inertia of the simplified model of a single component equals its actual diametrical moment of inertia. After all components are independently modeled, they are assembled according to actual assembly relationships. The final overall model automatically satisfies that the total mass, center of mass, polar moment of inertia, and diametrical moment of inertia of the entire rotor are completely consistent with the actual rotor.

[0072] Figure 3 A model of a roulette wheel according to an embodiment of the present invention is shown.

[0073] like Figure 3 As shown, since this model is a simplified version of the roulette wheel's geometry, it can also be called a simplified roulette wheel model or a roulette wheel model. The simplified roulette wheel model is configured as a ring structure 200, which includes a ring portion 201, a first protrusion 202, and a second protrusion 203 sequentially along the radial inward direction of the ring structure. The second protrusion 203 protrudes outward along the axial direction of the ring structure 200, and the first protrusion 202 protrudes outward from the second protrusion 203 along the axial direction.

[0074] According to an embodiment of the present invention, the quality of the simplified roulette model satisfies the following conditions.

[0075] The first condition is that the sum of the masses of the first protrusion, the second protrusion, and the annular part is equal to the mass of the roulette wheel model, which can be expressed as equation (1).

[0076] (1).

[0077] The first condition is that the sum of the static moments of the first protrusion, the second protrusion, and the annular part relative to the reference line is equal to the static moment of the roulette wheel model relative to the reference line. This condition can be expressed as equation (2).

[0078] (2).

[0079] The first condition is that the sum of the polar moments of inertia of the first protrusion, the second protrusion, and the annular part about the same axis of rotation is equal to the polar moment of inertia of the disk about the axis of rotation, which is along the axial direction of the annular structure.

[0080] (3).

[0081] The fourth condition is that the sum of the diametrical moments of inertia of the first protrusion, the second protrusion, and the annular part is equal to the diametrical moment of inertia of the disk model.

[0082] (4).

[0083] In equations (1) to (4), l1, l2, and l3 are the axial lengths of the annular portion, the second protrusion, and the first protrusion, respectively; r1 is the inner diameter of the second protrusion; r2 is the outer diameter of the first protrusion; r3 is the outer diameter of the annular structure, which is also the outer diameter of the wheel; m1, m2, and m3 are the masses of the annular portion, the second protrusion, and the first protrusion, respectively; m is the total mass of the wheel (or a simplified model of the wheel); Oz is the distance along the axial direction between the center of mass and the reference point at the right end; Jx is the polar moment of inertia of the wheel (or the simplified model of the wheel); J... y Let be the rotational inertia of the diameter of the disk (or a simplified model of the disk).

[0084] Figure 4 A schematic diagram of a rotor-bearing model provided according to an embodiment of the present invention is shown.

[0085] like Figure 4 As shown, this rotor-bearing model can be simply referred to as the simplified rotor-bearing model.

[0086] The model is constructed according to the rules defined in the embodiments of the present invention: the flexible rotor of the gas turbine is divided into all independent components such as multi-stage disks and each section of the main shaft, and each independent component is geometrically simplified separately; the simplified model of a single component satisfies the same mass, center of mass position, polar moment of inertia, and diametrical moment of inertia as the original component, and all equivalent components are axially spliced ​​according to the actual assembly relationship to form a complete rotor-bearing simplified model.

[0087] Figure 4In the model, (0,0) is the origin of the coordinate system. The entire model is uniformly calibrated with this origin to determine the axial and radial coordinates of all shaft segments, the wheel, the model, and the three-point support points, ensuring that the centroid positions of each rotor component model and the corresponding real component are consistent in the same coordinate system.

[0088] The dimension 889.225mm is the span between the two bearing supports at the cylindrical support position of rolling bearing No. 5 (cylindrical roller bearing), which is used to characterize the assembly positioning datum of the rotor and bearing.

[0089] Figure 5 A model of a rotor-bearing system subjected to multiple boundary conditions according to an embodiment of the present invention is shown.

[0090] like Figure 5 As shown, the model is based on Figure 4 Various operational boundary conditions are fully applied to the model, intuitively demonstrating the coupled loading forms of multiple factors such as temperature, load, speed, aerodynamics, and lubrication.

[0091] Figure 5 In this model, each stage of the wheel is geometrically simplified independently. The mass, center of mass, polar moment of inertia, and diametrical moment of inertia of the single-stage wheel model are consistent with the original wheel. All the wheels and shaft segments are combined to form an equivalent flexible rotor body, which can simulate the centrifugal force and flexural deformation generated by rotation. Figure 5 The unbalanced load in the simulation is one of the load boundary conditions, which is directly applied to the corresponding position and characterizes the mass eccentricity excitation caused by the processing and assembly of the flexible rotor of the gas turbine. The simulation can calculate the rotor flexural deformation and the additional alternating stress of the bearing under the action of the unbalanced load, which can be used to evaluate the rotor vibration and bearing fatigue load. Figure 5 The bearings in the corresponding Figure 4 Rolling bearings No. 4 and No. 5 are used. The bearings can be automatically modeled using parametric methods, eliminating the need for finite element mesh preprocessing. They are assembled with the rotor model to bear all transmitted loads and output contact stresses. Speed ​​boundary conditions and power parameters are directly applied to the entire rotor-bearing system, simulating different operating speeds and power output conditions of the gas turbine. Speed ​​determines the rotor's centrifugal inertial force and vibration excitation frequency, while power is related to the overall aerodynamic load and axial thrust, which are directly measurable operating parameters of the unit. Axial load, a load boundary condition, is applied to the rotor shaft end or bearing thrust surface, characterizing the axial force generated by the gas turbine's aerodynamic thrust. It, along with radial load and unbalanced load, constitutes a composite load field.

[0092] Figure 6 A load distribution diagram of a cylindrical roller bearing according to an embodiment of the present invention is shown.

[0093] like Figure 6As shown, the horizontal axis angle (0°~330°) represents the circumferential angle position of the bearing's inner raceway (including the inner and outer raceways). Angle graduations are evenly distributed along the bearing circumference to distinguish the load-bearing state of the rollers in different orientations. The radial axis values ​​(in N) correspond to the magnitude of the normal contact load borne by the bearing rollers at each angular position. The roller load distribution curves for each circumferential angle visually present the differences in force experienced by the rollers at different positions during bearing operation.

[0094] Figure 7 A stress distribution diagram of the inner raceway of a cylindrical ball bearing according to an embodiment of the present invention is shown.

[0095] like Figure 7 As shown, the horizontal axis angular position (deg) represents the circumferential angle of the bearing's inner raceway; the vertical axis contact stress (MPa) is the contact stress value generated in the contact area between the roller and the inner raceway. The curve value range of 303~1439MPa represents the range of raceway contact stress obtained from simulation calculations, and the peak stress represents the location where the bearing is most prone to pitting and fatigue failure.

[0096] Figure 8 A mode shape diagram of a flexible rotor according to an embodiment of the present invention is shown.

[0097] like Figure 8 As shown, the mode at 984.1Hz represents the first-order natural mode of the rotor, corresponding to a natural frequency of 984.1Hz. The horizontal axis offset represents the axial coordinates of the rotor. The vertical axis displacement amplitude (range -1.0~1.0) represents the relative deformation of the rotor at each axial position, and the curve represents the bending mode shape of the rotor. The curve profile represents the flexural deformation of the rotor at this natural frequency, reflecting the resonant vibration characteristics of the flexible rotor.

[0098] As a second aspect of the present invention, a stress verification apparatus is also provided for implementing the stress verification method described above.

[0099] Figure 9 A block diagram of a stress verification apparatus according to an embodiment of the present invention is shown.

[0100] like Figure 9 As shown, the stress verification device 900 includes: a simplification module 910, an assembly module 920, and a simulation module 930.

[0101] The simplification module 910 is used to simplify the geometry of the flexible gas turbine rotor and verify the model of the flexible gas turbine rotor based on the simplified geometry. Specifically, the model of the flexible gas turbine rotor has the same mass, center of mass, polar moment of inertia, and diametrical moment of inertia as the model of the flexible gas turbine rotor. The assembly module 920 installs the bearing model onto the model of the flexible gas turbine rotor according to the bearing's mounting position, thus obtaining the rotor-bearing system model. The simulation module 930 simulates the rotor-bearing system model to directly obtain the bearing stress.

[0102] According to embodiments of the present invention, any plurality of modules among the simplification module 910, assembly module 920, and simulation module 930 can be merged into one module, or any one of these modules can be split into multiple modules. Alternatively, at least a portion of the functionality of one or more of these modules can be combined with at least a portion of the functionality of other modules and implemented in one module. According to embodiments of the present invention, at least one of the simplification module 910, assembly module 920, and simulation module 930 can be at least partially implemented as a hardware circuit, such as a field-programmable gate array (FPGA), a programmable logic array (PLA), a system-on-a-chip, a system-on-a-substrate, a system-on-package, an application-specific integrated circuit (ASIC), or any other reasonable means of integrating or packaging the circuit, or implemented in software, hardware, or firmware, or in any appropriate combination of any of these three implementation methods. Alternatively, at least one of the simplification module 910, assembly module 920, and simulation module 930 can be at least partially implemented as a computer program module, which can perform corresponding functions when the computer program module is run.

[0103] Figure 10 A block diagram of an electronic device suitable for implementing a stress verification method according to an embodiment of the present invention is shown.

[0104] like Figure 10As shown, an electronic device 1000 according to an embodiment of the present invention includes a processor 1001, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 1002 or a program loaded from a storage portion 1008 into a random access memory (RAM) 1003. The processor 1001 may include, for example, a general-purpose microprocessor (e.g., a CPU), an instruction set processor and / or an associated chipset and / or a special-purpose microprocessor (e.g., an application-specific integrated circuit (ASIC)), etc. The processor 1001 may also include onboard memory for caching purposes. The processor 1001 may include a single processing unit or multiple processing units for performing different actions of the method flow according to an embodiment of the present invention.

[0105] RAM 1003 stores various programs and data required for the operation of electronic device 1000. Processor 1001, ROM 1002, and RAM 1003 are interconnected via bus 1004. Processor 1001 executes various operations of the method flow according to embodiments of the present invention by executing programs in ROM 1002 and / or RAM 1003. It should be noted that the programs may also be stored in one or more memories other than ROM 1002 and RAM 1003. Processor 1001 may also execute various operations of the method flow according to embodiments of the present invention by executing programs stored in said one or more memories.

[0106] According to an embodiment of the present invention, the electronic device 1000 may further include an input / output (I / O) interface 1005, which is also connected to a bus 1004. The electronic device 1000 may also include one or more of the following components connected to the input / output (I / O) interface 1005: an input section 1006 including a keyboard, mouse, etc.; an output section 1007 including a cathode ray tube (CRT), liquid crystal display (LCD), etc., and a speaker, etc.; a storage section 1008 including a hard disk, etc.; and a communication section 1009 including a network interface card such as a LAN card, modem, etc. The communication section 1009 performs communication processing via a network such as the Internet. A drive 1010 is also connected to the input / output (I / O) interface 1005 as needed. A removable medium 1011, such as a disk, optical disk, magneto-optical disk, semiconductor memory, etc., is installed on the drive 1010 as needed so that computer programs read from it can be installed into the storage section 1008 as needed.

[0107] The present invention also provides a computer-readable storage medium, which may be included in the device / apparatus / system described in the above embodiments; or it may exist independently and not assembled into the device / apparatus / system. The computer-readable storage medium carries one or more programs, which, when executed, implement the method according to the embodiments of the present invention.

[0108] According to embodiments of the present invention, a computer-readable storage medium may be a non-volatile computer-readable storage medium, such as including, but not limited to: portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof. In the present invention, a computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in conjunction with an instruction execution system, apparatus, or device. For example, according to embodiments of the present invention, a computer-readable storage medium may include ROM 1002 and / or RAM 1003 and / or one or more memories other than ROM 1002 and RAM 1003 described above.

[0109] The embodiments of the present invention have been described above. However, these embodiments are merely illustrative and not intended to limit the scope of the invention. Although various embodiments have been described above, this does not mean that the measures in the various embodiments cannot be used advantageously in combination. The scope of the invention is defined by the appended claims and their equivalents. Various substitutions and modifications can be made by those skilled in the art without departing from the scope of the invention, and all such substitutions and modifications should fall within the scope of the invention.

Claims

1. A stress verification method for a bearing, wherein the bearing is mounted on a flexible rotor of a gas turbine, forming a rotor-bearing system with the flexible rotor of the gas turbine, the verification method comprising: The geometry of the gas turbine flexible rotor is simplified, and a model of the gas turbine flexible rotor is determined based on the simplified geometry. The model of the gas turbine flexible rotor has the same mass as the gas turbine flexible rotor; the model of the gas turbine flexible rotor has the same center of mass position as the gas turbine flexible rotor in the same coordinate system; the model of the gas turbine flexible rotor has the same polar moment of inertia as the gas turbine flexible rotor; and the model of the gas turbine flexible rotor has the same diametrical moment of inertia as the gas turbine flexible rotor. Based on the installation position of the bearing on the flexible rotor of the gas turbine, the model of the bearing is installed on the model of the flexible rotor of the gas turbine to obtain the model of the rotor-bearing system; The model of the rotor-bearing system is simulated to directly obtain the stress of the bearing, thereby realizing the stress verification of the bearing.

2. The stress verification method according to claim 1, characterized in that, After obtaining the model of the rotor-bearing system, and before simulating the model of the rotor-bearing system, the verification method further includes: Multiple boundary conditions are applied to the model of the rotor-bearing system. These boundary conditions include temperature boundary conditions, load boundary conditions, speed boundary conditions, and aerodynamic boundary conditions. The temperature boundary conditions characterize the temperature distribution of the rotor-bearing system model. The load boundary conditions characterize the position and direction of the axial load, unbalanced load, and radial load on the rotor-bearing system model. The contact boundary conditions characterize the lubrication state of the contact interface between the rolling elements and raceways of the bearing. The speed boundary conditions characterize the speed of the rotor-bearing system model. The aerodynamic boundary conditions characterize the aerodynamic forces applied to the rotor-bearing system model.

3. The stress verification method according to claim 1, characterized in that, The gas turbine flexible rotor includes multi-stage discs; The geometry of the flexible rotor of the gas turbine is simplified, including the simplification of the geometry of each stage of the rotor.

4. The stress verification method according to claim 3, characterized in that, The model of the flexible gas turbine rotor has the same mass as the flexible gas turbine rotor, including: The mass of the roulette wheel model is the same as the mass of the roulette wheel; The model of the flexible gas turbine rotor has the same center of mass position as the flexible gas turbine rotor, including: The center of mass of the roulette wheel model is the same as the center of mass of the roulette wheel; The model of the flexible rotor of the gas turbine has the same polar rotational inertia as the flexible rotor of the gas turbine, including: The polar moment of inertia of the roulette wheel model is the same as that of the roulette wheel. The model of the flexible rotor of the gas turbine has the same diameter moment of inertia as the flexible rotor of the gas turbine, including: The diametrical moment of inertia of the model of the wheel is the same as that of the wheel itself.

5. The stress verification method according to claim 4, characterized in that, The model of the roulette wheel obtained from the simplified roulette wheel is configured as a ring structure, which includes a ring portion, a first protrusion and a second protrusion in sequence along the radial inward direction of the ring structure; The second protrusion protrudes outward along the axial direction of the annular structure, and the first protrusion protrudes outward from the second protrusion along the axial direction.

6. The stress verification method according to claim 5, characterized in that, The quality of the roulette wheel model satisfies the following condition: The sum of the masses of the first protrusion, the second protrusion, and the annular portion is equal to the mass of the model of the roulette wheel; The sum of the static moments of the first protrusion, the second protrusion, and the annular portion relative to the reference line is equal to the static moment of the roulette wheel model relative to the reference line. The sum of the extreme moments of inertia of the first protrusion, the second protrusion, and the annular portion about the same axis of rotation is equal to the extreme moment of inertia of the wheel about the axis of rotation, which is along the axial direction of the annular structure. The sum of the diametrical moments of inertia of the first protrusion, the second protrusion, and the annular portion is equal to the diametrical moment of inertia of the disk model.

7. The stress verification method according to claim 1, characterized in that, Simulation of a rotor-bearing system with multiple boundary conditions also yields the following results: The three-dimensional dynamic stiffness matrix of the bearing, the load distribution and magnitude of the bearing rollers, the deformation of the flexible rotor of the gas turbine and the unbalanced response under unbalanced load, wherein the unbalanced response characterizes the vibration state of the flexible rotor of the gas turbine under the action of the flexible rotor of the gas turbine.

8. A stress verification device for implementing the stress verification method according to any one of claims 1 to 7, the verification device comprising: A simplification module is used to simplify the geometry of a gas turbine flexible rotor and determine the model of the gas turbine flexible rotor based on the simplified geometry. The model of the gas turbine flexible rotor has the same mass, the same center of mass, the same polar moment of inertia, and the same diametrical moment of inertia as the gas turbine flexible rotor. The assembly module installs the bearing model onto the model of the flexible gas turbine rotor according to the bearing's installation position on the flexible gas turbine rotor, thereby obtaining a rotor-bearing system model. The simulation module is suitable for simulating rotor-bearing system models and directly obtaining bearing stress.

9. An electronic device, comprising: One or more processors; Memory, used to store one or more computer programs. The characteristic feature is that the one or more processors execute the one or more computer programs to implement the steps of the method according to any one of claims 1 to 7.

10. A computer-readable storage medium having a computer program or instructions stored thereon, characterized in that, When the computer program or instructions are executed by a processor, they implement the steps of the method according to any one of claims 1 to 7.

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