Gas turbine rolling bearing dynamic stress calculation method and device, medium and product

Abstract

To provide a technique that can accurately calculate the dynamic stress of a gas turbine rolling bearing under an impact load working condition.SOLUTION: The method comprises the steps of: calculating the impact acceleration borne by a gas turbine rolling bearing according to a working condition curve of the impact load working condition where the gas turbine rolling bearing is located; calculating to obtain a total load actual value based on the impact acceleration; taking the initial pressure distribution as input, and calculating pressure distribution and shear stress distribution by using an oil film thickness equation, a Reynolds equation and a non-Newtonian fluid model under the constraint of the total load actual value; and calculating according to the pressure distribution and the shear stress distribution to obtain the stress distribution of the contact surface and the subsurface of the rolling body and the inner ring in the gas turbine rolling bearing. Then considering the bearing lubrication condition in the stress calculation process under the impact load working condition, the dynamic stress of the gas turbine rolling bearing under the impact load working condition can be accurately calculated.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The present invention relates to the field of stress calculation technology, and more particularly to a method, device, medium and product for calculating three-dimensional dynamic stress in a rolling bearing for a gas turbine under impact load. [Background technology]

[0002] During operation, rolling bearings for gas turbines undergo cyclic contact with the roller conveyor. This causes cyclic contact stresses on the bearing rings (including the inner and outer rings), which reduces the material's fatigue performance and significantly impacts the bearing's accuracy, performance, and lifespan. The bearing contact condition and stress distribution are important factors in assessing the bearing's operating state and lifespan. Most existing stress analysis models are designed for land and aerospace applications, with relatively few applications in the marine sector. The marine working environment is significantly different from that in other fields, and typical operating conditions, including frequent transient changes, must be considered. However, existing stress analysis models are analyzed under dry contact or steady-state operating conditions, ignoring the effects of sea wave impact during actual ship operation.

[0003] Based on this, there is an urgent need for a technique that can accurately calculate the dynamic stresses in rolling bearings for gas turbines under shock load operating conditions. Summary of the Invention [Problem to be solved by the invention]

[0004] An object of the present invention is to provide a method, device, medium, and product for calculating dynamic stress in a rolling bearing for a gas turbine, which can accurately calculate the dynamic stress in the rolling bearing for a gas turbine under impact load operating conditions. [Means for solving the problem]

[0005] In order to achieve the above object, the present invention provides the following solutions.

[0006] A dynamic stress calculation method for a rolling bearing for a gas turbine, comprising: calculating an impact acceleration received by the gas turbine rolling bearing according to an operating condition curve of an impact load operating condition of the gas turbine rolling bearing, and calculating an actual value of the total load based on the impact acceleration, wherein the operating condition curve is a curve of change in acceleration of the impact load that changes over time; using an initial pressure distribution as an input to perform iterative calculations using an oil film thickness equation and a Renaud equation to obtain an oil film thickness distribution and a pressure distribution; calculating and obtaining a total load calculated value according to the pressure distribution; determining whether the calculated total load value is equal to the actual total load value; if not, using the pressure distribution as an initial pressure distribution, returning to the step of "using the initial pressure distribution as an input to perform iterative calculations using an oil film thickness equation and a Renaud equation to obtain an oil film thickness distribution and a pressure distribution", the oil film thickness distribution includes the oil film thickness at each position point in a calculation domain of the gas turbine rolling bearing, and the pressure distribution includes the pressure at each position point in the calculation domain of the gas turbine rolling bearing, the calculation domain including the contact surface between the rolling element and the inner ring of the gas turbine rolling bearing; calculating a shear stress distribution using a non-Newtonian fluid model with the oil film thickness distribution and the pressure distribution as inputs, the shear stress distribution including shear stresses at each position point in a calculation domain of the gas turbine rolling bearing; and calculating and obtaining stress distributions on the contact surfaces and sub-surfaces between the rolling elements and the inner ring in the rolling bearing for a gas turbine according to the pressure distribution and the shear stress distribution.

[0007] The computer device includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the dynamic stress calculation method for a rolling bearing for a gas turbine.

[0008] A computer-readable storage medium has a computer program stored therein, which, when executed by a processor, implements the steps of the dynamic stress calculation method for a rolling bearing for a gas turbine.

[0009] A computer program product includes a computer program, which, when executed by a processor, implements the steps of the dynamic stress calculation method for a rolling bearing for a gas turbine. [Effects of the Invention]

[0010] According to the specific embodiments provided by the present invention, the present invention discloses the following technical effects.

[0011] The present invention discloses a method, device, medium and product for calculating dynamic stress of a rolling bearing for a gas turbine, which calculates the impact acceleration experienced by the rolling bearing for a gas turbine according to the operating condition curve of the rolling bearing for a shock load operating condition of the gas turbine, calculates the actual value of the total load based on the impact acceleration, and uses the initial pressure distribution as input to calculate the pressure distribution and shear stress distribution using the oil film thickness equation, the Renaud equation and a non-Newtonian fluid model under the constraint of the actual value of the total load, and further calculates the stress distribution on the contact surface and sub-surface between the rolling element and the inner ring in the rolling bearing for a gas turbine according to the pressure distribution and shear stress distribution, and takes the lubrication condition of the bearing into consideration during the stress calculation under impact load operating conditions, thereby making it possible to accurately calculate the dynamic stress of the rolling bearing for a gas turbine under impact load operating conditions. [Brief explanation of the drawings]

[0012] In order to more clearly describe the embodiments of the present invention or the technical solutions in the prior art, the drawings that need to be used in the embodiments will be briefly described below. Obviously, the drawings in the following description are only some embodiments of the present invention, and those skilled in the art can obtain other drawings based on these drawings without creative efforts.

[0013] [Figure 1] 1 is a method flowchart of a dynamic stress calculation method for a rolling bearing for a gas turbine provided in accordance with a first embodiment of the present invention; [Figure 2] 2A and 2B are schematic diagrams showing the change trends of the dimensionless impact load distribution and the maximum stress distribution of the inner roller conveyor when the initial load operating condition provided by Example 1 of the present invention is 5000 N. Here, Fig. 2A shows the dimensionless impact load distribution, and Fig. 2B shows the maximum stress distribution of the inner roller conveyor. [Figure 3] 3A and 3B are three-dimensional cloud images of the bearing surface and sub-surface stress distribution in the xoy plane under load-impact conditions provided by Example 1 of the present invention, where Fig. 3A is a three-dimensional cloud image of the steady-state loading stage with 625 calculation steps, Fig. 3B is a three-dimensional cloud image of the loading detonation stage with 1250 calculation steps, Fig. 3C is a three-dimensional cloud image of the linear regression stage with 1563 calculation steps, and Fig. 3D is a three-dimensional cloud image of the bubble pulsation peak value stage with 3438 calculation steps. [Figure 4] 4A and 4B are three-dimensional cloud images of the bearing surface and sub-surface stress distribution in the xoz plane under load-impact conditions provided by Example 1 of the present invention, where Fig. 4A is a three-dimensional cloud image of the steady-state load stage with 625 calculation steps, Fig. 4B is a three-dimensional cloud image of the load-detonation stage with 1250 calculation steps, Fig. 4C is a three-dimensional cloud image of the linear regression stage with 1563 calculation steps, and Fig. 4D is a three-dimensional cloud image of the bubble pulsation peak value stage with 3438 calculation steps. [Figure 5] 5A and 5B are three-dimensional cloud images of the bearing surface and sub-surface stress distribution in the yoz plane under load impact conditions provided by Example 1 of the present invention, where Fig. 5A is a three-dimensional cloud image of the steady-state load stage with 625 calculation steps, Fig. 5B is a three-dimensional cloud image of the load detonation stage with 1250 calculation steps, Fig. 5C is a three-dimensional cloud image of the linear regression stage with 1563 calculation steps, and Fig. 5D is a three-dimensional cloud image of the bubble pulsation peak value stage with 3438 calculation steps. [Figure 6] 6A and 6B are three-dimensional cloud images of the bearing surface and sub-surface stress distribution in the xoy plane under load-impact conditions provided by Example 1 of the present invention, where Fig. 6A is a three-dimensional cloud image of 5000N, Fig. 6B is a three-dimensional cloud image of 7000N, and Fig. 6C is a three-dimensional cloud image of 9000N. DETAILED DESCRIPTION OF THE INVENTION

[0014] The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, any other embodiments obtained by those skilled in the art without any creative efforts fall within the scope of protection of the present invention.

[0015] Example 1 As shown in FIG. 1, the dynamic stress calculation method for a rolling bearing for a gas turbine according to this embodiment includes the following:

[0016] S1: Calculate the impact acceleration received by the gas turbine rolling bearing according to an operating condition curve of the impact load operating condition of the gas turbine rolling bearing, and calculate an actual value of the total load based on the impact acceleration, where the operating condition curve is a curve of change in the acceleration of the impact load that changes over time.

[0017] In this embodiment, first, an impact load equation is constructed, and then the impact load equation is solved according to the operating conditions to obtain the impact acceleration.

[0018] The waveform of the actual impact load during construction is very complex. In order to facilitate analysis and because the load at the peak value stage of the subsequent bubble pulsation also affects the hull, this embodiment refers to the empirical formula in the warship specification BV043 / 85 given by the German Federal Ministry of Defense and performs an approximation process to construct an impact load equation.

[0019] Considering that the acceleration operating condition of the rolling bearing for gas turbines is such that the rising stage of the shock wave part curve is regarded as a step signal, the first half of the falling stage is approximately linear, and the latter half is an exponential decay curve, the empirical formula is

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[0020] It was considered that the peak load value in the first bubble pulsation cycle is 10-20% of the peak load value of the shock wave, and that the peak load value in the second bubble pulsation cycle is attenuated to 80-90% of the peak load value in the first bubble pulsation cycle. To facilitate analysis, the waveform of each bubble pulsation cycle was simplified to an ideal half-sine wave, and the expression for the shock load (i.e., the shock load equation) was

number

[0021] Equation (2) is the calculation formula for impact acceleration used in this embodiment. After obtaining the operating status of the bearing (i.e., the operating status curve) through on-site inspection, the acceleration peak value and duration can be determined, and then the impact acceleration at each time can be calculated by substituting Equation (2).

[0022] Calculating the actual value of the total load based on the impact acceleration specifically includes calculating the actual value of the total load using Newton's second law with the impact acceleration as an input, that is, the actual value of the total load is equal to the product of the weight of the gas turbine rolling bearing and the impact acceleration.

[0023] S2: Using the initial pressure distribution as input, perform iterative calculations using the oil film thickness equation and the Renaud equation to obtain an oil film thickness distribution and a pressure distribution, calculate and obtain a total load calculation value according to the pressure distribution, and determine whether the calculated total load value is equal to the actual total load value; if not, use the pressure distribution as the initial pressure distribution, and return to the step of "using the initial pressure distribution as input, perform iterative calculations using the oil film thickness equation and the Renaud equation to obtain an oil film thickness distribution and a pressure distribution", where the oil film thickness distribution includes the oil film thickness at each position point in the calculation domain of the gas turbine rolling bearing, and the pressure distribution includes the pressure at each position point in the calculation domain of the gas turbine rolling bearing, and the calculation domain includes the contact surfaces of the rolling elements and the inner ring of the gas turbine rolling bearing.

[0024] In this embodiment, the initial pressure distribution is calculated according to an empirical formula, and the initial oil film thickness is the same at each position in the calculation domain, i.e., the initial oil film thickness distribution is obtained. The initial oil film thickness distribution is then substituted into the Renault equation to obtain the initial pressure distribution.

[0025] The empirical formula for calculating the initial oil film thickness is

number

[0026] After obtaining the initial pressure distribution, the initial pressure distribution is used as input to perform iterative calculations using the oil film thickness equation and the Renault equation to obtain the oil film thickness distribution and pressure distribution, and the total load calculation value is calculated according to the pressure distribution to determine whether the calculated total load value is equal to the actual total load value. If so, the iteration is terminated and S3 is executed; if not, the iteration is continued and the pressure distribution is used as the initial pressure distribution, and the process returns to the step of "using the initial pressure distribution as input to perform iterative calculations using the oil film thickness equation and the Renault equation to obtain the oil film thickness distribution and pressure distribution".

[0027] Here, calculating and obtaining the calculated total load value according to the pressure distribution specifically includes integrating the pressure change within the entire calculation domain (e.g., an elliptical domain) to obtain the calculated total load value as follows:

number

[0028] In this embodiment, the initial pressure distribution is used as an input, and the oil film thickness equation and the Renault equation are used to perform iterative calculations to obtain the oil film thickness distribution and the pressure distribution, which specifically includes the following:

[0029] (1) The initial pressure distribution is taken as input and the intermediate oil film thickness distribution is calculated using the oil film thickness equation. Taking into consideration the influence of the transient radius of curvature and elastic deformation during bearing operation, the oil film thickness equation used in this example is:

number

[0030]

number

[0031] After obtaining the initial pressure distribution, the pressure at each position in the calculation domain is determined and substituted into equation (6) to calculate the elastic deformation at each position, which is then substituted into equation (5) to calculate the oil film at each position. The oil film thickness at all positions constitutes the intermediate oil film thickness distribution.

[0032] (2) The intermediate oil film thickness distribution was obtained by calculating the intermediate pressure distribution using the Renault equation as input.

[0033] In this embodiment, the Renault equation is used to solve the pressure distribution of the elastohydrodynamic lubrication oil film between the rolling elements and the inner roller conveyor under impact conditions, and the constructed Renault equation (i.e., the transient state Renault equation expression) is

number

[0034] When the pressure applied to the lubricating oil film changes, the force between the oil film molecules and the distance between the molecules change, so the viscosity and density of the oil film also change accordingly. In this embodiment, the viscosity and density of the oil film are regarded as pressure-related parameters, and the specific calculation formula is

number

[0035]

number

[0036] The boundary conditions for solving the Renaud equation are

number

[0037] In the Renault equation, only the pressure is unknown, and the oil film thickness at each location is determined according to the intermediate oil film thickness distribution, which is then substituted into equation (7) and combined with the boundary condition of equation (10). The pressure at each location is calculated using a sequential encryption method, and the pressure at all locations constitutes the intermediate pressure distribution. Using a sequential encryption method can improve calculation efficiency, and of course, other methods can also be used to solve this embodiment.

[0038] (3) Determine whether the condition for ending the iteration is reached, and if so, take the intermediate oil film thickness distribution as the oil film thickness distribution, and the intermediate pressure distribution as the pressure distribution; if not, take the intermediate pressure distribution as the initial pressure distribution for the next iteration, and return to the step of "using the initial pressure distribution as input to calculate and obtain the intermediate oil film thickness distribution using the oil film thickness equation."

[0039] In this embodiment, the condition for ending the iteration is that the error in the intermediate pressure distribution obtained in two adjacent iterative calculations is less than a predetermined error, and at this point, the pressure distribution is considered to have converged, and the iteration is ended.

[0040] Here, the error calculation formula is

number

[0041] The given error is 10 -3 In this case, the iteration error err between two adjacent iterations of the oil film pressure may be 10 -3 If it is equal to or less than 1, it is judged as convergence, the iteration is terminated, and the oil film thickness distribution and pressure distribution are obtained.

[0042] S3: Using the oil film thickness distribution and the pressure distribution as inputs, calculate the shear stress distribution using a non-Newtonian fluid model, where the shear stress distribution includes the shear stress at each position point in the calculation domain of the gas turbine rolling bearing.

[0043] Bearing friction under elastohydrodynamic lubrication conditions is mainly caused by fluid shear friction. The friction force in the fluid lubrication region is calculated using the viscoelastic Bair-Winer non-Newtonian fluid rheology model. The non-Newtonian fluid model used in this example is

number

[0044]

number

[0045] G ∞ and τ L depends on the rheological properties of the lubricating oil and is a function of pressure and temperature. Since the lubricating oil used in this example belongs to a typical mineral oil, G is calculated using the Dyson empirical formula. ∞ and τ L can be estimated as shown below,

number

[0046]

number

number

[0047] S4: The stress distribution on the contact surface and sub-surface between the rolling element and the inner ring in the rolling bearing for a gas turbine is calculated and obtained according to the pressure distribution and the shear stress distribution.

[0048] In this embodiment, the stress distribution on the contact surface and sub-surface between the rolling element and the inner ring in the rolling bearing for a gas turbine calculated according to the pressure distribution and shear stress distribution specifically includes the following:

[0049] (1) A plurality of stress components are calculated at each three-dimensional point in the solution domain of the rolling bearing for a gas turbine according to the pressure distribution and shear stress distribution, and the solution domain includes the contact surface and sub-surface between the rolling element and the inner ring in the rolling bearing for a gas turbine.

[0050] According to the KL Johnson theory, the unit normal force p(x,y) and the unit tangential force q x (x,y), q y When (x, y) simultaneously act on the surface of a semi-infinite body, the stress components at each three-dimensional point can be given by the following equation:

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[0051]

number

number

number

number

number

number

[0052] Calculate using the above formulas (18) to (23) TIFF2025168145000047.tif1043 is obtained, and then the pressure distribution and shear stress distribution can be obtained by taking Equation (17) as input to calculate multiple stress components at each three-dimensional point in the solution domain of the gas turbine rolling bearing.

[0053] (2) For each three-dimensional point, determine the first principal stress, the second principal stress, and the third principal stress of the three-dimensional point based on a plurality of stress components, and calculate and obtain the stress of the three-dimensional point based on the first principal stress, the second principal stress, and the third principal stress of the three-dimensional point, where the stress includes an equivalent stress and a maximum shear stress.

[0054] Multiple stress components (i.e., σ xx , σ xy , σ xz , σ yy , σ zz , σ yz ) are sorted in order from largest to smallest, and the first stress component is selected as the first principal stress, the second stress component is selected as the second principal stress, and the third stress component is selected as the third principal stress. Taking into consideration that the shear force and pressure are generated between the bearings due to the influence of the impact load, the first principal stress σ1, second principal stress σ2, and third principal stress σ3 of each three-dimensional point inside the bearing can be obtained by solving the problem.

[0055] Equivalent stress σ of the rolling element and inner roller conveyor νm (using Von Mises stress)

number

number

[0056] In this embodiment, the typical load excitation of a rolling bearing for a gas turbine and the influence of an underwater shock load environment are comprehensively considered. The surface and sub-surface stress excitation sources are divided into two parts: surface normal compressive stress and surface tangent shear stress. These are obtained by the bearing elastohydrodynamic lubrication analysis (i.e., the oil film thickness equation, the Renault equation, and the non-Newtonian fluid model). Combined with the surface and sub-surface stress analysis model (i.e., the equation in S4), the three-dimensional dynamic stress of the bearing contact surface and sub-surface under shock load conditions can be accurately predicted, and the accuracy of the predicted contact surface and sub-surface stress distribution can be effectively improved.

[0057] In order to deeply reveal the variation rules of the bearing contact surface and subsurface under mixed lubrication conditions under impact operating conditions, the stress field distribution of rolling bearings under different load operating conditions was studied.

[0058] This example mainly compares the effects of impact load on bearing surface and subsurface stress under four different load operating conditions, where the load operating conditions are w = 5000N, w = 7000N, w = 9000N, and w = 11000N, respectively. The calculation parameters are as shown in Table 1: spiral speed is 3m / s, slide-to-roll ratio is 0.2 (where the speed of the rolling element is 3.3m / s, and the rotation speed of the inner roller conveyor is 2.7m / s).

[0059] Table 1 Parameters used in bearing stress analysis calculations TIFF2025168145000050.tif90152

[0060] Figure 2 shows the change trends of the dimensionless impact load distribution and the maximum stress distribution of the inner roller conveyor when the initial load operating condition is 5000 N. From Figure 2, the maximum stress of the surface and subsurface corresponding to the steady-state load stage is 684 MPa. When the calculation step reaches 1250, which is the load impact stage (i.e., the load detonation stage), the maximum stress corresponding to the inner roller conveyor is 936 MPa, a 36.8% increase from the steady-state load stage. When the calculation step is from 1250 to 1563, it is the linear decay stage, during which the maximum stress decreased by 8.5%. When the calculation step is from 1563 to 2813, it is the rapid exponential decay stage (i.e., the bubble pulsation peak value stage), during which the maximum stress decreased by 21%. It can be seen that the effect of the first bubble pulsation on bearing stress is weaker than that of the load detonation stage, with the maximum stress in this stage increasing by only 6.4%.

[0061] Figure 3 shows the three-dimensional stress distribution in the x-oy plane at different load impact stages when the initial load is 5000N. Figure 3(a) shows the length of the calculation domain in the x direction, and (b) shows the length of the calculation domain in the y direction. Figure 3 shows the significant impact of load impact on the bearing surface and subsurface stress. Figure 3(a)-(d) show the stress change process from load impact to unloading. During the detonation stage, the stress peak value and the area of ​​the high stress region increase significantly compared to the steady-state loading stage. By the unloading process, the stress region decreases and gradually returns to the steady-state pattern.

[0062] Figure 4 shows the three-dimensional stress distribution in the xoz plane at different load impact stages when the initial load operating condition is 5000N. The detonation stage of the load generates surface stress that increases beyond the peak stress value generated in the steady-state load stage and is simultaneously applied to deeper layers. Taking a load of w=5000N as an example, during the steady-state load stage (625 calculation steps), the maximum stress occurs at z=0.73a. When the detonation stage is reached, the maximum stress occurs at z=0.96a. After the first part of the linear unloading process is completed, the linear decay stage (1563 calculation steps) is reached, where the maximum stress occurs at z=0.83a. The impact load gradually shifts the maximum sub-surface stress to the sub-surface.

[0063] Figure 5 shows the three-dimensional stress distribution on the yoz plane at different load impact stages when the initial load is 5000N. The variation of sub-surface stress on the yoz plane is the same as on the xoz plane. At the same time, the maximum stress on the bearing on the yoz plane is 11.4% lower than on the xoz plane, which is consistent with the trend in existing literature. The maximum surface stress in the direction of higher curvature decreases, and on the yoz plane, the bearing is subjected to impact loads, and the high-stress area increases accordingly.

[0064] Figure 6 shows the stress distribution of the inner roller conveyor under different initial load conditions during the detonation load stage. Figure 6 shows three different initial load operating conditions. As the initial load increases, the peak stress value between the bearing contact surfaces increases accordingly. At the same time, the actual stress generation area expands in the x direction. When the load w=5000N, the width of the high stress area is 0.8a. As the load increases to 7000N and 9000N operating conditions, the corresponding width increases to 0.6a and 0.83a.

[0065] In this embodiment, for the typical operating conditions of a gas turbine bearing, a three-dimensional dynamic stress analysis model of the bearing surface and sub-surface under impact load was established, and the three-dimensional dynamic stress distribution characteristics of the bearing surface and sub-surface under load and impact conditions were studied. The sub-surface stress distribution of the bearing under several sets of different initial load operating conditions was compared, and it was found that the sub-surface stress during the load detonation stage increased significantly, and at the same time, the area and depth of the high stress region also increased.

[0066] Example 2 A computer device includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to realize the steps of the dynamic stress calculation method for a rolling bearing for a gas turbine described in Example 1.

[0067] Example 3 A computer-readable storage medium having a computer program stored therein, the computer program implementing the steps of the dynamic stress calculation method for a rolling bearing for a gas turbine described in Example 1 when executed by a processor.

[0068] Example 4 A computer program product includes a computer program that, when executed by a processor, implements the steps of the dynamic stress calculation method for a rolling bearing for a gas turbine described in Example 1.

[0069] The technical features of the above embodiments can be combined in any way, and for the sake of brevity, not all possible combinations of the technical features in the above embodiments are described, but as long as there is no contradiction in the combinations of these technical features, all should be considered within the scope described in this specification.

[0070] In this specification, specific examples are used to explain the principles and embodiments of the present invention, and the description of the above examples is only useful for understanding the method of the present invention and its core idea, and at the same time, those skilled in the art will be able to change the form for implementing the invention and the scope of application according to the idea of ​​the present invention. Therefore, the contents of this specification should not be understood as limiting the present invention.

Claims

1. A dynamic stress calculation method for a rolling bearing for a gas turbine, comprising: calculating an impact acceleration received by the gas turbine rolling bearing according to an operating condition curve of an impact load operating condition of the gas turbine rolling bearing, and calculating an actual value of the total load based on the impact acceleration, wherein the operating condition curve is a curve of change in acceleration of the impact load that changes over time; using an initial pressure distribution as an input to perform iterative calculations using an oil film thickness equation and a Renaud equation to obtain an oil film thickness distribution and a pressure distribution; calculating and obtaining a total load calculated value according to the pressure distribution; determining whether the calculated total load value is equal to the actual total load value; if not, using the pressure distribution as an initial pressure distribution, returning to the step of "using the initial pressure distribution as an input to perform iterative calculations using an oil film thickness equation and a Renaud equation to obtain an oil film thickness distribution and a pressure distribution", the oil film thickness distribution includes the oil film thickness at each position point in a calculation domain of the gas turbine rolling bearing, and the pressure distribution includes the pressure at each position point in the calculation domain of the gas turbine rolling bearing, the calculation domain including the contact surface between the rolling element and the inner ring of the gas turbine rolling bearing; calculating a shear stress distribution using a non-Newtonian fluid model with the oil film thickness distribution and the pressure distribution as inputs, the shear stress distribution including shear stresses at each position point in a calculation domain of the gas turbine rolling bearing; a calculation of the dynamic stress of a rolling bearing for a gas turbine, the calculation comprising calculating and obtaining the stress distribution on the contact surface and sub-surface between the rolling elements and the inner ring in the rolling bearing for a gas turbine according to the pressure distribution and the shear stress distribution.

2. The formula for calculating impact acceleration is: and where: is the impact acceleration at time t, is the peak acceleration value of the impact load, τ1 is the duration of the impact load, Specifically, the actual value of the total load is calculated based on the impact acceleration.

2. The method for calculating dynamic stress of a rolling bearing for a gas turbine according to claim 1, further comprising the step of: calculating an actual value of a total load using the impact acceleration as an input and Newton's second law.

3. Specifically, the oil film thickness distribution and pressure distribution can be obtained by performing iterative calculations using the oil film thickness equation and the Renault equation with the initial pressure distribution as input. Using the initial pressure distribution as input, the intermediate oil film thickness distribution is calculated using the oil film thickness equation. The intermediate oil film thickness distribution is used as input, and the intermediate pressure distribution is calculated using the Renault equation.

2. The method for calculating dynamic stress in a rolling bearing for a gas turbine according to claim 1, further comprising: determining whether an iteration termination condition is reached; if so, using the intermediate oil film thickness distribution as the oil film thickness distribution and the intermediate pressure distribution as the pressure distribution; and if not, using the intermediate pressure distribution as the initial pressure distribution for the next iteration, returning to the step of "using the initial pressure distribution as an input to calculate and obtain the intermediate oil film thickness distribution using the oil film thickness equation."

4. The equation for the oil film thickness is and where h is the thickness of the oil film at the location point (x, y), x and y are the abscissa and ordinate of the location point (x, y), respectively, and h ０ is the rigid center film thickness of the gas turbine rolling bearing, R is the equivalent total radius of curvature of the gas turbine rolling bearing, ν is the elastic deformation at the position point (x, y), and δ １ is the surface roughness of the bearing rolling element at the position point (x, y), and δ ２ is the surface roughness of the roller conveyor in the bearing at the position point (x, y), where E' is the bearing contact pair overall elastic modulus, Ω is the computational domain, is the position point is the pressure at ξ and are the position points 2. The method for calculating dynamic stress in a rolling bearing for a gas turbine according to claim 1, wherein the abscissa and ordinate are respectively:

5. The Renault equation is: and 2. The method for calculating dynamic stress in a rolling bearing for a gas turbine according to claim 1, wherein ρ is the density of the lubricating oil at the position point (x, y), x and y are the abscissa and ordinate of the position point (x, y), respectively, h is the oil film thickness at the position point (x, y), η is the viscosity of the lubricating oil at the position point (x, y), p is the pressure at the position point (x, y), u is the spiral velocity of the rolling elements and the inner roller conveyor, and t is time.

6. The non-Newtonian fluid model and where: is the shear rate of the lubricating oil at the position point (x, y), which is calculated based on the distribution of the oil film thickness, is the derivative of the shear stress at the point (x, y), and G ∞ is the ultimate shear modulus at the location point (x, y), and τ Ｌ 2. The dynamic stress calculation method for a rolling bearing for a gas turbine according to claim 1, wherein η is the ultimate shear stress at the position point (x, y), η is the viscosity of the lubricating oil at the position point (x, y), and τ is the shear stress at the position point (x, y).

7. Specifically, the stress distribution on the contact surface and sub-surface between the rolling element and the inner ring in the gas turbine rolling bearing can be calculated and obtained according to the pressure distribution and the shear stress distribution, as follows: calculating and obtaining a plurality of stress components at each three-dimensional point in a solution domain of the gas turbine rolling bearing according to the pressure distribution and the shear stress distribution, the solution domain including a contact surface and a sub-surface between a rolling element and an inner ring in the gas turbine rolling bearing; For each of the three-dimensional points, determine a first principal stress, a second principal stress, and a third principal stress of the three-dimensional point based on a plurality of stress components; calculate a stress of the three-dimensional point based on the first principal stress, the second principal stress, and the third principal stress of the three-dimensional point, wherein the stress includes an equivalent stress and a maximum shear stress; 2. The dynamic stress calculation method for a rolling bearing for a gas turbine according to claim 1, further comprising determining a stress distribution on a contact surface and a sub-surface between a rolling element and an inner ring in the rolling bearing for a gas turbine based on the stresses at all the three-dimensional points.

8. A computer device including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the method for calculating dynamic stress in a rolling bearing for a gas turbine according to any one of claims 1 to 7.

9. A computer-readable storage medium having a computer program stored thereon, the computer program implementing the steps of the method for calculating dynamic stress in a rolling bearing for a gas turbine according to any one of claims 1 to 7 when executed by a processor.

10. A computer program product including a computer program, which, when executed by a processor, implements the steps of the method for calculating dynamic stress in a rolling bearing for a gas turbine according to any one of claims 1 to 7.

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