Dynamic stress calculation method, device, medium and product for rolling bearings for gas turbines

Abstract

A technique is provided that can accurately calculate the dynamic stresses of rolling bearings for gas turbines under shock load operating conditions. [Solution] The present invention includes calculating the impact acceleration received by the gas turbine rolling bearing according to an operating condition curve of the gas turbine rolling bearing under impact load operating conditions, calculating an actual value of the total load based on the impact acceleration, using the initial pressure distribution as an input and under the constraint of the actual value of the total load, calculating the pressure distribution and shear stress distribution using the oil film thickness equation, the Renault equation and a non-Newtonian fluid model, and further calculating the stress distribution on the contact surface and sub-surface between the rolling elements and the inner ring in the gas turbine rolling bearing according to the pressure distribution and shear stress distribution. During the stress calculation under impact load operating conditions, the lubrication condition of the bearing is taken into account, making it possible to accurately calculate the dynamic stress of the gas turbine rolling bearing under impact load operating conditions.

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 of a rolling bearing for a gas turbine under impact load. [Background technology]

[0002] During operation, the rollers of the rolling bearings for gas turbines are in cyclic contact with the roller conveyor, so the bearing rings (including the inner and outer rings) are subject to cyclic contact stress, which reduces the fatigue performance of the material and has a significant impact on the accuracy, performance and life of the rolling bearings. The bearing contact state and stress distribution are important factors for evaluating the operating state and life of the bearings. Most of the existing stress analysis models are for land and aerospace fields, and are relatively less applied to the marine field. The working environment of the marine field is very different from that of other fields, and it is necessary to consider the typical operating conditions with many instantaneous changes. However, the existing stress analysis models are analyzed under dry contact operating conditions or under steady-state operating conditions, and ignore the effects from the sea wave impact operating conditions during actual ship operation.

[0003] Based on this, there is an urgent need for a technique that can accurately calculate the dynamic stresses in gas turbine rolling bearings 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 dynamic stress calculation method, device, medium, and product for a rolling bearing for a gas turbine, which can accurately calculate the dynamic stress of a rolling bearing for a gas turbine under shock 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 the steps of: 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 a 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, performing 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 calculation value according to the pressure distribution, and judging whether the total load calculation value is equal to an actual value of the total load; if not, using the pressure distribution as an initial pressure distribution, returning to the step of "using an initial pressure distribution as an input, performing 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, the pressure distribution includes the pressure at each position point in a calculation domain of the gas turbine rolling bearing, the calculation domain includes a contact surface between a rolling element and an inner ring in 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 rolling bearing for a gas turbine; The method includes calculating and obtaining a 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 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, the processor executing the computer program to realize the steps of the dynamic stress calculation method for a rolling bearing for a gas turbine.

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

[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. Effect 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 dynamic stress calculation method, device, medium and product for a rolling bearing for a gas turbine, which calculates the impact acceleration received 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 rolling bearing for a gas turbine, calculates and obtains an actual value of the total load based on the impact acceleration, and uses the oil film thickness equation, the Renault equation and the non-Newtonian fluid model to calculate the pressure distribution and the shear stress distribution under the constraint of the actual value of the total load using the initial pressure distribution as an input, and further calculates and obtains 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 the shear stress distribution, and takes into account the lubrication condition of the bearing during the stress calculation under the shock load operating condition, so as to accurately calculate the dynamic stress of the rolling bearing for a gas turbine under the shock load operating condition. [Brief description 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 necessary to be used in the embodiments are 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 by Example 1 of the present invention; [Diagram 2] 2 is a schematic diagram showing the change trend 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 5000N, where Fig. 2(a) is the dimensionless impact load distribution, and Fig. 2(b) is the maximum stress distribution of the inner roller conveyor. [Diagram 3] 3A and 3B are three-dimensional cloud images of the bearing surface and sub-surface stress distribution in the xoy plane under the load-impact condition provided by the embodiment 1 of the present invention, where FIG. 3A is a three-dimensional cloud image of the steady-state load stage of 625 calculation steps, FIG. 3B is a three-dimensional cloud image of the load-detonation stage of 1250 calculation steps, FIG. 3C is a three-dimensional cloud image of the linear regression stage of 1563 calculation steps, and FIG. 3D is a three-dimensional cloud image of the bubble pulsation peak value stage of 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 the load-impact condition provided by the first embodiment of the present invention, where FIG. 4A is a three-dimensional cloud image of the steady-state load stage of 625 calculation steps, FIG. 4B is a three-dimensional cloud image of the load-detonation stage of 1250 calculation steps, FIG. 4C is a three-dimensional cloud image of the linear regression stage of 1563 calculation steps, and FIG. 4D is a three-dimensional cloud image of the bubble pulsation peak value stage of 3438 calculation steps. [Diagram 5] 5A and 5B are three-dimensional cloud images of the bearing surface and sub-surface stress distribution in the yoz plane under the load impact condition provided by the embodiment 1 of the present invention, where FIG. 5A is a three-dimensional cloud image of the steady state load stage of 625 calculation steps, FIG. 5B is a three-dimensional cloud image of the load detonation stage of 1250 calculation steps, FIG. 5C is a three-dimensional cloud image of the linear regression stage of 1563 calculation steps, and FIG. 5D is a three-dimensional cloud image of the bubble pulsation peak value stage of 3438 calculation steps. [Figure 6] 6A and 6B are three-dimensional cloud images of 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. 6(a) is a three-dimensional cloud image of 5000N, Fig. 6(b) is a three-dimensional cloud image of 7000N, and Fig. 6(c) is a three-dimensional cloud image of 9000N. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0014] The technical solutions in the embodiments of the present invention will be described below 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, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative efforts are all within the protection scope 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 in 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 complicated, and 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 of the naval ship specification BV043 / 85 given by the German Federal Ministry of Defense, performs approximation processing on it, and constructs 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

number

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

number

[0021] Equation (2) is the impact acceleration calculation formula used in this embodiment. After obtaining the operating status of the bearing (i.e., the operating status curve) by on-site inspection, the acceleration peak value and duration can be determined, and 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 an input, perform iterative calculations using the oil film thickness equation and the Renault 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 judge whether the calculated total load value is equal to the actual value of the total load, and if not, return to the step of "using the initial pressure distribution as an input, perform iterative calculations using the oil film thickness equation and the Renault 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 surface between the rolling element and the inner ring of the gas turbine rolling bearing.

[0024] In this embodiment, the method of calculating the initial pressure distribution is to calculate the initial oil film thickness according to an empirical formula, and the initial oil film thickness at each position in the calculation domain is the same, that is, the initial oil film thickness distribution is obtained, and the initial oil film thickness distribution is 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 an 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 a total load calculation value is calculated according to the pressure distribution to determine whether the total load calculation value is equal to the actual value of the total load. If so, the iteration is terminated and S3 is executed; if not, the iteration is continued and the pressure distribution is the initial pressure distribution, and the process returns to the step of "using the initial pressure distribution as an 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 total load calculation value according to the pressure distribution specifically includes integrating the pressure change in the entire calculation domain (e.g., an elliptical domain) to obtain the total load calculation value as follows:

number

[0028] In this embodiment, the initial pressure distribution is 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, specifically including 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 to obtain it. Taking into consideration the effects of the transient radius of curvature and elastic deformation during bearing operation, the oil film thickness equation used in this embodiment is

number

[0030]

number

[0031] After obtaining the initial pressure distribution, the pressure at each position in the calculation domain is determined, and then substituted into equation (6) to calculate the elastic deformation at each position. 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 of the rolling body and the inner roller conveyor under impact conditions. 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 an unknown value, and the oil film thickness at each position 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), and the pressure at each position is calculated using a sequential encryption method, and the pressure at all the position points constitutes the intermediate pressure distribution. Using the sequential encryption method can improve the calculation efficiency, and of course, this embodiment can also use other methods to solve the problem.

[0038] (3) Determine whether the condition for ending the iteration is reached. 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, at which point the pressure distribution is deemed to have converged and the iteration is ended.

[0040] Here, the formula for the error is

number

[0041] The given error is 10 -3 In this case, the iteration error err of the oil film pressure between two adjacent iterations may be 10 -3 If it is equal to or less than 0, 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 a shear stress distribution using a non-Newtonian fluid model, where the shear stress distribution includes shear stresses at each position point in a calculation domain of the rolling bearing for a gas turbine.

[0043] Bearing friction under elastohydrodynamic lubrication conditions is mainly caused by fluid shear friction. The friction force in the hydrodynamic lubrication region is calculated by the viscoelastic Bair-Winer non-Newtonian fluid rheology model. The non-Newtonian fluid model used in this study 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 was 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 based on 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 according to the pressure distribution and the shear stress distribution is calculated and obtained, specifically including the following:

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

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

number

[0051]

number

number

number

number

number

number

[0052] Calculate using the above formulas (18) to (23) TIFF0007675465000047.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 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; and calculate and obtain 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, 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 rearranged from largest to smallest, 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 account that the impact load generates shear force and pressure between the bearings, the first principal stress σ1, the second principal stress σ2, and the third principal stress σ3 of each three-dimensional point inside the bearing can be obtained by solving the problem.

[0055] Equivalent stress σ of rolling elements 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 the underwater shock load environment are comprehensively taken into consideration, and the surface and sub-surface stress excitation sources are divided into two parts: surface normal compressive stress and surface tangent shear stress, which are obtained by the bearing elastohydrodynamic lubrication analysis (i.e., the oil film thickness equation, the Renault equation and the non-Newtonian fluid model), and 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 the shock load condition can be accurately predicted, and the accuracy of the contact surface and sub-surface stress prediction distribution can be effectively improved.

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

[0058] This embodiment mainly compares the effects of impact load on bearing surface and sub-surface stress under four sets of different load operating conditions, where the load operating conditions are w = 5000N, w = 7000N, w = 9000N, and w = 11000N, respectively, and the calculation parameters are, as shown in Table 1, the spiral speed is 3m / s, and the slide-to-roll ratio is 0.2 (where the speed of the rolling body 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 TIFF0007675465000050.tif90152

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

[0061] Figure 3 shows the three-dimensional stress distribution in the xoy plane at different load impact stages when the initial load operating condition is 5000N, (a) in Figure 3 is the length of the calculation area in the x direction, and (b) is the length of the calculation area in the y direction. From Figure 3, the impact of the load impact on the bearing surface and sub-surface stress is very significant, and (a) to (d) in Figure 3 show the stress change process from the load impact to after unloading, and it can be seen that the load detonation stage has a significant increase in the stress peak value and the area of ​​high stress area compared to the steady state load stage, and the stress area decreases until the unloading process, and gradually recovers to the steady state form.

[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 load detonation stage generates surface stress that increases from the stress peak value generated in the steady state load stage and is simultaneously applied to deeper layers. Take the load w=5000N as an example, in the steady state load stage (625 calculation steps), the maximum stress occurs at z=0.73a, when it reaches the load detonation stage, the maximum stress occurs at z=0.96a, when the load completes the first part of the linear unloading process, it is in the linear decay stage (1563 calculation steps), and the maximum stress occurs at z=0.83a. Due to the impact load, the maximum sub-surface stress gradually moves 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 operating condition is 5000N. In the yoz plane, the variation rule of the sub-surface stress is the same as that in the xoz plane. At the same time, the maximum stress of the bearing in the yoz plane is 11.4% lower than that in the xoz plane, which is consistent with the change trend of the results in the existing literature. The maximum surface stress in the direction of higher curvature is reduced, and in the yoz plane, the bearing is subjected to the impact load, and the high stress area is increased accordingly.

[0064] Figure 6 shows the stress distribution of the inner roller conveyor under different initial load conditions during the load detonation stage. From Figure 6, it can be seen that there are three sets of different initial load operating conditions. As the initial load increases, the stress peak 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 typical operating conditions of gas turbine bearings, a three-dimensional dynamic stress analysis model of the bearing surface and sub-surface under impact load is established, the three-dimensional dynamic stress distribution characteristics of the bearing surface and sub-surface under load and impact conditions are studied, and the sub-surface stress distribution of the bearing under multiple sets of different initial load operating conditions is compared, and it is found that the sub-surface stress during the load detonation stage increases significantly, and at the same time, the area and occurrence depth of the high stress area also increase simultaneously.

[0066] Example 2 A computer device includes a memory, a processor, and a computer program stored in the memory and executable on the processor, the processor executing 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, which, when executed by a processor, realizes the steps of the dynamic stress calculation method for a rolling bearing for a gas turbine described in Example 1.

[0069] Each technical feature of the above embodiments can be combined in any way, and for the sake of brevity, not all possible combinations of each technical feature 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, the principle and embodiment of the present invention are described by applying specific examples, and the description of the above examples is only to contribute to understanding the method of the present invention and its core idea, and at the same time, for those skilled in the art, there are all modifications to 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 limitations on the present invention.

Claims

1. A dynamic stress calculation method for a rolling bearing for a gas turbine, comprising the steps of: 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 a 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, performing 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 calculation value according to the pressure distribution, and judging whether the total load calculation value is equal to an actual value of the total load; if not, using the pressure distribution as an initial pressure distribution, returning to the step of "using an initial pressure distribution as an input, performing 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, the pressure distribution includes the pressure at each position point in a calculation domain of the gas turbine rolling bearing, the calculation domain includes a contact surface between a rolling element and an inner ring in 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 rolling bearing for a gas turbine; a pressure distribution and a shear stress distribution in the gas turbine rolling bearing, the pressure distribution and the shear stress distribution being calculated to obtain a stress distribution on a contact surface and a sub-surface between a rolling element and an inner ring in the gas turbine rolling bearing.

2. The formula for calculating impact acceleration is: and Where: is the impact acceleration at time t, is the peak acceleration value of the shock load, τ1 is the duration of the shock 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 by using the impact acceleration as an input and Newton's second law.

3. To obtain the oil film thickness distribution and the pressure distribution by performing iterative calculations using the oil film thickness equation and the Renaud equation with the initial pressure distribution as input, specifically, The initial pressure distribution is input, and the intermediate oil film thickness distribution is calculated using the oil film thickness equation. The intermediate oil film thickness distribution is input, and the intermediate pressure distribution is calculated using the Renaud equation.

2. The method for calculating dynamic stress in a rolling bearing for a gas turbine according to claim 1, further comprising: judging whether an iteration end condition is reached, and if so, taking the intermediate oil film thickness distribution as the oil film thickness distribution and the intermediate pressure distribution as the pressure distribution; and if not, taking the intermediate pressure distribution as the initial pressure distribution for the next iteration, and returning to the step of "using the initial pressure distribution as an input to calculate and obtain the intermediate oil film thickness distribution by utilizing 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 total elastic modulus and Ω is the computational domain. is the location 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 of said dynamic stress are respectively:

5. The Renaud 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 speed 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 lubricant 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: x 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 calculation of 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 the shear stress distribution includes the following steps: calculating and obtaining a plurality of stress components at each three-dimensional point in a solution domain of the rolling bearing for a gas turbine 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 rolling bearing for a gas turbine; 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; and 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, the stress including an equivalent stress and a maximum shear stress; 2. The method for calculating dynamic stress in 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, the processor executing the computer program to realize steps of the dynamic stress calculation method for 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 being characterized in that, when executed by a processor, the computer program realizes the steps of the dynamic stress calculation method for a rolling bearing for a gas turbine according to any one of claims 1 to 7.

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

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