Turbine blade feature mockup design method accounting for temperature gradients
By identifying the equivalent stress concentration points of the turbine blade's three-dimensional model, acquiring target data, and adjusting characteristic parameters, the problem of poor realism in existing simulations was solved, achieving highly realistic simulation of turbine blades.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- NORTHWESTERN POLYTECHNICAL UNIV
- Filing Date
- 2026-03-06
- Publication Date
- 2026-06-12
Smart Images
Figure CN122197188A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of turbine blade technology, and more specifically, to a design method for turbine blade feature simulation components that take temperature gradients into account. Background Technology
[0002] Turbine blades, with their superior performance, are widely used in various engines in the aerospace field. However, the extreme environments of high temperature, high pressure, and high speed that engines operate under for extended periods make turbine blades susceptible to defects and damage such as chipping or cracking. These defects and damage alter the aerodynamic shape and structural integrity of the blades, affecting engine performance and reducing efficiency in minor cases, and potentially leading to rotor blade fracture in severe cases, seriously threatening the safety of the engine and aircraft. Due to the complex internal cooling structure, low yield, and high manufacturing cost of turbine blades, a characteristic simulation of the turbine blade is first obtained during blade design, and this simulation is then subjected to life testing.
[0003] In a current design method for a three-dimensional model of a turbine blade, the first step is to obtain and establish a three-dimensional model of a simulated component similar to the turbine blade. Then, simulation is performed to make the stress distribution inside the three-dimensional model of the simulated component similar to that inside the real turbine blade. Finally, a feature simulation component is manufactured based on the three-dimensional model of the simulated component.
[0004] However, the above simulation is incomplete, resulting in poor realism in the simulation of various data of turbine blades by the feature simulation parts obtained by the above method.
[0005] It should be noted that the information disclosed in the background section above is only used to enhance the understanding of the background of this disclosure, and therefore may include information that does not constitute prior art known to those skilled in the art. Summary of the Invention
[0006] This application provides a method for designing turbine blade feature simulation components considering temperature gradients, which can solve the problem of poor simulation realism in related technologies. The technical solution is as follows: According to one aspect of this application, a method for designing turbine blade feature simulations considering temperature gradients is provided for a target turbine blade, the method comprising: A three-dimensional model of the turbine blade is obtained based on the parameters of the target turbine blade. Finite element simulation is performed on the three-dimensional model of the turbine blade to determine the equivalent stress concentration area in the three-dimensional model of the turbine blade. The equivalent stress concentration area is the region with the largest equivalent stress in the three-dimensional model of the turbine blade. Acquire the target equivalent stress, target temperature gradient data, and target stress gradient data at the equivalent stress concentration location. The target stress gradient data includes the stress gradient data at the equivalent stress concentration location, starting from the equivalent stress concentration point. A three-dimensional model of the simulated part at the equivalent stress concentration location is established based on the initial feature parameters; Set the initial temperature field data for the three-dimensional model of the simulation component; Obtain the initial temperature gradient data of the three-dimensional model of the simulated component; When the initial temperature gradient data matches the target temperature gradient data, a displacement load is applied to the three-dimensional model of the simulation component so that the equivalent stress of the three-dimensional model of the simulation component is equal to the target equivalent stress. Obtain the initial stress gradient data of the three-dimensional model of the simulated part, starting from the equivalent stress concentration point; Determine whether the difference between the initial stress gradient data and the target stress gradient data is less than a difference threshold; When the difference is not less than the difference threshold, the initial feature parameters are adjusted, and the step of establishing the three-dimensional model of the simulated part of the equivalent stress concentration location based on the initial feature parameters is repeated. When the difference is less than the difference threshold, the initial feature parameter is determined as the target parameter, and the feature simulation part is manufactured with the target parameter.
[0007] Optionally, the finite element simulation of the three-dimensional model of the turbine blade includes: The operating parameters of the target turbine blade are obtained, including the temperature field data and load conditions of the target turbine blade. Finite element simulation was performed on the three-dimensional model of the turbine blade based on the operating parameters to obtain equivalent stress distribution data; Based on the equivalent stress distribution data, the locations of concentrated equivalent stress in the three-dimensional model of the turbine blade are determined.
[0008] Optionally, the process of acquiring the target stress gradient data includes: Obtain the direction of the first principal stress at the equivalent stress concentration site; The equivalent stress at the equivalent stress concentration point within the first plane is determined as the maximum value of the equivalent stress. The first plane is a plane perpendicular to the direction of the first principal stress at the equivalent stress concentration location. Obtain the target stress gradient data at the equivalent stress concentration point of the equivalent stress concentration region. The stress gradient data includes multiple stress values inside the equivalent stress concentration region in a first direction, starting from the equivalent stress concentration point. The first direction is the direction of the fastest descent path of the equivalent stress at the equivalent stress concentration point, which is perpendicular to the plane of maximum principal stress.
[0009] Optionally, the process of acquiring the target temperature gradient data includes: Starting from the equivalent stress concentration point, obtain multiple temperature values in a second direction, where the second direction is parallel to the surface normal at the equivalent stress concentration point and faces inward toward the interior of the equivalent stress concentration area.
[0010] Optionally, the equivalent stress concentration site is the leading edge of the root of the target turbine blade; The process of establishing a three-dimensional model of the simulated component at the equivalent stress concentration location based on initial feature parameters includes: A three-dimensional model of the simulated part is established, including a circular boss, a first connecting part, a second connecting part, a first chamfer structure, and a second chamfer structure. The first connecting part and the second connecting part are respectively located on both sides of the circular boss in the axial direction. The first connecting part is connected to one circular surface of the circular boss through the first chamfer structure, and the second connecting part is connected to the other circular surface of the circular boss through the second chamfer structure. The initial feature parameters include the first radius of the first chamfer structure, the second radius of the second chamfer structure, the thickness of the boss in the axial direction, and the diameter of the circular boss.
[0011] Optionally, the first connecting part includes a first connecting rod and a first clamping rod. One end of the first connecting rod is connected to the first chamfered structure, and the other end is connected to the first clamping rod. The diameter of the first connecting rod is smaller than the diameter of the circular boss.
[0012] Optionally, the second connecting part includes a second connecting rod and a second clamping rod. One end of the second connecting rod is connected to the second chamfered structure, and the other end is connected to the second clamping rod. The diameter of the second connecting rod is equal to the diameter of the first connecting rod.
[0013] Optionally, the simulated 3D model includes a central hole penetrating the circular boss, the first connecting portion, the second connecting portion, the first chamfered structure, and the second chamfered structure. The central hole is used to introduce air to adjust the initial temperature gradient data of the simulated 3D model.
[0014] Optionally, after obtaining the initial temperature gradient data of the three-dimensional model of the simulation part, the method further includes: When the initial temperature gradient data does not match the target temperature gradient data, the flow rate and temperature of the air introduced into the central hole are adjusted, and the step of obtaining the initial temperature gradient data of the three-dimensional model of the simulation part is repeated.
[0015] Optionally, the method further includes: The lifespan of the simulated feature was tested. The life test data of the simulated feature is obtained.
[0016] The beneficial effects of the technical solutions provided in this application include at least the following: A method for designing a turbine blade feature simulation component considering temperature gradients is provided. This method identifies the equivalent stress concentration points in the 3D model of the turbine blade and acquires target equivalent stress, target temperature gradient data, and target stress gradient data at these points to establish comprehensive simulation baseline data. Then, a 3D model of the simulation component at the equivalent stress concentration points is built based on initial feature parameters. Initial temperature field data is set for the 3D model, and initial temperature gradient data is acquired. When the initial temperature gradient data matches the target temperature gradient data, a displacement load is applied to the 3D model, and initial stress gradient data is acquired starting from the equivalent stress concentration point. If the difference between the initial stress gradient data and the target stress gradient data is not less than a threshold, the initial feature parameters are adjusted. If the difference is less than the threshold, the initial feature parameters are determined as target parameters, and the feature simulation component is manufactured using these target parameters. The feature simulation component obtained through this simulation considers the influence of the temperature field on the turbine blade in the real working environment, enabling it to reproduce the temperature distribution, equivalent stress level, and stress gradient changes of the target turbine blade. This achieves the beneficial effect of improving the realism of the simulation of various turbine blade data.
[0017] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description
[0018] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this disclosure and, together with the description, serve to explain the principles of this disclosure. It is obvious that the drawings described below are merely some embodiments of this disclosure, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort.
[0019] Figure 1 This is a flowchart of a turbine blade feature simulation design method considering temperature gradients, provided in an embodiment of this application.
[0020] Figure 2 This is a flowchart of another turbine blade feature simulation design method considering temperature gradients provided in the embodiments of this application.
[0021] Figure 3 This is a stress gradient variation curve of a target turbine blade provided in an embodiment of this application.
[0022] Figure 4 This is a partial structural schematic diagram of a target turbine blade provided in an embodiment of this application.
[0023] Figure 5 This is a schematic diagram of the structure of a simulation component provided in the embodiments of this application.
[0024] Figure 6 This is a comparison curve of initial stress gradient data and target stress gradient data provided in an embodiment of this application.
[0025] Figure 7 This is a schematic diagram of the structure of a simulation component shown in an embodiment of this application.
[0026] The accompanying drawings illustrate specific embodiments of this application, which will be described in more detail below. These drawings and descriptions are not intended to limit the scope of the concept in any way, but rather to illustrate the concept of this application to those skilled in the art through reference to particular embodiments. Detailed Implementation
[0027] To make the objectives, technical solutions, and advantages of this application clearer, the embodiments of this application will be described in further detail below with reference to the accompanying drawings.
[0028] Figure 1 This is a flowchart illustrating a turbine blade feature simulation design method considering temperature gradients, provided in an embodiment of this application. This method is used for a target turbine blade and may include the following steps: Step 101: Obtain the three-dimensional model of the turbine blade based on the parameters of the target turbine blade.
[0029] Step 102: Perform finite element simulation on the three-dimensional model of the turbine blade to determine the equivalent stress concentration area in the three-dimensional model of the turbine blade. The equivalent stress concentration area is the region with the largest equivalent stress in the three-dimensional model of the turbine blade.
[0030] Step 103: Obtain target equivalent stress, target temperature gradient data, and target stress gradient data at the equivalent stress concentration location. The target stress gradient data includes the stress gradient data at the equivalent stress concentration location, starting from the equivalent stress concentration point.
[0031] Step 104: Establish a three-dimensional model of the simulated part of the equivalent stress concentration area based on the initial feature parameters.
[0032] Step 105: Set the initial temperature field data for the three-dimensional model of the simulation component.
[0033] Step 106: Obtain the initial temperature gradient data of the three-dimensional model of the simulation part.
[0034] Step 107: When the initial temperature gradient data matches the target temperature gradient data, apply a displacement load to the three-dimensional model of the simulation part so that the equivalent stress of the three-dimensional model of the simulation part is equal to the target equivalent stress.
[0035] Step 108: Obtain the initial stress gradient data of the three-dimensional model of the simulation part, starting from the equivalent stress concentration point.
[0036] Step 109: Determine whether the difference between the initial stress gradient data and the target stress gradient data is less than the difference threshold.
[0037] Step 110: When the difference is not less than the difference threshold, adjust the initial feature parameters and re-execute step 104.
[0038] Step 111: When the difference is less than the difference threshold, determine the initial feature parameter as the target parameter, and manufacture the feature simulation part with the target parameter.
[0039] In summary, this application provides a method for designing a turbine blade feature simulation component considering temperature gradients. By identifying the equivalent stress concentration points in the three-dimensional model of the turbine blade, the method acquires target equivalent stress, target temperature gradient data, and target stress gradient data at these points to establish comprehensive simulation baseline data. Then, based on initial feature parameters, a three-dimensional model of the simulation component at the equivalent stress concentration points is established. Initial temperature field data of the three-dimensional model is set, and initial temperature gradient data is acquired. When the initial temperature gradient data matches the target temperature gradient data, a displacement load is applied to the three-dimensional model to acquire initial stress gradient data starting from the equivalent stress concentration point. When the difference between the initial stress gradient data and the target stress gradient data is not less than a difference threshold, the initial feature parameters are adjusted. If the difference is less than the difference threshold, the initial feature parameters are determined as target parameters, and the feature simulation component is manufactured using these target parameters. The feature simulation obtained through the above simulation takes into account the influence of the temperature field on the turbine blade in the real working environment. This allows the feature simulation to reproduce the temperature distribution, equivalent stress level, and stress gradient change data of the target turbine blade, thus achieving the beneficial effect of improving the realism of the feature simulation for various data of the turbine blade.
[0040] Figure 2This is a flowchart of another turbine blade feature simulation design method considering temperature gradients provided in this application embodiment. This turbine blade feature simulation design method considering temperature gradients is used for a target turbine blade, and the method may include the following steps: Step 201: Obtain the three-dimensional model of the turbine blade based on the parameters of the target turbine blade.
[0041] The target turbine blade is the actual turbine blade used. In this embodiment, the target turbine blade is made of nickel-based polycrystalline superalloy. Parameters such as the density, elastic constant, coefficient of thermal expansion, conductivity, and specific heat of the nickel-based polycrystalline superalloy as a function of temperature are obtained. Based on these parameters, a three-dimensional model of the turbine blade is obtained. The resulting three-dimensional model and material properties of the turbine blade are consistent with the actual blade, providing accurate input for subsequent finite element simulations and ensuring the reliability of stress analysis and temperature field calculations.
[0042] Step 202: Obtain the operating parameters of the target turbine blade, including the temperature field data and load conditions of the target turbine blade.
[0043] Temperature field data refers to the spatial distribution of temperature values at every point inside and on the surface of an object at a given moment. For example, in an aero-engine, the leading edge of a turbine blade has a high surface temperature due to direct contact with the high-temperature exhaust gases, while the internal cooling channels result in a lower internal temperature. Temperature field data can be obtained through thermodynamic simulation or experimental measurement, and accurate thermal stress can be calculated from this data. Load conditions refer to the mechanical loads acting on the target turbine blade, which can include centrifugal loads, aerodynamic loads, etc. These operating parameters are set based on the actual operating conditions of the engine to simulate the real thermo-mechanical coupling environment, providing accurate input for subsequent finite element simulations and improving the accuracy of stress concentration location identification.
[0044] Step 203: Perform finite element simulation on the three-dimensional model of the turbine blade based on the operating parameters to obtain equivalent stress distribution data.
[0045] The 3D model of the turbine blade obtained in step 201 is imported into the finite element analysis software, and the operating parameters obtained in step 202 are applied to the model as loads and boundary conditions. Appropriate boundary conditions are set according to the actual service conditions of the blade in the engine. For example, the transient temperature field and transient stress at a certain speed are simulated during the engine startup process from 0 to 18000 revolutions per minute (RPM) to obtain transient equivalent stress distribution data. The data results can be used to generate an equivalent stress distribution cloud map, visually displaying the stress level in each region of the blade.
[0046] Step 204: Determine the location of concentrated equivalent stress in the three-dimensional model of the turbine blade based on the equivalent stress distribution data.
[0047] The equivalent stress concentration area is the region with the highest equivalent stress in the 3D model of the turbine blade. By observing the equivalent stress distribution cloud map, the stress concentration area can be clearly identified. In this embodiment, the leading edge of the turbine blade root is taken as the equivalent stress concentration area for illustration, because this region usually generates high stress due to geometric abrupt changes (such as rounded chamfers) and load concentration.
[0048] Step 205: Obtain target equivalent stress, target temperature gradient data, and target stress gradient data at the equivalent stress concentration location. The target stress gradient data includes the stress gradient data at the equivalent stress concentration location, starting from the equivalent stress concentration point.
[0049] The process of acquiring target temperature gradient data includes: acquiring multiple temperature values in a second direction starting from the equivalent stress concentration point, wherein the second direction is parallel to the surface normal at the equivalent stress concentration point and toward the interior of the equivalent stress concentration area.
[0050] The process of acquiring target stress gradient data includes: acquiring the first principal stress direction of the equivalent stress concentration location; determining the equivalent stress at the equivalent stress concentration point in the first plane as the maximum value of the equivalent stress, where the first plane is a plane perpendicular to the first principal stress direction of the equivalent stress concentration location; acquiring target stress gradient data at the equivalent stress concentration point of the equivalent stress concentration location, where the stress gradient data includes multiple stress values inside the equivalent stress concentration location along the first direction, starting from the equivalent stress concentration point, where the first direction is the direction of the fastest decreasing path of the equivalent stress at the equivalent stress concentration point, perpendicular to the plane of maximum principal stress.
[0051] Figure 3 This is a stress gradient variation curve of a target turbine blade provided in an embodiment of this application. Figure 3 The diagram shows the target stress gradient curve of the stress concentration point at the leading edge of the turbine blade root. The horizontal axis represents the distance from the equivalent stress concentration point in the first direction. The vertical axis represents the equivalent stress value in megapascals (MPa). In other words, in the first plane, the curve representing the change in equivalent stress value with distance is extracted along the path of fastest decrease in equivalent stress, starting from the equivalent stress concentration point. This curve represents the target stress gradient and can serve as a comparative reference for subsequent simulation design and optimization.
[0052] Step 206: Establish a three-dimensional model of the simulated part of the equivalent stress concentration area based on the initial feature parameters.
[0053] Figure 4 This is a partial structural schematic diagram of a target turbine blade provided in an embodiment of this application. Figure 5 This is a schematic diagram of the structure of a simulation component provided in the embodiments of this application, wherein... Figure 4 A schematic diagram of a partial structure of the target turbine blade is shown, as follows. Figure 4 and Figure 5 As shown, the connection area between the blade 11 and the rim plate 12 of the target turbine blade, that is, the leading edge Q at the root of the blade 11, has a rounded chamfer 13. The rounded chamfer 13 is a critical area for stress concentration. Therefore, Figure 5 That is to Figure 4 Based on the rounded chamfer 13, for Figure 4 The abstracted and parameterized simulation of the blade root chamfer is presented. Specifically, a 3D model of the simulation component is established, including a circular boss 21, a first connecting part 22, a second connecting part 23, a first chamfer structure 24, and a second chamfer structure 25. The first connecting part 22 and the second connecting part 23 are located on both sides of the circular boss 21 along the axial direction and serve as clamps for connecting the simulation component to the testing machine, having a threaded structure. The first connecting part 22 is connected to one circular surface of the circular boss 21 through the first chamfer structure 24, and the second connecting part 23 is connected to the other circular surface of the circular boss 21 through the second chamfer structure 25. The initial characteristic parameters include the first radius R1 of the first chamfer structure 24, the second radius R2 of the second chamfer structure 25, the thickness h of the circular boss 21 along the axial direction, and the diameter L of the circular boss 21. The circular boss 21 is the core area of the simulation component, used to reproduce the mechanical behavior of the stress concentration area of the real blade. Its protruding shape is designed to generate geometric discontinuities under load, thereby simulating a stress concentration area. The first chamfer structure 24 and the second chamfer structure 25 simulate the arc chamfer 13 of the leading edge of the root of the target turbine blade. The size of the chamfer radius determines the degree of stress concentration: the smaller the radius, the more significant the stress concentration effect; the larger the radius, the more gradual the stress distribution.
[0054] The first connecting part 22 includes a first connecting rod 221 and a first clamping rod 222. One end of the first connecting rod 221 is connected to the first chamfered structure 24, and the other end is connected to the first clamping rod 222. The diameter of the first connecting rod 221 is smaller than the diameter of the circular boss 21.
[0055] The second connecting part 23 includes a second connecting rod 231 and a second clamping rod 232. One end of the second connecting rod 231 is connected to the second chamfered structure 25, and the other end is connected to the second clamping rod 232. The diameter of the second connecting rod 231 is equal to the diameter of the first connecting rod 221.
[0056] The simulated 3D model also includes a through circular boss 21, a first connecting part 22, a second connecting part 23, a first chamfered structure 24, and a center hole 26 in the second chamfered structure 25. Figure 5 The image shows a cross-section of the central hole 26, which is used to introduce air (such as cold air) to adjust the initial temperature gradient data of the three-dimensional model of the simulation part.
[0057] Step 207: Set the initial temperature field data for the three-dimensional model of the simulation component.
[0058] In the finite element simulation model, a thermal load is applied to the simulated component. First, the outer wall temperatures of the circular boss 21, the first chamfer structure 24, and the second chamfer structure 25 are set. These temperatures correspond to the surface temperatures of the equivalent stress concentration points of the target turbine blade, ensuring that the maximum temperatures at the stress concentration points of the target turbine blade and the simulated component are spatially aligned. Second, room temperature air is introduced into the central hole at an initial flow rate. Convection heat transfer generates a temperature gradient along the wall thickness of the simulated component, simulating the temperature distribution of the target turbine blade and providing a starting point for temperature gradient comparison and adjustment.
[0059] Step 208: Obtain the initial temperature gradient data of the three-dimensional model of the simulation part.
[0060] The temperature values of the outer surface of the simulated part and the temperature values at a certain depth (e.g., 1 mm) inside are extracted to form a temperature gradient curve. The process of obtaining the initial temperature gradient data of the three-dimensional model of the simulated part can also refer to the process of obtaining the target temperature gradient data, which will not be repeated here in the embodiments of this application.
[0061] Step 209: When the initial temperature gradient data does not match the target temperature gradient data, adjust the flow rate and temperature of the air entering the central hole, and repeat step 208.
[0062] Iterative adjustments are made until the initial temperature gradient data matches the target temperature gradient data, ensuring that the temperature distribution on the outer wall and inside of the simulated component matches the target turbine blade, thereby improving the accuracy of the thermo-mechanical coupling simulation.
[0063] Step 210: When the initial temperature gradient data matches the target temperature gradient data, apply a displacement load to the three-dimensional model of the simulation part so that the equivalent stress of the three-dimensional model of the simulation part is equal to the target equivalent stress.
[0064] By adjusting the axial displacement applied to one end of the simulation part, the maximum equivalent stress generated by its circular boss 21, first chamfer structure 24 and second chamfer structure 25 is equal to the target equivalent stress of the target turbine blade, thereby ensuring that the maximum stress value of the stress concentration part of the target turbine blade and the simulation part is consistent in space, creating conditions for stress gradient extraction and comparison.
[0065] Step 211: Obtain the initial stress gradient data of the three-dimensional model of the simulation part, starting from the equivalent stress concentration point.
[0066] Extract the first principal stress direction from the stress concentration point of the simulated component. Then, in a plane perpendicular to the first principal stress direction, starting from the equivalent stress concentration point, extract the curve of equivalent stress value as a function of distance along the path of fastest decrease in equivalent stress to obtain the initial stress gradient data. This method is consistent with the method for extracting the target stress gradient in step 205.
[0067] Step 212: Determine whether the difference between the initial stress gradient data and the target stress gradient data is less than the difference threshold.
[0068] Figure 6 This is a comparison curve of initial stress gradient data and target stress gradient data provided in an embodiment of this application. The horizontal axis represents the distance from the equivalent stress concentration point in a first direction. The vertical axis represents the value of the equivalent stress, in megapascals (MPa). Figure 6 As shown, the initial stress gradient curve of the simulated part is compared with... Figure 3 The target stress gradient curves of the target turbine blade obtained from the data are plotted in the same coordinate system. A preset difference threshold is set, and the relative error of the stress values at corresponding points on the two curves is calculated. The maximum relative error among all data points is identified, and it is determined whether the maximum relative error is less than the preset difference threshold. In this embodiment, the difference threshold is 5% of the target stress gradient data. Figure 6 The maximum relative error shown is 3.4%, so step 214 can be performed.
[0069] Step 213: When the difference is not less than the difference threshold, adjust the initial feature parameters and repeat step 206.
[0070] Adjust at least one parameter among the first radius R1 of the first chamfer structure 24, the second radius R2 of the second chamfer structure 25, the thickness h of the circular boss 21 in the axial direction, and the diameter L of the circular boss 21, and repeat step 206 iteratively until the error between the two curves is less than the difference threshold. Optionally, only the first radius R1 can be adjusted.
[0071] Step 214: When the difference is less than the difference threshold, determine the initial feature parameters as the target parameters, and manufacture the feature simulation part with the target parameters.
[0072] When the stress gradient error meets the difference threshold requirement, the current geometric parameters are the final target parameters. Figure 7 This is a schematic diagram of the structure of a simulation component shown in an embodiment of this application. Figure 7Detailed drawings of a simulated component generated based on final target parameters are shown. Dimensions in the drawings are in millimeters. The total length of the simulated component along the axial direction is 140 mm. The right-angle side length of the chamfer C of the first clamping rod 222 is 0.5 mm, and 45° represents the chamfer angle. The length of the first clamping rod 222 along the axial direction is 30 mm. The radius R of the arc at the connection between the first clamping rod 222 and the first connecting rod 221 is 23.8 mm. The first radius R1 of the first chamfer structure 24 is 1.4 mm, and the second radius R2 of the second chamfer structure 25 is 2 mm. The thickness h of the circular boss 21 along the axial direction is 1.2 mm, and the diameter L of the circular boss 21 is 12 mm. The thread specification M12 of the first clamping rod 222 and the second clamping rod 232 indicates a nominal thread diameter of 12 mm. The diameter of the first connecting rod 221 is 8.5 mm, and the diameter of the center hole is 6.5 mm. A physical simulated component can be manufactured based on these detailed drawings. The manufacturing process may include CNC machining, 3D printing and other techniques to ensure geometric accuracy and material consistency.
[0073] Step 215: Perform a life test on the feature simulation part to obtain the life test data of the feature simulation part.
[0074] Fatigue or creep tests are conducted on fabricated simulants to test their lifespan under simulated real-world conditions, such as temperature gradients and mechanical loads. For example, a thermal gradient mechanical fatigue testing machine can be used to reproduce temperature gradients through induction heating or resistance heating. The damage evolution process, crack initiation time, and failure cycle of the simulant are recorded to obtain life test data. This data is used to evaluate the material's performance under thermo-mechanical coupling, verify the reliability of the simulant, and provide experimental data for turbine blade life prediction.
[0075] In summary, this application provides a method for designing a turbine blade feature simulation component considering temperature gradients. By identifying the equivalent stress concentration points in the three-dimensional model of the turbine blade, the method acquires target equivalent stress, target temperature gradient data, and target stress gradient data at these points to establish comprehensive simulation baseline data. Then, based on initial feature parameters, a three-dimensional model of the simulation component at the equivalent stress concentration points is established. Initial temperature field data of the three-dimensional model is set, and initial temperature gradient data is acquired. When the initial temperature gradient data matches the target temperature gradient data, a displacement load is applied to the three-dimensional model to acquire initial stress gradient data starting from the equivalent stress concentration point. When the difference between the initial stress gradient data and the target stress gradient data is not less than a difference threshold, the initial feature parameters are adjusted. If the difference is less than the difference threshold, the initial feature parameters are determined as target parameters, and the feature simulation component is manufactured using these target parameters. The feature simulation obtained through the above simulation takes into account the influence of the temperature field on the turbine blade in the real working environment. This allows the feature simulation to reproduce the temperature distribution, equivalent stress level, and stress gradient change data of the target turbine blade, thus achieving the beneficial effect of improving the realism of the feature simulation for various data of the turbine blade.
[0076] The above description is merely an optional embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.
Claims
1. A design method for turbine blade feature simulation components considering temperature gradients, characterized in that, For a target turbine blade, the method includes: A three-dimensional model of the turbine blade is obtained based on the parameters of the target turbine blade. Finite element simulation is performed on the three-dimensional model of the turbine blade to determine the equivalent stress concentration area in the three-dimensional model of the turbine blade. The equivalent stress concentration area is the region with the largest equivalent stress in the three-dimensional model of the turbine blade. Acquire the target equivalent stress, target temperature gradient data, and target stress gradient data at the equivalent stress concentration location. The target stress gradient data includes the stress gradient data at the equivalent stress concentration location, starting from the equivalent stress concentration point. A three-dimensional model of the simulated part at the equivalent stress concentration location is established based on the initial feature parameters; Set the initial temperature field data for the three-dimensional model of the simulation component; Obtain the initial temperature gradient data of the three-dimensional model of the simulated component; When the initial temperature gradient data matches the target temperature gradient data, a displacement load is applied to the three-dimensional model of the simulation component so that the equivalent stress of the three-dimensional model of the simulation component is equal to the target equivalent stress. Obtain the initial stress gradient data of the three-dimensional model of the simulated part, starting from the equivalent stress concentration point; Determine whether the difference between the initial stress gradient data and the target stress gradient data is less than a difference threshold; When the difference is not less than the difference threshold, the initial feature parameters are adjusted, and the step of establishing the three-dimensional model of the simulated part of the equivalent stress concentration location based on the initial feature parameters is repeated. When the difference is less than the difference threshold, the initial feature parameter is determined as the target parameter, and the feature simulation part is manufactured with the target parameter.
2. The method according to claim 1, characterized in that, The finite element simulation of the three-dimensional model of the turbine blade includes: The operating parameters of the target turbine blade are obtained, including the temperature field data and load conditions of the target turbine blade. Finite element simulation was performed on the three-dimensional model of the turbine blade based on the operating parameters to obtain equivalent stress distribution data; Based on the equivalent stress distribution data, the locations of concentrated equivalent stress in the three-dimensional model of the turbine blade are determined.
3. The method according to claim 1, characterized in that, The process of acquiring the target stress gradient data includes: Obtain the direction of the first principal stress at the equivalent stress concentration site; The equivalent stress at the equivalent stress concentration point within the first plane is determined as the maximum value of the equivalent stress. The first plane is a plane perpendicular to the direction of the first principal stress at the equivalent stress concentration location. Obtain the target stress gradient data at the equivalent stress concentration point of the equivalent stress concentration region. The stress gradient data includes multiple stress values inside the equivalent stress concentration region in a first direction, starting from the equivalent stress concentration point. The first direction is the direction of the fastest descent path of the equivalent stress at the equivalent stress concentration point, which is perpendicular to the plane of maximum principal stress.
4. The method according to claim 1, characterized in that, The process of acquiring the target temperature gradient data includes: Starting from the equivalent stress concentration point, obtain multiple temperature values in a second direction, where the second direction is parallel to the surface normal at the equivalent stress concentration point and toward the interior of the equivalent stress concentration area.
5. The method according to claim 1, characterized in that, The equivalent stress concentration point is the leading edge of the root of the target turbine blade; The process of establishing a three-dimensional model of the simulated component at the equivalent stress concentration location based on initial feature parameters includes: A three-dimensional model of the simulated part is established, including a circular boss, a first connecting part, a second connecting part, a first chamfer structure, and a second chamfer structure. The first connecting part and the second connecting part are respectively located on both sides of the circular boss in the axial direction. The first connecting part is connected to one circular surface of the circular boss through the first chamfer structure, and the second connecting part is connected to the other circular surface of the circular boss through the second chamfer structure. The initial feature parameters include the first radius of the first chamfer structure, the second radius of the second chamfer structure, the thickness of the boss in the axial direction, and the diameter of the circular boss.
6. The method according to claim 5, characterized in that, The first connecting part includes a first connecting rod and a first clamping rod. One end of the first connecting rod is connected to the first chamfered structure, and the other end is connected to the first clamping rod. The diameter of the first connecting rod is smaller than the diameter of the circular boss.
7. The method according to claim 6, characterized in that, The second connecting part includes a second connecting rod and a second clamping rod. One end of the second connecting rod is connected to the second chamfered structure, and the other end is connected to the second clamping rod. The diameter of the second connecting rod is equal to the diameter of the first connecting rod.
8. The method according to claim 7, characterized in that, The simulated 3D model includes a central hole that passes through the circular boss, the first connecting part, the second connecting part, the first chamfered structure, and the second chamfered structure. The central hole is used to introduce air to adjust the initial temperature gradient data of the simulated 3D model.
9. The method according to claim 8, characterized in that, After obtaining the initial temperature gradient data of the three-dimensional model of the simulation component, the method further includes: When the initial temperature gradient data does not match the target temperature gradient data, the flow rate and temperature of the air introduced into the central hole are adjusted, and the step of obtaining the initial temperature gradient data of the three-dimensional model of the simulation part is repeated.
10. The method according to any one of claims 1 to 9, characterized in that, The method further includes: The lifespan of the simulated feature was tested. The life test data of the simulated feature is obtained.