Design method of turbine blade force-thermal load impact characteristic simulation piece

Abstract

The application relates to a design method of a turbine blade force-thermal load impact feature simulation piece, which considers the dynamic data of the target temperature rising rate of the equivalent stress concentration position in the process of accelerating the finite element simulation model from a static state to a target rotating speed, and also considers the transient data of the equivalent stress concentration point of the equivalent stress concentration position at the target rotating speed, the stress gradient data of the equivalent stress concentration point as a starting point and the target equivalent stress of the equivalent stress concentration position, so that the beneficial effect of improving the authenticity of simulation of various data of the feature simulation piece on the turbine blade is achieved.

Description

Technical Field

[0001] This application relates to the field of turbine blade technology, and more specifically, to a design method for a turbine blade force and thermal load impact characteristic simulation component. 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, characteristic simulation parts of the turbine blade are first obtained during blade design, and life tests are then conducted on these simulation parts.

[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, based on the three-dimensional model of the simulated component, a feature simulation component is manufactured.

[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] The purpose of this application is to overcome the shortcomings of the prior art and provide a design method for a turbine blade force and thermal load impact characteristic simulation component.

[0007] According to one aspect of this application, a method for designing a turbine blade force-thermal load impact characteristic simulation component is provided for a target turbine blade, the method comprising: A finite element simulation model of the target turbine blade is obtained based on the parameters of the target turbine blade. A first thermal load is applied to the finite element simulation model, and the target heating rate of the equivalent stress concentration part is determined during the process of the finite element simulation model accelerating from a stationary state to the target rotational speed. The equivalent stress concentration point of the equivalent stress concentration part at the target rotational speed, the stress gradient data starting from the equivalent stress concentration point, and the target equivalent stress of the equivalent stress concentration part are also determined. The equivalent stress concentration part is the part of the finite element simulation model with the largest equivalent stress. A geometric model of the equivalent stress concentration area is established based on the undetermined characteristic parameters; A second thermal load is applied to the geometric model, and the heating rate of the geometric model is obtained; When the heating rate of the geometric model matches the target heating rate, a displacement load is applied to the geometric model so that the equivalent stress of the geometric model is equal to the target equivalent stress. Obtain the initial stress gradient data of the geometric model 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 undetermined feature parameters are adjusted, and the step of establishing the geometric model of the equivalent stress concentration part based on the undetermined feature parameters is re-executed; When the difference is less than the difference threshold, the undetermined feature parameter is determined as the target parameter, and the feature simulation part is manufactured with the target parameter.

[0008] Optionally, the method further includes: When the heating rate of the geometric model does not match the target heating rate, the second heat load is adjusted, and the steps of applying the second heat load to the geometric model and obtaining the heating rate of the geometric model are repeated.

[0009] Optionally, the target heating rate includes a first heating rate, which is the heating rate at the equivalent stress concentration point of the equivalent stress concentration region.

[0010] Optionally, the target heating rate further includes a second heating rate, which is the heating rate at a target location extending a specified distance from the equivalent stress concentration point along a second direction toward the interior of the equivalent stress concentration region. The second direction is parallel to the surface normal at the equivalent stress concentration point and toward the interior of the equivalent stress concentration region.

[0011] Optionally, the first heating rate satisfies a first heating rate formula, which includes: ; in, The first heating rate, The temperature at which the equivalent stress concentration point of the finite element simulation model is located at the target rotational speed is given. The equivalent stress concentration point of the finite element simulation model is the temperature under the static state. The first moment when the finite element simulation model accelerates to the target rotational speed. The second moment of the finite element simulation model in the static state.

[0012] Optionally, the second heating rate satisfies a second heating rate formula, which includes: ; in, The second heating rate, The temperature at the target position in the finite element simulation model at the target rotational speed is [temperature value]. The temperature at the target location in the finite element simulation model under static conditions. This refers to the third moment when the finite element simulation model accelerates to the target rotational speed. This is the fourth moment of the finite element simulation model in the static state.

[0013] Optionally, applying a second thermal load to the geometric model includes: An external gas heating component and a gas cooling channel located inside the geometric model are provided; The geometric model is heated by the external gas heating assembly, and gas is introduced into the gas cooling channel to apply a second thermal load to the geometric model.

[0014] Optionally, adjusting the second thermal load includes: Adjust the gas flow rate of the external gas heating assembly and / or the gas flow rate in the gas cooling channel to adjust the second thermal load.

[0015] Optionally, the equivalent stress concentration site is the leading edge of the root of the target turbine blade; The process of establishing a geometric model of the equivalent stress concentration region based on undetermined feature parameters includes: A geometric model is established, comprising a circular boss, a first connecting portion, a second connecting portion, a first chamfer structure, and a second chamfer structure. The first connecting portion and the second connecting portion are located on opposite sides of the circular boss along the axial direction. The first connecting portion is connected to one circular surface of the circular boss via the first chamfer structure, and the second connecting portion is connected to the other circular surface of the circular boss via the second chamfer structure. The undetermined feature parameters include the first radius of the first chamfer structure, the second radius of the second chamfer structure, the thickness of the boss along the axial direction, and the diameter of the circular boss.

[0016] Optionally, the target rotational speed is 18,000 revolutions per minute.

[0017] The beneficial effects of the technical solutions provided in this application include at least the following: A method for designing turbine blade feature simulation components considering temperature gradients is provided. This method establishes comprehensive simulation baseline data by determining the target heating rate of the equivalent stress concentration area during the acceleration of the finite element simulation model from a stationary state to a target speed, the equivalent stress concentration point at the target speed, the stress gradient data starting from the equivalent stress concentration point, and the target equivalent stress at the equivalent stress concentration area. Then, a geometric model of the equivalent stress concentration area is established based on undetermined feature parameters. After applying a second thermal load to the geometric model, the heating rate of the geometric model is obtained. When the heating rate of the geometric model matches the target heating rate, a displacement load is applied to the geometric model to make the equivalent stress of the geometric model equal to the target equivalent stress. The difference between the initial stress gradient data and the target stress gradient data is then obtained. If this difference is not less than a threshold, the undetermined feature parameters are adjusted until the difference is less than the threshold. At this point, the undetermined feature parameters are determined as target parameters, and the feature simulation component is manufactured using these target parameters.

[0018] The simulated feature obtained through the above simulation takes into account the dynamic data of the target heating rate of the equivalent stress concentration part during the acceleration of the finite element simulation model from a static state to the target speed. It also takes into account the equivalent stress concentration point when the equivalent stress concentration part is at the target speed, the stress gradient data starting from the equivalent stress concentration point, and the target equivalent stress at the equivalent stress concentration part, etc., which achieves the beneficial effect of improving the realism of the simulation of various data of turbine blades by the simulated feature.

[0019] 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

[0020] 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.

[0021] Figure 1 This is a flowchart illustrating a method for designing a turbine blade force and thermal load impact characteristic simulation component, as shown in an embodiment of this application.

[0022] Figure 2 This is a flowchart illustrating another method for designing a turbine blade force and thermal load impact characteristic simulation component, as shown in an embodiment of this application.

[0023] Figure 3 This is a temperature change curve of a finite element simulation model of a target turbine blade in an embodiment of this application.

[0024] Figure 4 This is a structural diagram of a finite element simulation model of a target turbine blade in an embodiment of this application.

[0025] Figure 5 This is a schematic diagram of the stress gradient at the leading edge stress concentration point of a turbine blade root in an embodiment of this application.

[0026] Figure 6 This is a structural diagram of another target turbine blade finite element simulation model provided in the embodiments of this application.

[0027] Figure 7 This is a schematic diagram of the geometric model of an equivalent stress concentration area provided in an embodiment of this application.

[0028] Figure 8 This is a comparison chart of temperature change curves of a finite element simulation model of a target turbine blade in an embodiment of this application.

[0029] Figure 9 This is a schematic diagram comparing the stress gradient at a stress concentration point in an embodiment of this application. Detailed Implementation

[0030] 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.

[0031] Figure 1 This is a flowchart illustrating a method for designing a turbine blade force and thermal load impact characteristic simulation component, as shown in an embodiment of this application. The method is used for a target turbine blade and may include the following steps: Step 101: Obtain the finite element simulation model of the target turbine blade based on the parameters of the target turbine blade.

[0032] Step 102: Apply the first thermal load to the finite element simulation model and determine the target heating rate of the equivalent stress concentration part, the equivalent stress concentration point when the equivalent stress concentration part is at the target speed, the stress gradient data starting from the equivalent stress concentration point, and the target equivalent stress at the equivalent stress concentration part during the process of the finite element simulation model accelerating from the stationary state to the target speed.

[0033] Among them, the equivalent stress concentration area is the area with the largest equivalent stress in the finite element simulation model.

[0034] Step 103: Establish a geometric model of the equivalent stress concentration area based on the undetermined characteristic parameters.

[0035] Step 104: Apply a second thermal load to the geometric model and obtain the heating rate of the geometric model.

[0036] Step 105: When the heating rate of the geometric model matches the target heating rate, apply a displacement load to the geometric model so that the equivalent stress of the geometric model is equal to the target equivalent stress.

[0037] Step 106: Obtain the initial stress gradient data of the geometric model starting from the equivalent stress concentration point.

[0038] Step 107: Determine whether the difference between the initial stress gradient data and the target stress gradient data is less than the difference threshold. If the difference is not less than the difference threshold, proceed to step 108; if the difference is less than the difference threshold, proceed to step 109.

[0039] Step 108: Adjust the undetermined feature parameters. Then repeat step 103.

[0040] Step 109: Determine the undetermined feature parameters as target parameters, and manufacture feature simulation parts using the target parameters.

[0041] In summary, this application provides a method for designing a turbine blade feature simulation component considering temperature gradients. This method establishes comprehensive simulation baseline data by determining the target heating rate of the equivalent stress concentration area during the acceleration of the finite element simulation model from a stationary state to a target speed, the equivalent stress concentration point at the target speed, the stress gradient data starting from the equivalent stress concentration point, and the target equivalent stress at the equivalent stress concentration area. Then, a geometric model of the equivalent stress concentration area is established based on the undetermined feature parameters. After applying a second thermal load to the geometric model, the heating rate of the geometric model is obtained. When the heating rate of the geometric model matches the target heating rate, a displacement load is applied to the geometric model to make the equivalent stress of the geometric model equal to the target equivalent stress. The difference between the initial stress gradient data and the target stress gradient data is then obtained. When this difference is not less than a difference threshold, the undetermined feature parameters are adjusted until the difference is less than the difference threshold. At this point, the undetermined feature parameters are determined as target parameters, and the feature simulation component is manufactured using the target parameters.

[0042] The simulated feature obtained through the above simulation takes into account the dynamic data of the target heating rate of the equivalent stress concentration part during the acceleration of the finite element simulation model from a static state to the target speed. It also takes into account the equivalent stress concentration point when the equivalent stress concentration part is at the target speed, the stress gradient data starting from the equivalent stress concentration point, and the target equivalent stress at the equivalent stress concentration part, etc., which achieves the beneficial effect of improving the realism of the simulation of various data of turbine blades by the simulated feature.

[0043] Figure 2 This is a flowchart illustrating another method for designing a turbine blade force and thermal load impact characteristic simulation component, as shown in an embodiment of this application. This method is used for a target turbine blade and may include the following steps: Step 201: Obtain the finite element simulation model of the target turbine blade based on the parameters of the target turbine blade.

[0044] In this step, a three-dimensional finite element simulation model of the target turbine blade can be obtained, and the material parameters of the blade (such as the density, elastic constant as a function of temperature, coefficient of thermal expansion, conductivity, specific heat, etc.) can be imported into the finite element simulation software.

[0045] Step 202: Apply the first thermal load to the finite element simulation model.

[0046] Additionally, this step can determine the target heating rate of the equivalent stress concentration area during the acceleration of the finite element simulation model from a stationary state to the target rotational speed, as well as the equivalent stress concentration point when the equivalent stress concentration area is at the target rotational speed, the stress gradient data starting from the equivalent stress concentration point, and the target equivalent stress at the equivalent stress concentration area.

[0047] Among them, the equivalent stress concentration area is the area with the largest equivalent stress in the finite element simulation model.

[0048] The target speed can be 18,000 revolutions per minute (rpm).

[0049] In one exemplary embodiment, the target heating rate includes a first heating rate, which is the heating rate at the equivalent stress concentration point of the equivalent stress concentration region.

[0050] Optionally, the target heating rate may further include a second heating rate, which is the heating rate at a target location extending a specified distance from the equivalent stress concentration point along a second direction toward the interior of the equivalent stress concentration region. The second direction is parallel to the surface normal at the equivalent stress concentration point and toward the interior of the equivalent stress concentration region.

[0051] Alternatively, please refer to Figure 3 and Figure 4 , Figure 3 This is a temperature variation curve of a finite element simulation model of a target turbine blade in one embodiment of this application. Figure 4 This is a structural diagram of a finite element simulation model of a target turbine blade in an embodiment of this application. The dangerous point at the leading edge blade root (point A) is the equivalent stress concentration point mentioned above. The location (point B) where the dangerous point at the leading edge blade root is 1 mm deep (of course, the specified distance can also be other distances, and this embodiment of the application does not limit this) is the target position extending a specified distance from the equivalent stress concentration point along the second direction toward the interior of the equivalent stress concentration point.

[0052] Wherein, the first heating rate satisfies the first heating rate formula, which includes: ; in, The first heating rate, The temperature at the equivalent stress concentration point of the finite element simulation model at the target rotational speed. The temperature at the equivalent stress concentration point in the finite element simulation model under static conditions. This represents the first moment when the finite element simulation model accelerates to the target rotational speed. This represents the second moment in the finite element simulation model when it is at rest.

[0053] In one exemplary embodiment, the second heating rate satisfies a second heating rate formula, which includes: ; in, For the second heating rate, The temperature at the target location in the finite element simulation model at the target rotational speed. The temperature at the target location in the finite element simulation model under static conditions. This refers to the third moment when the finite element simulation model accelerates to the target rotational speed. This represents the fourth moment in the finite element simulation model when it is at rest.

[0054] In other words, steady-state verification was performed in this embodiment: to ensure the accuracy of the model, boundary conditions were first set according to a certain stable service condition of the engine (taking stable operation at 18,000 rpm as an example), and steady-state / steady-state calculations were performed. Subsequently, the calculated key macroscopic parameters (such as mass flow rate, turbine outlet temperature, and pressure ratio) were compared with known experimental data to prove that the established calculation model has high accuracy and rationality.

[0055] Next, transient analysis is performed: Based on the reliable model that has passed steady-state verification, transient / unsteady calculations are carried out. According to the actual service conditions of the engine, key dynamic processes are simulated (taking engine start-up as an example). In this process, the boundary conditions (such as speed) are set as functions that change with time, thereby simulating the force-thermal shock experienced by the blades.

[0056] Then, through transient analysis, the transient flow field, transient temperature field and transient stress distribution of the blades at any time during the engine startup process are obtained. The equivalent stress concentration points can be identified through the transient stress cloud map.

[0057] After determining the location of the maximum equivalent stress concentration at the leading edge of the blade root at 18,000 rpm, key physical parameters are precisely extracted. These parameters include the temperature at that point (i.e., the maximum value of the temperature gradient), the maximum equivalent stress at that point, and the direction of the first principal stress used to determine the stress gradient extraction path.

[0058] Then, stress gradient data can be extracted in a plane perpendicular to the direction of the first principal stress, starting from the point of equivalent stress concentration and using the equivalent stress at that point as the maximum value. Since the stress gradient direction is the direction of the fastest stress decrease, and this direction lies in a plane perpendicular to the direction of the first principal stress, data is extracted in this plane, starting from the stress concentration point and following the path of the fastest decrease in equivalent stress. The relationship between the equivalent stress value and distance along this path is plotted as a curve. Please refer to [reference needed]. Figure 5 , Figure 5This is a schematic diagram of the stress gradient at the leading edge stress concentration point of a turbine blade root in an embodiment of this application.

[0059] Step 203: Establish a geometric model of the equivalent stress concentration area based on the undetermined characteristic parameters.

[0060] The equivalent stress concentration point is the leading edge of the root of the target turbine blade; Please refer to Figure 6 and Figure 7 , Figure 6 This is a structural diagram of another target turbine blade finite element simulation model provided in this application embodiment. Figure 7 This is a schematic diagram of the geometric model of an equivalent stress concentration region provided in an embodiment of this application. Figure 7 Therefore Figure 6 Based on the rounded chamfer R in the middle, for Figure 6 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.

[0061] 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.

[0062] 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.

[0063] 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 7 The image shows a cross-section of the central hole 26, which is used to introduce air (such as cold air) to regulate the temperature data of the ensemble model.

[0064] Step 204: Apply a second thermal load to the geometric model and obtain the heating rate of the geometric model.

[0065] An external gas heating component and a gas cooling channel located inside the geometric model are installed; the geometric model is heated by the external gas heating component, and gas is introduced into the gas cooling channel to apply a second thermal load to the geometric model.

[0066] Step 205: When the heating rate of the geometric model matches the target heating rate, apply a displacement load to the geometric model so that the equivalent stress of the geometric model is equal to the target equivalent stress.

[0067] Please refer to Figure 8 , Figure 8 This is a comparison chart of temperature change curves of a finite element simulation model of a target turbine blade in an embodiment of this application. The critical point on the outer wall of the simulated feature is the equivalent stress concentration point of the geometric model. The location 1 mm deep from the critical point on the outer wall of the simulated feature is the target position of the equivalent stress concentration point of the geometric model, extending a specified distance inward along the second direction towards the equivalent stress concentration point. Matching can be determined based on this chart; for example, a difference in heating rate of less than 5% is considered a match.

[0068] Step 206: When the heating rate of the geometric model does not match the target heating rate, adjust the second thermal load. Execute step 204.

[0069] The second thermal load can be adjusted by adjusting the gas flow rate of the external gas heating component and / or the gas flow rate in the gas cooling channel.

[0070] Step 207: Obtain the initial stress gradient data of the geometric model starting from the equivalent stress concentration point.

[0071] The process of obtaining the initial stress gradient data of the geometric model starting from the equivalent stress concentration point can refer to the above steps. For example, the initial stress gradient data can be extracted from the equivalent stress concentration point in a plane perpendicular to the first principal stress direction, with the equivalent stress at that point as the maximum value.

[0072] Step 208: Determine whether the difference between the initial stress gradient data and the target stress gradient data is less than the difference threshold. If the difference is not less than the difference threshold, proceed to step 209; if the difference is less than the difference threshold, proceed to step 210.

[0073] Please refer to Figure 9 , Figure 9 This is a schematic diagram comparing the stress gradient at a stress concentration point in an embodiment of this application. The leading edge of the turbine blade root represents the curve of the target stress gradient data, and the feature simulation component R(2.0, 1.3)-h0.8-L10 represents the curve of an initial stress gradient data. The threshold value can be 5% of the target stress gradient data. Figure 9 If the difference shown is less than 3.5%, the next step can be proceeded.

[0074] Step 209: When the difference is not less than the difference threshold, adjust the undetermined feature parameters. Execute step 203.

[0075] 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.

[0076] Step 210: When the difference is less than the difference threshold, determine the undetermined feature parameter as the target parameter, and manufacture the feature simulation part with the target parameter.

[0077] When the stress gradient error meets the difference threshold requirement, the current geometric parameters are the final target parameters.

[0078] Step 211: Perform a life test on the feature simulation part to obtain the life test data of the feature simulation part.

[0079] For example, fatigue or creep tests can be performed on fabricated simulants to test their lifespan under simulated real-world conditions, such as applied temperature gradients and mechanical loads. For example, a thermal gradient mechanical fatigue testing machine can be used to reproduce the temperature gradient 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.

[0080] In summary, this application provides a method for designing a turbine blade feature simulation component considering temperature gradients. This method establishes comprehensive simulation baseline data by determining the target heating rate of the equivalent stress concentration area during the acceleration of the finite element simulation model from a stationary state to a target speed, the equivalent stress concentration point at the target speed, the stress gradient data starting from the equivalent stress concentration point, and the target equivalent stress at the equivalent stress concentration area. Then, a geometric model of the equivalent stress concentration area is established based on the undetermined feature parameters. After applying a second thermal load to the geometric model, the heating rate of the geometric model is obtained. When the heating rate of the geometric model matches the target heating rate, a displacement load is applied to the geometric model to make the equivalent stress of the geometric model equal to the target equivalent stress. The difference between the initial stress gradient data and the target stress gradient data is then obtained. When this difference is not less than a difference threshold, the undetermined feature parameters are adjusted until the difference is less than the difference threshold. At this point, the undetermined feature parameters are determined as target parameters, and the feature simulation component is manufactured using the target parameters.

[0081] The simulated feature obtained through the above simulation takes into account the dynamic data of the target heating rate of the equivalent stress concentration part during the acceleration of the finite element simulation model from a static state to the target speed. It also takes into account the equivalent stress concentration point when the equivalent stress concentration part is at the target speed, the stress gradient data starting from the equivalent stress concentration point, and the target equivalent stress at the equivalent stress concentration part, etc., which achieves the beneficial effect of improving the realism of the simulation of various data of turbine blades by the simulated feature.

[0082] In this application, the term "and / or" is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, or B existing alone. Additionally, the character " / " in this document generally indicates that the preceding and following related objects have an "or" relationship.

[0083] In this application, the term "at least one of A and B" merely describes the relationship between related objects, indicating that three relationships can exist. For example, "at least one of A and B" can represent: A existing alone, A and B existing simultaneously, and B existing alone. Similarly, "at least one of A, B, and C" indicates that seven relationships can exist, representing: A existing alone, B existing alone, C existing alone, A and B existing simultaneously, A and C existing simultaneously, C and B existing simultaneously, and A, B, and C existing simultaneously. Likewise, "at least one of A, B, C, and D" indicates that fifteen relationships can exist, representing: A existing alone, B existing alone, C existing alone, D existing alone, A and B existing simultaneously, A and C existing simultaneously, A and D existing simultaneously, C and B existing simultaneously, D and B existing simultaneously, C and D existing simultaneously, A, B, and C existing simultaneously, A, B, and D existing simultaneously, A, C, and D existing simultaneously, and A, B, C, and D existing simultaneously.

[0084] In this application, the terms "first," "second," "third," and "fourth," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. The term "multiple" refers to two or more unless otherwise expressly defined.

[0085] 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 method of designing a turbine blade force-thermal load impact feature mockup, characterized in that, For a target turbine blade, the method includes: A finite element simulation model of the target turbine blade is obtained based on the parameters of the target turbine blade. A first thermal load is applied to the finite element simulation model, and the target temperature rise rate of the equivalent stress concentration part is determined during the process of the finite element simulation model accelerating from a stationary state to the target rotational speed. The equivalent stress concentration point of the equivalent stress concentration part at the target rotational speed, the stress gradient data starting from the equivalent stress concentration point, and the target equivalent stress of the equivalent stress concentration part are also determined. The equivalent stress concentration part is the part of the finite element simulation model with the largest equivalent stress. A geometric model of the equivalent stress concentration area is established based on the undetermined characteristic parameters; A second thermal load is applied to the geometric model, and the heating rate of the geometric model is obtained; When the heating rate of the geometric model matches the target heating rate, a displacement load is applied to the geometric model so that the equivalent stress of the geometric model is equal to the target equivalent stress. Obtain the initial stress gradient data of the geometric model 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 undetermined feature parameters are adjusted, and the step of establishing the geometric model of the equivalent stress concentration part based on the undetermined feature parameters is re-executed; When the difference is less than the difference threshold, the undetermined 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 method further includes: When the heating rate of the geometric model does not match the target heating rate, the second heat load is adjusted, and the steps of applying the second heat load to the geometric model and obtaining the heating rate of the geometric model are repeated.

3. The method according to claim 1, characterized in that, The target heating rate includes a first heating rate, which is the heating rate at the equivalent stress concentration point of the equivalent stress concentration region.

4. The method according to claim 3, characterized in that, The target heating rate further includes a second heating rate, which is the heating rate at a target location extending a specified distance from the equivalent stress concentration point along a second direction toward the interior of the equivalent stress concentration region. The second direction is parallel to the surface normal at the equivalent stress concentration point and toward the interior of the equivalent stress concentration region.

5. The method according to claim 3, characterized in that, The first heating rate satisfies a first heating rate formula, which includes: ； in, The first heating rate, The temperature at which the equivalent stress concentration point of the finite element simulation model is located at the target rotational speed is given. The equivalent stress concentration point of the finite element simulation model is the temperature under the static state. The first moment when the finite element simulation model accelerates to the target rotational speed. The second moment of the finite element simulation model in the static state.

6. The method according to claim 4, characterized in that, The second heating rate satisfies the second heating rate formula, which includes: ； in, The second heating rate, The temperature at the target position in the finite element simulation model at the target rotational speed is [temperature value]. The temperature at the target location in the finite element simulation model under static conditions. This refers to the third moment when the finite element simulation model accelerates to the target rotational speed. This is the fourth moment of the finite element simulation model in the static state.

7. The method according to claim 2, characterized in that, The loading of the second thermal load onto the geometric model includes: An external gas heating component and a gas cooling channel located inside the geometric model are provided; The geometric model is heated by the external gas heating assembly, and gas is introduced into the gas cooling channel to apply a second thermal load to the geometric model.

8. The method according to claim 7, characterized in that, The adjustment of the second thermal load includes: Adjust the gas flow rate of the external gas heating assembly and / or the gas flow rate in the gas cooling channel to adjust the second thermal load.

9. 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 geometric model of the equivalent stress concentration region based on undetermined feature parameters includes: A geometric model is established, comprising a circular boss, a first connecting portion, a second connecting portion, a first chamfer structure, and a second chamfer structure. The first connecting portion and the second connecting portion are located on opposite sides of the circular boss along the axial direction. The first connecting portion is connected to one circular surface of the circular boss via the first chamfer structure, and the second connecting portion is connected to the other circular surface of the circular boss via the second chamfer structure. The undetermined feature parameters include the first radius of the first chamfer structure, the second radius of the second chamfer structure, the thickness of the boss along the axial direction, and the diameter of the circular boss.

10. The method according to any one of claims 1 to 9, characterized in that, The target speed is 18,000 revolutions per minute.

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