Method, device, electronic device and storage medium for determining the life of a turbine blade

Abstract

The present application provides a method, device, electronic device and storage medium for determining the life of a turbine blade. The method includes: obtaining the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature and turbine inlet temperature of a gas turbine unit during different working hours; calculating the temperature field corresponding to the turbine blade in the gas turbine unit at different working hours according to the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature and turbine inlet temperature; determining the stress tensor matrix corresponding to the turbine blade according to the elastic matrix of the turbine blade, the temperature field corresponding to the turbine blade at each working hour and the blade rotation speed corresponding to the working hour in the historical working process of the turbine blade; and determining the life of the turbine blade according to all the stress tensor matrices and the stress life formula. By means of the present application, the amount of calculation can be reduced and the time for determining the life of the turbine blade can be saved.

Description

Technical Field

[0001] The present application relates to the technical field of turbine blades, and in particular, to a method, device, electronic device and storage medium for determining the life of a turbine blade. Background Art

[0002] With the development of industry, gas turbines have also been applied in various fields. However, during the start-up and shutdown processes of gas turbines, the loads on the turbine blades in the gas turbines will shorten the service life of the turbine blades and reduce the reliability of blade use. Only by accurately predicting the thermo-mechanical fatigue life of the blades can the safe period of the blades be determined and the reliability of blade use be ensured.

[0003] In the prior art, the life of a turbine blade is determined by numerical simulation calculation. It is necessary to separately simulate the transient working processes of the three major components of the gas turbine, namely the compressor, the combustor, and the turbine, to obtain detailed information on the flow and heat transfer of these three components, and then convert this information into the data required for the simulation calculation of the transient temperature field of the blade and the blade life through a large amount of calculations. Obviously, the computational amount of this method is very large and will consume a lot of time. Summary of the Invention

[0004] In view of this, the purpose of the present application is to provide a method, device, electronic device and storage medium for determining the life of a turbine blade, which can reduce the computational amount and save the time for determining the life of the turbine blade.

[0005] In a first aspect, an embodiment of the present application provides a method for determining the life of a turbine blade, the method comprising:

[0006] Obtaining the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a working gas turbine unit at different working durations;

[0007] Calculating the temperature field corresponding to the turbine blade in the gas turbine unit at different working durations according to the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature;

[0008] Determining the stress tensor matrix corresponding to the turbine blade according to the elastic matrix of the turbine blade, the temperature field corresponding to the turbine blade at each working duration, and the blade rotation speed corresponding to the working duration in the historical working process of the turbine blade;

[0009] Determining the life of the turbine blade according to all the stress tensor matrices and the stress-life formula.

[0010] In a possible implementation manner, obtaining the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a working gas turbine unit at different working durations includes:

[0011] Obtain the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the gas turbine unit in operation at different operating durations according to a preset initial time interval;

[0012] Calculate the heat transfer boundary values corresponding to different operating durations of the turbine blade based on the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature; the heat transfer boundary values include the heat transfer coefficient and the fluid temperature;

[0013] Judge whether the absolute value of the difference between the heat transfer boundary values of two adjacent operating durations in time meets a preset threshold;

[0014] If the absolute value does not meet the preset threshold, insert a collection point in the middle of the end time points corresponding to the two operating durations respectively; according to the preset initial time interval and all collection points, judge again whether the absolute value of the difference between the heat transfer boundary values of two adjacent operating durations in the current working process meets the preset threshold;

[0015] If the absolute value meets the preset threshold, take the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the gas turbine unit obtained in different operating durations in the current working process as the final obtained results.

[0016] In a possible implementation manner, calculate the temperature field corresponding to different operating durations of the turbine blade in the gas turbine unit according to the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature, including:

[0017] Perform mesh division on the three-dimensional model of the turbine blade according to the shape characteristics and heat transfer characteristics of the turbine blade; the heat transfer characteristics include the heat transfer coefficient and the heat flux density;

[0018] Calculate the temperature at the position of each grid of the turbine blade at different operating durations according to the heat transfer boundary values of each operating duration and the position of each grid;

[0019] Determine the temperature field corresponding to different operating durations of the turbine blade according to the temperature at the position of each grid of the turbine blade at different operating durations.

[0020] In a possible implementation manner, determine the stress tensor matrix corresponding to the turbine blade for the elastic matrix of the turbine blade, the temperature field corresponding to each operating duration of the turbine blade, and the blade speed corresponding to the operating duration of the turbine blade in the historical working process, including:

[0021] Apply the blade speed and temperature field corresponding to the operating duration of the turbine blade in the historical working process and in the current working process to the turbine blade;

[0022] Based on the yield criterion of the turbine blade, according to the elastic matrix of the turbine blade and the temperature fields at different working durations, determine the stress tensor matrix corresponding to each grid position of the turbine blade at different working durations during the current working process.

[0023] In a possible implementation manner, according to all the stress tensor matrices and the stress-life formula, determine the life of the turbine blade, including:

[0024] According to all the stress tensor matrices, calculate the difference between the maximum value and the minimum value of the stress tensor at each node position in each grid of the turbine blade during the current working process, and obtain the stress tensor amplitude at each node position;

[0025] According to the stress tensor amplitude, use the stress-life formula to calculate the low-cycle fatigue life at each node position;

[0026] Determine the minimum low-cycle fatigue life as the life of the turbine blade.

[0027] In a second aspect, an embodiment of the present application further provides a device for determining the life of a turbine blade, and the device includes:

[0028] An acquisition module, configured to acquire the compressor inlet flow rate, the compressor outlet pressure, the compressor outlet temperature, and the turbine inlet temperature of the gas turbine unit during operation at different working durations;

[0029] A calculation module, configured to calculate the temperature field corresponding to the turbine blade in the gas turbine unit at different working durations according to the compressor inlet flow rate, the compressor outlet pressure, the compressor outlet temperature, and the turbine inlet temperature;

[0030] A determination module: configured to determine the stress tensor matrix corresponding to the turbine blade according to the elastic matrix of the turbine blade, the temperature field corresponding to the turbine blade at each working duration, and the blade rotation speed corresponding to the working duration during the historical working process of the turbine blade;

[0031] The determination module is further configured to determine the life of the turbine blade according to all the stress tensor matrices and the stress-life formula.

[0032] In a possible implementation manner, the acquisition module is specifically configured to acquire the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a gas turbine unit in operation at different working durations according to a preset initial time interval; calculate the heat transfer boundary values corresponding to the turbine blades at different working durations according to the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature; the heat transfer boundary values include the heat transfer coefficient and the fluid temperature; determine whether the absolute value of the difference between the heat transfer boundary values at two adjacent working durations in time meets a preset threshold; if the absolute value does not meet the preset threshold, insert a collection point at the middle of the end time points corresponding to the two working durations respectively; according to the preset initial time interval and all the collection points, determine again whether the absolute value of the difference between the heat transfer boundary values at two adjacent working durations in time during the current working process meets the preset threshold; if the absolute value meets the preset threshold, use the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the gas turbine unit obtained during the current working process at different working durations as the final acquisition result.

[0033] In a possible implementation manner, the calculation module is specifically configured to perform mesh division on the three-dimensional model of the turbine blade according to the shape characteristics and heat transfer characteristics of the turbine blade; the heat transfer characteristics include the heat transfer coefficient and the heat flux density; calculate the temperature at the position of each grid of the turbine blade at different working durations according to the heat transfer boundary values at each working duration and the position of each grid; determine the temperature field corresponding to the turbine blade at different working durations according to the temperature at the position of each grid of the turbine blade at different working durations.

[0034] In a possible implementation manner, the determination module is specifically configured to apply the blade rotation speed and temperature field corresponding to the working duration of the turbine blade in the historical working process and in the current working process to the turbine blade; based on the yield criterion of the turbine blade, determine the stress tensor matrix corresponding to the position of each grid of the turbine blade at different working durations in the current working process according to the elastic matrix of the turbine blade and the temperature field at different working durations.

[0035] In a possible implementation manner, the determination module is further configured to calculate the difference between the maximum stress tensor and the minimum stress tensor at the position of each node in each grid of the turbine blade during the current working process according to all the stress tensor matrices, to obtain the stress tensor amplitude at the position of each node; calculate the low-cycle fatigue life at the position of each node according to the stress tensor amplitude using the stress-life formula; determine the minimum low-cycle fatigue life as the life of the turbine blade.

[0036] In a third aspect, an electronic device includes: a processor, a memory, and a bus. The memory stores machine-readable instructions executable by the processor. When the electronic device runs, the processor communicates with the memory through the bus. When the machine-readable instructions are executed by the processor, the steps of the method for determining the life of a turbine blade as described in the first aspect above are performed.

[0037] In a fourth aspect, a computer-readable storage medium stores a computer program. When the computer program is run by a processor, the steps of the method for determining the life of a turbine blade as described in the first aspect above are performed.

[0038] This application provides a method, apparatus, electronic device, and storage medium for determining the life of a turbine blade. The method includes: obtaining the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a gas turbine unit during different working durations; calculating the temperature field corresponding to the turbine blade in the gas turbine unit at different working durations according to the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature; determining the stress tensor matrix corresponding to the turbine blade based on the elastic matrix of the turbine blade, the temperature field corresponding to the turbine blade at each working duration, and the blade rotation speed corresponding to the working duration in the historical working process of the turbine blade; and determining the life of the turbine blade according to all the stress tensor matrices and the stress-life formula. By obtaining the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the gas turbine unit during different working durations, calculating the temperature field corresponding to different working durations, then determining the stress tensor matrix corresponding to the turbine blade at different working durations, and finally determining the life of the turbine blade according to the stress-life formula, this application reduces the amount of calculation and saves the time for determining the life of the turbine blade.

[0039] To make the above objects, features, and advantages of this application more obvious and understandable, the following specific preferred embodiments are given and described in detail in conjunction with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] To more clearly illustrate the technical solutions of the embodiments of this application, the following briefly introduces the drawings required for the embodiments. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as limiting the scope. For those of ordinary skill in the art, other related drawings can be obtained based on these drawings without creative efforts.

[0041] Figure 1 Shows a flowchart of a method for determining the life of a turbine blade provided by an embodiment of this application;

[0042] Figure 2The flowchart of another method for determining the life of a turbine blade provided by an embodiment of the present application is shown;

[0043] Figure 3 The structural schematic diagram of a device for determining the life of a turbine blade provided by an embodiment of the present application is shown;

[0044] Figure 4 The structural schematic diagram of an electronic device provided by an embodiment of the present application is shown. Detailed implementation manners

[0045] To make the objectives, technical solutions, and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. It should be understood that the accompanying drawings in the present application are only for the purposes of illustration and description, and are not used to limit the protection scope of the present application. In addition, it should be understood that the schematic drawings are not drawn in actual proportions. The flowcharts used in the present application show the operations implemented according to some embodiments of the present application. It should be understood that the operations in the flowchart may not be implemented in sequence, and the steps without logical context relationships may be reversed in order or implemented simultaneously. In addition, those skilled in the art can add one or more other operations to the flowchart or remove one or more operations from the flowchart under the guidance of the content of the present application.

[0046] In addition, the described embodiments are only some embodiments of the present application, rather than all embodiments. The components of the embodiments of the present application described and illustrated in the accompanying drawings here can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the present application claimed, but only represents the selected embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative efforts belong to the protection scope of the present application.

[0047] To enable those skilled in the art to use the content of the present application, the following implementation manners are given in combination with a specific application scenario, the "turbine blade technology field". For those skilled in the art, without departing from the spirit and scope of the present application, the general principles defined here can be applied to other embodiments and application scenarios. Although the present application is mainly described around the "turbine blade technology field", it should be understood that this is only an exemplary embodiment.

[0048] The following provides a detailed description of a method for determining the life of a turbine blade provided by an embodiment of the present application.

[0049] Please refer to Figure 1 , Figure 1Flow chart of a method for determining the life of a turbine blade provided by an embodiment of the present application.

[0050] The following describes each step of the embodiment of the present application by way of example:

[0051] S101. Obtain the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a gas turbine unit in operation at different operating durations.

[0052] Further, according to a preset initial time interval, obtain the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a gas turbine unit in operation at different operating durations.

[0053] For example, if the preset initial time interval is 1 s, the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the turbine blade during operation for 1 s, 2 s, 3 s,..., Ns will be obtained.

[0054] Further, according to the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature, calculate the heat transfer boundary values corresponding to the turbine blade at different operating durations.

[0055] Among them, the heat transfer boundary values include the heat transfer coefficient and the fluid temperature. The heat transfer coefficient includes the inner heat transfer coefficient and the outer heat transfer coefficient, and the fluid temperature includes the inner fluid temperature and the outer fluid temperature.

[0056] For example, if the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature during operation for 1 s, 2 s, and 3 s are obtained, then the heat transfer boundary values during operation for 1 s, 2 s, and 3 s will be calculated respectively according to the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature during operation for 1 s, 2 s, and 3 s.

[0057] Here, the outer heat transfer coefficient h g and the outer fluid temperature T g,local are calculated according to the following formula:

[0058]

[0059] T g,local = f2(T2, T3, P) × f1(x, y),

[0060]

[0061] k g = f4(T g,local ) = (0.086 × T g,local - 0.885) × 0.001;

[0062] where C0 is a known constant, m is the compressor inlet flow rate, μ g is the local gas dynamic viscosity, k g is the local gas thermal conductivity, f1, f2, f3, and f4 are the corresponding gas-side functions respectively, (x, y) is the position coordinate of the burner outlet section, p is the compressor outlet pressure, T2 is the compressor outlet temperature, and T3 is the turbine inlet temperature.

[0063] Here, the inner heat transfer coefficient h is calculated according to the following formula c and the outer fluid temperature T c,local :

[0064]

[0065] T c,local = f5(T2, T3, p) × f6(x, y, z),

[0066]

[0067] k c = f8(T c,local ) = (0.0507 × T c,local + 14.3931) * 0.001;

[0068] where C1 is a known constant, m is the compressor inlet flow rate, μ c is the local cold air dynamic viscosity, k c is the local cold air thermal conductivity, f5, f6, f7, and f8 are the corresponding gas-side functions respectively, (x, y, z) is the spatial coordinate of the turbine blade, p is the compressor outlet pressure, T2 is the compressor outlet temperature, and T3 is the turbine inlet temperature.

[0069] Furthermore, it is judged whether the absolute value of the difference between the heat transfer boundary values of two adjacent working durations in time satisfies a preset threshold; if the absolute value does not satisfy the preset threshold, a collection point is inserted in the middle of the end time points corresponding to the two working durations respectively; according to the preset initial time interval and all collection points, it is judged again whether the absolute value of the difference between the heat transfer boundary values of two adjacent working durations in time in the current working process satisfies the preset threshold; if the absolute value satisfies the preset threshold, the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the gas turbine unit obtained in different working durations in the current working process are used as the final obtained results.

[0070] Here, if the absolute value meets the preset threshold, during the current working process, according to the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature, calculate the heat transfer boundary values corresponding to different working durations of the turbine blade as the final calculation result.

[0071] Among them, the difference in the heat transfer boundary value includes the difference in the inner heat transfer coefficient, the difference in the outer heat transfer coefficient, the difference in the inner fluid temperature, and the difference in the outer fluid temperature. If the absolute value of any difference does not meet the preset condition, it means that the absolute value does not meet the preset threshold.

[0072] For example, the preset initial time interval is 1 s. By calculating the heat transfer boundary values at working durations of 1 s, 2 s, and 3 s, then it will be judged whether the absolute value of the difference in the heat transfer boundary values between two adjacent working durations in time (working duration of 1 s and working duration of 2 s, working duration of 2 s and working duration of 3 s) meets the preset threshold.

[0073] If the difference in the heat transfer boundary values between the working duration of 1 s and the working duration of 2 s does not meet the preset threshold, and the difference in the heat transfer boundary values between the working duration of 2 s and the working duration of 3 s meets the preset threshold, then a collection point will be inserted between the working duration of 1 s and the working duration of 2 s. According to the preset initial time interval and all collection points, it can be known that the heat transfer boundary values at working durations of 1 s, 1.5 s, 2 s, and 3 s in the current working process will be calculated, and then it will be judged again whether the absolute value of the difference in the heat transfer boundary values between two adjacent working durations in time (working duration of 1 s, working duration of 1.5 s, working duration of 1.5 s and working duration of 2 s, working duration of 2 s and working duration of 3 s) meets the preset threshold. If the judgment result shows that only the absolute value of the difference in the heat transfer boundary values between the working duration of 2 s and the working duration of 3 s does not meet the preset threshold, then a collection point will be inserted between the working duration of 2 s and the working duration of 3 s, and the heat transfer boundary values at working durations of 1 s, 1.5 s, 2 s, 2.5 s, and 3 s in the current working process will be calculated, and the judgment will be carried out again.

[0074] If the differences in the heat transfer boundary values between the working duration of 1 s and the working duration of 2 s, and between the working duration of 2 s and the working duration of 3 s both meet the preset threshold, then the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the gas turbine unit obtained at different working durations during the current working process will be used as the final obtained result.

[0075] S102. According to the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature, calculate the temperature field corresponding to different working durations of the turbine blade in the gas turbine unit.

[0076] Furthermore, the three-dimensional model of the turbine blade is meshed according to the shape characteristics and heat transfer characteristics of the turbine blade; the heat transfer characteristics include heat transfer coefficient and heat flux density.

[0077] Among them, the shape characteristics refer to the curvature of the turbine blade surface, and the heat transfer characteristics include the heat transfer coefficient and heat flux density.

[0078] Here, more grids are divided at locations where the curvature of the turbine blade surface is large, or the heat flux density is large, and the fluid temperature on the turbine blade surface changes dramatically. For the cooling structures on the inner surface of the turbine blade, such as film holes, spoiler columns, flow ribs, trailing edge slits and other smaller cooling structures, a grid size of 0.2D is selected, where D is the cooling characteristic size. For the pressure surface and suction surface of the outer surface of the turbine blade, a grid size of 0.03S is selected, where S is the chord length of the turbine blade. For the outer surfaces of the turbine blade with large curvature, such as the leading edge, trailing edge, and blade top, a grid size of 0.01L is selected, where L is the characteristic size of the surface.

[0079] Further, according to the heat exchange boundary value of each working time and the position of each grid, the temperature of each grid position of the turbine blade at different working times is calculated;

[0080] Here, the heat exchange boundary value corresponding to the turbine blade at different working times as the final calculation result in step S101 is applied to the position of the grid located on the geometric surface of the turbine blade, and the temperature of each grid position of the turbine blade at different working times is obtained by solving the following equation.

[0081] Heat conduction calculation equation:

[0082] Among them, T is the temperature at the location of the grid, λm is the thermal conductivity of the turbine blade material, ρ is the density of the turbine blade material, c is the specific heat capacity of the turbine blade material, and x, y, and z are the coordinates of the location of the grid.

[0083] Furthermore, according to the temperature of each grid position at the different working time of the turbine blade, the temperature field corresponding to the different working time of the turbine blade is determined.

[0084] S103, determining a stress tensor matrix corresponding to the turbine blade based on the elastic matrix of the turbine blade, the temperature field of the turbine blade corresponding to each working time, and the blade rotation speed of the turbine blade corresponding to the working time in the historical working process.

[0085] Further, applying a blade rotation speed and a temperature field corresponding to the working time of the turbine blade in the historical working process and in the current working process to the turbine blade;

[0086] For example, apply the blade rotation speed and temperature field corresponding to the working duration of the turbine blade in the current working process during the historical working process of the turbine blade. For example, if the current working duration of the turbine blade is 1 s, then apply the blade rotation speed and temperature field of the turbine blade when the working duration is 1 s during the historical working process.

[0087] Further, based on the yield criterion of the turbine blade, determine the stress tensor matrix corresponding to different working durations at the position of each grid in the current working process of the turbine blade according to the elastic matrix of the turbine blade and the temperature field of different working durations.

[0088] Among them, the yield criterion is the yield criterion corresponding to the material of the turbine blade. If the turbine blade is an isotropic material, the Von Mises (Von Mises Stress, equivalent stress) yield criterion is adopted. If the turbine blade is an anisotropic material, the Hill 48 yield criterion is adopted.

[0089] Here, based on the yield criterion of the turbine blade, according to the elastic matrix of the turbine blade and the temperature field of different working durations, obtain the stress field of the turbine blade corresponding to different durations in the current working process, and then extract the stress tensor matrix corresponding to different working durations at each grid in the current working process of the turbine blade.

[0090] Among them, the elastic matrix is the elastic matrix corresponding to the material of the turbine blade, and σ ij is the stress tensor along the ij direction of each node.

[0091] S104. Determine the life of the turbine blade according to all stress tensor matrices and the stress-life formula.

[0092] Further, according to all stress tensor matrices, calculate the difference between the maximum value and the minimum value of the stress tensor at the position of each node in each grid of the turbine blade in the current working process to obtain the stress tensor amplitude at the position of each node.

[0093] Further, according to the stress tensor amplitude, calculate the low-cycle fatigue life at the position of each node by using the stress-life formula.

[0094] Here, first calculate the equivalent stress amplitude at the position of each node through the following formula:

[0095]

[0096] Among them, is the equivalent stress amplitude, and Δσ ij is the stress amplitude along the ij direction at the position of each node.

[0097] Then, calculate the low-cycle fatigue life at the location of each node through the stress-life formula: where N f is the low-cycle fatigue life, B L is the fatigue strength coefficient, and n L is the fatigue strength index.

[0098] Furthermore, determine the minimum low-cycle fatigue life as the life of the turbine blade.

[0099] The present application provides a method for determining the life of a turbine blade. The method includes: obtaining the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a gas turbine unit in operation at different working durations; calculating the temperature field corresponding to the turbine blade in the gas turbine unit at different working durations according to the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature; determining the stress tensor matrix corresponding to the turbine blade according to the elastic matrix of the turbine blade, the temperature field corresponding to the turbine blade at each working duration, and the blade rotation speed corresponding to the working duration in the historical working process of the turbine blade; and determining the life of the turbine blade according to all the stress tensor matrices and the stress-life formula. By obtaining the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the gas turbine unit at different working durations, calculating the temperature field corresponding to different working durations, then determining the stress tensor matrix corresponding to the turbine blade at different working durations, and finally determining the life of the turbine blade according to the stress-life formula, the calculation amount is reduced and the time for determining the life of the turbine blade is saved.

[0100] Please refer to Figure 2 , Figure 2 which is a flowchart of another method for determining the life of a turbine blade provided by an embodiment of the present application. The descriptions of S201 to S205 can refer to the description of S101 and can achieve the same technical effects. The repeated content will not be elaborated. The method includes:

[0101] S201. Obtain the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a gas turbine unit in operation at different working durations according to a preset initial time interval.

[0102] Among them, the preset initial time interval is not specifically limited and can be determined according to actual situations.

[0103] S202. Calculate the heat transfer boundary values corresponding to the turbine blade at different working durations according to the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature.

[0104] S203. Determine whether the absolute value of the difference between the heat transfer boundary values of two adjacent working durations in time meets a preset threshold value.

[0105] Here, the preset threshold value means that the absolute value of the difference between the heat transfer boundary values of two adjacent working durations exceeds 20% of the heat transfer boundary value of the previous working duration among the two adjacent working durations.

[0106] S204. If the absolute value does not meet the preset threshold value, insert a collection point at the middle of the end time points corresponding to the two working durations; according to the preset initial time interval and all collection points, determine again whether the absolute value of the difference between the heat transfer boundary values of two adjacent working durations in the current working process meets the preset threshold value.

[0107] S205. If the absolute value meets the preset threshold value, use the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the gas turbine unit obtained during the current working process at different working durations as the final obtained results.

[0108] The method provided by the embodiments of the present application obtains the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a gas turbine unit at multiple different working durations by setting an initial time interval, then adds collection points by determining whether the absolute value of the difference between the heat transfer boundary values of two adjacent working durations in time meets the preset threshold value, and finally determines the final collection working duration to obtain the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the turbine blade at different working durations. Compared with obtaining all the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature during the working process of the turbine blade in the prior art, the calculation amount is reduced, and the time for determining the life of the turbine blade is saved.

[0109] Please refer to Figure 3 , Figure 3 which is a schematic structural diagram of a device for determining the life of a turbine blade provided by the present application. As shown in Figure 3 the device for determining the life of the turbine blade shown, includes:

[0110] An acquisition module 301, configured to acquire the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a gas turbine unit in operation at different working durations;

[0111] A calculation module 302, configured to calculate the temperature field corresponding to the turbine blade in the gas turbine unit at different working durations according to the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature;

[0112] Determination module 303: For the elastic matrix of the turbine blade, the temperature field corresponding to each working duration of the turbine blade, and the blade rotation speed corresponding to the working duration in the historical working process of the turbine blade, determine the stress tensor matrix corresponding to the turbine blade;

[0113] The determination module 303 is further configured to determine the life of the turbine blade according to all the stress tensor matrices and the stress-life formula.

[0114] In a possible implementation manner, the acquisition module 301 is specifically configured to acquire the compressor inlet flow rate, the compressor outlet pressure, the compressor outlet temperature, and the turbine inlet temperature of the gas turbine unit in operation at different working durations according to a preset initial time interval; calculate the heat transfer boundary values corresponding to the turbine blade at different working durations according to the compressor inlet flow rate, the compressor outlet pressure, the compressor outlet temperature, and the turbine inlet temperature; the heat transfer boundary values include the heat transfer coefficient and the fluid temperature; determine whether the absolute value of the difference between the heat transfer boundary values at two adjacent working durations in time meets a preset threshold; if the absolute value does not meet the preset threshold, insert a collection point in the middle of the end time points corresponding to the two working durations; according to the preset initial time interval and all the collection points, determine again whether the absolute value of the difference between the heat transfer boundary values at two adjacent working durations in time during the current working process meets the preset threshold; if the absolute value meets the preset threshold, use the compressor inlet flow rate, the compressor outlet pressure, the compressor outlet temperature, and the turbine inlet temperature of the gas turbine unit obtained during the current working process at different working durations as the final acquisition result.

[0115] In a possible implementation manner, the calculation module 302 is specifically configured to perform mesh division on the three-dimensional model of the turbine blade according to the shape characteristics and heat transfer characteristics of the turbine blade; the heat transfer characteristics include the heat transfer coefficient and the heat flux density; calculate the temperature at the position of each grid of the turbine blade at different working durations according to the heat transfer boundary values at each working duration and the position of each grid; determine the temperature field corresponding to the turbine blade at different working durations according to the temperature at the position of each grid of the turbine blade at different working durations.

[0116] In a possible implementation manner, the determination module 303 is specifically configured to apply the blade rotation speed and temperature field corresponding to the working duration of the turbine blade in the historical working process and in the current working process to the turbine blade; based on the yield criterion of the turbine blade, determine the stress tensor matrix corresponding to the position of each grid of the turbine blade at different working durations during the current working process according to the elastic matrix of the turbine blade and the temperature fields at different working durations.

[0117] In a possible implementation manner, the determining module 303 is further configured to calculate, according to all stress tensor matrices, the difference between the maximum stress tensor and the minimum stress tensor at the position of each node in each grid of the turbine blade during the current working process, so as to obtain the stress tensor amplitude at the position of each node; calculate the low-cycle fatigue life at the position of each node according to the stress tensor amplitude by using the stress-life formula; and determine the life of the turbine blade as the minimum low-cycle fatigue life.

[0118] The present application provides a device for determining the life of a turbine blade. The device includes: an obtaining module 301, configured to obtain the compressor inlet flow rate, the compressor outlet pressure, the compressor outlet temperature, and the turbine inlet temperature of a gas turbine unit during different working durations; a calculating module 302, configured to calculate the temperature field of the turbine blade in the gas turbine unit corresponding to different working durations according to the compressor inlet flow rate, the compressor outlet pressure, the compressor outlet temperature, and the turbine inlet temperature; a determining module 303: determining the stress tensor matrix corresponding to the turbine blade according to the elastic matrix of the turbine blade, the temperature field of the turbine blade corresponding to each working duration, and the blade rotation speed corresponding to the working duration of the turbine blade in the historical working process; and the determining module 303 is further configured to determine the life of the turbine blade according to all stress tensor matrices and the stress-life formula. By obtaining the compressor inlet flow rate, the compressor outlet pressure, the compressor outlet temperature, and the turbine inlet temperature of the gas turbine unit during different working durations, calculating the temperature field corresponding to different working durations, then determining the stress tensor matrix corresponding to the turbine blade at different working durations, and finally determining the life of the turbine blade according to the stress-life formula, the present application reduces the calculation amount and saves the time for determining the life of the turbine blade.

[0119] Please refer to Figure 4 , Figure 4 which is a schematic structural diagram of an electronic device provided by an embodiment of the present application. As Figure 4 shown in

[0120] the electronic device 400 includes a processor 401, a memory 402, and a bus. Figure 1 and Figure 2 When the electronic device 400 runs, the processor 401 communicates with the memory 402 through the bus. When the machine-readable instructions stored in the memory 402 are executed by the processor 401, the steps of the method for determining the life of the turbine blade in the method embodiments as described above

[0121] An embodiment of the present application also provides a computer-readable storage medium, on which a computer program is stored. When the computer program is run by a processor, it can execute the steps of the method for determining the life of a turbine blade in the method embodiment as described above. For the specific implementation manner, reference can be made to the method embodiment, which will not be elaborated herein. Figure 1 and Figure 2 shown in the method embodiment. For the specific implementation manner, reference can be made to the method embodiment, which will not be elaborated herein.

[0122] Those skilled in the art can clearly understand that for the convenience and brevity of description, the specific working processes of the systems, devices, and units described above can refer to the corresponding processes in the foregoing method embodiments, which will not be elaborated herein.

[0123] In several embodiments provided by the present application, it should be understood that the disclosed systems, devices, and methods can be implemented in other ways. The device embodiments described above are merely illustrative. For example, the division of the units is only a logical function division, and there can be other division methods in actual implementation. For another example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the couplings, direct couplings, or communication connections shown or discussed with each other can be through some communication interfaces. The indirect couplings or communication connections of the devices or units can be in electrical, mechanical, or other forms.

[0124] The units described as separate components may or may not be physically separated. The components shown as units may or may not be physical units, that is, they can be located in one place or distributed to multiple network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0125] In addition, in each embodiment of the present application, the functional units can be integrated in a processing unit, or each unit can exist physically alone, or two or more units can be integrated in one unit.

[0126] When the above-mentioned functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a non-volatile computer-readable storage medium executable by a processor. Based on such understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or part of this technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to enable a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in various embodiments of this application. The aforementioned storage medium includes: various media such as USB flash drives, mobile hard disks, read-only memories (ROM), random access memories (RAM), magnetic disks, or optical discs that can store program codes.

[0127] Finally, it should be noted that the above-mentioned embodiments are only specific implementation manners of this application, used to illustrate the technical solutions of this application, rather than limiting it. The protection scope of this application is not limited thereto. Although this application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: any person skilled in the art within the technical scope disclosed in this application can still modify the technical solutions recorded in the foregoing embodiments, or can easily think of changes, or perform equivalent replacements on some of the technical features; and these modifications, changes, or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of this application, and should all be covered by the protection scope of this application. Therefore, the protection scope of this application shall be subject to the protection scope of the claims.

Claims

1. A method for determining the life of a turbine blade, characterized in that, The method includes: Obtaining the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a gas turbine unit in operation at different operating durations; Calculating the heat transfer boundary values corresponding to different operating durations of the turbine blade according to the compressor inlet flow rate, the compressor outlet pressure, the compressor outlet temperature, and the turbine inlet temperature; the heat transfer boundary values include a heat transfer coefficient and a fluid temperature; Performing mesh division on the three-dimensional model of the turbine blade according to the shape characteristics and heat transfer characteristics of the turbine blade in the gas turbine unit; the heat transfer characteristics include a heat transfer coefficient and a heat flux density; Calculating the temperature at the position of each grid of the turbine blade at different operating durations according to the heat transfer boundary values at each operating duration and the position of each grid; Determining the temperature field corresponding to different operating durations of the turbine blade according to the temperature at the position of each grid of the turbine blade at different operating durations; Determining the stress tensor matrix corresponding to the turbine blade according to the elastic matrix of the turbine blade, the temperature field corresponding to each operating duration of the turbine blade, and the blade rotation speed corresponding to the operating duration in the historical operation process of the turbine blade; Determining the life of the turbine blade according to all the stress tensor matrices and the stress-life formula.

2. The method according to claim 1, characterized in that, The obtaining the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a gas turbine unit in operation at different operating durations includes: Obtaining the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the gas turbine unit in operation at different operating durations according to a preset initial time interval; Judging whether the absolute value of the difference between the heat transfer boundary values of two adjacent operating durations in time meets a preset threshold; If the absolute value does not meet the preset threshold, inserting a collection point at the middle of the end time points corresponding to the two operating durations; and judging again whether the absolute value of the difference between the heat transfer boundary values of two adjacent operating durations in time during the current operation process meets the preset threshold according to the preset initial time interval and all the collection points; If the absolute value meets the preset threshold, taking the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the gas turbine unit obtained during the current operation process at different operating durations as the final obtained result.

3. The method according to claim 1, characterized in that, The determining the stress tensor matrix corresponding to the turbine blade according to the elastic matrix of the turbine blade, the temperature field corresponding to each operating duration of the turbine blade, and the blade rotation speed corresponding to the operating duration in the historical operation process of the turbine blade includes: Applying the blade rotation speed and temperature field corresponding to the operating duration in the historical operation process and in the current operation process to the turbine blade; Based on the yield criterion of the turbine blade, determining the stress tensor matrix corresponding to the position of each grid of the turbine blade at different operating durations during the current operation process according to the elastic matrix of the turbine blade and the temperature fields at different operating durations.

4. The method according to claim 3, characterized in that, Determining the life of the turbine blade according to all stress tensor matrices and stress-life formulas includes: According to all stress tensor matrices, calculating the difference between the maximum stress tensor and the minimum stress tensor at the position of each node in each grid during the current working process of the turbine blade, and obtaining the stress tensor amplitude at the position of each node; According to the stress tensor amplitude, calculating the low-cycle fatigue life at the position of each node by using the stress-life formula; Determining the minimum low-cycle fatigue life as the life of the turbine blade.

5. A device for determining the life of a turbine blade, characterized in that, The device includes: An acquisition module for acquiring the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of a working gas turbine unit at different working durations; The acquisition module is further configured to calculate the heat transfer boundary values corresponding to the turbine blade at different working durations according to the compressor inlet flow rate, the compressor outlet pressure, the compressor outlet temperature, and the turbine inlet temperature; the heat transfer boundary values include a heat transfer coefficient and a fluid temperature; A calculation module for performing mesh division on the three-dimensional model of the turbine blade according to the shape characteristics and heat transfer characteristics of the turbine blade in the gas turbine unit; the heat transfer characteristics include a heat transfer coefficient and a heat flux density; calculating the temperature at the position of each grid of the turbine blade at different working durations according to the heat transfer boundary values at each working duration and the position of each grid; determining the temperature field corresponding to the turbine blade at different working durations according to the temperature at the position of each grid of the turbine blade at different working durations; A determination module for determining the stress tensor matrix corresponding to the turbine blade according to the elastic matrix of the turbine blade, the temperature field corresponding to the turbine blade at each working duration, and the blade rotation speed corresponding to the working duration in the historical working process of the turbine blade; The determination module is further configured to determine the life of the turbine blade according to all stress tensor matrices and stress-life formulas.

6. The device for determining the life of a turbine blade according to claim 5, characterized in that, The acquisition module is specifically configured to: Acquire the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the working gas turbine unit at different working durations according to a preset initial time interval; Judge whether the absolute value of the difference between the heat transfer boundary values of two adjacent working durations in time meets a preset threshold; If the absolute value does not meet the preset threshold, insert a collection point in the middle of the end time points corresponding to the two working durations; according to the preset initial time interval and all collection points, judge again whether the absolute value of the difference between the heat transfer boundary values of two adjacent working durations in time during the current working process meets the preset threshold; If the absolute value meets the preset threshold, use the compressor inlet flow rate, compressor outlet pressure, compressor outlet temperature, and turbine inlet temperature of the working gas turbine unit obtained during the current working process at different working durations as the final acquisition result.

7. An electronic device, characterized in that, Including: A processor, a memory, and a bus, wherein the memory stores machine-readable instructions executable by the processor. When the electronic device is running, the processor communicates with the memory via the bus, and the processor executes the machine-readable instructions to perform the steps of the method for determining the life of a turbine blade according to any one of claims 1 to 4.

8. A computer-readable storage medium, characterized in that, A computer program is stored on the computer-readable storage medium, and when the computer program is run by a processor, it performs the steps of the method for determining the life of a turbine blade according to any one of claims 1 to 4.

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