Method for correcting characteristic pattern of original component of gas turbine

Abstract

The invention is suitable for the technical field of gas turbine control, provides a method for correcting an original component feature map of a gas turbine, and aims to solve the problem that the actual operation environment of the gas turbine is complex and changeable, and the performance condition of a real component can not be accurately corresponding to the feature map only through one-time correction. Therefore, according to the method, static correction and dynamic scheduling of the component characteristic diagram are combined, the problem that the original component characteristic diagram is not matched with an actual system is solved, meanwhile, the problem that the error between a gas turbine simulation model and actual test run data is large is effectively solved, and then the modeling precision of the gas turbine is effectively improved.

Description

Technical Field

[0001] The present application belongs to the field of gas turbine control technology, and in particular to a method for correcting a characteristic diagram of an original component of a gas turbine. Background Art

[0002] At present, the modeling method commonly used at home and abroad is to use analytical methods to establish the mathematical model of the gas turbine. It mainly has the following steps: first, the characteristic curves of each component of the gas turbine are obtained by using the test data of the gas turbine, so as to obtain the performance parameters of the engine components through interpolation calculation. Secondly, the component-level model is established based on the characteristics of the system components, and according to the gas thermodynamics laws and physical laws followed in the working process of the gas turbine, the unknown parameters are iteratively solved in combination with the characteristics of the gas turbine components and the common working conditions, so as to establish the overall model of the gas turbine. In this process, the performance of the characteristic diagram directly determines the model accuracy of the gas turbine. However, the original component characteristic diagram is mostly obtained from previous test data and combined with engineering experience. Due to the characteristics of its system, the gas turbine is easily affected by the environment. Therefore, different test environments will also have a certain impact on the performance of its components. At the same time, with the continuous operation of the gas turbine, its own characteristics will change more or less. These factors will cause the original component characteristic diagram to be unable to match the actual performance parameters. Summary of the invention

[0003] The embodiment of the present application provides a method for correcting an original component characteristic diagram of a gas turbine, which can solve the problem in the prior art that the original component characteristic diagram cannot match the actual performance parameters.

[0004] In a first aspect, an embodiment of the present application provides a method for correcting a characteristic diagram of an original component of a gas turbine, comprising:

[0005] Drawing an initial two-dimensional characteristic map based on an original component characteristic map of a target gas turbine;

[0006] Acquiring demand design point data and steady-state operating point data of the target gas turbine;

[0007] By means of a data recalibration method, the initial two-dimensional characteristic diagram is corrected based on the demand design point data to obtain a first two-dimensional characteristic diagram;

[0008] Calculating the relative conversion speed corresponding to each steady-state operating point according to the steady-state operating point data, and expanding the first two-dimensional characteristic diagram based on the relative conversion speed by a linear interpolation method to obtain a second two-dimensional characteristic diagram, wherein the second two-dimensional characteristic diagram includes an expanded speed line corresponding to the relative conversion and an initial speed line of the initial two-dimensional characteristic diagram;

[0009] According to the condition that the overall error function between each speed line and each steady-state operating point in the second two-dimensional characteristic diagram is minimized, the second two-dimensional characteristic diagram is adjusted to obtain a third two-dimensional characteristic diagram;

[0010] According to the test data of the target gas turbine, when the simulation model of the target gas turbine performs real-time calculation, the third two-dimensional characteristic diagram is dynamically corrected so that the output result of the simulation model matches the test data.

[0011] Optionally, the step of correcting the initial two-dimensional characteristic diagram based on the demand design point data to obtain the first two-dimensional characteristic diagram by the data recalibration method includes:

[0012] Selecting actual design points in the initial two-dimensional characteristic diagram according to preset experimental data;

[0013] By means of data recalibration, the initial two-dimensional characteristic diagram is stretched with pressure ratio equal to 1, flow equal to 0, and efficiency equal to 0 as the scaling center, so that the actual design point is consistent with the demand design point corresponding to the demand design point data, thereby obtaining a first two-dimensional characteristic diagram.

[0014] Optionally, the step of adjusting the second two-dimensional characteristic diagram according to the condition that the overall error function between each speed line and each steady-state operating point in the second two-dimensional characteristic diagram is minimized to obtain the third two-dimensional characteristic diagram comprises:

[0015] Selecting a target correction point on a speed line corresponding to the steady-state operating point according to the steady-state operating point data;

[0016] The second two-dimensional characteristic diagram is adjusted according to the target correction point and the steady-state operating point so that the overall error function between each speed line and each steady-state operating point in the second two-dimensional characteristic diagram is minimized, thereby obtaining a two-dimensional characteristic diagram to be processed;

[0017] The expanded speed line in the two-dimensional characteristic diagram to be processed is removed to obtain the third two-dimensional characteristic diagram.

[0018] Optionally, the step of dynamically correcting the third two-dimensional characteristic diagram according to the test data of the target gas turbine when the simulation model of the target gas turbine performs real-time calculation includes:

[0019] Acquiring test design point data and test steady-state operating point data of the target gas turbine according to the test data of the target gas turbine, and calculating a relative conversion speed of the test steady-state operating point based on the test design point data and the test steady-state operating point data;

[0020] According to the relative converted speed, the isospeed lines corresponding to the relative converted speed are expanded by linear interpolation, and the operation data of the steady-state operating point is calculated according to the isospeed lines and the third two-dimensional characteristic diagram as the correction point data;

[0021] Acquire actual operating data of the target gas turbine, calculate an initial value of the correction value under steady-state conditions by a first preset formula according to the actual operating data and the correction point data, and calculate the initial value of the correction value under each steady-state condition, and correspond it to the relative converted speed one by one, and finally obtain a correction vector;

[0022] According to the correction vector, the third two-dimensional characteristic diagram is dynamically corrected when the simulation model of the target gas turbine performs real-time calculation.

[0023] Optionally, the step of calculating the target operating data of the steady-state operating point according to the constant speed line and the third two-dimensional characteristic diagram includes:

[0024] Functional relationships through different operating data:

[0025]

[0026]

[0027]

[0028] Calculate the operating data of the steady-state operating point, where π P i is the pressure ratio of the steady-state operating point in the test data, Z Pi is the pressure ratio coefficient of the steady-state operating point, They are respectively the maximum and minimum values ​​of pressure ratio, flow rate, and efficiency on the equal speed line corresponding to the steady-state operating point, W mqi is the flow rate obtained by interpolation at the steady-state operating point, η mqi is the efficiency obtained by interpolation at the steady-state operating point.

[0029] Optionally, the actual operation data and the correction point data are used to calculate an initial value of the correction value under steady-state conditions using the first preset formula, wherein the first preset formula is:

[0030]

[0031]

[0032] COE πd [i]=1

[0033] Among them, W rqi and η rqi It is the flow rate and efficiency when actually running to this steady-state operating point.

[0034] Optionally, the step of dynamically correcting the third two-dimensional characteristic diagram according to the correction vector when the simulation model of the target gas turbine performs real-time calculation includes:

[0035] Acquiring output data of the simulation model of the target gas turbine, and calculating real-time converted speed data based on the output data;

[0036] Calculating a real-time correction coefficient for the third two-dimensional characteristic diagram by a second preset formula according to the real-time converted speed data and the correction vector;

[0037] The correction value is updated according to the error value of the test data and the output data of the simulation model of the target gas turbine to form a new correction vector, and the third two-dimensional characteristic diagram is adjusted based on the updated correction vector to obtain the target two-dimensional characteristic diagram, so that the simulation model constructed based on the target two-dimensional characteristic diagram outputs a simulation result that matches the test data.

[0038] Optionally, the second preset formula is:

[0039] Coe Wd (t) = interp(COE Wd ,N qi ,n t )

[0040] Coe πd (t) = interp(COE πd ,N qi ,n t )

[0041] Coe ηd (t) = interp(COE ηd ,N qi ,n t )

[0042] Among them, Coe Wd (t), Coe πd (t), Coe ηd (t) corresponds to the dynamic correction coefficient of flow rate, pressure ratio and efficiency of the characteristic diagram at time t, COE Wd , COE πd , COE ηd , N qi is the correction vector and the relative conversion speed vector corresponding to the correction vector, n t is the converted speed at time t, and interp(X,Y,y) is the linear interpolation function.

[0043] Compared with the prior art, the embodiments of the present invention have the following beneficial effects:

[0044] Combining the static correction of the component characteristic diagram with dynamic scheduling not only solves the problem of the mismatch between the original component characteristic diagram and the actual system, but also effectively reduces the large error between the gas turbine simulation model and the actual test data, and effectively improves the accuracy of gas turbine modeling. Considering that the actual operating environment of the gas turbine is complex and changeable, a one-time correction alone cannot ensure that the characteristic diagram can accurately correspond to the performance of the real component. Combining the static correction of the component characteristic diagram with dynamic scheduling can more accurately correct the original component characteristic diagram and avoid the problem of mismatch between the original component characteristic diagram and the actual system. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0046] Figure 1 It is a flow chart of a method for correcting a characteristic diagram of an original component of a gas turbine provided in an embodiment of the present application;

[0047] Figure 2 is a flow chart of a method for correcting a characteristic diagram of an original component of a gas turbine provided by another embodiment of the present application;

[0048] Figure 3 It is a structural schematic diagram of a device for correcting a characteristic diagram of an original component of a gas turbine according to an embodiment of the present application;

[0049] Figure 4 is a structural block diagram of an electronic device in one embodiment;

[0050] Figure 5 It is a structural block diagram of a computer device in another embodiment. DETAILED DESCRIPTION

[0051] In the following description, specific details such as specific system structures, technologies, etc. are provided for the purpose of illustration rather than limitation, so as to provide a thorough understanding of the embodiments of the present application. However, it should be clear to those skilled in the art that the present application may also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to prevent unnecessary details from obstructing the description of the present application.

[0052] It should be understood that when used in the present specification and the appended claims, the term "comprising" indicates the presence of described features, wholes, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, wholes, steps, operations, elements, components and / or combinations thereof.

[0053] It should also be understood that the term “and / or” used in the specification and appended claims refers to any and all possible combinations of one or more of the associated listed items, and includes these combinations.

[0054] As used in the specification and appended claims of this application, the term "if" can be interpreted as "when" or "uponce" or "in response to determining" or "in response to detecting", depending on the context. Similarly, the phrase "if it is determined" or "if [described condition or event] is detected" can be interpreted as meaning "uponce it is determined" or "in response to determining" or "uponce [described condition or event] is detected" or "in response to detecting [described condition or event]", depending on the context.

[0055] In addition, in the description of the present application specification and the appended claims, the terms "first", "second", "third", etc. are only used to distinguish the descriptions and cannot be understood as indicating or implying relative importance.

[0056] References to "one embodiment" or "some embodiments" etc. described in the specification of this application mean that one or more embodiments of the present application include specific features, structures or characteristics described in conjunction with the embodiment. Therefore, the statements "in one embodiment", "in some embodiments", "in some other embodiments", "in some other embodiments", etc. that appear in different places in this specification do not necessarily refer to the same embodiment, but mean "one or more but not all embodiments", unless otherwise specifically emphasized in other ways. The terms "including", "comprising", "having" and their variations all mean "including but not limited to", unless otherwise specifically emphasized in other ways.

[0057] Figure 1 A schematic flow chart of a method for correcting a characteristic diagram of an original component of a gas turbine provided by the present application is shown. An embodiment of the present application provides a method for correcting a characteristic diagram of an original component of a gas turbine, comprising:

[0058] S101, drawing an initial two-dimensional characteristic diagram according to an original component characteristic diagram of a target gas turbine;

[0059] Exemplarily, the original component characteristic diagrams include gas turbine compressor and turbine characteristic diagrams, involving information such as relative conversion speed, pressure ratio, flow rate, efficiency, etc. The generated two-dimensional characteristic diagrams are pressure ratio-flow rate characteristic diagram (or flow rate-pressure ratio characteristic diagram) and pressure ratio-efficiency characteristic diagram;

[0060] S102, obtaining demand design point data and steady-state operating point data of the target gas turbine;

[0061] Exemplarily, the demand design point data and steady-state operating point data of the target gas turbine are obtained in the aerodynamic requirement file for controlling the target gas turbine; taking the compressor as an example, it at least includes the compressor inlet flow rate W c 、Pressure ratio π c And the efficiency η c , inlet temperature T0 and air pressure P0, compressor outlet pressure P 31 , power turbine outlet temperature T5, gas turbine speed n g and power turbine speed n p ;

[0062] S103, using a data recalibration method, correcting the initial two-dimensional characteristic diagram based on the demand design point data to obtain a first two-dimensional characteristic diagram;

[0063] S104, calculating the relative converted speed corresponding to each steady-state operating point according to the steady-state operating point data, and expanding the first two-dimensional characteristic diagram based on the relative converted speed by a linear interpolation method to obtain a second two-dimensional characteristic diagram, wherein the second two-dimensional characteristic diagram includes an expanded speed line corresponding to the relative conversion and an initial speed line of the initial two-dimensional characteristic diagram;

[0064] For example, the converted speed {n1, n2, n3, ..., n ds ,…,n a}, and compare it with the design point conversion speed to obtain the relative conversion speed {n cor1 ,n cor2 ,n cor3 ,…,1.0,…,n cora};

[0065] S105, adjusting the second two-dimensional characteristic diagram according to the condition that the overall error function between each speed line and each steady-state operating point corresponding to the speed in the second two-dimensional characteristic diagram is minimized, to obtain a third two-dimensional characteristic diagram;

[0066] S106. Based on the test data of the target gas turbine, when the simulation model of the target gas turbine performs real-time calculation, dynamically correct the third two-dimensional characteristic diagram so that the output result of the simulation model matches the test data.

[0067] Combining the static correction of the component characteristic diagram with dynamic scheduling not only solves the problem of the mismatch between the original component characteristic diagram and the actual system, but also effectively reduces the large error between the gas turbine simulation model and the actual test data, and effectively improves the accuracy of gas turbine modeling. Considering that the actual operating environment of the gas turbine is complex and changeable, a one-time correction alone cannot ensure that the characteristic diagram can accurately correspond to the performance of the real component. Combining the static correction of the component characteristic diagram with dynamic scheduling can more accurately correct the original component characteristic diagram and avoid the problem of mismatch between the original component characteristic diagram and the actual system.

[0068] In a possible implementation manner, the step of correcting the initial two-dimensional characteristic diagram based on the demand design point data to obtain the first two-dimensional characteristic diagram by the data recalibration method includes:

[0069] Selecting actual design points in the initial two-dimensional characteristic diagram according to preset experimental data;

[0070] By means of data recalibration, the initial two-dimensional characteristic diagram is stretched with pressure ratio equal to 1, flow equal to 0, and efficiency equal to 0 as the scaling center, so that the actual design point is consistent with the demand design point corresponding to the demand design point data, thereby obtaining a first two-dimensional characteristic diagram.

[0071] Exemplarily, data such as flow rate pressure ratio and efficiency of each component corresponding to the design point (the required design point data) are obtained from the pneumatic requirement file;

[0072] Select appropriate points from the characteristic diagram (refer to the experimental data file) as the design points of the original component characteristic diagram;

[0073] With the pressure ratio equal to 1, flow equal to 0, and efficiency equal to 0 as the scaling center, the original component characteristic diagram is stretched so that its design point is consistent with the design point required in the file, and the design point correction coefficient is as follows:

[0074]

[0075] In the formula, is the correction factor of design point flow rate, pressure ratio and efficiency, W ds , π ds , η ds W is the design point component characteristic in the aerodynamic requirements document. map , π map , ηmap Design point component properties in the original component property diagram.

[0076] According to the data of the first two-dimensional characteristic diagram, two speed lines closest to the relative converted speed corresponding to each steady-state operating point are selected, and the characteristic diagram is expanded by linear interpolation;

[0077] Taking the pressure ratio-flow characteristic diagram as an example, for the steady-state operating point p x For example, the closest speed lines are speed lines l1 and l2 (l2>l1), so the speed should be supplemented as n x The constant speed line l x ′, and the second two-dimensional characteristic diagram is obtained. The formula for each point on the newly added constant speed line is as follows:

[0078]

[0079] In a possible implementation manner, the step of adjusting the second two-dimensional characteristic diagram according to the condition that the overall error function between each speed line and each steady-state operating point in the second two-dimensional characteristic diagram is minimized to obtain the third two-dimensional characteristic diagram includes:

[0080] Selecting a target correction point on a speed line corresponding to the steady-state operating point according to the steady-state operating point data;

[0081] The second two-dimensional characteristic diagram is adjusted according to the target correction point and the steady-state operating point so that the overall error function between each speed line and each steady-state operating point in the second two-dimensional characteristic diagram is minimized, thereby obtaining a two-dimensional characteristic diagram to be processed;

[0082] The expanded speed line in the two-dimensional characteristic diagram to be processed is removed to obtain the third two-dimensional characteristic diagram.

[0083] Exemplarily, taking the design point as the origin, the supplemented characteristic diagram is adjusted by overall translation, stretching or rotation, so that the overall error function of each speed line and its corresponding steady-state operating point in the corrected component characteristic diagram is minimized, and the supplemented equal speed lines are deleted to keep the data dimension unchanged.

[0084] Exemplarily, according to the data of each steady-state operating point in the aerodynamic requirement file (the steady-state operating point data), based on engineering experience, a suitable correction point is selected on the equal speed line corresponding to the steady-state operating point data and matched with the steady-state operating point, and the objective function value is minimized by translation, stretching, rotation and other adjustments, and the adjusted characteristic diagram is obtained as the template characteristic diagram (the third two-dimensional characteristic diagram), wherein the formula of the objective function (error function) is as follows:

[0085] e s =∑e i

[0086] e i =L(p i ,l i ),i=1,2,…,num p

[0087] Where L(p,l) is the distance from point p to line l, num p is the number of steady-state operating points of the gas turbine.

[0088] Since the characteristic diagram is formed by connecting the engine characteristic data points corresponding to the constant speed lines, when calculating the distance from the steady-state operating point to its corresponding constant speed line, it can be simplified to calculating the distance from the point to the straight line formed by the two closest points on the constant speed line. At this point, the static correction process of the original component characteristic diagram is completed.

[0089] In a possible implementation manner, the step of dynamically correcting the third two-dimensional characteristic diagram according to the test data of the target gas turbine when the simulation model of the target gas turbine performs real-time calculation includes:

[0090] Acquiring test design point data and test steady-state operating point data of the target gas turbine according to the test data of the target gas turbine, and calculating a relative conversion speed of the test steady-state operating point based on the test design point data and the test steady-state operating point data;

[0091] According to the relative converted speed, expanding the constant speed line corresponding to the relative converted speed by linear interpolation, and calculating the correction point data of the steady-state operating point according to the constant speed line and the third two-dimensional characteristic diagram;

[0092] Acquire actual operating data of the target gas turbine, calculate an initial value of the correction value under steady-state conditions by a first preset formula according to the actual operating data and the correction point data, and calculate the initial value of the correction value under each steady-state condition, and correspond it to the relative converted speed one by one, and finally obtain a correction vector;

[0093] According to the correction vector, the third two-dimensional characteristic diagram is dynamically corrected when the simulation model of the target gas turbine performs real-time calculation.

[0094] In a possible implementation manner, the step of calculating the correction point data of the steady-state operating point according to the constant speed line and the third two-dimensional characteristic diagram includes:

[0095] Functional relationships through different operating data:

[0096]

[0097]

[0098]

[0099] Calculate the operating data of the steady-state operating point, where π Pi is the pressure ratio of the steady-state operating point in the test data, Z Pi is the pressure ratio coefficient of the steady-state operating point, They are respectively the maximum and minimum values ​​of pressure ratio, flow rate, and efficiency on the equal speed line corresponding to the steady-state operating point, W mqi is the flow rate obtained by interpolation at the steady-state operating point, η mqi is the efficiency obtained by interpolation at the steady-state operating point.

[0100] For example, the part of the system in steady state in the test data is selected, the average value is calculated, and the converted speed at that time is calculated to obtain the steady-state operating point data (π rqi ,W rqi ,η rqi ) and its relative conversion speed n corresponding to the actual design point conversion speed rqi , and record it as actual operation data;

[0101] Specifically, the test data needs to be preprocessed, including deleting outliers and supplementing missing values.

[0102] Exemplarily, the actual operation data and the correction point data are calculated using the first preset formula to calculate the initial value of the correction value under steady-state conditions, wherein the first preset formula is:

[0103]

[0104]

[0105] COE πd [i]=1

[0106] The initial value of the correction value under each steady-state condition is calculated and matched one by one with the relative converted speed, and finally the correction vector is obtained.

[0107] Specifically, in this actual example, since the compressor and the gas turbine are coaxial, the characteristic correction vectors of the compressor and the gas turbine correspond to the gas turbine relative converted speed vector, and the power turbine characteristic correction vector corresponds to the power turbine relative converted speed vector.

[0108] In a possible implementation manner, the step of dynamically correcting the third two-dimensional characteristic diagram according to the correction vector when the simulation model of the target gas turbine performs real-time calculation includes:

[0109] Acquiring output data of the simulation model of the target gas turbine, and calculating real-time converted speed data based on the output data;

[0110] Calculating a real-time correction coefficient for the third two-dimensional characteristic diagram by a second preset formula according to the real-time converted speed data and the correction vector;

[0111] The correction value is updated according to the error value of the test data and the output data of the simulation model of the target gas turbine to form a new correction vector, and the third two-dimensional characteristic diagram is adjusted based on the updated correction vector to obtain the target two-dimensional characteristic diagram, so that the simulation model constructed based on the target two-dimensional characteristic diagram outputs a simulation result that matches the test data.

[0112] Exemplarily, according to the output data of the real-time simulation of the system, the real-time converted speed data is calculated, and according to the correction vector obtained in the above steps, for the system state at time t, the correction coefficient to be used in the characteristic diagram at this time is calculated using the following formula:

[0113] Coe Wd (t) = interp(COE Wd ,N qi ,n t )

[0114] Coe πd (t) = interp(COE πd ,N qi ,n t )

[0115] Coe ηd (t) = interp(COE ηd ,N qi ,n t )

[0116] Among them, Coe Wd (t), Coe πd (t), Coe ηd (t) corresponds to the dynamic correction coefficient of flow rate, pressure ratio and efficiency of the characteristic diagram at time t, COE Wd , COE πd , COE ηd , N qi is the correction vector and the relative conversion speed vector corresponding to the correction vector, n t is the converted speed at time t, and interp(X,Y,y) is the linear interpolation function.

[0117] Taking the dispatch strategy of the compressor inlet flow correction value in a specific practical example as an example, the calculation formula is as follows:

[0118] Coe Wcd (t) = interp(COE Wcd ,N gqi ,n gt )

[0119] According to the error between the test data and the simulation results, the correction vector is adjusted so that the error range between the model output result and the test data reaches the required range.

[0120] In a specific practical example, the error function should include the compressor outlet pressure P 31 , power turbine outlet temperature T5, gas turbine speed n g and power turbine speed n p These performance requirements require data error information, and the following function can be used as the error function for particle swarm optimization:

[0121]

[0122] Among them, P 31 ,T5,N g ,N p Output value for model target, P 31 ′,T5′,N g ′,N p ′ is the actual output value of the model, and c1, c2, c3, c4 are the weighted coefficients of each item. In this process, the correction vector should be adjusted step by step according to the error of each steady-state condition to finally meet the overall requirements.

[0123] See also Figure 2 As shown, in one embodiment, a method for correcting the characteristic diagram of an original component of a gas turbine is provided, including: static correction and dynamic scheduling, wherein the static correction process includes: collecting data information such as design points and steady-state operating points and corresponding them to the original characteristic diagram of the component, correcting the general characteristic diagram according to the design point data, and setting an error function according to the steady-state operating point data to further correct the characteristic diagram; the dynamic scheduling process includes: setting a correction vector required for dynamic scheduling according to the test data, dynamically scheduling the correction vector based on the test data to compensate the model, and obtaining the error information between the model output and the actual output by the correction vector, and if the error does not meet the requirements, then the correction vector is corrected.

[0124] See also Figure 3 As shown, in one embodiment, a device for correcting a characteristic diagram of an original component of a gas turbine is provided, the device comprising:

[0125] A data conversion module 201 is used to draw an initial two-dimensional characteristic diagram according to an original component characteristic diagram of a target gas turbine;

[0126] A data receiving module 202 is used to obtain the demand design point data and steady-state operating point data of the target gas turbine;

[0127] A first correction module 203, configured to correct the initial two-dimensional characteristic diagram based on the demand design point data by a data recalibration method to obtain a first two-dimensional characteristic diagram;

[0128] An expansion module 204 is used to calculate the relative conversion speed corresponding to each steady-state operating point according to the steady-state operating point data, and expand the first two-dimensional characteristic diagram based on the relative conversion speed by a linear interpolation method to obtain a second two-dimensional characteristic diagram, wherein the second two-dimensional characteristic diagram includes an expanded speed line corresponding to the relative conversion and an initial speed line of the initial two-dimensional characteristic diagram;

[0129] A second correction module 205 is used to adjust the second two-dimensional characteristic diagram according to the condition that the overall error function between each speed line and each steady-state operating point in the second two-dimensional characteristic diagram is minimized to obtain a third two-dimensional characteristic diagram;

[0130] The dynamic correction module 206 is used to dynamically correct the third two-dimensional characteristic diagram according to the test data of the target gas turbine when the simulation model of the target gas turbine performs real-time calculation, so that the output result of the simulation model matches the test data.

[0131] In one embodiment, an electronic device 300 is provided, such as Figure 4 As shown, the computer program 311 stored in the memory 310 and executable on the processor 320 is implemented as follows: an initial two-dimensional characteristic diagram is drawn according to the original component characteristic diagram of the target gas turbine; demand design point data and steady-state operating point data of the target gas turbine are obtained; the initial two-dimensional characteristic diagram is corrected based on the demand design point data by a data recalibration method to obtain a first two-dimensional characteristic diagram; the relative conversion speed corresponding to each steady-state operating point is calculated according to the steady-state operating point data, and the relative conversion speed corresponding to each steady-state operating point is calculated by linear interpolation. The method expands the first two-dimensional characteristic diagram based on the relative converted speed to obtain a second two-dimensional characteristic diagram, wherein the second two-dimensional characteristic diagram includes an expanded speed line corresponding to the relative conversion and an initial speed line of the initial two-dimensional characteristic diagram; the second two-dimensional characteristic diagram is adjusted according to the condition that the overall error function between each speed line and each steady-state operating point in the second two-dimensional characteristic diagram is minimized to obtain a third two-dimensional characteristic diagram; and according to the test data of the target gas turbine, when the simulation model of the target gas turbine performs real-time calculation, the third two-dimensional characteristic diagram is dynamically corrected to make the output result of the simulation model match the test data.

[0132] In one embodiment, a computer readable storage medium 400 is provided, such as Figure 5 As shown, a computer program 411 is stored thereon, and when the computer program 411 is executed by the processor, the following steps are implemented: drawing an initial two-dimensional characteristic diagram according to the original component characteristic diagram of the target gas turbine; obtaining the demand design point data and steady-state operating point data of the target gas turbine; correcting the initial two-dimensional characteristic diagram based on the demand design point data by a data recalibration method to obtain a first two-dimensional characteristic diagram; calculating the relative conversion speed corresponding to each steady-state operating point according to the steady-state operating point data, and expanding the first two-dimensional characteristic diagram based on the relative conversion speed by a linear interpolation method to obtain a second two-dimensional characteristic diagram, wherein the second two-dimensional characteristic diagram includes an expanded speed line corresponding to the relative conversion and an initial speed line of the initial two-dimensional characteristic diagram; adjusting the second two-dimensional characteristic diagram according to the condition that the overall error function between each speed line in the second two-dimensional characteristic diagram and each steady-state operating point is minimized to obtain a third two-dimensional characteristic diagram; and dynamically correcting the third two-dimensional characteristic diagram when the simulation model of the target gas turbine performs real-time calculation according to the test data of the target gas turbine, so that the output result of the simulation model matches the test data.

[0133] Those of ordinary skill in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this application.

[0134] In the embodiments provided in the present application, it should be understood that the disclosed devices / network equipment / terminal equipment and methods can be implemented in other ways. For example, the device / network equipment / terminal equipment embodiments described above are only schematic. For example, the division of the modules or units is only a logical function division. There may be other division methods in actual implementation, such as 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 mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of devices or units, which can be electrical, mechanical or other forms.

[0135] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0136] The embodiments described above are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, a person skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. Such modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application, and should all be included in the protection scope of the present application.

Claims

1. A method for correcting an original component characteristic map of a gas turbine, characterized in that: include: Drawing an initial two-dimensional characteristic map based on an original component characteristic map of a target gas turbine; Acquiring demand design point data and steady-state operating point data of the target gas turbine; By means of a data recalibration method, the initial two-dimensional characteristic diagram is corrected based on the demand design point data to obtain a first two-dimensional characteristic diagram; Calculating the relative conversion speed corresponding to each steady-state operating point according to the steady-state operating point data, and expanding the first two-dimensional characteristic diagram based on the relative conversion speed by a linear interpolation method to obtain a second two-dimensional characteristic diagram, wherein the second two-dimensional characteristic diagram includes an expanded speed line corresponding to the relative conversion and an initial speed line of the initial two-dimensional characteristic diagram; According to the condition that the overall error function between each speed line in the second two-dimensional characteristic diagram and each steady-state operating point corresponding to the converted speed is minimized, the second two-dimensional characteristic diagram is adjusted to obtain a third two-dimensional characteristic diagram; According to the test data of the target gas turbine, when the simulation model of the target gas turbine performs real-time calculation, the third two-dimensional characteristic diagram is dynamically corrected so that the output result of the simulation model matches the test data.

2. The method for correcting the original component characteristic map of a gas turbine according to claim 1, characterized in that: The step of correcting the initial two-dimensional characteristic diagram based on the demand design point data by the data recalibration method to obtain a first two-dimensional characteristic diagram includes: Selecting actual design points in the initial two-dimensional characteristic diagram according to preset experimental data; By means of data recalibration, the initial two-dimensional characteristic diagram is stretched with pressure ratio equal to 1, flow equal to 0, and efficiency equal to 0 as the scaling center, so that the actual design point is consistent with the demand design point corresponding to the demand design point data, thereby obtaining a first two-dimensional characteristic diagram.

3. The method for correcting the original component characteristic map of a gas turbine according to claim 1, characterized in that: The step of adjusting the second two-dimensional characteristic diagram according to the condition that the overall error function between each speed line in the second two-dimensional characteristic diagram and each steady-state operating point corresponding to the converted speed is minimized to obtain the third two-dimensional characteristic diagram comprises: Selecting a target correction point on a speed line corresponding to the steady-state operating point according to the steady-state operating point data; The second two-dimensional characteristic diagram is adjusted according to the target correction point and the steady-state operating point so that the overall error function between each speed line and each steady-state operating point in the second two-dimensional characteristic diagram is minimized, thereby obtaining a two-dimensional characteristic diagram to be processed; The expanded speed line in the two-dimensional characteristic diagram to be processed is removed to obtain the third two-dimensional characteristic diagram.

4. The method for correcting the original component characteristic map of a gas turbine according to claim 1, characterized in that: The step of dynamically correcting the third two-dimensional characteristic diagram according to the test data of the target gas turbine when the simulation model of the target gas turbine performs real-time calculation comprises: Acquiring test design point data and test steady-state operating point data of the target gas turbine according to the test data of the target gas turbine, and calculating a corresponding relative converted speed based on the test design point data and the test steady-state operating point data; According to the relative converted speed, the isospeed lines corresponding to the relative converted speed are expanded by linear interpolation, and the operation data of the steady-state operating point is calculated according to the isospeed lines and the third two-dimensional characteristic diagram as the correction point data; Acquire actual operating data of the target gas turbine, calculate an initial value of the correction value under steady-state conditions by a first preset formula according to the actual operating data and the correction point data, and calculate the initial value of the correction value under each steady-state condition, and correspond it to the relative converted speed one by one, and finally obtain a correction vector; According to the correction vector, the third two-dimensional characteristic diagram is dynamically corrected when the simulation model of the target gas turbine performs real-time calculation.

5. The method for correcting the original component characteristic map of a gas turbine according to claim 4, characterized in that: The step of calculating the operating data of the steady-state operating point according to the constant speed line and the third two-dimensional characteristic diagram comprises: Functional relationships through different operating data: Calculate the operating data of the steady-state operating point, where π qi is the pressure ratio of the steady-state operating point in the test data, Z qi is the pressure ratio coefficient of the steady-state operating point, They are respectively the maximum and minimum values ​​of pressure ratio, flow rate, and efficiency on the equal speed line corresponding to the steady-state operating point, W mqi is the flow rate obtained by interpolation at the steady-state operating point, η mqi is the efficiency obtained by interpolation at the steady-state operating point.

6. The method for correcting the original component characteristic map of a gas turbine according to claim 4, characterized in that: The step of calculating the initial value of the correction value under steady-state conditions by a first preset formula according to the actual operation data and the correction point data comprises: The actual operation data and the correction point data are calculated using the first preset formula to calculate the initial value of the correction value under steady-state conditions, wherein the first preset formula is: COE πd [i]=1 Among them, W rqi and η rqi It is the flow rate and efficiency when actually running to this steady-state operating point.

7. The method for correcting the original component characteristic map of a gas turbine according to claim 4, characterized in that: The step of dynamically correcting the third two-dimensional characteristic diagram according to the correction vector when the simulation model of the target gas turbine performs real-time calculation comprises: Acquiring output data of the simulation model of the target gas turbine, and calculating real-time converted speed data based on the output data; Calculating a real-time correction coefficient for the third two-dimensional characteristic diagram by a second preset formula according to the real-time converted speed data and the correction vector; The correction value is updated according to the error value between the test data and the output data of the simulation model of the target gas turbine, thereby forming a new correction vector, and the third two-dimensional characteristic diagram is dynamically corrected based on the updated correction vector, so that the simulation model constructed based on the target two-dimensional characteristic diagram outputs a simulation result that matches the test data.

8. The method for correcting the original component characteristic map of a gas turbine according to claim 5, characterized in that: The second preset formula is: Coe Wd (t)=interp(COE Wd ,N qi ,n t ) Coe πd (t)=interp(COE πd ,N qi ,n t ) Coe ηd (t)=interp(COE ηd ,N qi ,n t ) Among them, Coe Wd (t), Coe πd (t), Coe ηd (t) corresponds to the dynamic correction coefficient of flow rate, pressure ratio and efficiency of the characteristic diagram at time t, COE Wd , COE πd , COE ηd , N qi is the correction vector and the relative conversion speed vector corresponding to the correction vector, n t is the converted speed at time t, and interp(X,Y,y) is the linear interpolation function.

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