Method and apparatus for correcting gas turbine performance test results considering Reynolds number effect

Abstract

This application provides a method and apparatus for correcting gas turbine performance test results considering the Reynolds number effect. The method includes: obtaining a first turbine efficiency and a first Reynolds number of the gas turbine under a first operating condition, and a second Reynolds number under a second operating condition; and determining the second turbine efficiency of the gas turbine under the second operating condition based on the first Reynolds number, the first turbine efficiency, the second Reynolds number, and a target expression. Using the gas turbine performance test result correction method considering the Reynolds number effect provided in this application can significantly improve the accuracy of predicting turbine efficiency under actual operating conditions based on test data.

Description

Technical Field

[0001] This application relates to the field of gas turbine performance testing, and in particular to a method and apparatus for correcting gas turbine performance test results considering the Reynolds number effect. Background Technology

[0002] Turbine testing is a crucial step in engine development. During turbine aerodynamic performance testing, the high inlet temperature and pressure make it difficult and costly to simulate the actual operating conditions of the prototype turbine, and test safety is also challenging. Therefore, model turbines are generally used in turbine testing to simulate the operation under medium temperature and pressure conditions.

[0003] For gas turbines, the necessary similarity criteria are expansion ratio, equivalent rotational speed, specific heat ratio, and Reynolds number (Re). Due to limitations in experimental conditions, it is often difficult to ensure that the Reynolds number Re under the test conditions is equal to the Reynolds number Re under the corresponding prototype conditions in actual turbine tests. Inequality between Reynolds numbers Re and the experimental turbine efficiency obtained from turbine simulation tests will lead to discrepancies between the experimental turbine efficiency and the prototype turbine efficiency. Therefore, it is necessary to consider the impact of unequal Reynolds numbers Re and correct the experimental results accordingly.

[0004] However, in existing related technologies, the prediction of turbine efficiency under actual operating conditions based on data obtained from test conditions still has a large deviation. Summary of the Invention

[0005] The purpose of this application is to provide a method and apparatus for correcting gas turbine performance test results considering the Reynolds number effect, thereby improving the accuracy of turbine efficiency prediction based on test results. This application provides a method for correcting gas turbine performance test results considering the Reynolds number effect, comprising: obtaining a first turbine efficiency and a first Reynolds number of the gas turbine under a first operating condition, and a second Reynolds number under a second operating condition; determining the second turbine efficiency of the gas turbine under the second operating condition based on the first Reynolds number, the first turbine efficiency, the second Reynolds number, and a target expression; the target expression is:

[0006]

[0007] Where η1 is the first turbine efficiency, Re1 is the first Reynolds number, Re2 is the second Reynolds number, and η2 is the second turbine efficiency; the sum of parameters A, B, and C is 1.

[0008] Optionally, the parameters of the target expression include: a first parameter and a second parameter; determining the second turbine efficiency of the gas turbine under the second operating condition includes: when the first Reynolds number is in the non-self-model region, using the first parameter as a parameter of the target expression to determine the second turbine efficiency; or, when the first Reynolds number is in the self-model region, using the second parameter as a parameter of the target expression to determine the second turbine efficiency.

[0009] Optionally, when the first parameter is used as a parameter of the target expression, the target expression is:

[0010]

[0011] Optionally, when the second parameter is used as a parameter of the target expression, the target expression is:

[0012]

[0013] This application also provides a gas turbine performance test result correction device considering the Reynolds number effect, comprising: an acquisition module for acquiring a first turbine efficiency and a first Reynolds number of the gas turbine under a first operating condition, and a second Reynolds number under a second operating condition; and a determination module for determining the second turbine efficiency of the gas turbine under the second operating condition based on the first Reynolds number, the first turbine efficiency, the second Reynolds number, and a target expression; wherein the target expression is:

[0014]

[0015] Where η1 is the first turbine efficiency, Re1 is the first Reynolds number, Re2 is the second Reynolds number, and η2 is the second turbine efficiency; the sum of parameters A, B, and C is 1.

[0016] Optionally, the parameters of the target expression include: a first parameter and a second parameter; the determining module is specifically used to determine the second turbine efficiency by using the first parameter as a parameter of the target expression when the first Reynolds number is in the non-self-model region; or, the determining module is specifically used to determine the second turbine efficiency by using the second parameter as a parameter of the target expression when the first Reynolds number is in the self-model region.

[0017] Optionally, when the first parameter is used as a parameter of the target expression, the target expression is:

[0018]

[0019] Optionally, when the second parameter is used as a parameter of the target expression, the target expression is:

[0020]

[0021] This application also provides a computer program product, including a computer program / instructions that, when executed by a processor, implement the steps of the gas turbine performance test result correction method considering Reynolds number effects as described above.

[0022] This application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the steps of the gas turbine performance test result correction method considering Reynolds number effect as described above.

[0023] This application also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the steps of the method for correcting gas turbine performance test results considering Reynolds number effects as described above.

[0024] The method and apparatus for correcting gas turbine performance test results considering the Reynolds number effect provided in this application, after obtaining the first turbine efficiency and first Reynolds number of the gas turbine under a first operating condition and the second Reynolds number under a second operating condition based on the test results, determines the second turbine efficiency of the gas turbine under the second operating condition according to the first Reynolds number, the first turbine efficiency, the second Reynolds number and the target expression, which can significantly improve the prediction accuracy of turbine efficiency of gas turbine under actual operating conditions based on test data. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0026] Figure 1 This is a flowchart illustrating the method for correcting gas turbine performance test results considering the Reynolds number effect provided in this application;

[0027] Figure 2 This is a schematic diagram of the turbine efficiency versus Reynolds number provided in this application;

[0028] Figure 3 This is one of the schematic diagrams illustrating the relationship between turbine efficiency loss and total pressure loss coefficient provided in this application;

[0029] Figure 4 This is the second schematic diagram showing the relationship between turbine efficiency loss and total pressure loss coefficient provided in this application;

[0030] Figure 5 This is a schematic diagram comparing the actual turbine efficiency predicted by the test result correction method provided in this application with the prediction results of existing prediction methods;

[0031] Figure 6 This is a schematic diagram of the structure of the gas turbine performance test result correction device considering the Reynolds number effect provided in this application;

[0032] Figure 7 This is a schematic diagram of the structure of the electronic device provided in this application. Detailed Implementation

[0033] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0034] The terms "first," "second," etc., used in the specification and claims of this application are used to distinguish similar objects and not to describe a specific order or sequence. It should be understood that such use of data can be interchanged where appropriate so that embodiments of this application can be implemented in orders other than those illustrated or described herein, and the objects distinguished by "first," "second," etc., are generally of the same class and the number of objects is not limited; for example, a first object can be one or more. Furthermore, in the specification and claims, "and / or" indicates at least one of the connected objects, and the character " / " generally indicates that the preceding and following objects are in an "or" relationship.

[0035] Turbine testing is a crucial step in engine development. During turbine aerodynamic performance testing, the high inlet temperature and pressure make simulating the prototype turbine's operating conditions extremely difficult, costly, and pose significant safety risks. Therefore, model turbines are typically used in turbine testing, conducting simulations under medium-temperature and medium-pressure environments. The simulation testing methodology involves modeling the turbine according to similarity principles, determining the aerodynamic parameters under simulated conditions, conducting tests on simulated equipment, and measuring and calculating the turbine's flow field and performance. Turbine efficiency is one of the most important test results in turbine simulation testing. For gas turbines, the necessary similarity criteria are the expansion ratio, equivalent rotational speed, specific heat ratio, and Reynolds number (Re). Due to limitations in testing conditions, it is often difficult to ensure that the Reynolds number (Re) of the test conditions is equal to that of the corresponding prototype conditions in actual turbine testing. This inequality in Reynolds number (Re) leads to discrepancies between the experimental turbine efficiency obtained from the turbine simulation and the prototype turbine efficiency. Therefore, it is necessary to consider the impact of the inequality in Reynolds number (Re) and correct the test results accordingly.

[0036] Currently, the domestic methods for correcting the Reynolds number Re are derived from the efficiency correction method established in the United States in the last century. This method assumes that the turbine efficiency loss (1-η) only considers friction loss, and further assumes that friction loss is related to the Reynolds number Re. -0.2 The effect of unequal Reynolds numbers on efficiency is proportional. When the Reynolds number Re is small and not in the self-model region, a correction formula is used to correct for the effect of unequal Reynolds numbers on efficiency. However, when the Reynolds number Re is in the self-model region, the effect of unequal Reynolds numbers on efficiency is ignored, and the similarity criterion of Reynolds number Re automatically degenerates. However, the turbine efficiency prediction results under actual operating conditions obtained by this correction method also have a large deviation.

[0037] To address the aforementioned issues, the technical solution provided in this application embodiment effectively improves the accuracy of turbine efficiency prediction results under actual operating conditions by considering the influence of the Reynolds number Re in the self-model region on turbine efficiency.

[0038] The following description, in conjunction with the accompanying drawings, details the method for correcting gas turbine performance test results considering the Reynolds number effect provided in this application through specific embodiments and application scenarios.

[0039] like Figure 1 As shown in the embodiment of this application, a method for correcting gas turbine performance test results considering the Reynolds number effect is provided. This method may include the following steps 101 to 103:

[0040] Step 101: Obtain the first turbine efficiency and first Reynolds number of the gas turbine under the first operating condition, and the second Reynolds number under the second operating condition.

[0041] For example, the first operating condition mentioned above is a test condition. It is understood that since the actual working environment of a gas turbine is high temperature and high pressure, it is difficult to simulate under test conditions and there are certain dangers involved. Therefore, simulation can be carried out under a medium temperature and medium pressure environment based on the principle of similarity. Then, based on the aerodynamic parameters obtained under the test environment, the aerodynamic parameters of the gas turbine under actual operating conditions can be predicted.

[0042] For example, the second operating condition described above is the actual operating condition of the gas turbine.

[0043] Step 102: Determine the second turbine efficiency of the gas turbine under the second operating condition based on the first Reynolds number, the first turbine efficiency, the second Reynolds number, and the target expression.

[0044] The target expression is:

[0045]

[0046] Where η1 is the first turbine efficiency, Re1 is the first Reynolds number, Re2 is the second Reynolds number, and η2 is the second turbine efficiency; the sum of parameters A, B, and C is 1.

[0047] For example, in order to find out the reason for the large deviation in the turbine efficiency prediction results in related technologies, we used a certain type of turbine to perform numerical simulations at different Reynolds numbers Re, and obtained the actual turbine efficiency values ​​under operating conditions 1 to 9 in Table 1 below:

[0048] Operating conditions 1 2 3 4 5 Reynolds number Re <![CDATA[2×10 4 ]]> <![CDATA[4×10 4 ]]> <![CDATA[1×10 5 ]]> <![CDATA[2×10 5 ]]> <![CDATA[3×10 5 ]]> efficiency 84.21％ 84.81％ 85.64％ 86.17％ 86.57％ Operating conditions 6 7 8 9 Reynolds number Re <![CDATA[5×10 5 ]]> <![CDATA[8×10 5 ]]> <![CDATA[1.2×10 6 ]]> <![CDATA[1.5×10 6 ]]> efficiency 86.78％ 87.03％ 87.20％ 87.31％

[0049] Table 1

[0050] Since the total inlet temperature remains constant under all operating conditions, the specific heat ratio is assumed to be equal under all conditions. Simultaneously, the expansion ratio and equivalent rotational speed are kept constant. This verifies the accuracy of the correction formula in the industry standard. The calculation results are shown in the table below, and the turbine efficiency as a function of Reynolds number (Re) is shown in the figure. Figure 2 As shown.

[0051] like Figure 2 As shown, when the Reynolds number Re is greater than 3 × 10 5 In the self-modular region, the efficiency increases slowly with the increase of the Reynolds number Re, far less than the efficiency growth in the non-self-modular region. However, when the Reynolds number Re changes significantly, for example, from 5 × 10⁻⁶, the efficiency increases much more slowly. 5 Increased to 1.5×10 6 At that time, the efficiency improved by 0.53%, a change that cannot be ignored in actual experiments. Therefore, the previous practice of ignoring the impact of changes in the Reynolds number Re in the self-modulus region on efficiency is flawed.

[0052] The figure also shows that when the Reynolds number Re is in the non-self-modular region, the efficiency does indeed improve significantly with the increase of the Reynolds number Re. For example, when the Reynolds number Re increases from 2 × 10⁻⁶, the efficiency does improve significantly. 4 Increased to 3×10 5 At that time, efficiency improved by 2.4%. However, the reliability of the efficiency correction formula in the industry standard needs to be verified through calculation.

[0053] With a Reynolds number Re of 3 × 10 5 Using operating condition 5 as a baseline, the estimated efficiencies for operating conditions 1-4 were calculated according to the Reynolds number (Re) correction formula in the industry standard, and compared with their actual efficiencies to verify the accuracy of the Reynolds number (Re) correction formula. The calculated data are shown in Table 2 below.

[0054] Operating conditions Reynolds number Re efficiency Estimated efficiency Predicted efficiency deviation 1 <![CDATA[2×10 4 ]]> 84.21％ 79.81～80.78％ -4.40～-3.43％ 2 <![CDATA[4×10 4 ]]> 84.81％ 81.90～82.57％ -2.91～-2.24％ 3 <![CDATA[1×10 5 ]]> 85.64％ 84.26～84.59％ -1.38～-1.05％ 4 <![CDATA[2×10 5 ]]> 86.17％ 85.78～85.89％ -0.39～-0.28％

[0055] Table 2

[0056] The results in Table 2 show that, with a Reynolds number Re of 3 × 10⁻⁶, 5 Using the operating conditions as a benchmark, the efficiency predicted by the Reynolds number (Re) correction formula deviates significantly from the actual efficiency. Furthermore, the greater the difference between the Reynolds number (Re) and the benchmark Reynolds number (Re), the greater the deviation in the predicted efficiency. Therefore, it is believed that the efficiency correction formula currently used in industry standards, which considers the influence of the Reynolds number (Re), is not ideal because it only considers the relationship between friction loss and the Reynolds number (Re), while secondary flow losses in the turbine flow field also vary with the Reynolds number (Re).

[0057] For example, it can be seen from the following two calculation methods that the turbine efficiency loss (1-η) is linearly related to the total pressure loss coefficient of the turbine blade passage.

[0058] (I) Efficiency one-dimensional calculation and evaluation formula:

[0059]

[0060] Where Y S Y represents the total pressure loss coefficient of the stator blades. R This represents the total pressure loss coefficient of the moving blades. Assuming other parameters remain constant, the turbine efficiency loss (1-η) is calculated as a function of Y. S Y R The relationship of change is as follows Figure 3 As shown. By Figure 3 It can be seen that the turbine efficiency loss (1-η) is linearly related to the total pressure loss coefficient.

[0061] (II) As shown in Table 3 below, the total pressure loss coefficient and efficiency of a certain type of turbine at different Reynolds numbers are:

[0062] Reynolds number Re <![CDATA[Y S ]]> <![CDATA[Y R ]]> η 1-η <![CDATA[3×10 4 ]]> 0.1444 0.3017 85.20％ 14.80％ <![CDATA[5×10 4 ]]> 0.1356 0.2804 86.13％ 13.87％ <![CDATA[1×10 5 ]]> 0.1301 0.2621 86.70％ 13.30％ <![CDATA[2×10 5 ]]> 0.1225 0.2489 87.35％ 12.65％

[0063] Table 3

[0064] like Figure 4 As shown, this represents the relationship between turbine efficiency loss (1-η) and total pressure loss coefficient.

[0065] Both of the above methods show that the turbine efficiency loss (1-η) has a clear linear relationship with the total pressure loss coefficient.

[0066] The total pressure loss coefficient of the turbine blade passage mainly includes: airfoil loss, secondary flow loss, and leakage flow loss.

[0067] Numerical simulations were performed on a certain type of turbine at different Reynolds numbers Re. Then, its airfoil loss, endwall loss, and leakage loss were calculated. The results are shown in Table 4 below.

[0068] Reynolds number Re End wall loss Leaf shape loss Leakage loss <![CDATA[8.26×10 5 ]]> 0.0608 0.0948 0.0996 <![CDATA[4.13×10 5 ]]> 0.0630 0.0988 0.0996 <![CDATA[2.07×10 5 ]]> 0.0662 0.1036 0.0981 <![CDATA[1.04×10 5 ]]> 0.0702 0.1124 0.0979 <![CDATA[4.13×10 4 ]]> 0.0771 0.1203 0.0977

[0069] Table 4

[0070] As shown in the table, with the decrease of Reynolds number Re, endwall losses and airfoil losses increase significantly, while leakage losses change very little, which is consistent with the conclusions of many studies in the literature. Therefore, it is believed that among the losses in turbine flow, the airfoil losses and secondary flow losses that change with Reynolds number Re are mainly those that change with Reynolds number Re. For the same turbine, leakage losses hardly change with Reynolds number Re. According to the theories of laminar and turbulent boundary layers, the loss coefficient of the laminar boundary layer is related to the Reynolds number Re. -0.5 The turbulent boundary layer loss coefficient is directly proportional to the Reynolds number Re. -0.25 It is directly proportional. Therefore, it can be assumed that when the Reynolds number Re < 3 × 10⁻⁶, the relationship is proportional. 5 At that time, the blade shape loss and the Reynolds number Re -0.5 Proportional; Reynolds number Re > 3 × 10 5 At that time, the blade shape loss and the Reynolds number Re -0.25 The secondary flow loss is directly proportional to the Reynolds number. A portion of the secondary flow loss originates from the development of channel vortices, which primarily develop from horseshoe vortices. Horseshoe vortices are formed by the inlet endwall boundary layer at the blade leading edge. Therefore, the inlet endwall boundary layer thickness is one of the factors affecting secondary flow loss, and thus, secondary flow loss is also influenced by the Reynolds number Re. Christopher R. Marks' low Reynolds number experimental data shows the trend of secondary flow loss with Reynolds number. Analysis of his data reveals that secondary flow loss is directly proportional to the Reynolds number Re. -0.17 Proportional.

[0071] Based on the above conclusions, we can obtain the following form for the objective expression:

[0072]

[0073] Furthermore, based on the above conclusions, the Reynolds number Re needs to be expressed differently in the self-modular region and the non-self-modular region. Therefore, based on the above formula, it can be determined that the values ​​of A, B, C, n1, and n2 are different when the Reynolds number Re is in the self-modular region and the non-self-modular region.

[0074] For example, the parameters of the target expression include: a first parameter and a second parameter; step 102 above may include step 102a or step 102b:

[0075] Step 102a: When the first Reynolds number is in the non-self-mode region, the first parameter is used as the parameter of the target expression to determine the second turbine efficiency.

[0076] Step 102b: When the first Reynolds number is in the self-mode region, the second parameter is used as the parameter of the target expression to determine the second turbine efficiency.

[0077] Using operating condition 5 as the baseline, substituting the efficiencies of operating conditions 1, 2, 3, and 4 into the above objective expression, we obtain the objective expression as follows:

[0078]

[0079] Therefore, when the Reynolds number Re is in the non-self-modeling region, the above formula should be used to correct the efficiency in order to obtain a more accurate air-cooled turbine efficiency corresponding to the Reynolds number Re.

[0080] For example, when the first Reynolds number is located in the non-self-modular region, and the first parameter is used as the parameter of the target expression, the target expression is the first expression mentioned above.

[0081] When the Reynolds number Re is within the self-modular region, the efficiency still varies with the Reynolds number Re. Taking condition 5 as the baseline, substituting the efficiencies of conditions 6, 7, 8, and 9, we obtain:

[0082]

[0083] Therefore, when the Reynolds number Re is in the self-model region, the above formula should be used to correct the efficiency in order to obtain a more accurate air-cooled turbine efficiency corresponding to the Reynolds number Re.

[0084] For example, when the first Reynolds number is located in the self-modular region, and the second parameter is used as the parameter of the target expression, the target expression is the second expression described above.

[0085] Therefore, the objective expression used in the gas turbine performance test result correction method considering Reynolds number effect provided in this application embodiment is as follows:

[0086]

[0087] For a certain type of data verification turbine, the turbine efficiency at different Reynolds numbers Re was estimated using the modified formula in the original industry standard and the above objective expression, respectively. The calculation results are as follows: Figure 5 As shown in the figure, the deviation between the calculated results and the actual turbine efficiency at the corresponding Reynolds number Re is shown in the table below. It can be seen from the figure that when the Reynolds number Re is in the non-self-modeling region, the turbine efficiency estimated by the target expression provided in this embodiment is significantly closer to the corresponding actual turbine efficiency than the original efficiency correction formula. When Re is in the self-modeling region, the turbine efficiency estimated by the original efficiency correction formula no longer changes with the Reynolds number Re, while the trend of efficiency estimated by the target expression provided in this embodiment with the Reynolds number Re is consistent with the trend of actual efficiency with the Reynolds number Re.

[0088] Table 5 below shows a comparison of the turbine efficiency deviations between the gas turbine performance test result correction method considering the Reynolds number effect provided in this application embodiment and the existing prediction methods:

[0089] Re Original Efficiency Deviation This estimated efficiency deviation <![CDATA[3×10 4 ]]> -2.80～-2.07％ 0.52％ <![CDATA[5×10 4 ]]> -2.39～-1.85％ 0.16％ <![CDATA[7.5×10 5 ]]> -0.60％ 0.03％ <![CDATA[1.06×10 6 ]]> -0.68％ 0.13％

[0090] Table 5

[0091] As shown in Table 5 above, the deviation between the turbine efficiency predicted by the gas turbine performance test result correction method considering the Reynolds number effect provided in the embodiments of this application and the turbine efficiency under actual operating conditions has been significantly reduced.

[0092] It should be noted that the above target expression, expression one, and expression two are obtained based on the test data of the above-mentioned turbine. The above data verification turbine is used to verify the above expressions in order to prove that the above expressions have universality.

[0093] The gas turbine performance test result correction method considering the Reynolds number effect provided in this application, after obtaining the first turbine efficiency and first Reynolds number of the gas turbine under a first operating condition and the second Reynolds number under a second operating condition based on the test results, determines the second turbine efficiency of the gas turbine under the second operating condition according to the first Reynolds number, the first turbine efficiency, the second Reynolds number, and the target expression. Furthermore, different formulas are used to predict the turbine efficiency under the second operating condition for different Reynolds numbers located in the self-modeling region and the non-self-modeling region. Thus, the accuracy of predicting the turbine efficiency of the gas turbine under actual operating conditions based on test data can be significantly improved.

[0094] It should be noted that the gas turbine performance test result correction method considering Reynolds number effect provided in this application embodiment can be executed by a gas turbine performance test result correction device considering Reynolds number effect, or a control module in the gas turbine performance test result correction device considering Reynolds number effect for executing the gas turbine performance test result correction method considering Reynolds number effect. This application embodiment uses the execution of the gas turbine performance test result correction method considering Reynolds number effect by a gas turbine performance test result correction device considering Reynolds number effect as an example to illustrate the gas turbine performance test result correction device considering Reynolds number effect provided in this application embodiment.

[0095] It should be noted that, in the embodiments of this application, the methods for correcting gas turbine performance test results considering the Reynolds number effect shown in the accompanying drawings of the various methods are all illustrated by way of example with reference to one of the accompanying drawings of the embodiments of this application. In specific implementation, the methods for correcting gas turbine performance test results considering the Reynolds number effect shown in the accompanying drawings of the various methods can also be implemented in conjunction with any other accompanying drawings shown in the above embodiments, which will not be elaborated here.

[0096] The following description of the application provides that the method for correcting gas turbine performance test results considering Reynolds number effects described below can be referred to in conjunction with the method described above.

[0097] Figure 6 A schematic diagram of the structure of the gas turbine performance test result correction device considering the Reynolds number effect provided in the embodiments of this application is shown below. Figure 6 As shown, it specifically includes:

[0098] Acquisition module 601 is used to acquire the first turbine efficiency and first Reynolds number of the gas turbine under a first operating condition, and the second Reynolds number under a second operating condition; determination module 602 is used to determine the second turbine efficiency of the gas turbine under the second operating condition based on the first Reynolds number, the first turbine efficiency, the second Reynolds number, and a target expression; the target expression is:

[0099]

[0100] Where η1 is the first turbine efficiency, Re1 is the first Reynolds number, Re2 is the second Reynolds number, and η2 is the second turbine efficiency; the sum of parameters A, B, and C is 1.

[0101] Thus, after obtaining the first turbine efficiency and first Reynolds number of the gas turbine under the first operating condition and the second Reynolds number under the second operating condition based on the test results, the second turbine efficiency of the gas turbine under the second operating condition can be determined according to the first Reynolds number, the first turbine efficiency, the second Reynolds number and the target expression, which can greatly improve the prediction accuracy of turbine efficiency of gas turbine under actual operating conditions based on test data.

[0102] Optionally, the parameters of the target expression include: a first parameter and a second parameter; the determining module 602 is specifically used to determine the second turbine efficiency by using the first parameter as a parameter of the target expression when the first Reynolds number is in the non-self-model region; or, the determining module 602 is specifically used to determine the second turbine efficiency by using the second parameter as a parameter of the target expression when the first Reynolds number is in the self-model region.

[0103] Optionally, when the first parameter is used as a parameter of the target expression, the target expression is:

[0104]

[0105] Optionally, when the second parameter is used as a parameter of the target expression, the target expression is:

[0106]

[0107] The gas turbine performance test result correction device considering the Reynolds number effect provided in this application, after obtaining the first turbine efficiency and first Reynolds number of the gas turbine under a first operating condition and the second Reynolds number under a second operating condition based on test results, determines the second turbine efficiency of the gas turbine under the second operating condition according to the first Reynolds number, the first turbine efficiency, the second Reynolds number, and a target expression. Furthermore, different formulas are used to predict the turbine efficiency under the second operating condition for different Reynolds numbers located in the self-modeling region and the non-self-modeling region. Thus, the accuracy of predicting the turbine efficiency of the gas turbine under actual operating conditions based on test data can be significantly improved.

[0108] Figure 7 An example is a schematic diagram of the physical structure of an electronic device, such as... Figure 7As shown, the electronic device may include a processor 710, a communications interface 720, a memory 730, and a communication bus 740, wherein the processor 710, the communications interface 720, and the memory 730 communicate with each other via the communication bus 740. The processor 710 can call logical instructions in the memory 730 to execute a method for correcting gas turbine performance test results considering the Reynolds number effect. This method includes: obtaining a first turbine efficiency and a first Reynolds number of the gas turbine under a first operating condition, and a second Reynolds number under a second operating condition; and determining the second turbine efficiency of the gas turbine under the second operating condition based on the first Reynolds number, the first turbine efficiency, the second Reynolds number, and a target expression.

[0109] Furthermore, the logical instructions in the aforementioned memory 730 can be implemented as software functional units and, when sold or used as independent products, can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or a portion of the 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 cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM, Reynolds number read-only memory), random access memory (RAM), magnetic disks, or optical disks.

[0110] On the other hand, this application also provides a computer program product, which includes a computer program stored on a non-transitory computer-readable storage medium. The computer program includes program instructions, and when the program instructions are executed by a computer, the computer is able to execute the gas turbine performance test result correction method considering the Reynolds number effect provided by the above methods. The method includes: obtaining a first turbine efficiency and a first Reynolds number of the gas turbine under a first operating condition, and a second Reynolds number under a second operating condition; and determining the second turbine efficiency of the gas turbine under the second operating condition based on the first Reynolds number, the first turbine efficiency, the second Reynolds number, and a target expression.

[0111] In another aspect, this application also provides a non-transitory computer-readable storage medium storing a computer program thereon, which, when executed by a processor, is implemented to perform the above-described methods for correcting gas turbine performance test results considering Reynolds number effects. The method includes: obtaining a first turbine efficiency and a first Reynolds number of the gas turbine under a first operating condition, and a second Reynolds number under a second operating condition; and determining the second turbine efficiency of the gas turbine under the second operating condition based on the first Reynolds number, the first turbine efficiency, the second Reynolds number, and a target expression.

[0112] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0113] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments or some parts of the embodiments.

[0114] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application.

Claims

1. A method for correcting gas turbine performance test results considering the Reynolds number effect, characterized in that, include: Obtain the first turbine efficiency and first Reynolds number of the gas turbine under the first operating condition, and the second Reynolds number under the second operating condition; The second turbine efficiency of the gas turbine under the second operating condition is determined based on the first Reynolds number, the first turbine efficiency, the second Reynolds number, and the target expression. The target expression is: ； in, η 1 represents the first turbine efficiency, and the Reynolds number is... Re 1 is the first Reynolds number. Reynolds number Re 2 is the second Reynolds number. η 2 represents the efficiency of the second turbine; the sum of parameters A, B, and C is 1; The parameters of the target expression include: a first parameter and a second parameter; determining the second turbine efficiency of the gas turbine under the second operating condition includes: When the first Reynolds number is in the non-self-modular region, the first parameter is used as the parameter of the target expression to determine the second turbine efficiency; or, When the first Reynolds number is in the self-mode region, the second parameter is used as a parameter of the target expression to determine the second turbine efficiency.

2. The method according to claim 1, characterized in that, When the first parameter is used as a parameter of the target expression, the target expression is: 。 3. The method according to claim 1, characterized in that, When the second parameter is used as a parameter of the target expression, the target expression is: 。 4. A device for correcting gas turbine performance test results considering the Reynolds number effect, characterized in that, The device includes: The acquisition module is used to acquire the first turbine efficiency and the first Reynolds number of the gas turbine under the first operating condition, and the second Reynolds number under the second operating condition; The determining module is configured to determine the second turbine efficiency of the gas turbine under the second operating condition based on the first Reynolds number, the first turbine efficiency, the second Reynolds number, and the target expression. The target expression is: ； in, η 1 represents the first turbine efficiency, and the Reynolds number is... Re 1 is the first Reynolds number. Reynolds number Re 2 is the second Reynolds number. η 2 represents the efficiency of the second turbine; the sum of parameters A, B, and C is 1; The parameters of the target expression include: a first parameter and a second parameter; The determining module is specifically used to determine the second turbine efficiency by using the first parameter as a parameter of the target expression when the first Reynolds number is in the non-self-modular region; or, The determining module is specifically used to determine the second turbine efficiency by using the second parameter as a parameter of the target expression when the first Reynolds number is in the self-mode region.

5. The apparatus according to claim 4, characterized in that, When the first parameter is used as a parameter of the target expression, the target expression is: 。 6. The apparatus according to claim 4, characterized in that, When the second parameter is used as a parameter of the target expression, the target expression is: 。 7. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the steps of the method for correcting gas turbine performance test results considering Reynolds number effects as described in any one of claims 1 to 3.

8. A computer program product comprising a computer program / instructions, characterized in that, When the computer program / instruction is executed by the processor, it implements the steps of the method for correcting gas turbine performance test results considering Reynolds number effects as described in any one of claims 1 to 3.

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