A multi-stage compressor aerodynamic matching design method

Abstract

The present invention belongs to the technical field of compressor aerodynamic design. The present invention provides a multi-stage compressor aerodynamic matching design method, including: successively detecting the uniformity of the wake flow of the front-stage blades among adjacent blades of a multi-stage compressor; if it is not uniform, then through correlation analysis, judging whether the uniformity of the wake flow of the front-stage blades among adjacent blades can be adjusted by adjusting the inter-blade stage spacing between adjacent blades. If so, then adjust the inter-blade stage spacing between adjacent blades according to the results of the correlation analysis, thereby reducing the vibration and fatigue risks of the rear-stage blades among adjacent blades and ensuring the safe and stable operation of the multi-stage compressor. After adjusting the inter-blade stage spacing between adjacent blades, through mutual deviation analysis of the inter-blade stage spacing between adjacent blades under different working conditions and combining the application proportion performance of the working conditions in the flight profile mission, screen the reference group of blade stage spacing as the reference data for the multi-stage compressor aerodynamic matching design, realizing a more comprehensive and reasonable multi-stage compressor aerodynamic matching design.

Description

Technical Field

[0001] The present invention belongs to the technical field of compressor aerodynamic design, and specifically relates to a multi-stage compressor aerodynamic matching design method. Background Art

[0002] In equipment such as aero-engines, the multi-stage compressor, as a key component, its operating performance is crucial to the overall stability and efficiency of the equipment. At present, there are many deficiencies in the operation simulation and aerodynamic matching design of multi-stage compressors in the prior art. On the one hand, during the operation of the multi-stage compressor, the uniformity of the wake flow of the front-stage blades among adjacent blades is not effectively detected and regulated, resulting in uneven wake flow of the front-stage blades, making the rear-stage blades bear unstable aerodynamic forces, increasing the risk of vibration and fatigue, and seriously affecting the safe and stable operation of the multi-stage compressor. On the other hand, during the aerodynamic matching design of the multi-stage compressor, there is a lack of systematic analysis and optimization of the inter-blade stage spacing under different working conditions, and it is impossible to screen appropriate reference data for the inter-blade stage spacing in combination with the application proportion of the working conditions in the flight profile mission, resulting in an incomplete and unreasonable aerodynamic matching design and making it difficult to meet the actual operation requirements. These problems restrict the improvement of the performance of multi-stage compressors and the expansion of their applications.

[0003] Therefore, the present invention provides a multi-stage compressor aerodynamic matching design method. Summary of the Invention

[0004] In order to make up for the deficiencies of the prior art and solve at least one of the technical problems proposed in the background art.

[0005] The technical solution adopted by the present invention to solve its technical problems is as follows:

[0006] A multi-stage compressor aerodynamic matching design method, comprising:

[0007] During the operation simulation of the multi-stage compressor under different working conditions, the uniformity of the wake flow of the front-stage blades among adjacent blades of the multi-stage compressor is detected in sequence;

[0008] If the detection result shows non-uniformity, then through correlation analysis, it is judged whether the uniformity of the wake flow of the front-stage blades among adjacent blades can be adjusted by adjusting the inter-blade stage spacing;

[0009] If it can, then the inter-blade stage spacing between adjacent blades is adjusted according to the correlation analysis result;

[0010] After the inter-blade stage spacing between adjacent blades is adjusted, the inter-blade stage spacing under different working conditions is recorded and integrated to obtain a parameter group of the inter-blade stage spacing under different working conditions;

[0011] Perform blade stage spacing deviation analysis on the adjacent blade stage spacing parameter groups under different working conditions, and combine the application performances under different working conditions to screen the blade stage spacing reference group from the adjacent blade stage spacing parameter groups under different working conditions.

[0012] Further, the process of detecting the uniformity of the wake flow of the front-stage blades among adjacent blades of a multistage compressor is as follows:

[0013] According to the operation simulation results of the multistage compressor, extract the air flow velocities at each grid node in the wake region between adjacent blades, and integrate them to obtain a grid air flow sequence. Calculate and integrate the standard deviations of each grid air flow sequence to obtain an air flow uniformity index sequence;

[0014] Through the processing and analysis of the air flow uniformity index sequence, obtain the blade wake uniformity characteristics, including non-uniformity maintenance characteristics and non-uniformity deviation characteristics;

[0015] Sum the non-uniformity maintenance characteristics and the non-uniformity deviation characteristics to obtain the wake air flow uniformity value;

[0016] If the wake air flow uniformity value is greater than the preset wake air flow uniformity threshold, it indicates that the wake air flow of the front-stage blades is non-uniform; otherwise, it indicates that the wake air flow of the front-stage blades is uniform.

[0017] Further, the method for obtaining the non-uniformity maintenance characteristics is as follows:

[0018] In the air flow uniformity index sequence, count the proportion of the number of air flow uniformity indexes greater than the preset uniformity index to obtain the non-uniformity maintenance characteristics.

[0019] Further, the method for obtaining the non-uniformity deviation characteristics is as follows:

[0020] Calculate the deviation between the mean value of the air flow uniformity indexes greater than the preset uniformity index after averaging and the preset uniformity index to determine the degree of air flow non-uniformity, and obtain the ratio of the degree of air flow non-uniformity to the preset uniformity index to obtain the non-uniformity deviation characteristics.

[0021] Further, the correlation analysis process is as follows:

[0022] Integrate the different adjacent blade stage spacings and the wake air flow uniformity values obtained after performing multistage compressor operation simulations on different adjacent blade stage spacings respectively to obtain a stage spacing sequence and a wake air flow uniformity sequence;

[0023] Use the Pearson correlation coefficient method to calculate the correlation between the stage spacing sequence and the wake air flow uniformity sequence to obtain the Pearson correlation coefficient, and perform absolute value processing to obtain the correlation value between the stage spacing and the wake air flow uniformity;

[0024] If the correlation value is greater than or equal to the correlation threshold, it indicates that the uniformity of the wake airflow in the previous-stage blades of the adjacent blade groups can be adjusted by adjusting the inter-stage spacing of the adjacent blades.

[0025] Furthermore, the process of adjusting the inter-stage spacing of adjacent blades according to the correlation analysis results is as follows:

[0026] Draw a curve of the wake airflow uniformity value changing with the inter-stage spacing based on the inter-stage spacing sequence and the wake airflow uniformity sequence, and perform curve fitting using the least squares method to obtain a correlation adjustment model;

[0027] Obtain the deviation between the wake airflow uniformity value and the preset wake airflow uniformity threshold to get the wake airflow uniformity adjustment amount;

[0028] Use the wake airflow uniformity adjustment amount as the input of the correlation adjustment model, output the inter-stage spacing adjustment value, and adjust the inter-stage spacing of adjacent blades according to the inter-stage spacing adjustment value.

[0029] Furthermore, the process of screening the reference group of blade inter-stage spacings is as follows:

[0030] Perform deviation processing on the adjacent blade inter-stage spacing parameter group and other adjacent blade inter-stage spacing parameter groups to obtain the inter-stage spacing deviation performance value of the adjacent blade inter-stage spacing parameter group;

[0031] Obtain the deviation between the application performance value of the working condition and the inter-stage spacing deviation performance value of the adjacent blade inter-stage spacing parameter group to get the working condition priority value;

[0032] Among all working conditions, select the adjacent blade inter-stage spacing parameter group corresponding to the working condition with the largest working condition priority value as the reference group of blade inter-stage spacings.

[0033] Furthermore, the specific way to obtain the inter-stage spacing deviation performance value of the adjacent blade inter-stage spacing parameter group is as follows:

[0034] Use the Manhattan distance method to calculate the inter-stage spacing deviation between the adjacent blade inter-stage spacing parameter group and other adjacent blade inter-stage spacing parameter groups, and perform mean value processing on the obtained inter-stage spacing deviation to get the average inter-stage spacing difference of the adjacent blade inter-stage spacing parameter group. Obtain the ratio of the average inter-stage spacing difference of the adjacent blade inter-stage spacing parameter group to the total average inter-stage spacing difference to get the inter-stage spacing deviation performance value of the adjacent blade inter-stage spacing parameter group.

[0035] Furthermore, the total average inter-stage spacing difference is obtained by summing up the average inter-stage spacing differences of all adjacent blade inter-stage spacing parameter groups.

[0036] Furthermore, the application performance value of the working condition is the proportion of the application duration of different working conditions corresponding to a multi-stage compressor in the flight mission profile.

[0037] The beneficial effects of the present invention are as follows:

[0038] 1. During the operation simulation of a multi-stage compressor under different working conditions, the uniformity of the wake flow of the front-stage blades among adjacent blades of the multi-stage compressor is detected in sequence; if it is not uniform, through correlation analysis, it is judged whether the uniformity of the wake flow of the front-stage blades among adjacent blades can be adjusted by adjusting the inter-blade stage spacing. If so, the inter-blade stage spacing is adjusted according to the correlation analysis results. Through the analysis of the uniformity of the wake flow of the front-stage blades, and on the premise that the uniformity of the wake flow of the front-stage blades among adjacent blades can be adjusted by adjusting the inter-blade stage spacing, the inter-blade stage spacing is adjusted to make the uniformity of its blade wake flow meet the set requirements, thereby reducing the vibration and fatigue risks of the rear-stage blades among adjacent blades and ensuring the safe and stable operation of the multi-stage compressor.

[0039] 2. After the inter-blade stage spacing is adjusted, through the mutual deviation analysis of the inter-blade stage spacing under different working conditions and combined with the application proportion performance of the working conditions in the flight profile mission, a reference group of blade stage spacings is selected from the group of inter-blade stage spacings under different working conditions as the reference data for the start-up matching design of the multi-stage compressor, realizing a more comprehensive and reasonable aerodynamic matching design of the multi-stage compressor. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] The present invention will be further described below with reference to the drawings.

[0041] Figure 1 is the flowchart of the steps of a method for aerodynamic matching design of a multi-stage compressor according to Embodiment 1 of the present invention;

[0042] Figure 2 is the flowchart of the steps of a method for aerodynamic matching design of a multi-stage compressor according to Embodiment 2 of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0043] In order to make the technical means, creative features, achieved purposes and effects of the present invention easy to understand, the present invention will be further described below in conjunction with specific embodiments.

[0044] Embodiment 1: Please refer to Figure 1 As shown, a method for aerodynamic matching design of a multi-stage compressor according to an embodiment of the present invention includes the following steps:

[0045] S1: During the operation simulation of a multi-stage compressor under different working conditions, the uniformity of the wake flow of the front-stage blades among adjacent blades of the multi-stage compressor is detected in sequence;

[0046] S2: If the detection result of the uniformity of the wake flow of the front-stage blades shows non-uniformity, then through correlation analysis, it is judged whether the uniformity of the wake flow of the front-stage blades among adjacent blades can be adjusted by adjusting the inter-stage spacing between adjacent blade stages;

[0047] S3: If the uniformity of the wake flow of the front-stage blades among adjacent blade groups can be adjusted by adjusting the inter-stage spacing between adjacent blade stages, then adjust the inter-stage spacing between adjacent blade stages according to the correlation analysis result;

[0048] The method described in S1-S3 above simulates the operation of a multi-stage compressor under different working conditions, detects the uniformity of the wake flow of the front-stage blades, and conducts an analysis of the adjustment of the inter-stage spacing between adjacent blade stages according to the detection result, so as to achieve the reference design of the uniform matching of the air flow between multiple blades in the multi-stage compressor.

[0049] The specific implementation of S1 is as follows:

[0050] In S1, different working conditions include the acceleration state working condition, the constant speed state working condition, and the deceleration state working condition of the engine;

[0051] In S1, the execution process of simulating the operation of the multi-stage compressor is specifically as follows:

[0052] According to the accurate geometric design drawings of the compressor, use 3D modeling software (such as SolidWorks, CATIA, etc.) to construct a 3D model of the multi-stage compressor including the moving blades and static blades of each stage. Import the constructed 3D model of the multi-stage compressor into the selected CFD software. According to the engine takeoff thrust requirement, refer to the relevant engine performance manual, and set the boundary parameters such as the air flow velocity, temperature, and pressure under different working conditions. At the same time, conduct grid division on the wake area (internal flow field) between adjacent blades in the multi-stage compressor, and conduct simulation of the operation of the multi-stage compressor after grid division. Among them, the grid division method specifically uses local refinement technology to generate high-quality structured grids;

[0053] In S1, the process of detecting the uniformity of the wake flow of the front-stage blades among adjacent blades of the multi-stage compressor in sequence is as follows:

[0054] According to the simulation result of the operation of the multi-stage compressor, extract the air flow velocity at each grid node in the wake area between adjacent blades, and integrate to obtain the grid air flow sequence;

[0055] Obtain the grid air flow sequences at different simulation times, calculate the standard deviation corresponding to each grid air flow sequence to obtain the air flow uniformity index at different simulation times, and integrate to obtain the air flow uniformity index sequence;

[0056] It is understandable that the standard deviation corresponding to each grid air flow sequence is calculated. The standard deviation reflects the uniformity of the air flow velocities at different grid nodes within the grid air flow sequence, which is an air flow uniformity index. And the grid air flow sequence only corresponds to a certain instantaneous simulation moment during the operation of the multistage compressor. Therefore, the standard deviations (air flow uniformity indices) corresponding to the grid air flow sequences at different simulation moments are integrated to obtain an air flow uniformity index sequence. The air flow uniformity index sequence contains the air flow uniformity indices in the wake region between adjacent blades during the entire simulation process, and can reflect the air flow uniformity situation in the wake region between adjacent blades during the entire simulation process;

[0057] In the air flow uniformity index sequence, the air flow uniformity index is compared and analyzed with a preset uniformity index to obtain the wake uniformity characteristics of the blades, including non-uniform maintenance characteristics and non-uniform deviation characteristics. Specifically:

[0058] The proportion of the number of air flow uniformity indices greater than the preset uniformity index is statistically calculated to obtain the non-uniform maintenance characteristics;

[0059] The deviation between the mean value of the air flow uniformity indices greater than the preset uniformity index after averaging and the preset uniformity index is calculated to determine the degree of air flow non-uniformity, and the ratio of the degree of air flow non-uniformity to the preset uniformity index is obtained to get the non-uniform deviation characteristics;

[0060] Exemplarily, assume that the air flow uniformity indices greater than the preset uniformity index are QL1, QL2, QL3......QLn respectively, n is the number of air flow uniformity indices greater than the preset uniformity index, and the preset uniformity index is YQL; then the calculation method of the non-uniform deviation characteristic FJT is:

[0061]

[0062] The non-uniform maintenance characteristics and non-uniform deviation characteristics are summed to obtain the wake air flow uniformity value;

[0063] The wake air flow uniformity value is compared with a preset wake air flow uniformity threshold;

[0064] If the wake air flow uniformity value is greater than the preset wake air flow uniformity threshold, it indicates that the wake air flow of the previous-stage blades is non-uniform;

[0065] If the wake air flow uniformity value is less than or equal to the preset wake air flow uniformity threshold, it indicates that the wake air flow of the previous-stage blades is uniform, then the current inter-blade stage spacing remains unchanged, and the wake air flow uniformity of the next group of adjacent blades is detected;

[0066] It should be noted that there are multiple stages of blades in a multistage compressor. When conducting the detection of the uniformity of wake flow, it is carried out sequentially. For example, if the blade numbers in a multistage compressor are in the order of 1 - 2 - 3 - 4......Z, then the adjacent blades for which the wake flow uniformity detection is preferentially carried out are 1 - 2, and the detection sequence is 1 - 2, 2 - 3, 3 - 4......(Z - 1) - Z, where Z is the number of blades in the multistage compressor. The significance of conducting the detection sequentially is as follows: The wake flow uniformity detection is carried out in order, and adjustments are made when it is non-uniform, so that the adjustments of each subsequent group of adjacent blades are not affected by the adjustments of the previous group of adjacent blades;

[0067] It can be understood that the physical meaning of summing the non-uniform maintenance feature and the non-uniform deviation feature to obtain the wake flow uniformity value is as follows: The non-uniform maintenance feature reflects the proportion of the number of airflow uniformity indicators greater than the preset uniformity index. If the proportion is relatively large, it reflects that in the operation simulation of the multistage compressor, the wake flow of the front-stage blades is non-uniform at multiple simulation moments, which is more accurate compared to the wake flow uniformity detection at a single simulation moment. The non-uniform deviation feature reflects the comprehensive deviation degree between the airflow uniformity index and the preset uniformity index. If the deviation degree is large, it reflects that in the operation simulation of the multistage compressor, the degree of non-uniformity of the wake flow of the front-stage blades is relatively serious. Therefore, summing the non-uniform maintenance feature and the non-uniform deviation feature comprehensively reflects the uniformity of the wake flow of the front-stage blades among adjacent blades of the multistage compressor through the maintenance performance and severity of the non-uniformity phenomenon of the blade wake flow;

[0068] The specific implementation of S2 is as follows:

[0069] In S2, if the detection result of the wake flow uniformity of the front-stage blades shows non-uniformity, the execution process of the correlation analysis is as follows:

[0070] Set different inter-stage spacings between adjacent blades, and conduct the operation simulation of the multistage compressor. Integrate the different inter-stage spacings between adjacent blades and the wake flow uniformity values obtained after the operation simulation of the multistage compressor with different inter-stage spacings between adjacent blades respectively to obtain an inter-stage spacing sequence and a wake flow uniformity sequence;

[0071] Use the Pearson correlation coefficient method to calculate the correlation between the inter-stage spacing sequence and the wake flow uniformity sequence, obtain the Pearson correlation coefficient, and perform absolute value processing to obtain the correlation value between the inter-stage spacing and the wake flow uniformity;

[0072] Compare the correlation value with the correlation threshold;

[0073] If the correlation value is greater than or equal to the correlation threshold, it indicates that there is a linear variation correlation between the adjacent blade stage spacing and the uniformity of the wake flow of the previous stage blades in the adjacent blade group. The uniformity of the wake flow of the previous stage blades in the adjacent blade group can be adjusted by adjusting the adjacent blade stage spacing;

[0074] If the correlation value is less than the correlation threshold, it indicates that there is no linear variation correlation between the adjacent blade stage spacing and the uniformity of the wake flow of the previous stage blades in the adjacent blade group. Then, other adjustment analyses are performed, including but not limited to wake flow guidance and blade profile adjustment;

[0075] It can be understood that by judging whether the uniformity of the wake flow of the previous stage blades in the adjacent blades can be adjusted by adjusting the adjacent blade stage spacing, it can provide a basis for the subsequent adjustment of the uniformity of the wake flow of the previous stage blades in the adjacent blades. Among them, using the Pearson correlation coefficient to analyze the correlation between the adjacent blade stage spacing and the uniformity of the wake flow of the previous stage blades in the adjacent blade group can effectively judge whether there is a linear correlation. Its significance lies in that if there is a linear correlation, it indicates that there is a regular linear influence between the adjacent blade stage spacing and the uniformity of the wake flow of the previous stage blades in the adjacent blade group. Then, the adjacent blade stage spacing can be adjusted according to the uniformity of the wake flow, so that the uniformity of its wake flow can meet the set requirements of uniformity;

[0076] The specific implementation of S3 is as follows:

[0077] In S3, the execution process of adjusting the adjacent blade stage spacing according to the correlation analysis result includes:

[0078] In the X-Y coordinate system, according to the stage spacing sequence and the wake flow uniformity sequence, draw a change curve of the wake flow uniformity value with respect to the stage spacing, and use the least squares method for curve fitting to obtain a fitting model, which is the correlation adjustment model;

[0079] Obtain the deviation between the wake flow uniformity value and the preset wake flow uniformity threshold to get the wake flow uniformity adjustment amount;

[0080] Use the wake flow uniformity adjustment amount as the input of the correlation adjustment model and output the stage spacing adjustment value;

[0081] Adjust the adjacent blade stage spacing according to the stage spacing adjustment value. After adjusting the adjacent blade stage spacing, continue to detect and adjust the wake flow uniformity of the previous stage blades for the next group of adjacent blades until all adjacent blades are detected and adjusted;

[0082] It can be understood that, according to the inter-stage spacing sequence and the wake flow uniformity sequence, a change curve of the wake flow uniformity value with respect to the inter-stage spacing is plotted, and curve fitting is performed using the least squares method to obtain a fitting model. This fitting model reflects the linear change relationship between the inter-stage spacing of adjacent blades and the wake flow uniformity of the leading blade in the adjacent blades. When the wake flow uniformity of the leading blade in the adjacent blades does not meet the set requirements, the deviation between the wake flow uniformity of the leading blade in the adjacent blades and the set requirements, that is, the wake flow uniformity adjustment amount, is used as the input of the fitting model, so as to output the adjustment amount of the inter-stage spacing of the adjacent blades, and then adjust the inter-stage spacing of the adjacent blades according to the adjustment amount of the inter-stage spacing of the adjacent blades, so that the wake flow uniformity of the leading blade in the adjacent blades can meet the set requirements, thereby reducing the vibration and fatigue risks of the trailing blade in the adjacent blades and ensuring the safe and stable operation of the multi-stage compressor;

[0083] Embodiment 2: Please refer to Figure 2 As shown, for a multi-stage compressor aerodynamic matching design method described in an embodiment of the present invention, on the basis of Embodiment 1, after adjusting the inter-stage spacing of adjacent blades of the multi-stage compressor, considering that the design of the inter-stage spacing of the blades of the multi-stage compressor needs to face the problem of different working conditions, therefore, deviation analysis is performed on the inter-stage spacing parameter groups of the blades under different working conditions, aiming to find a better inter-stage spacing parameter group as the final design reference for the inter-stage spacing of the blades of the multi-stage compressor, and provide a more comprehensive design basis for the aerodynamic matching design of the multi-stage compressor. This embodiment includes the following steps:

[0084] S4: After adjusting the inter-stage spacing of adjacent blades, record and integrate the inter-stage spacing of adjacent blades under different working conditions to obtain the inter-stage spacing parameter groups of adjacent blades under different working conditions;

[0085] S5: Perform inter-stage spacing deviation analysis on the inter-stage spacing parameter groups of adjacent blades under different working conditions, and combine the application performance of different working conditions to screen the inter-stage spacing reference group from the inter-stage spacing parameter groups of adjacent blades under different working conditions;

[0086] The methods described in S4 and S5 above record and integrate the inter-stage spacing of adjacent blades under different working conditions to obtain the inter-stage spacing parameter groups of adjacent blades under different working conditions; and perform inter-stage spacing deviation analysis to screen the inter-stage spacing reference group, so as to provide a reference basis for the airflow uniform matching design between multiple stages of blades in the multi-stage compressor more comprehensively and accurately;

[0087] The specific implementation of S4 is:

[0088] In S4, after the adjustment of the adjacent blade stage spacing, record and integrate the adjacent blade stage spacings under different working conditions to obtain the adjacent blade stage spacing parameter groups under different working conditions. Among them, each working condition corresponds to a group of adjacent blade stage spacing parameter groups adjusted according to the air flow uniformity between multiple stages of blades;

[0089] The specific implementation of S5 is as follows:

[0090] In S5, the process of analyzing the blade stage spacing deviation of the adjacent blade stage spacing parameter groups under different working conditions and screening the reference group of blade stage spacings in combination with the application performance of different working conditions is as follows:

[0091] Based on any group of adjacent blade stage spacing parameter groups, use the Manhattan distance method to calculate the stage spacing deviation between the adjacent blade stage spacing parameter group and other adjacent blade stage spacing parameter groups, and perform an averaging process on the obtained stage spacing deviations to obtain the average stage spacing difference of the adjacent blade stage spacing parameter group;

[0092] Exemplarily, the method of using the Manhattan distance method to calculate the stage spacing deviation between the adjacent blade stage spacing parameter group and other adjacent blade stage spacing parameter groups is as follows:

[0093] Suppose the stage spacing deviation between two groups of adjacent blade stage spacing parameter groups is calculated. The first group of adjacent blade stage spacing parameter group is (x1, x2, x3......xn), xn represents the nth adjacent blade stage spacing, n is the number of adjacent blade stage spacing parameters, and the second group of adjacent blade stage spacing parameter group is (y1, y2, y3......yn), yn represents the nth adjacent blade stage spacing, n is the number of adjacent blade stage spacing parameters;

[0094] Through the Manhattan distance formula: , calculate the stage spacing deviation PC between the two groups of adjacent blade stage spacing parameter groups; where xi represents the ith adjacent blade stage spacing in the first group of adjacent blade stage spacing parameter groups, and yi represents the ith adjacent blade stage spacing in the second group of adjacent blade stage spacing parameter groups;

[0095] Based on the average stage spacing difference of any group of adjacent blade stage spacing parameter groups, obtain the ratio of the average stage spacing difference of the adjacent blade stage spacing parameter group to the total average stage spacing difference to obtain the stage spacing deviation performance value of the adjacent blade stage spacing parameter group;

[0096] Among them, the total average stage spacing difference is obtained by summing the average stage spacing differences of all adjacent blade stage spacing parameter groups;

[0097] Based on historical flight reports, obtain the proportion of application duration of different operating conditions corresponding to a multistage compressor in the flight mission profile, and respectively obtain the application performance values of each operating condition;

[0098] It should be noted that the meaning of the application duration of an operating condition is: the operating duration of the multistage compressor under different operating conditions;

[0099] Exemplarily, analyze the operating conditions of each compressor, such as the acceleration condition during takeoff, the constant-speed condition during cruise, the deceleration condition during landing, etc., and determine the application performance value of the operating condition according to its proportion in the flight mission profile. For example, if the cruise time of a certain type of civil airliner accounts for 70% of the total flight time (constant-speed condition), the takeoff and landing phases (including acceleration and deceleration conditions) together account for 30%, the acceleration condition is 16% and the deceleration condition is 14%, then the application performance value of the constant-speed condition is 0.7, and the acceleration and deceleration conditions are 0.16 and 0.14 respectively;

[0100] Based on any one operating condition, obtain the deviation between the application performance value of the operating condition and the inter-stage spacing deviation performance value of the adjacent blade stage spacing parameter group to obtain the operating condition priority value;

[0101] It should be noted that the operating condition corresponding to the application performance value of the operating condition and the operating condition corresponding to the inter-stage spacing deviation performance value of the adjacent blade stage spacing parameter group are the same operating condition;

[0102] Among all operating conditions, select the adjacent blade stage spacing parameter group corresponding to the operating condition with the largest operating condition priority value as the blade stage spacing reference group;

[0103] It can be understood that after adjusting the adjacent blade stage spacing, by performing mutual deviation analysis on the adjacent blade stage spacings under different operating conditions and combining the application proportion performance of the operating conditions in the flight profile mission, the blade stage spacing reference group is screened from the adjacent blade stage spacing groups under different operating conditions as the reference data for the start-up matching design of the multistage compressor, realizing a more comprehensive and reasonable aerodynamic matching design of the multistage compressor.

[0104] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. What is described in the above embodiments and the specification only illustrates the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and these changes and improvements all fall within the scope of the present invention claimed. The scope of protection claimed by the present invention is defined by the appended claims and their equivalents.

Claims

1. A method for aerodynamic matching design of a multistage compressor, characterized in that: Including: During the operation simulation of a multi-stage compressor under different working conditions, the uniformity of the wake airflow of the front-stage blade among adjacent blades of the multi-stage compressor is detected in sequence; The process of detecting the uniformity of the wake airflow of the front-stage blade among adjacent blades of the multi-stage compressor is as follows: According to the operation simulation results of the multi-stage compressor, the airflow velocities at each grid node in the wake area between adjacent blades are extracted, and a grid airflow sequence is integrated. By calculating and integrating the standard deviations of each grid airflow sequence, an airflow uniformity index sequence is obtained; Through the processing and analysis of the airflow uniformity index sequence, the wake uniformity characteristics of the blade are obtained, including non-uniformity maintenance characteristics and non-uniformity deviation characteristics; The non-uniformity maintenance characteristics and non-uniformity deviation characteristics are summed to obtain the wake airflow uniformity value; If the wake airflow uniformity value is greater than the preset wake airflow uniformity threshold, it indicates that the wake airflow of the front-stage blade is non-uniform, otherwise it indicates that the wake airflow of the front-stage blade is uniform; The acquisition method of the non-uniformity maintenance characteristics is as follows: In the airflow uniformity index sequence, the proportion of the number of airflow uniformity indexes greater than the preset uniformity index is statistically calculated to obtain the non-uniformity maintenance characteristics; The acquisition method of the non-uniformity deviation characteristics is as follows: Calculate the deviation between the mean value of the airflow uniformity indexes greater than the preset uniformity index after mean value processing and the preset uniformity index, determine the degree of airflow non-uniformity, and obtain the proportion of the degree of airflow non-uniformity to the preset uniformity index to obtain the non-uniformity deviation characteristics; If the detection result shows non-uniformity, through correlation analysis, it is judged whether the uniformity adjustment of the wake airflow of the front-stage blade among adjacent blades can be achieved by adjusting the inter-blade stage spacing; If it can, the inter-blade stage spacing between adjacent blades is adjusted according to the correlation analysis result; After adjusting the inter-blade stage spacing between adjacent blades, the inter-blade stage spacings under different working conditions are recorded and integrated to obtain a parameter group of the inter-blade stage spacings under different working conditions; Perform an inter-blade stage spacing deviation analysis on the parameter group of the inter-blade stage spacings under different working conditions, and combine the application performance of different working conditions to screen a reference group of the inter-blade stage spacings from the parameter group of the inter-blade stage spacings under different working conditions.

2. A pneumatic matching design method for a multi-stage compressor according to claim 1, characterized in that: The correlation analysis process is as follows: The inter-stage spacing sequences and the wake airflow uniformity sequences obtained by integrating the different inter-blade stage spacings and the wake airflow uniformity values obtained after the operation simulation of the multi-stage compressor with different inter-blade stage spacings are respectively integrated; The Pearson correlation coefficient method is used to calculate the correlation between the inter-stage spacing sequence and the wake airflow uniformity sequence, and the Pearson correlation coefficient is obtained and absolute value processing is performed to obtain the correlation value between the inter-stage spacing and the wake airflow uniformity; If the correlation value is greater than or equal to the correlation threshold, it indicates that the uniformity adjustment of the wake airflow of the front-stage blade among adjacent blade groups can be achieved by adjusting the inter-blade stage spacing.

3. A pneumatic matching design method for a multi-stage compressor according to claim 2, characterized in that: The process of adjusting the inter-blade stage spacing between adjacent blades according to the correlation analysis result is: Draw a curve showing the variation of the wake flow uniformity value with the inter-stage spacing based on the inter-stage spacing sequence and the wake flow uniformity sequence, and perform curve fitting using the least squares method to obtain an associated adjustment model; Obtain the deviation between the wake flow uniformity value and the preset wake flow uniformity threshold to get the wake flow uniformity adjustment amount; Use the wake flow uniformity adjustment amount as the input of the associated adjustment model, output the inter-stage spacing adjustment value, and adjust the adjacent blade inter-stage spacing according to the inter-stage spacing adjustment value.

4. A multi-stage compressor aerodynamic matching design method according to claim 1, characterized in that: The process of screening the reference group of blade inter-stage spacings is as follows: Perform deviation processing on the adjacent blade inter-stage spacing parameter group and other adjacent blade inter-stage spacing parameter groups to obtain the inter-stage spacing deviation performance value of the adjacent blade inter-stage spacing parameter group; Obtain the deviation between the application performance value of the working condition and the inter-stage spacing deviation performance value of the adjacent blade inter-stage spacing parameter group to get the working condition priority value; Among all working conditions, select the adjacent blade inter-stage spacing parameter group corresponding to the working condition with the largest working condition priority value as the reference group of blade inter-stage spacings.

5. A multi-stage compressor aerodynamic matching design method according to claim 4, characterized in that: The specific way to obtain the inter-stage spacing deviation performance value of the adjacent blade inter-stage spacing parameter group is as follows: Calculate the inter-stage spacing deviation between the adjacent blade inter-stage spacing parameter group and other adjacent blade inter-stage spacing parameter groups using the Manhattan distance method, perform mean value processing on the obtained inter-stage spacing deviation to get the inter-stage spacing average difference of the adjacent blade inter-stage spacing parameter group, and obtain the ratio of the inter-stage spacing average difference of the adjacent blade inter-stage spacing parameter group to the total inter-stage spacing average difference to get the inter-stage spacing deviation performance value of the adjacent blade inter-stage spacing parameter group.

6. A multi-stage compressor aerodynamic matching design method according to claim 5, characterized in that: The total inter-stage spacing average difference is obtained by summing the inter-stage spacing average differences of all adjacent blade inter-stage spacing parameter groups.

7. A multi-stage compressor aerodynamic matching design method according to claim 4, characterized in that: The application performance value of the working condition is the proportion of the application duration of different working conditions corresponding to the multi-stage compressor in the flight mission profile.

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