Pneumatic matching design method for multi-stage gas compressor

Abstract

The invention belongs to the technical field of pneumatic design of gas compressors, and provides a pneumatic matching design method of a multi-stage gas compressor, which comprises the following steps of: detecting the wake airflow uniformity of a front-stage blade in adjacent blades of the multi-stage gas compressor in sequence; if the wake airflow is not uniform, whether the wake airflow of the front-stage blade in the adjacent blades can be uniformly adjusted by adjusting the inter-stage distance of the adjacent blades or not is judged through correlation analysis, and if yes, the inter-stage distance of the adjacent blades is adjusted according to a correlation analysis result, so that the vibration and fatigue risks of the rear-stage blade in the adjacent blades are reduced; the method comprises the steps that after the inter-stage spacing of adjacent blades is adjusted, mutual deviation analysis is conducted on the inter-stage spacing of the adjacent blades under different working conditions, and in combination with application proportion performance of the working conditions in a flight profile task, a blade inter-stage spacing reference set is screened; and as reference data of pneumatic matching design of the multi-stage gas compressor, more comprehensive and reasonable pneumatic matching design of the multi-stage gas compressor is realized.

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 aeroengines, the multi-stage compressor, as a key component, its operating performance is crucial for 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, causing the rear-stage blades to bear unstable aerodynamic forces, increasing the risks 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 spacing between adjacent blades under different working conditions, and it is impossible to screen appropriate reference data for the inter-blade spacing by combining the application proportion of the working conditions in the flight profile mission, resulting in an incomplete and unreasonable aerodynamic matching design and being difficult to meet the actual operation requirements. These problems restrict the improvement of the performance and the expansion of the application of the multi-stage compressor.

[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: A multi-stage compressor aerodynamic matching design method, comprising: 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 sequentially detected; 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 spacing between adjacent blades; If it can, then the inter-blade spacing between adjacent blades is adjusted according to the correlation analysis result; After the inter-blade spacing between adjacent blades is adjusted, the inter-blade spacing between adjacent blades under different working conditions is recorded and integrated to obtain a parameter group of the inter-blade spacing between adjacent blades under different working conditions; The deviation analysis of the inter-blade spacing is carried out on the parameter group of the inter-blade spacing between adjacent blades under different working conditions, and in combination with the application performance of different working conditions, a reference group of the inter-blade spacing is screened from the parameter group of the inter-blade spacing between adjacent blades under different working conditions.

[0006] Further, the process of detecting the uniformity of the wake flow of the front-stage blade among adjacent blades of the multistage compressor is as follows: 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; Through the processing and analysis of the air flow uniformity index sequence, obtain the wake uniformity characteristics of the blade, including the non-uniformity maintenance characteristic and the non-uniformity deviation characteristic; Sum the non-uniformity maintenance characteristic and the non-uniformity deviation characteristic to obtain the wake air flow uniformity value; 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 blade is non-uniform, otherwise it indicates that the wake air flow of the front-stage blade is uniform.

[0007] Further, the method for obtaining the non-uniformity maintenance characteristic is as follows: 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 characteristic.

[0008] Further, the method for obtaining the non-uniformity deviation characteristic is as follows: 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 characteristic.

[0009] Further, the correlation analysis process is as follows: Integrate the wake air flow uniformity values obtained after performing multistage compressor operation simulations on different adjacent blade inter-stage spacings and different adjacent blade inter-stage spacings respectively to obtain an inter-stage spacing sequence and a wake air flow uniformity sequence; Use the Pearson correlation coefficient method to calculate the correlation between the inter-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 inter-stage spacing and the wake air flow uniformity; If the correlation value is greater than or equal to the correlation threshold, it indicates that the uniformity of the wake air flow of the front-stage blade in the adjacent blade group can be adjusted by adjusting the adjacent blade inter-stage spacing.

[0010] Further, the process of adjusting the adjacent blade inter-stage spacing according to the correlation analysis result is as follows: Draw a change curve of the wake air flow uniformity value with respect to the inter-stage spacing based on the inter-stage spacing sequence and the wake air flow uniformity sequence, and use the least squares method for curve fitting to obtain a correlation adjustment model; Obtain the deviation between the wake airflow uniformity value and the preset wake airflow uniformity threshold to obtain the wake airflow uniformity adjustment amount; 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 adjacent blade inter-stage spacing according to the inter-stage spacing adjustment value.

[0011] Further, the process of screening the blade inter-stage spacing reference group 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 obtain 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 blade inter-stage spacing reference group.

[0012] Further, the specific method for obtaining the inter-stage spacing deviation performance value of the adjacent blade inter-stage spacing parameter group is as follows: 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 averaging processing on the obtained inter-stage spacing deviation to obtain the inter-stage spacing average difference of the adjacent blade inter-stage spacing parameter group. 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 obtain the inter-stage spacing deviation performance value of the adjacent blade inter-stage spacing parameter group.

[0013] Further, 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.

[0014] Further, 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.

[0015] The beneficial effects of the present invention are as follows: 1. During the operation simulation of the multi-stage compressor under different working conditions, the wake airflow uniformity of the front-stage blades among the adjacent blades of the multi-stage compressor is detected in sequence; if it is uneven, through correlation analysis, it is judged whether the wake airflow of the front-stage blades among the adjacent blades can be adjusted to be uniform by adjusting the adjacent blade inter-stage spacing. If so, adjust the adjacent blade inter-stage spacing according to the correlation analysis result. Through the analysis of the wake airflow uniformity of the front-stage blades, and on the premise that the wake airflow of the front-stage blades among the adjacent blades can be adjusted to be uniform by adjusting the adjacent blade inter-stage spacing, adjust the adjacent blade inter-stage spacing so that the wake airflow uniformity of its blades meets the set requirements, thereby reducing the vibration and fatigue risks of the rear-stage blades among the adjacent blades and ensuring the safe and stable operation of the multi-stage compressor.

[0016] 2. After adjusting the inter-stage spacing of adjacent blades, through mutual deviation analysis of the inter-stage spacing of adjacent blades under different working conditions, and combining the application proportion performance of the working conditions in the flight profile mission, a reference group of inter-stage blade spacings is selected from the group of inter-stage blade 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

[0017] The present invention will be further described below with reference to the accompanying drawings.

[0018] Figure 1 is a flowchart of the steps of a method for aerodynamic matching design of a multi-stage compressor according to Embodiment 1 of the present invention; Figure 2 is a 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

[0019] 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.

[0020] 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: S1: 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 the adjacent blades of the multi-stage compressor is detected in sequence; 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 the adjacent blades can be adjusted by adjusting the inter-stage spacing of the adjacent blades; S3: If the uniformity of the wake flow of the front-stage blades among the adjacent blade groups can be adjusted by adjusting the inter-stage spacing of the adjacent blades, then the inter-stage spacing of the adjacent blades is adjusted according to the correlation analysis result; The method described in S1-S3 above realizes the reference design of the uniform matching of the air flow between the multi-stage blades in the multi-stage compressor by simulating the operation of the multi-stage compressor under different working conditions, detecting the uniformity of the wake flow of the front-stage blades, and carrying out the adjustment analysis of the inter-stage spacing of the adjacent blades according to the detection results.

[0021] The specific implementation of S1 is as follows: 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; In S1, the execution process of the operation simulation of the multi-stage compressor is specifically as follows: According to the precise geometric design drawings of the compressor, use 3D modeling software (such as SolidWorks, CATIA, etc.) to construct a 3D model of a multi-stage compressor including the moving blades and stationary 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 manuals to set the boundary parameters such as the velocity, temperature, and pressure of the airflow under different working conditions. At the same time, perform mesh division on the wake region (internal flow field) between adjacent blades in the multi-stage compressor, and conduct simulation of the operation of the multi-stage compressor after mesh division. Among them, the mesh division method specifically uses local refinement technology to generate high-quality structured meshes; In S1, the process of sequentially 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, extract the airflow velocities at each grid node in the wake region between adjacent blades, and integrate them to obtain a grid airflow sequence; Obtain the grid airflow sequences at different simulation times. By calculating the standard deviation corresponding to each grid airflow sequence, obtain the airflow uniformity index at different simulation times, and integrate them to obtain an airflow uniformity index sequence; It can be understood that by calculating the standard deviation corresponding to each grid airflow sequence, the standard deviation reflects the uniformity of the airflow velocities at different grid nodes in the grid airflow sequence, which is an airflow uniformity index. And the grid airflow sequence only corresponds to a certain instantaneous simulation time during the operation of the multi-stage compressor. Therefore, integrate the standard deviations (airflow uniformity indices) corresponding to the grid airflow sequences at different simulation times to obtain an airflow uniformity index sequence. The airflow uniformity index sequence contains the airflow uniformity indices in the wake region between adjacent blades during the entire simulation process, and can reflect the airflow uniformity situation in the wake region between adjacent blades during the entire simulation process; In the airflow uniformity index sequence, compare and analyze the airflow uniformity index with the preset uniformity index to obtain the blade wake uniformity characteristics, including non-uniform maintenance characteristics and non-uniform deviation characteristics. Specifically: Statistical proportion of the number of airflow uniformity indices greater than the preset uniformity index to obtain non-uniform maintenance characteristics; Calculate the deviation between the mean value of the airflow uniformity indices greater than the preset uniformity index after averaging and the preset uniformity index to determine the degree of airflow non-uniformity, and obtain the ratio of the degree of airflow non-uniformity to the preset uniformity index to obtain non-uniform deviation characteristics; Exemplarily, assume that the airflow uniformity indices greater than the preset uniformity index are QL1, QL2, QL3......QLn respectively, where n is the number of airflow 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:

[0022] Sum the non-uniform maintenance feature and the non-uniform deviation feature to obtain the uniformity value of the wake airflow; Compare the uniformity value of the wake airflow with a preset uniformity threshold of the wake airflow; If the uniformity value of the wake airflow is greater than the preset uniformity threshold of the wake airflow, it indicates that the wake airflow of the previous-stage blade is non-uniform; If the uniformity value of the wake airflow is less than or equal to the preset uniformity threshold of the wake airflow, it indicates that the wake airflow of the previous-stage blade is uniform. Then, without changing the current inter-blade spacing between adjacent blades, perform the wake airflow uniformity detection on the next set of adjacent blades; It should be noted that there are multiple stages of blades in a multi-stage compressor. When performing the wake airflow uniformity detection, it is carried out sequentially. For example, if the blade numbers in the multi-stage compressor are in the order of 1-2-3-4......Z, the adjacent blades for which the wake airflow uniformity detection is preferentially performed are 1-2, and the detection sequence is 1-2, 2-3, 3-4......(Z-1)-Z. Here, Z is the number of blades in the multi-stage compressor. The significance of performing the detection sequentially is as follows: perform the wake airflow uniformity detection in order and make adjustments when it is non-uniform, so that the adjustments of the subsequent sets of adjacent blades are not affected by the adjustments of the previous sets of adjacent blades; It can be understood that the physical meaning of summing the non-uniform maintenance feature and the non-uniform deviation feature to obtain the uniformity value of the wake airflow 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 multi-stage compressor, the wake airflow of the previous-stage blade is non-uniform at multiple simulation moments, which is more accurate compared to the wake airflow 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 multi-stage compressor, the degree of non-uniformity of the wake airflow of the previous-stage blade is relatively serious. Therefore, summing the non-uniform maintenance feature and the non-uniform deviation feature comprehensively reflects the uniformity of the wake airflow of the previous-stage blade among adjacent blades in the multi-stage compressor through the maintenance performance and severity of the non-uniformity phenomenon of the blade wake airflow; The specific implementation of S2 is as follows: In S2, if the detection result of the wake airflow uniformity of the previous-stage blade shows non-uniformity, the execution process of the correlation analysis is as follows: Set different inter-blade spacings between adjacent blades and perform the operation simulation of the multi-stage compressor. Integrate the different inter-blade spacings between adjacent blades and the uniformity values of the wake airflow obtained after performing the operation simulation of the multi-stage compressor with different inter-blade spacings between adjacent blades respectively to obtain an inter-blade spacing sequence and a wake airflow uniformity sequence; The Pearson correlation coefficient method is used to calculate the correlation between the inter-stage spacing sequence and the wake airflow uniformity sequence, obtaining the Pearson correlation coefficient, and performing absolute value processing to obtain the correlation value between the inter-stage spacing and the wake airflow uniformity; Compare the correlation value with the correlation threshold; 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 inter-stage spacing and the uniformity of the wake airflow of the previous-stage blades in the adjacent blade group, and the uniformity of the wake airflow of the previous-stage blades in the adjacent blade group can be adjusted by adjusting the adjacent blade inter-stage spacing; If the correlation value is less than the correlation threshold, it indicates that there is no linear variation correlation between the adjacent blade inter-stage spacing and the uniformity of the wake airflow of the previous-stage blades in the adjacent blade group, and other adjustment analyses are performed, including but not limited to wake airflow guidance and blade profile adjustment; It can be understood that by judging whether the uniformity of the wake airflow of the previous-stage blades in the adjacent blades can be adjusted by adjusting the adjacent blade inter-stage spacing, it can provide a basis for the subsequent adjustment of the uniformity of the wake airflow of the previous-stage blades in the adjacent blades. Among them, using the Pearson correlation coefficient to analyze the correlation between the adjacent blade inter-stage spacing and the uniformity of the wake airflow 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 means that there is a regular linear influence between the adjacent blade inter-stage spacing and the uniformity of the wake airflow of the previous-stage blades in the adjacent blade group, and the adjacent blade inter-stage spacing can be adjusted according to the uniformity of the wake airflow so that the uniformity of its wake airflow can meet the set requirements of uniformity; The specific implementation of S3 is as follows: In S3, the execution process of adjusting the adjacent blade inter-stage spacing according to the correlation analysis result includes: In the X-Y coordinate system, draw a change curve of the wake airflow uniformity value with the change of the inter-stage spacing according to the inter-stage spacing sequence and the wake airflow uniformity sequence, and use the least squares method for curve fitting to obtain a fitting model, which is the correlation adjustment model; Obtain the deviation between the wake airflow uniformity value and the preset wake airflow uniformity threshold to obtain the wake airflow uniformity adjustment amount; Take the wake airflow uniformity adjustment amount as the input of the correlation adjustment model and output the inter-stage spacing adjustment value; Adjust the adjacent blade inter-stage spacing according to the inter-stage spacing adjustment value. After adjusting the adjacent blade inter-stage spacing, continue to detect and adjust the wake airflow uniformity of the previous-stage blades for the next group of adjacent blades until all adjacent blades are detected and adjusted; 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 blade stages and the wake flow uniformity of the front-stage blade in adjacent blades. When the wake flow uniformity of the front-stage blade in adjacent blades does not meet the set requirements, the deviation between the wake flow uniformity of the front-stage blade in 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 adjacent blades. Then, the inter-stage spacing of adjacent blades is adjusted according to the adjustment amount of the inter-stage spacing of adjacent blades, so that the wake flow uniformity of the front-stage blade in adjacent blades can meet the set requirements, thereby reducing the vibration and fatigue risks of the rear-stage blade in adjacent blades and ensuring the safe and stable operation of the multi-stage compressor; Example 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 the present invention adjusts the inter-stage spacing of adjacent blade stages of the multi-stage compressor, considering that the design of the inter-stage spacing of the blade stages 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 blade stages under different working conditions. The purpose is to find a better inter-stage spacing parameter group as the final design reference for the inter-stage spacing of the blade stages 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: S4: After adjusting the inter-stage spacing of adjacent blade stages, record and integrate the inter-stage spacing of adjacent blade stages under different working conditions to obtain the inter-stage spacing parameter groups of adjacent blade stages under different working conditions; S5: Perform inter-stage spacing deviation analysis on the inter-stage spacing parameter groups of adjacent blade stages 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 blade stages under different working conditions; The methods described in S4 and S5 above record and integrate the inter-stage spacing of adjacent blade stages under different working conditions to obtain the inter-stage spacing parameter groups of adjacent blade stages 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 a multi-stage compressor more comprehensively and accurately; The specific implementation of S4 is: In S4, after adjusting the inter-stage spacing of adjacent blade stages, record and integrate the inter-stage spacing of adjacent blade stages under different working conditions to obtain the inter-stage spacing parameter groups of adjacent blade stages under different working conditions, where each working condition corresponds to a group of inter-stage spacing parameter groups of adjacent blade stages adjusted according to the airflow uniformity between multiple stages of blades; The specific implementation of S5 is: In S5, the process of analyzing the blade stage spacing deviation for the adjacent blade stage spacing parameter groups under different working conditions and screening the reference group of blade stage spacing in combination with the application performance under different working conditions is as follows: 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; 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: 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), where xn represents the nth adjacent blade stage spacing, and n is the number of adjacent blade stage spacing parameters. The second group of adjacent blade stage spacing parameter group is (y1, y2, y3......yn), where yn represents the nth adjacent blade stage spacing, and n is the number of adjacent blade stage spacing parameters; 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; 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; 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; Based on the historical flight reports, obtain the proportion of the application duration of different working conditions corresponding to the multi-stage compressor in the flight mission profile, and respectively obtain the application performance values of each working condition; It should be noted that the meaning of the application duration of the working condition is: the running duration of the multi-stage compressor under different working conditions; 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; Based on any one of the operating conditions, 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; It should be noted that the operating conditions corresponding to the application performance value of the operating condition and the operating conditions corresponding to the inter-stage spacing deviation performance value of the adjacent blade stage spacing parameter group are the same operating condition; Among all the 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; It can be understood that after the adjacent blade stage spacing is adjusted, 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 multi-stage compressor, realizing a more comprehensive and reasonable aerodynamic matching design of the multi-stage compressor.

[0023] 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 multi-stage 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 blades among adjacent blades of the multi-stage compressor is detected in sequence; If the detection result shows non-uniformity, through correlation analysis, it is judged whether the uniformity of the wake airflow of the front-stage blades among adjacent blades can be adjusted 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 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; Perform an analysis of the deviation of the inter-blade stage spacing on the parameter group of the inter-blade stage spacing under different working conditions, and combine the application performance under different working conditions to screen a reference group of the inter-blade stage spacing from the parameter group of the inter-blade stage spacing under different working conditions.

2. A method for aerodynamic matching design of a multi-stage compressor according to claim 1, characterized in that: The process of detecting the uniformity of the wake airflow of the front-stage blades 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. Through the calculation and integration of 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 blade wake uniformity characteristics are obtained, including non-uniformity maintenance characteristics and non-uniformity deviation characteristics; The non-uniformity maintenance characteristics and the 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 blades is non-uniform, otherwise it indicates that the wake airflow of the front-stage blades is uniform.

3. A method for aerodynamic matching design of a multi-stage compressor according to claim 2, characterized in that: The acquisition method of the non-uniformity maintenance characteristics is: 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.

4. A method for aerodynamic matching design of a multi-stage compressor according to claim 2, characterized in that: The acquisition method of the non-uniformity deviation characteristics is: Calculate the deviation between the mean value of the airflow uniformity indexes greater than the preset uniformity index after averaging and the preset uniformity index to determine the degree of airflow non-uniformity, and obtain the ratio of the degree of airflow non-uniformity to the preset uniformity index to obtain the non-uniformity deviation characteristics.

5. A method for aerodynamic matching design of a multi-stage compressor according to claim 1, characterized in that: The correlation analysis process is: The different inter-blade stage spacings and the wake airflow uniformity values obtained after performing the operation simulation of the multi-stage compressor with different inter-blade stage spacings are respectively integrated to obtain an inter-stage spacing sequence and a wake airflow uniformity sequence; The Pearson correlation coefficient method is used to calculate the correlation between the inter-stage spacing sequence and the wake airflow uniformity sequence to obtain the Pearson correlation coefficient, and an absolute value process 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 in the previous-stage blades of the adjacent blade groups can be achieved by adjusting the inter-blade stage spacing.

6. A multi-stage compressor aerodynamic matching design method according to claim 5, characterized in that: The process of adjusting the inter-blade stage spacing according to the correlation analysis result is as follows: Draw a curve of the wake airflow uniformity value changing with the inter-blade stage spacing according to the inter-blade stage spacing sequence and the wake airflow uniformity sequence, and perform curve fitting using the least squares method to obtain a correlation adjustment model; Obtain the deviation between the wake airflow uniformity value and the preset wake airflow uniformity threshold to obtain the wake airflow uniformity adjustment amount; Use the wake airflow uniformity adjustment amount as the input of the correlation adjustment model, output the inter-blade stage spacing adjustment value, and adjust the inter-blade stage spacing of the adjacent blades according to the inter-blade stage spacing adjustment value.

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

8. A multi-stage compressor aerodynamic matching design method according to claim 7, characterized in that: The specific way to obtain the inter-blade stage spacing deviation performance value of the inter-blade stage spacing parameter group of adjacent blades is as follows: Use the Manhattan distance method to calculate the inter-blade stage spacing deviation between the inter-blade stage spacing parameter group of adjacent blades and other inter-blade stage spacing parameter groups of adjacent blades, and perform averaging processing on the obtained inter-blade stage spacing deviation to obtain the average inter-blade stage spacing difference of the inter-blade stage spacing parameter group of adjacent blades, and obtain the ratio of the average inter-blade stage spacing difference of the inter-blade stage spacing parameter group of adjacent blades to the total average inter-blade stage spacing difference to obtain the inter-blade stage spacing deviation performance value of the inter-blade stage spacing parameter group of adjacent blades.

9. A multi-stage compressor aerodynamic matching design method according to claim 8, characterized in that: The total average inter-blade stage spacing difference is obtained by summing the average inter-blade stage spacing differences of all inter-blade stage spacing parameter groups of adjacent blades.

10. A multi-stage compressor aerodynamic matching design method according to claim 7, 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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