Axial flow compressor stall preemptive diagnosis and analysis method, device, equipment and medium

Abstract

The present application discloses a method, apparatus, equipment and medium for preemptive diagnosis and analysis of stall of an axial flow compressor. The method comprises the following steps: S1. performing high-fidelity numerical simulation of the axial flow compressor according to a standardized flow field simulation process and simulation method; S2. establishing a multi-condition high-fidelity axial flow compressor flow field parameter database according to the simulation results; S3. extracting and mining three key flow field characteristic parameters from the multi-condition high-fidelity axial flow compressor flow field parameter database; S4. performing preemptive comprehensive diagnosis based on the three key flow field characteristic parameters, determining the preemptive stall stage and the preemptive stall direction position, and finally outputting the preemptive stall stage of the axial flow compressor and its spanwise position. The present application can quickly locate the first stage and the corresponding spanwise position that cause the axial flow compressor to stall, improve the speed and accuracy of preemptive stall diagnosis, and point out the direction for the refined design and optimization of axial flow compressors.

Description

Technical Field

[0001] The present invention relates to the field of engine technology, and in particular to a method, device, equipment and medium for preemptive stall diagnosis and analysis of an axial flow compressor. Background Art

[0002] As one of the three core components of an aircraft engine, the compressor converts mechanical energy into the pressure potential and kinetic energy of the gas, thereby providing high-pressure ratio air for the combustion chamber. Axial-flow compressors typically use flow-pressure ratio and flow-efficiency characteristics to determine the matching positions of the compressor stages. Analysis of the stall-initiating stage and its spanwise position is typically performed by analyzing the flow field details near the stall point. This analysis primarily examines phenomena such as whether the shock wave has pushed out of the blade passage, whether there has been significant separation in the boundary layer on the blade surface, or whether there has been significant separation at the root / tip corner of the blade, affecting the main flow area. However, in actual analysis of the detailed flow field of an axial-flow compressor, it is found that the aforementioned three phenomena often occur simultaneously or are not obvious near the stall point, making it difficult to locate the first stage and its corresponding spanwise position that causes the axial-flow compressor to stall. This hinders further refinement of the axial-flow compressor design and margin improvement, making it difficult to implement targeted and refined improvements. Summary of the Invention

[0003] On the one hand, the present application provides a method for preemptive diagnosis and analysis of axial compressor stall, which is used to solve the technical problem that it is difficult to locate the first stage and corresponding spanwise position that cause the axial compressor stall during the existing aircraft engine compressor design process, which is not conducive to further refined design and margin improvement of the axial compressor.

[0004] This application is implemented through the following scheme:

[0005] A method for preemptive stall diagnosis and analysis of an axial flow compressor comprises the following steps:

[0006] S1. Perform high-fidelity numerical simulation of an axial flow compressor based on standardized flow field simulation procedures and methods.

[0007] S2. Establish a high-fidelity axial compressor flow field parameter database for multiple operating conditions based on simulation results;

[0008] S3. Extracting and mining three key flow field characteristic parameters from the multi-operating-condition high-fidelity axial compressor flow field parameter database, including the matching margin of each stage and the margin increment matrix FA of the preceding and following stages in the hierarchical characteristics, the sensitivity of the flow coefficient-load coefficient curve to change FB, and the sensitivity of the spanwise pressure ratio to the operating condition change FC;

[0009] S4. Perform a comprehensive preemptive diagnosis based on the matching margins of each stage and the margin increment matrix FA of the preceding and succeeding stages, the flow coefficient-load coefficient curve change sensitivity FB, and the spanwise pressure ratio sensitivity FC to operating condition changes in the hierarchical characteristics. Define a stall preemptive stage function and a stall preemptive direction position function. Use the stall preemptive stage function and the stall preemptive direction position function to quickly locate the first stage that causes the axial flow compressor to stall and its corresponding spanwise position. Determine the stall preemptive stage and the stall preemptive direction position, and ultimately output the stall preemptive stage and spanwise position of the axial flow compressor.

[0010] Furthermore, the step S1 specifically includes the steps of:

[0011] S11. Preparation of axial compressor blade profile and flow channel geometry data: According to the standardized flow field simulation process and simulation method, blade profile geometry data files and flow channel geometry data files must be prepared according to the format requirements of the numerical simulation software. The blade profile geometry data exceeds the hub and casing flow channels.

[0012] S12. Numerical simulation of axial flow compressor: According to the standardized flow field simulation process and simulation method, the axial flow compressor is meshed, parameterized and calculated to obtain high-fidelity numerical simulation results of the axial flow compressor under multiple working conditions. The numerical simulation state points include at least five state points, including the blockage point, design point, peak efficiency point, peak efficiency left branch midpoint, and near-gasping point.

[0013] Furthermore, the step S2 specifically includes the steps of:

[0014] S21. Post-process the numerical simulation results to obtain the graded characteristic parameters of each state point and establish an axial flow compressor flow field parameter database.

[0015] Furthermore, the flow field parameters include the inlet converted flow rate, flow coefficient, load factor, stage pressure ratio, stage efficiency, rotor pressure ratio, rotor efficiency, and stator total pressure recovery coefficient of each stage of the axial flow compressor.

[0016] Furthermore, the step S3 specifically includes the steps of:

[0017] S31. According to the axial flow compressor flow field parameter database, extract the inlet conversion flow rate and stage pressure ratio of each stage in the stage characteristics, combine the compressor stage aerodynamic design value, calculate the stage matching margin and the margin increment matrix FA of the previous and next stages in the stage characteristics, and the matching margin of each stage , subscript i Indicates the i class, dp represents the design point, stall Indicates the near-breathing point; the margin increment of the front and rear stages Δ i+1 =SM i+1 -SM i , mis the import conversion flow, π is the stage pressure ratio, which is used to obtain the contribution of each stage to the total margin of the axial compressor;

[0018] S32. Based on the axial compressor flow field parameter database, draw the flow coefficient-load coefficient curves of each stage, and numerically fit the curve function to obtain the flow coefficient-load coefficient curve change sensitivity FB, which is used to determine the stall-first stage by combining the matching margins of each stage and the margin increment matrix FA of the preceding and succeeding stages in the stage characteristics;

[0019] S33. Based on the axial compressor flow field parameter database, plot the evolution curve of the spanwise pressure ratio of each row of rotors / stators as the operating conditions change. Obtain the sensitivity FC of the spanwise pressure ratio of each row of rotors / stators as the operating conditions change, which is used to determine the stall leading direction position. The spanwise pressure ratio includes the rotor spanwise pressure ratio and the stator spanwise total pressure recovery coefficient.

[0020] Furthermore, in step S4, determining the stall priority level specifically includes the following steps:

[0021] S41. The work capacity and matching position of each stage of the axial compressor rotor are determined based on the matching margin of each stage, the margin increment of the preceding and following stages, and the flow coefficient-load coefficient curve. This allows analysis of which stage has insufficient work capacity, i.e., the stall-first stage. Therefore, the stall-first stage function is defined as:

[0022] α=f1(FA,FB)=a 00 +a 10 FA+a 20 FA 2 +a 01 FB+a 11 FA·FB+a 02 Facebook 2 ;

[0023] Where, 、 、 、 、 and is the regression coefficient;

[0024] Substitute the matching margin of each level and the margin increment matrix FA of the preceding and following levels in the graded characteristics and the change sensitivity FB of the flow coefficient-load coefficient curve of each level into the stall first level function α;

[0025] When the first derivative of the stall priority function α'= f When 1(FA, FB)'≥0, it indicates that the working capacity of the current stage rotor has reached its limit and the working capacity is insufficient, and the current stage rotor is judged to be the stall first stage.

[0026] Furthermore, in step S4, determining the stall leading direction position specifically includes the following steps:

[0027] S42. The work capacity of each row of rotors / stators at each spanwise position is determined based on the evolution curve of the spanwise pressure ratio of each row of rotors / stators as the operating conditions change. Thus, the spanwise position where the work capacity is insufficient can be determined, and the stall-leading direction position can be located. Therefore, the stall-leading direction position function is defined as:

[0028] β=f2(FC,span)=b 00 +b 10 FC+b 20 FC 2 +b 01 span+b 11 FC span+b 02 span 2 ;

[0029] Where, 、 、 、 、 and is the regression coefficient, span represents the relative spanwise height section position and takes the value [0~1];

[0030] Substitute the spanwise pressure ratio sensitivity FC of each row of rotors / stators to the operating conditions into the stall advance direction position function;

[0031] When β<0, it indicates that the rotor is at the stall-first development position in the span height section, which is the position that needs to be optimized in order to further improve the margin.

[0032] On the other hand, the present application also provides an axial flow compressor stall preemptive diagnosis and analysis device, comprising:

[0033] Numerical simulation module, used to perform high-fidelity numerical simulation of axial flow compressors based on standardized flow field simulation processes and simulation methods;

[0034] Database establishment module, used to establish a high-fidelity axial compressor flow field parameter database under multiple working conditions based on simulation results;

[0035] A flow field characteristic parameter acquisition module is used to extract and mine three key flow field characteristic parameters from the multi-operating-condition high-fidelity axial compressor flow field parameter database, including the matching margin of each stage and the margin increment matrix FA of the preceding and following stages in the hierarchical characteristics, the sensitivity of the flow coefficient-load coefficient curve to change FB, and the sensitivity of the spanwise pressure ratio to the operating condition change FC;

[0036] The stall-first stage and spanwise position judgment module is used to perform a comprehensive diagnosis based on the matching margins of each stage and the margin increment matrix FA of the preceding and succeeding stages in the hierarchical characteristics, the flow coefficient-load coefficient curve change sensitivity FB, and the spanwise pressure ratio sensitivity FC to operating condition changes, to judge the stall-first stage and the stall-first spanwise position, and ultimately output the stall-first stage and spanwise position of the axial flow compressor.

[0037] On the other hand, the present 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 implements the steps of the axial compressor stall preemptive diagnosis and analysis method when executing the computer program.

[0038] On the other hand, the present application further provides a storage medium, which includes a stored program, and when the program is running, controls the device where the storage medium is located to execute the steps of the axial compressor stall preemptive diagnosis and analysis method.

[0039] Compared with the existing technology, this application has the following beneficial effects:

[0040] The present invention provides an axial flow compressor stall preemptive diagnosis and analysis method, an apparatus, equipment and a medium. In the axial flow compressor stall preemptive diagnosis and analysis method, a stall preemptive stage function focuses on evaluating the work capacity of each stage of the compressor. When the compressor deviates from the design operating conditions, if the work capacity of a certain stage is insufficient, it is difficult to maintain a stable airflow compression process. This unstable state increases the risk of stall, thereby leading to airflow separation and performance degradation. When the work capacity of a certain stage is insufficient, the function value will be greater than or equal to 0, thereby judging that the stage is the stall preemptive stage; the stall preemptive development direction position function is mainly used to evaluate the flow state of the compressor rotor and stator at different spanwise positions. By analyzing the sensitivity of the compressor to changes in the pressure ratio / total pressure recovery coefficient at different spanwise positions, the function can accurately reflect the work capacity of each spanwise position and can also reveal whether the airflow separates on the blade surface. When the work capacity of a certain position is insufficient or the airflow separates, the function value will be less than 0, thereby judging the corresponding spanwise section as the stall preemptive position. Therefore, the axial flow compressor stall preemptive diagnosis analysis method can quickly locate the first stage that causes the axial flow compressor stall and the corresponding spanwise position, improve the speed and accuracy of the stall preemptive diagnosis, and provide a direction for the refined design and optimization of the axial flow compressor, thereby further improving the compressor performance and stable operating margin.

[0041] In addition to the above-described purposes, features and advantages, the present application also has other purposes, features and advantages. The present application will be further described in detail below with reference to the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of this application. The exemplary embodiments and descriptions of this application are intended to explain this application and do not constitute an improper limitation on this application. In the accompanying drawings:

[0043] Figure 1 This is a flow chart of a method for proactively diagnosing and analyzing stall of an axial flow compressor according to a preferred embodiment of the present application;

[0044] Figure 2 Schematic diagram of the rotor flow coefficient-pressure rise coefficient of an axial flow compressor when α'<0;

[0045] Figure 3 Schematic diagram of the rotor flow coefficient-pressure rise coefficient of an axial flow compressor when α'≥0;

[0046] Figure 4 The diagram of the evolution curve of the rotor pressure ratio of an axial flow compressor when β>0;

[0047] Figure 5 Schematic diagram of the evolution curve of the rotor pressure ratio of an axial flow compressor when β is less than 0;

[0048] Figure 6 Schematic diagram of the evolution curve of the total pressure recovery coefficient of the stator of an axial flow compressor when β>0;

[0049] Figure 7 Schematic diagram of the evolution curve of the total pressure recovery coefficient of the stator of an axial flow compressor when β is less than 0;

[0050] Figure 8 This is a schematic diagram of a module of an axial flow compressor stall preemptive diagnosis and analysis device according to a preferred embodiment of the present application;

[0051] Figure 9 This is a schematic block diagram of an electronic device according to a preferred embodiment of the present application;

[0052] Figure 10 It is a diagram of the internal structure of a computer device according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0053] The embodiments of the present application are described in detail below with reference to the accompanying drawings, but the present application can be implemented in a variety of different ways defined and covered below.

[0054] like Figure 1 As shown, the preferred embodiment of the present application provides an axial flow compressor stall preemptive diagnosis and analysis method, comprising the steps of:

[0055] S1. Perform high-fidelity numerical simulation of an axial flow compressor based on standardized flow field simulation procedures and methods.

[0056] S2. Establish a high-fidelity axial compressor flow field parameter database for multiple operating conditions based on simulation results;

[0057] S3. Extracting and mining three key flow field characteristic parameters from the multi-operating-condition high-fidelity axial compressor flow field parameter database, including the matching margin of each stage and the margin increment matrix FA of the preceding and following stages in the hierarchical characteristics, the sensitivity of the flow coefficient-load coefficient curve to change FB, and the sensitivity of the spanwise pressure ratio to the operating condition change FC;

[0058] S4. Perform a comprehensive preemptive diagnosis based on the matching margins of each stage and the margin increment matrix FA of the preceding and succeeding stages, the flow coefficient-load coefficient curve change sensitivity FB, and the spanwise pressure ratio sensitivity FC to operating condition changes in the hierarchical characteristics. Define a stall preemptive stage function and a stall preemptive direction position function. Use the stall preemptive stage function and the stall preemptive direction position function to quickly locate the first stage that causes the axial flow compressor to stall and its corresponding spanwise position. Determine the stall preemptive stage and the stall preemptive direction position, and ultimately output the stall preemptive stage and spanwise position of the axial flow compressor.

[0059] This embodiment provides a stall-preemptive diagnostic analysis method for an axial-flow compressor. In this method, a stall-preemptive stage function focuses on evaluating the work capacity of each compressor stage. When the compressor operates off-design, insufficient work capacity at a stage makes it difficult to maintain a stable airflow compression process. This instability increases the risk of stall, leading to airflow separation and performance degradation. When a stage's work capacity is insufficient, the function value will be greater than or equal to 0, thus identifying that stage as the stall-preemptive stage. A stall-preemptive spanwise position function primarily evaluates the flow state at different spanwise positions of the compressor rotor and stator. By analyzing the sensitivity of the compressor's pressure ratio / total pressure recovery coefficient to changes at different spanwise positions, this function accurately reflects the work capacity at each spanwise position and can also reveal whether airflow separation occurs on the blade surface. When work capacity is insufficient or airflow separation occurs at a particular position, the function value will be less than 0, thus identifying the corresponding spanwise section as the stall-preemptive position. Therefore, the axial flow compressor stall preemptive diagnosis analysis method can quickly locate the first stage that causes the axial flow compressor stall and the corresponding spanwise position, improve the speed and accuracy of the stall preemptive diagnosis, and provide a direction for the refined design and optimization of the axial flow compressor, thereby further improving the compressor performance and stable operating margin.

[0060] Preferably, the step S1 specifically includes the steps of:

[0061] S11. Preparation of axial compressor blade profile and flow channel geometry data: According to the standardized flow field simulation process and simulation method, blade profile geometry data files need to be prepared according to the format requirements of the numerical simulation software ( ) and flow channel geometry data files (hub.curve, shroud.curve), where the blade geometry data exceeds the hub and casing flow channels;

[0062] S12. Numerical simulation of axial flow compressor: According to the standardized flow field simulation process and simulation method, the axial flow compressor is meshed, parameterized and calculated to obtain high-fidelity numerical simulation results of the axial flow compressor under multiple working conditions. The numerical simulation state points include at least five state points, including the blockage point, design point, peak efficiency point, and peak efficiency left branch midpoint near surge point. The reason for requiring at least five state points is to construct a complete compressor characteristic curve through multiple characteristic points, covering the full range of working conditions from blockage to surge, and providing a data basis for system matching and control.

[0063] This embodiment uses steps S11 and S12 to calculate high-fidelity numerical simulation results for an axial flow compressor under multiple operating conditions. This has the following advantages: A complete compressor characteristic curve is constructed using multiple characteristic points, enabling a comprehensive assessment of the compressor's aerodynamic performance, stability boundaries, and applicable operating range. By analyzing the variation patterns of these points, the compressor's operating state and performance changes under different operating conditions can be understood, providing a data foundation for the axial flow compressor flow field parameter database.

[0064] Preferably, the step S2 specifically includes the steps of:

[0065] S21. Post-process the numerical simulation results to obtain the graded characteristic parameters of each state point and establish an axial compressor flow field parameter database. The post-processing includes the cross-sectional average and circumferential average performance parameters such as the discharge volume of each stage / blade, pressure ratio, efficiency, etc.

[0066] Preferably, the flow field parameters include the inlet converted flow rate, flow coefficient, load factor, stage pressure ratio, stage efficiency, rotor pressure ratio, rotor efficiency, and stator total pressure recovery coefficient of each stage of the axial flow compressor.

[0067] This embodiment adopts step S21 to obtain the graded characteristic parameters of each state point and establish an axial flow compressor flow field parameter database. Its benefits include: providing comprehensive flow field parameter data, helping designers to more accurately understand the internal flow characteristics of the compressor, and providing data-driven support for aerodynamic design optimization, fault diagnosis, stability prediction and new technology development.

[0068] Preferably, the step S3 specifically includes the steps of:

[0069] S31. According to the axial flow compressor flow field parameter database, extract the inlet conversion flow rate and stage pressure ratio of each stage in the stage characteristics, combine the compressor stage aerodynamic design value, calculate the stage matching margin and the margin increment matrix FA of the previous and next stages in the stage characteristics, and the matching margin of each stage , subscript iIndicates the i class, dp represents the design point, stall Indicates the near-breathing point; the margin increment of the front and rear stages Δ i+1 =SM i+1 -SM i , m is the import conversion flow, π is the stage pressure ratio, which is used to obtain the contribution of each stage to the total margin of the axial compressor;

[0070] S32. Based on the axial compressor flow field parameter database, draw the flow coefficient-load coefficient curves of each stage, and numerically fit the curve function to obtain the flow coefficient-load coefficient curve change sensitivity FB, which is used to determine the stall-first stage by combining the matching margins of each stage and the margin increment matrix FA of the preceding and succeeding stages in the stage characteristics;

[0071] S33. Based on the axial compressor flow field parameter database, plot the evolution curve of the spanwise pressure ratio of each row of rotors / stators as the operating conditions change. Obtain the sensitivity FC of the spanwise pressure ratio of each row of rotors / stators as the operating conditions change, which is used to determine the stall leading direction position. The spanwise pressure ratio includes the rotor spanwise pressure ratio and the stator spanwise total pressure recovery coefficient.

[0072] This embodiment uses steps S31-S33 to extract and mine three key flow field characteristic parameters, including the matching margin of each stage and the incremental matrix FA of the margins of the preceding and succeeding stages in the hierarchical characteristics, the sensitivity of the flow coefficient-load coefficient curve to changes FB, and the sensitivity of the spanwise pressure ratio to changes in operating conditions FC. Its benefits include: it can comprehensively reflect the performance characteristics of the compressor from different angles. The FA parameter reflects the inter-stage matching performance, the FB parameter reflects the relationship between flow and load, and the FC parameter focuses on the change of the spanwise pressure ratio. By combining these parameters, the overall performance and operating status of the compressor can be more accurately evaluated, providing a reliable basis for performance optimization.

[0073] Preferably, in step S4, determining the stall priority level specifically includes the following steps:

[0074] S41. The work capacity and matching position of each stage of the axial compressor rotor are determined based on the matching margin of each stage, the margin increment of the preceding and following stages, and the flow coefficient-load coefficient curve. This allows analysis of which stage has insufficient work capacity, i.e., the stall-first stage. Therefore, the stall-first stage function is defined as:

[0075] α=f1(FA,FB)=a 00 +a 10 FA+a 20 FA 2 +a 01 FB+a 11 FA·FB+a 02 Facebook 2 ;

[0076] Where, 、 、 、 、 and is the regression coefficient;

[0077] Substitute the matching margin of each level and the margin increment matrix FA of the preceding and following levels in the graded characteristics and the change sensitivity FB of the flow coefficient-load coefficient curve of each level into the stall first level function α;

[0078] When the first derivative of the stall priority function α'= f When 1(FA, FB)'≥0, it indicates that the working capacity of the current stage rotor has reached its limit and the working capacity is insufficient, and the current stage rotor is judged to be the stall first stage.

[0079] In this embodiment, the work capacity of each stage of the axial flow compressor and its matching position can be determined based on the matching margin of each stage, the margin increment of the preceding and following stages, and the flow coefficient-load coefficient curve, so that the specific stage with insufficient work capacity, i.e., the stall-first stage, can be analyzed. Therefore, the stall-first stage function α= f 1(FA,FB), when the function α'= f When 1(FA,FB)'≥0, it indicates that the current stage has insufficient work capacity and is the first stage to stall. Figure 2 As shown in Figure 2, as the flow coefficient gradually decreases, the load coefficient continues to increase, and α' < 0, it shows that the rotor's work capacity is still very strong and has not approached the unstable state area; Figure 3 As shown in the figure, as the flow coefficient gradually decreases, the load factor approaches the horizontal level, α'≥0, indicating that the rotor's working capacity has reached its limit and has entered the unstable state region, that is, the rotor is at the stall-first stage.

[0080] In this embodiment, step S41 is used to establish the stall priority level function α= f 1(FA, FB), and judge that the current stage rotor is the stall-first stage according to the value of the stall-first stage function. Its benefits include: converting the complex flow field physical mechanism into a mathematical criterion that can be calculated in real time, simplifying the analysis process, improving the efficiency and speed of judgment, and quickly locating the stall-first stage.

[0081] Preferably, in step S4, determining the stall leading direction position specifically includes the steps of:

[0082] S42. The work capacity of each row of rotors / stators at each spanwise position is determined based on the evolution curve of the spanwise pressure ratio of each row of rotors / stators as the operating conditions change. Thus, the spanwise position where the work capacity is insufficient can be determined, and the stall-leading direction position can be located. Therefore, the stall-leading direction position function is defined as:

[0083] β=f2(FC,span)=b00 +b 10 FC+b 20 FC 2 +b 01 span+b 11 FC span+b 02 span 2 ;

[0084] Where, 、 、 、 、 and is the regression coefficient, span represents the relative spanwise height section position and takes the value [0~1];

[0085] Substitute the spanwise pressure ratio sensitivity FC of each row of rotors / stators to the operating conditions into the stall advance direction position function;

[0086] When β<0, it indicates that the rotor is at the stall-first development position in the span height section, which is the position that needs to be optimized in order to further improve the margin.

[0087] In this embodiment, the working capacity of each row of rotors / stators at each spanwise position can be determined based on the evolution curve of the spanwise pressure ratio of each row of rotors / stators as the working conditions change, thereby determining the spanwise position where the working capacity is insufficient, and thus locating the stall-leading spanwise position. Therefore, the function β= f 2(FC, span), when β<0, it indicates that the working capacity of the corresponding spanwise position is reduced. Combined with the distribution of other spanwise positions, it can be further determined whether it is the stall-first development position. Figure 4 and Figure 5 The curves showing the evolution of pressure ratios for two rows of different rotors in an axial flow compressor are shown. In the figure, CFD-1 to CFD-7 represent the compressor from the blockage point to the near-gasping point. Figure 4 For the intermediate compressor, the rotor pressure ratio of each operating condition from CFD-1 to CFD-7 at the same display height from the blocking point to the near-surge point shows a gradual increase along the entire spanwise distribution, that is, β(FC, span)>0, indicating that the rotor's work capacity is still strong. Figure 5 It can be clearly seen that the rotor pressure ratio increases first, and then decreases in the section with a spanwise height of less than 70%, that is, β(FC, 0-0.7) < 0, indicating that the rotor section with a spanwise height of less than 70% is the first position where stall develops, and is the position that needs to be optimized in order to further improve the margin. Figure 6 Figure and Figure 7 This is a schematic diagram of the evolution of the total pressure recovery coefficient of the stator of an axial compressor, where Figure 6The total pressure recovery coefficient of the stator shows a gradual increasing trend along the entire span, that is, β(FC, span)>0, indicating that the stator flows smoothly without flow separation; Figure 7 It can be clearly seen that the total pressure recovery coefficient of the stator decreases when the span-wise height section is above 70%, that is, β(FC, 0.7-1.0) < 0, indicating that the stator in the span-wise height section above 70% is the first stall development position, and is the position that needs to be optimized in order to further improve the margin.

[0088] In this embodiment, step S42 is used to establish the stall priority level function β= f 2(FC, span), and judge the stall-first development direction position according to the value of the stall-first level function. Its benefits include: converting the complex flow field physical mechanism into a mathematical criterion that can be calculated in real time, simplifying the analysis process, improving the efficiency and speed of judgment, and quickly locating the stall-first development direction position.

[0089] like Figure 8 As shown, another preferred embodiment of the present application further provides an axial flow compressor stall preemptive diagnosis and analysis device, comprising:

[0090] Numerical simulation module, used to perform high-fidelity numerical simulation of axial flow compressors based on standardized flow field simulation processes and simulation methods;

[0091] Database establishment module, used to establish a high-fidelity axial compressor flow field parameter database under multiple working conditions based on simulation results;

[0092] A flow field characteristic parameter acquisition module is used to extract and mine three key flow field characteristic parameters from the multi-operating-condition high-fidelity axial compressor flow field parameter database, including the matching margin of each stage and the margin increment matrix FA of the preceding and following stages in the hierarchical characteristics, the sensitivity of the flow coefficient-load coefficient curve to change FB, and the sensitivity of the spanwise pressure ratio to the operating condition change FC;

[0093] The stall-first stage and spanwise position judgment module is used to perform a comprehensive diagnosis based on the matching margins of each stage and the margin increment matrix FA of the preceding and succeeding stages in the hierarchical characteristics, the flow coefficient-load coefficient curve change sensitivity FB, and the spanwise pressure ratio sensitivity FC to operating condition changes, to judge the stall-first stage and the stall-first spanwise position, and ultimately output the stall-first stage and spanwise position of the axial flow compressor.

[0094] like Figure 9 As shown, a preferred embodiment of the present 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 implements the steps of the axial compressor stall preemptive diagnosis and analysis method in the above-mentioned embodiment when executing the computer program.

[0095] like Figure 10 As shown, the preferred embodiment of the present application further provides a computer device, which can be a terminal or a liveness detection server, and its internal structure diagram can be as shown in FIG. Figure 10 As shown. The computer device includes a processor, a memory, and a network interface connected via a system bus. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with other external computer devices via a network connection. When the computer program is executed by the processor, the steps of the above-mentioned axial compressor stall preemptive diagnosis and analysis method are implemented.

[0096] Those skilled in the art will understand that Figure 10 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than shown in the figure, or combine certain components, or have a different component arrangement.

[0097] A preferred embodiment of the present application further provides a storage medium, which includes a stored program, and when the program is running, controls the device where the storage medium is located to execute the steps of the axial compressor stall preemptive diagnosis and analysis method in the above embodiment.

[0098] It should be noted that the steps shown in the flowcharts of the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, and that, although a logical order is shown in the flowcharts, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0099] If the functions described in the method of this embodiment are implemented in the form of a software functional unit and sold or used as an independent product, they can be stored in a storage medium readable by one or more computing devices. Based on this understanding, the part of the embodiment of this application that contributes to the prior art or the part of the technical solution can be embodied in the form of a software product, which is stored in a storage medium and includes a number of instructions for enabling a computing device (which can be a personal computer, server, mobile computing device or network device, etc.) to execute all or part of the steps of the method described in each embodiment of this application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk, and other media that can store program code.

[0100] Those skilled in the art will appreciate that the embodiments of the present application may be provided as methods, systems, or computer program products. Therefore, the present application may take the form of a fully hardware embodiment, a fully software embodiment, or an embodiment combining software and hardware. Furthermore, the present application may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code. The solutions in the embodiments of the present application may be implemented in various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.

[0101] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each process and / or block in the flowchart and / or block diagram, as well as the combination of processes and / or blocks in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 a process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0102] These computer program instructions may also be stored in a computer readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 a process or multiple processes and / or boxes Figure 1 The function specified in one or more boxes.

[0103] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operational steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing the instructions executed on the computer or other programmable device for implementing the process. Figure 1 a process or multiple processes and / or boxes Figure 1 A step that specifies a function in one or more boxes.

[0104] Although the preferred embodiments of the present application have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present application.

[0105] Obviously, those skilled in the art may make various changes and modifications to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of the claims of this application and their equivalents, this application is intended to include these modifications and variations.

Claims

1. A method for preemptive stall diagnosis and analysis of an axial flow compressor, characterized in that: Including steps: S1. Perform high-fidelity numerical simulation of an axial flow compressor based on standardized flow field simulation procedures and methods. S2. Establish a high-fidelity axial compressor flow field parameter database for multiple operating conditions based on simulation results; S3. Extract and mine three key flow field characteristic parameters from the multi-operating condition high-fidelity axial compressor flow field parameter database, including the matching margin of each stage and the margin increment matrix FA of the preceding and following stages in the hierarchical characteristics, the flow coefficient-load coefficient curve change sensitivity FB, and the spanwise pressure ratio sensitivity FC as the operating condition changes. The matching margin of each stage and the margin increment matrix FA of the preceding and following stages in the hierarchical characteristics are obtained by extracting the inlet converted flow and stage pressure ratio of each stage in the hierarchical characteristics according to the axial compressor flow field parameter database, and calculating them in combination with the compressor stage aerodynamic design value; the flow coefficient-load coefficient curve change sensitivity FB is obtained by plotting the flow coefficient-load coefficient curve of each stage according to the axial compressor flow field parameter database, and obtaining the curve function by numerical fitting; the spanwise pressure ratio sensitivity FC as the operating condition changes is obtained by plotting the evolution law curve of the spanwise pressure ratio of each row of rotors / stators as the operating condition changes according to the axial compressor flow field parameter database; S4. Perform a preemptive comprehensive diagnosis based on the matching margins of each stage and the margin increment matrix FA of the preceding and succeeding stages, the flow coefficient-load coefficient curve change sensitivity FB, and the spanwise pressure ratio sensitivity FC to the operating condition in the hierarchical characteristics. Define a stall preemptive stage function and a stall preemptive direction position function. Use the stall preemptive stage function and the stall preemptive direction position function to quickly locate the first stage that causes the axial flow compressor to stall and its corresponding spanwise position. Determine the stall preemptive stage and the stall preemptive direction position, and ultimately output the stall preemptive stage and spanwise position of the axial flow compressor. The stall preemptive stage function is defined as follows: α=f1(FA,FB)=a 00 +a 10 F+a 20 AGO 2 +a 01 FB+a 11 FA·FB+a 02 FB 2 ; Where a 00 、a 10 、a 20 、a 01 、a 02 and a 11 is the regression coefficient; Define the stall advance direction position function: β=f2(FC,span)=b 00 +b 10 FC+b 20 FC 2 +b 01 span+b 11 FC·span+b 02 span 2 ; Where b 00 、b 10 、b 20 、b 01 、b 02 and b 11 is the regression coefficient, span represents the relative span-wise height section position and has a value of [0~1].

2. The axial flow compressor stall preemptive diagnosis and analysis method according to claim 1, characterized in that: The step S1 specifically includes the following steps: S11. Preparation of axial compressor blade profile and flow channel geometry data: According to the standardized flow field simulation process and simulation method, blade profile geometry data files and flow channel geometry data files must be prepared according to the format requirements of the numerical simulation software. The blade profile geometry data exceeds the hub and casing flow channels. S12. Numerical simulation of axial flow compressor: According to the standardized flow field simulation process and simulation method, the axial flow compressor is meshed, parameterized and calculated to obtain high-fidelity numerical simulation results of the axial flow compressor under multiple working conditions. The numerical simulation state points include at least five state points, including the blockage point, design point, peak efficiency point, peak efficiency left branch midpoint, and near-gasping point.

3. The axial flow compressor stall preemptive diagnosis and analysis method according to claim 1, characterized in that: The step S2 specifically includes the following steps: S21. Post-process the numerical simulation results to obtain the graded characteristic parameters of each state point and establish an axial flow compressor flow field parameter database.

4. The axial flow compressor stall preemptive diagnosis and analysis method according to claim 3, characterized in that: The flow field parameters include the inlet converted flow rate, flow coefficient, load factor, stage pressure ratio, stage efficiency, rotor pressure ratio, rotor efficiency, and stator total pressure recovery coefficient of each stage of the axial flow compressor.

5. The axial flow compressor stall preemptive diagnosis and analysis method according to claim 1, characterized in that: In step S3, when calculating and obtaining the matching margins of each level and the margin increment matrix FA of the previous and next levels in the hierarchical characteristics, the matching margins of each level The subscript i indicates the i-th stage, dp indicates the design point, and stall indicates the near-breathing point; Margin increment of the preceding and following stages Δ i+1 =SM i+1 -SM i , m is the inlet converted flow rate, π is the stage pressure ratio, which is used to obtain the contribution of each stage to the total margin of the axial flow compressor; The flow coefficient-load coefficient curve change sensitivity FB is used to determine the stall-first stage by combining the matching margins of each stage and the margin increment matrix FA of the preceding and following stages in the hierarchical characteristics; The sensitivity FC of the spanwise pressure ratio to the operating condition is used to determine the stall-leading spanwise position, and the spanwise pressure ratio includes the rotor spanwise pressure ratio and the stator spanwise total pressure recovery coefficient.

6. The axial flow compressor stall preemptive diagnosis and analysis method according to claim 5, characterized in that: In step S4, determining the stall priority level specifically includes the following steps: S41. Determine the work capacity and matching position of each stage of the axial compressor rotor based on the matching margins of each stage, the margin increments of the preceding and succeeding stages, and the flow coefficient-load coefficient curve, thereby analyzing which stage has insufficient work capacity, i.e., the first stage to stall. Substitute the matching margin of each level and the margin increment matrix FA of the preceding and following levels in the graded characteristics and the change sensitivity FB of the flow coefficient-load coefficient curve of each level into the stall first level function α; When the first-order derivative of the stall-first stage function α'=f1(FA,FB)'≥0, it indicates that the work capacity of the current stage rotor has reached its limit and the work capacity is insufficient, then the current stage rotor is judged to be the stall-first stage.

7. The axial flow compressor stall preemptive diagnosis and analysis method according to claim 6, characterized in that: In step S4, determining the stall leading direction position specifically includes the following steps: S42. Determine the work capacity of each row of rotors / stators at each spanwise position based on the curve of the evolution law of the spanwise pressure ratio of each row of rotors / stators as a function of the operating conditions, thereby determining the specific spanwise position where the work capacity is insufficient, and thus locating the stall-first development direction position; Substitute the spanwise pressure ratio sensitivity FC of each row of rotors / stators to the operating conditions into the stall advance direction position function; When β<0, it indicates that the rotor is at the stall-first development position in the span height section, which is the position that needs to be optimized in order to further improve the margin.

8. An axial flow compressor stall preemptive diagnosis and analysis device, characterized in that: include: Numerical simulation module, used to perform high-fidelity numerical simulation of axial flow compressors based on standardized flow field simulation processes and simulation methods; Database establishment module, used to establish a high-fidelity axial compressor flow field parameter database under multiple working conditions based on simulation results; The flow field characteristic parameter acquisition module is used to extract and mine three key flow field characteristic parameters from the multi-operating condition high-fidelity axial flow compressor flow field parameter database, including the matching margin of each stage and the margin increment matrix FA of the preceding and following stages in the hierarchical characteristics, the flow coefficient-load coefficient curve change sensitivity FB, and the spanwise pressure ratio sensitivity FC as the operating condition changes. Among them, the matching margin of each stage and the margin increment matrix FA of the preceding and following stages in the hierarchical characteristics are obtained by extracting the inlet converted flow and stage pressure ratio of each stage in the hierarchical characteristics based on the axial flow compressor flow field parameter database, and combining them with the compressor stage aerodynamic design value for calculation; the flow coefficient-load coefficient curve change sensitivity FB is obtained by plotting the flow coefficient-load coefficient curve of each stage based on the axial flow compressor flow field parameter database, and obtaining the curve function by numerical fitting; the spanwise pressure ratio sensitivity FC as the operating condition changes is obtained by plotting the evolution law curve of the spanwise pressure ratio of each row of rotors / stators as the operating condition changes based on the axial flow compressor flow field parameter database; The stall-first stage and spanwise position judgment module is used to perform a comprehensive diagnosis based on the matching margins of each stage and the margin increment matrix FA of the preceding and succeeding stages in the hierarchical characteristics, the sensitivity of the flow coefficient-load coefficient curve change FB, and the sensitivity of the spanwise pressure ratio to the operating condition change FC, to judge the stall-first stage and the stall-first spanwise position, and finally output the stall-first stage and spanwise position of the axial flow compressor. The stall-first stage function is defined as follows: α=f1(FA,FB)=a 00 +a 10 F+a 20 AGO 2 +a 01 FB+a 11 FA·FB+a 02 FB 2 ; Where a 00 、a 10 、a 20 、a 01 、a 02 and a 11 is the regression coefficient; Define the stall advance direction position function: β=f2(FC,span)=b 00 +b 10 FC+b 20 FC 2 +b 01 span+b 11 FC·span+b 02 span 2 ; Where b 00 、b 10 、b 20 、b 01 、b 02 and b 11 is the regression coefficient, span represents the relative span-wise height section position and has a value of [0~1].

9. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the computer program, the steps of the axial flow compressor stall preemptive diagnosis and analysis method according to any one of claims 1 to 7 are implemented.

10. A storage medium comprising a stored program, which controls a device where the storage medium is located to execute the steps of the axial compressor stall preemptive diagnosis and analysis method according to any one of claims 1 to 7 when the program is executed.

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