Method, device and equipment for diagnosing and analyzing stalling first of axial flow compressor and medium

Abstract

The invention discloses an axial flow compressor stall first diagnosis analysis method, device and equipment and a medium. The method comprises the steps that S1, high-fidelity numerical simulation is conducted on an axial flow compressor according to a standardized flow field simulation process and a simulation method; s2, establishing a multi-working-condition high-fidelity axial flow compressor flow field parameter database according to a simulation result; s3, three key flow field characteristic parameters are extracted and mined from the multi-working-condition high-fidelity axial flow compressor flow field parameter database; and S4, according to the three key flow field characteristic parameters, first-shot comprehensive diagnosis is conducted, the stall first-shot stage and the stall first-shot orientation position are judged, and finally the stall first-shot stage and the spanwise position of the axial flow compressor are output. According to the method, the first stage causing stall of the axial flow compressor and the corresponding spanwise position can be rapidly positioned, the stall first diagnosis speed and precision are improved, and the direction is pointed out for fine design and optimization of the axial flow compressor.

Description

Technical Field

[0001] The present invention relates to the technical field of engines, and in particular, to a method, device, equipment and medium for diagnosing and analyzing the pre-stall of an axial compressor. Background Art

[0002] As one of the three core components of an aeroengine, the function of a compressor is to convert mechanical energy into the pressure potential energy and kinetic energy of gas, so as to provide high-pressure ratio air for the combustion chamber. The axial compressor usually judges the matching position of each stage of the compressor through the flow rate-pressure ratio characteristic and the flow rate-efficiency characteristic; analyzing the pre-stall stage and its spanwise position generally involves analyzing the flow field details at the near-stall state point, mainly by analyzing whether the shock wave position has exited the blade passage, whether there is a relatively serious separation of the boundary layer on the blade surface, or whether there is a serious separation in the blade root / tip corner area and it affects the mainstream area and other phenomena. However, in the actual analysis of the axial compressor flow field details, it will be found that the above three phenomena often occur simultaneously or the phenomena are not obvious at the near-stall state point, making it difficult to locate the first stage and the corresponding spanwise position that cause the axial compressor to stall, which is not conducive to the further refined design and margin improvement of the axial compressor, and thus it is difficult to carry out targeted and refined improvements. Summary of the Invention

[0003] One aspect of the present application provides a method for diagnosing and analyzing the pre-stall of an axial compressor, which is used to solve the technical problem that it is difficult to locate the first stage and the corresponding spanwise position that cause the axial compressor to stall during the design process of the existing aeroengine compressor, which is not conducive to the further refined design and margin improvement of the axial compressor.

[0004] The present application is realized through the following solutions: A method for diagnosing and analyzing the pre-stall of an axial compressor includes the steps of: S1. Perform high-fidelity numerical simulation on the axial compressor according to the standardized flow field simulation process and simulation method; S2. Establish a multi-condition high-fidelity axial compressor flow field parameter database according to the simulation results; S3. Extract and mine three key flow field characteristic parameters from the multi-condition high-fidelity axial compressor flow field parameter database, including the matching margin of each stage and the front and rear stage margin increment matrix FA in the grading characteristics, the sensitivity FB of the change of the flow coefficient-load coefficient curve, and the sensitivity FC of the spanwise pressure ratio to the change of the working condition; S4. Based on the matching margins at all levels in the hierarchical characteristics, the front and rear stage margin increment matrix FA, the sensitivity FB of the flow coefficient-load coefficient curve change, and the sensitivity FC of the spanwise pressure ratio change with the operating condition, perform a preemptive comprehensive diagnosis. Define the stall preemption stage function and the stall preemption spanwise position function. Quickly locate the first stage and the corresponding spanwise position that cause the axial flow compressor to stall through the stall preemption stage function and the stall preemption spanwise position function, judge the stall preemption stage and the stall preemption spanwise position, and finally output the stall preemption stage of the axial flow compressor and its spanwise position.

[0005] Further, the specific steps of the step S1 include: S11. Preparation of the blade profile and flow passage geometric data of the axial flow compressor: According to the standardized flow field simulation process and simulation method, it is necessary to prepare the blade profile geometric data file and the flow passage geometric data file according to the format requirements of the numerical simulation software, where the blade profile geometric data exceeds the hub and casing flow passages; S12. Numerical simulation of the axial flow compressor: According to the standardized flow field simulation process and simulation method, perform grid division, parameter setting and calculation on the axial flow compressor to obtain the high-fidelity numerical simulation results of the axial flow compressor under multiple operating conditions. The numerical simulation state points include at least 5 state points including the block point, the design point, the peak efficiency point, the midpoint of the left branch of the peak efficiency, and the near surge point.

[0006] Further, the specific steps of the step S2 include: S21. Post-process the numerical simulation results to obtain the hierarchical characteristic parameters at each state point, and establish a flow field parameter database of the axial flow compressor.

[0007] Further, the flow field parameters include the inlet converted flow rate, flow coefficient, load coefficient, stage pressure ratio, stage efficiency, rotor pressure ratio, rotor efficiency, and stator total pressure recovery coefficient at each stage of the axial flow compressor.

[0008] Further, the specific steps of the step S3 include: S31. According to the flow field parameter database of the axial flow compressor, extract the inlet converted flow rate and stage pressure ratio at each level in the hierarchical characteristics, and combine with the hierarchical aerodynamic design values of the compressor to calculate the matching margins at each level in the hierarchical characteristics and the front and rear stage margin increment matrix FA. The matching margin at each level , the subscript i represents the i th stage, dp represents the design point, stall represents the near surge point; the front and rear stage margin increment - , 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; S32. Based on the axial flow compressor flow field parameter database, plot the flow coefficient - load coefficient curves for each stage, and numerically fit to obtain the curve function to get the sensitivity FB of the flow coefficient - load coefficient curve change, which is used to determine the first - stalled stage in combination with the matching margin of each stage and the front - and - rear - stage margin increment matrix FA in the stage characteristics. S33. Based on the axial flow compressor flow field parameter database, plot the evolution law curves of the span - wise pressure ratio of each row of rotor / stator varying with the working condition, and obtain the sensitivity FC of the span - wise pressure ratio of each row of rotor / stator varying with the working condition to determine the position of the first - developed stall direction. The span - wise pressure ratio includes the rotor span - wise pressure ratio and the stator span - wise total pressure recovery coefficient.

[0009] Furthermore, in the step S4, determining the first - stalled stage specifically includes the steps: S41. Based on the matching margin of each stage, the front - and - rear - stage margin increment, and the flow coefficient - load coefficient curve, judge the work - doing ability of each - stage rotor of the axial flow compressor and its matching position, so as to analyze which specific stage has insufficient work - doing ability, that is, the first - stalled stage. Therefore, define the first - stalled stage function: ; In the formula, , , , , and are regression coefficients; Substitute the matching margin of each stage and the front - and - rear - stage margin increment matrix FA in the stage characteristics and the sensitivity FB of the flow coefficient - load coefficient curve change of each stage into the first - stalled stage function α; When the first - derivative α’ = f 1(FA,FB)’≥0 of the first - stalled stage function, it indicates that the work - doing ability of the current - stage rotor has reached the limit and the work - doing ability is insufficient, then judge the current - stage rotor as the first - stalled stage.

[0010] Furthermore, in the step S4, determining the position of the first - developed stall direction specifically includes the steps: S42. Based on the evolution law curves of the span - wise pressure ratio of each row of rotor / stator varying with the working condition, judge the work - doing ability of each span - wise position of each row of rotor / stator, so as to judge the specific span - wise position with insufficient work - doing ability, and then the position of the first - developed stall direction can be located. Therefore, define the position function of the first - developed stall direction: ; In the formula, , , , , and are regression coefficients, span represents the relative span - wise height section position and takes values in [0~1]; Substitute the sensitivity FC of the spanwise pressure ratio of each row of stator and rotor to the operating condition change into the stall first developing spanwise position function; When β < 0, it indicates that the rotor is at the stall first developing spanwise position in the spanwise height section, which is the position that needs to be optimized in design when further improving the margin.

[0011] On the other hand, the present application also provides an axial compressor stall first occurrence diagnosis and analysis device, including: A numerical simulation module for performing high-fidelity numerical simulation on the axial compressor according to the standardized flow field simulation process and simulation method; A database establishment module for establishing a multi-operating condition high-fidelity axial compressor flow field parameter database according to the simulation results; A flow field characteristic parameter acquisition module for 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 front and rear stage margin increment matrix FA in the stage characteristics, the sensitivity FB of the flow coefficient-load coefficient curve change, and the sensitivity FC of the spanwise pressure ratio to the operating condition change; A stall first occurrence stage and spanwise position judgment module for performing a comprehensive first occurrence diagnosis according to the matching margin of each stage and the front and rear stage margin increment matrix FA in the stage characteristics, the sensitivity FB of the flow coefficient-load coefficient curve change, and the sensitivity FC of the spanwise pressure ratio to the operating condition change, judging the stall first occurrence stage and the stall first developing spanwise position, and finally outputting the stall first occurrence stage and its spanwise position of the axial compressor.

[0012] On the other hand, the present application also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, the steps of the axial compressor stall first occurrence diagnosis and analysis method are implemented.

[0013] On the other hand, the present application also provides a storage medium, which includes a stored program. When the program runs, it controls the device where the storage medium is located to execute the steps of the axial compressor stall first occurrence diagnosis and analysis method.

[0014] Compared with the prior art, the present application has the following beneficial effects: The present invention provides a method, device, equipment and medium for diagnosing and analyzing the incipient stall of an axial compressor. In the method for diagnosing and analyzing the incipient stall of the axial compressor, the incipient stall stage function focuses on evaluating the work capacity of each stage of the compressor. When the compressor operates deviating from the design condition, if the work capacity of a certain stage is insufficient, it is difficult to maintain a stable air flow compression process. This unstable state will increase the risk of stall, and then lead to air flow separation and performance degradation. When the work capacity of a certain stage is insufficient, the value of this function will be greater than or equal to 0, so as to determine that this stage is the incipient stall stage; the incipient stall development direction position function is mainly used to evaluate the flow states of the rotor and stator of the compressor at different spanwise positions. By analyzing the sensitivity of the change of pressure ratio / total pressure recovery coefficient of the compressor at different spanwise positions, this function can accurately reflect the work capacity of each spanwise position, and can also reveal whether air flow separation occurs on the blade surface. When the work capacity of a certain position is insufficient or air flow separation occurs, the value of this function will be less than 0, so as to determine that the corresponding spanwise section is the incipient stall position. Therefore, the method for diagnosing and analyzing the incipient stall of the axial compressor can quickly locate the first stage and the corresponding spanwise position that cause the axial compressor to stall, improve the speed and accuracy of incipient stall diagnosis, point out the direction for the refined design and optimization of the axial compressor, and further improve the performance and stable operation margin of the compressor.

[0015] In addition to the purposes, features and advantages described above, this application has other purposes, features and advantages. The following will refer to the drawings for a further detailed description of this application. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The drawings constituting a part of this application are used to provide a further understanding of this application. The schematic embodiments of this application and their descriptions are used to explain this application and do not constitute an improper limitation to this application. In the drawings: Figure 1 is a schematic flow chart of the method for diagnosing and analyzing the incipient stall of the axial compressor in the preferred embodiment of this application; Figure 2 is a schematic diagram of the rotor flow coefficient - pressure rise coefficient of an axial compressor when α' < 0; Figure 3 is a schematic diagram of the rotor flow coefficient - pressure rise coefficient of an axial compressor when α' ≥ 0; Figure 4 is a schematic diagram of the curve of the evolution law of the rotor pressure ratio of an axial compressor when β > 0; Figure 5 is a schematic diagram of the curve of the evolution law of the rotor pressure ratio of an axial compressor when β < 0; Figure 6 is a schematic diagram of the curve of the evolution law of the stator total pressure recovery coefficient of an axial compressor when β > 0; Figure 7Schematic diagram of the evolution law curve of the total pressure recovery coefficient of a stator of an axial compressor when β < 0; Figure 8 Schematic diagram of the module of the axial compressor stall pre-onset diagnosis and analysis device according to the preferred embodiment of the present application; Figure 9 Schematic block diagram of the entity of the electronic device according to the preferred embodiment of the present application; Figure 10 Internal structure diagram of the computer device according to the preferred embodiment of the present application. Detailed implementation manners

[0017] The embodiments of the present application will be described in detail below with reference to the accompanying drawings. However, the present application can be implemented in many different ways defined and covered by the following.

[0018] As Figure 1 shown, the preferred embodiment of the present application provides an axial compressor stall pre-onset diagnosis and analysis method, including the steps of: S1. Perform high-fidelity numerical simulation on the axial compressor according to the standardized flow field simulation process and simulation method; S2. Establish a multi-condition high-fidelity axial compressor flow field parameter database according to the simulation results; S3. Extract and mine three key flow field characteristic parameters from the multi-condition high-fidelity axial compressor flow field parameter database, including the matching margin of each stage and the front and rear stage margin increment matrix FA in the stage characteristics, the change sensitivity FB of the flow coefficient-load coefficient curve, and the change sensitivity FC of the spanwise pressure ratio with the working condition; S4. Perform pre-onset comprehensive diagnosis according to the matching margin of each stage and the front and rear stage margin increment matrix FA in the stage characteristics, the change sensitivity FB of the flow coefficient-load coefficient curve, and the change sensitivity FC of the spanwise pressure ratio with the working condition. Define the stall pre-onset stage function and the stall pre-onset development direction position function, and quickly locate the first stage and the corresponding spanwise position that cause the axial compressor to stall through the stall pre-onset stage function and the stall pre-onset development direction position function, judge the stall pre-onset stage and the stall pre-onset development direction position, and finally output the stall pre-onset stage of the axial compressor and its spanwise position.

[0019] This embodiment provides an axial compressor stall pre-onset diagnosis and analysis method. In the axial compressor stall pre-onset diagnosis and analysis method, the stall pre-onset stage function focuses on evaluating the work capacity of each stage of the compressor. When the compressor operates deviating from the design condition, if the work capacity of a certain stage is insufficient, it is difficult to maintain a stable air flow compression process. This unstable state will increase the risk of stall, and then lead to air flow 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 determining that this stage is a stall pre-onset stage; the stall pre-onset development direction position function is mainly used to evaluate the flow states of the compressor rotor and stator at different spanwise positions. By analyzing the change sensitivity of the pressure ratio / total pressure recovery coefficient of the compressor at different spanwise positions, this function can accurately reflect the work capacity of each spanwise position and can also reveal whether air flow separation occurs on the blade surface. When the work capacity at a certain position is insufficient or air flow separation occurs, the function value will be less than 0, thereby determining that the corresponding spanwise section is a stall pre-onset position. Therefore, the axial compressor stall pre-onset diagnosis and analysis method can quickly locate the first stage and the corresponding spanwise position that cause the axial compressor to stall, improve the speed and accuracy of stall pre-onset diagnosis, point out the direction for the refined design and optimization of the axial compressor, and further improve the performance and stable operating margin of the compressor.

[0020] Preferably, step S1 specifically includes the following steps: S11. Preparation of axial compressor blade profile and flow path geometric data: According to the standardized flow field simulation process and simulation method, it is necessary to prepare the blade profile geometric data file ( ) and the flow path geometric data files (hub.curve, shroud.curve) according to the format requirements of the numerical simulation software, where the blade profile geometric data exceeds the hub and casing flow paths; S12. Numerical simulation of axial compressor: According to the standardized flow field simulation process and simulation method, perform grid division, parameter setting and calculation on the axial compressor to obtain high-fidelity numerical simulation results of the axial compressor under multiple working conditions. The numerical simulation state points include at least 5 state points including the choke point, design point, peak efficiency point, and near-stall point at the midpoint of the left branch of the peak efficiency. The reason for requiring at least 5 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.

[0021] This embodiment uses steps S11 - S12 to calculate the high-fidelity numerical simulation results of the axial compressor under multiple working conditions. The benefits include: constructing a complete compressor characteristic curve through multiple characteristic points, which can comprehensively evaluate the aerodynamic performance, stability boundary and applicable working condition range of the compressor. By analyzing the change rules of these points, the working state and performance changes of the compressor under different working conditions can be understood, providing a data basis for the axial compressor flow field parameter database.

[0022] Preferably, step S2 specifically includes the following steps: S21. Post-process the numerical simulation results to obtain the hierarchical characteristic parameters of each state point, and establish a database of the flow field parameters of the axial compressor. Among them, the post-processing includes the overall performance parameters such as the sectional average and circumferential average of the flow rate, pressure ratio, efficiency, etc. of each stage / blade row.

[0023] Preferably, the flow field parameters include the corrected inlet flow rate, flow coefficient, loading coefficient, stage pressure ratio, stage efficiency, rotor pressure ratio, rotor efficiency, and stator total pressure recovery coefficient of each stage of the axial compressor.

[0024] In this embodiment, step S21 is adopted to obtain the hierarchical characteristic parameters of each state point and establish a database of the flow field parameters of the axial compressor. The benefits include: providing comprehensive flow field parameter data, helping designers 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.

[0025] Preferably, step S3 specifically includes the following steps: S31. According to the database of the flow field parameters of the axial compressor, extract the corrected inlet flow rate and stage pressure ratio of each stage in the hierarchical characteristics, and combine with the aerodynamic design values of each stage of the compressor to calculate and obtain the matching margin of each stage in the hierarchical characteristics and the margin increment matrix FA of the front and rear stages. The matching margin of each stage , the subscript i represents the i th stage, dp represents the design point, stall represents the near-stall point; the margin increment between the front and rear stages - , m is the corrected inlet 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 compressor; S32. According to the database of the flow field parameters of the axial compressor, plot the curves of the flow coefficient - loading coefficient of each stage, and numerically fit to obtain the curve function to obtain the sensitivity FB of the change of the flow coefficient - loading coefficient curve, which is used to judge the first stall stage in combination with the matching margin of each stage in the hierarchical characteristics and the margin increment matrix FA of the front and rear stages; S33. According to the database of the flow field parameters of the axial compressor, plot the evolution law curves of the spanwise pressure ratio of each row of rotor / stator changing with the working condition, and obtain the sensitivity FC of the spanwise pressure ratio of each row of rotor / stator changing with the working condition, which is used to judge the position of the first development direction of stall. The spanwise pressure ratio includes the rotor spanwise pressure ratio and the stator spanwise total pressure recovery coefficient.

[0026] In this embodiment, steps S31 - S33 are adopted to extract and mine three key flow field characteristic parameters, including the matching margin of each stage and the front - rear stage margin increment matrix FA in the grading characteristic, the sensitivity FB of the flow coefficient - load coefficient curve change, and the sensitivity FC of the spanwise pressure ratio change with the operating condition. The advantages 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 the flow rate and the load, and the FC parameter focuses on the change of the spanwise pressure ratio. By integrating these parameters, the overall performance and operating state of the compressor can be evaluated more accurately, providing a reliable basis for performance optimization.

[0027] Preferably, in step S4, the specific steps for determining the stall - leading stage include: S41. According to the matching margin of each stage, the front - rear stage margin increment, and the flow coefficient - load coefficient curve, judge the work - doing ability of each stage rotor of the axial - flow compressor and its matching position, so as to analyze which specific stage has insufficient work - doing ability, that is, the stall - leading stage. Therefore, a stall - leading stage function is defined: ; In the formula, , , , , and are regression coefficients; Substitute the matching margin of each stage and the front - rear stage margin increment matrix FA in the grading characteristic and the sensitivity FB of the flow coefficient - load coefficient curve change of each stage into the stall - leading stage function α; When the first - order derivative α’ = f 1(FA,FB)’≥0 of the stall - leading stage function, it indicates that the work - doing ability of the current - stage rotor has reached the limit and the work - doing ability is insufficient. Then, judge that the current - stage rotor is the stall - leading stage.

[0028] In this embodiment, according to the matching margin of each stage, the front - rear stage margin increment, and the flow coefficient - load coefficient curve, the work - doing ability of each stage of the axial - flow compressor and its matching position can be judged, so as to analyze which specific stage has insufficient work - doing ability, that is, the stall - leading stage. Therefore, the stall - leading stage function α = f 1(FA,FB) can be defined. When the function α’ = f 1(FA,FB)’≥0, it indicates that the work - doing ability of the current stage is insufficient and it is the stall - leading stage. As Figure 2 shows, as the flow coefficient gradually decreases and the load coefficient continuously increases, α’<0, indicating that the work - doing ability of this rotor is still very strong and has not approached the unstable state region; as Figure 3 shows, as the flow coefficient gradually decreases and the load coefficient approaches the horizontal, α’≥0, indicating that the work - doing ability of this rotor has reached the limit and entered the unstable state region, that is, this rotor is the stall - leading stage.

[0029] In this embodiment, the stall leading stage function α = f 1(FA, FB) is established in step S41, and it is determined whether the current stage rotor is the stall leading stage according to the value of the stall leading stage function. The advantages include: transforming the complex flow field physical mechanism into a mathematically computable criterion in real time, simplifying the analysis process, improving the efficiency and speed of judgment, and quickly locating the stall leading stage.

[0030] Preferably, in step S4, specifically determining the stall leading direction position includes the steps of: S42. Judging the work capacity of each spanwise position of each row of rotor / stator according to the evolution law curve of the spanwise pressure ratio of each row of rotor / stator changing with the working condition, so as to judge the spanwise position with insufficient work capacity, and thus locate the stall leading direction position. Therefore, the stall leading direction position function is defined as: ; In the formula, , , , , and are regression coefficients, span represents the relative spanwise height section position and takes values in [0~1]; Substitute the sensitivity FC of the spanwise pressure ratio of each row of rotor / stator changing with the working condition into the stall leading direction position function; When β < 0, it indicates that the rotor is at the stall leading direction position at the spanwise height section of span, which is the position that needs to be optimized in design when further improving the margin.

[0031] In this embodiment, according to the evolution law curve of the spanwise pressure ratio of each row of rotor / stator changing with the working condition, the work capacity of each spanwise position of each row of rotor / stator can be judged, so as to judge the spanwise position with insufficient work capacity, and thus locate the stall leading direction position. Therefore, the function β = f 2(FC, span) can be defined. When β < 0, it indicates that the work capacity at the corresponding spanwise position decreases. Combining the distribution of other spanwise positions, it is further judged whether it is the stall leading direction position. Figure 4 And Figure 5 show the evolution law curves of the pressure ratios of two rows of different rotors of the axial flow compressor. In the figure, CFD-1~CFD-7 represent the compressor from the blocked point to the near-stall point. Figure 4 For the compressor from the blocked point to the near-stall point, the pressure ratios of the rotors at the same display height for each working condition of CFD-1~CFD-7 show a gradually increasing trend along the entire spanwise distribution, that is, β(FC, span) > 0, indicating that the work capacity of this rotor is still very strong; Figure 5In the middle, it can be clearly seen that the rotor pressure ratio first increases, and then there is a phenomenon that the rotor pressure ratio decreases at the spanwise height section below 70%, that is, β(FC, 0 - 0.7) < 0, indicating that the rotor at the spanwise height section below 70% is the position where stall develops first, and it is the position that needs to be optimized in design when further improving the margin. Figure 6 Figure and Figure 7 is a schematic diagram of the evolution law curve of the total pressure recovery coefficient of the stator of an axial compressor, where Figure 6 the total pressure recovery coefficient of the stator shows a gradually increasing trend along the entire spanwise distribution, that is, β(FC, span) > 0, indicating that the flow of the stator is smooth and there is no flow separation; Figure 7 in the middle, it can be clearly seen that the total pressure recovery coefficient of the stator decreases at the spanwise height section above 70%, that is, β(FC, 0.7 - 1.0) < 0, indicating that the stator at the spanwise height section above 70% is the position where stall develops first, and it is the position that needs to be optimized in design when further improving the margin.

[0032] In this embodiment, the stall first-occurring stage function β = f 2(FC, span) is established in step S42, and the position where stall develops first is judged according to the value of the stall first-occurring stage function. The advantages include: transforming the complex physical mechanism of the flow field 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 position where stall develops first.

[0033] As Figure 8 shown, another preferred embodiment of the present application also provides an axial compressor stall first-occurring diagnosis and analysis device, including: A numerical simulation module for performing high-fidelity numerical simulation on the axial compressor according to the standardized flow field simulation process and simulation method; A database establishment module for establishing a multi-condition high-fidelity axial compressor flow field parameter database according to the simulation results; A flow field characteristic parameter acquisition module for extracting and mining three key flow field characteristic parameters from the multi-condition high-fidelity axial compressor flow field parameter database, including the matching margin of each stage and the front and rear stage margin increment matrix FA in the stage characteristics, the change sensitivity FB of the flow coefficient-load coefficient curve, and the change sensitivity FC of the spanwise pressure ratio with the working condition; A stall first-occurring stage and spanwise position judgment module for performing a comprehensive first-occurring diagnosis according to the matching margin of each stage and the front and rear stage margin increment matrix FA in the stage characteristics, the change sensitivity FB of the flow coefficient-load coefficient curve, and the change sensitivity FC of the spanwise pressure ratio with the working condition, judging the stall first-occurring stage and the position where stall develops first, and finally outputting the stall first-occurring stage of the axial compressor and its spanwise position.

[0034] As Figure 9As shown in the figure, a preferred embodiment of the present application further provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, the steps of the axial compressor stall pre-diagnosis analysis method in the above embodiment are implemented.

[0035] As Figure 10 shown in the figure, a preferred embodiment of the present application further provides a computer device, which may be a terminal or a living body detection server, and its internal structure diagram may be as Figure 10 shown in the figure. The computer device includes a processor, a memory, and a network interface connected through a system bus. Among them, 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 through a network connection. When the computer program is executed by the processor, the steps of the above axial compressor stall pre-diagnosis analysis method are implemented.

[0036] Those skilled in the art can understand that Figure 10 the structure shown in the figure is only a block diagram of some structures 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 those shown in the figure, or combine some components, or have different component arrangements.

[0037] A preferred embodiment of the present application further provides a storage medium, and the storage medium includes a stored program. When the program runs, it controls the device where the storage medium is located to execute the steps of the axial compressor stall pre-diagnosis analysis method in the above embodiment.

[0038] It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions. And although the logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in a different order than here.

[0039] When the functions described in the method of this embodiment are implemented in the form of software function units and sold or used as independent products, they can be stored in one or more computer-readable storage media. Based on this understanding, the part of this application embodiment that contributes to the prior art or part of this technical solution can be embodied in the form of a software product. This software product is stored in a storage medium and includes several instructions for causing a computer device (which can be a personal computer, a server, a mobile computing device, or a network device, etc.) to execute all or part of the steps of the methods described in various embodiments of this application. The foregoing storage media include: various media such as USB flash drives, mobile hard disks, read-only memories (ROM, Read-Only Memory), random access memories (RAM, Random Access Memory), magnetic disks, or optical discs that can store program codes.

[0040] Those skilled in the art should understand that the embodiments of this application can be provided as a method, a system, or a computer program product. Therefore, this application can adopt the form of a complete hardware embodiment, a complete software embodiment, or an embodiment combining software and hardware aspects. Moreover, this application can adopt the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk memories, CD-ROMs, optical memories, etc.) that contain computer-usable program codes. The solutions in the embodiments of this application can be implemented using various computer languages. For example, object-oriented programming languages such as Java and interpreted scripting languages such as JavaScript.

[0041] This application is described with reference to the flowcharts and / or block diagrams of methods, devices (systems), and computer program products according to the embodiments of this application. It should be understood that each flow and / or block in the flowchart and / or block diagram, as well as the combination of flows 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 the processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing devices to generate a machine, such that the instructions executed by the processor of the computer or other programmable data processing devices generate a device for implementing the functions specified in Figure 1 one flow or multiple flows and / or blocks Figure 1 one block or multiple blocks.

[0042] These computer program instructions can 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, such that the instructions stored in the computer-readable memory generate a manufactured article including an instruction device that implements the functions specified in Figure 1 one flow or multiple flows and / or blocks Figure 1The functions specified in one or more boxes.

[0043] These computer program instructions can also be loaded onto a computer or other programmable data processing device, so that a series of operation steps are executed on the computer or other programmable device to generate a computer-implemented process. Thus, the instructions executed on the computer or other programmable device provide for implementing the steps of the functions specified in Figure 1 one process or more processes and / or boxes Figure 1 the functions specified in one box or more boxes.

[0044] Although the preferred embodiments of the present application have been described, those skilled in the art can make additional changes and modifications to these embodiments once they learn the basic creative concept. Therefore, the appended claims are intended to be construed to include the preferred embodiments as well as all changes and modifications that fall within the scope of the present application.

[0045] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalent technologies, the present application is also intended to include these modifications and variations.

Claims

1. An axial compressor stall pre-diagnosis and analysis method, characterized in that, Including the steps: S1. Conduct high-fidelity numerical simulation on the axial-flow compressor according to the standardized flow field simulation process and simulation method; S2. Establish a multi-condition high-fidelity axial-flow compressor flow field parameter database based on the simulation results; S3. Extract and mine three key flow field characteristic parameters from the multi-condition high-fidelity axial-flow compressor flow field parameter database, including the matching margin of each stage and the front and rear stage margin increment matrix FA in the stage characteristics, the change sensitivity FB of the flow coefficient-load coefficient curve, and the change sensitivity FC of the spanwise pressure ratio with the working condition; S4. Conduct preemptive comprehensive diagnosis according to the matching margin of each stage and the front and rear stage margin increment matrix FA, the change sensitivity FB of the flow coefficient-load coefficient curve, and the change sensitivity FC of the spanwise pressure ratio with the working condition in the stage characteristics, define the stall preemptive stage function and the stall pre-developing spanwise position function, quickly locate the first stage and the corresponding spanwise position that cause the axial-flow compressor to stall through the stall preemptive stage function and the stall pre-developing spanwise position function, judge the stall preemptive stage and the stall pre-developing spanwise position, and finally output the stall preemptive stage of the axial-flow compressor and its spanwise position.

2. The stall pre-diagnosis analysis method of an axial flow compressor according to claim 1, characterized in that The specific steps of step S1 include: S11. Preparation of axial-flow compressor blade profile and flow passage geometric data: According to the standardized flow field simulation process and simulation method, it is necessary to prepare the blade profile geometric data file and the flow passage geometric data file according to the format requirements of the numerical simulation software, where the blade profile geometric data exceeds the hub and casing flow passage; S12. Numerical simulation of axial-flow compressor: According to the standardized flow field simulation process and simulation method, conduct grid division, parameter setting and calculation on the axial-flow compressor to obtain the high-fidelity numerical simulation results of the multi-condition axial-flow compressor. The numerical simulation state points include at least 5 state points such as the blocked point, design point, peak efficiency point, midpoint of the left branch of the peak efficiency, and near-stall point.

3. The axial compressor stall pre-diagnosis analysis method according to claim 1, wherein The specific steps of step S2 include: S21. Post-process the numerical simulation results to obtain the stage characteristic parameters of each state point, and establish an axial-flow compressor flow field parameter database.

4. The axial compressor stall pre-diagnosis analysis method according to claim 3, wherein The flow field parameters include the inlet converted flow rate, flow coefficient, load coefficient, 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 compressor stall pre-diagnosis analysis method according to claim 1, characterized in that, The specific steps of step S3 include: S31. According to the axial flow compressor flow field parameter database, extract the inlet corrected flow rate and stage pressure ratio of each stage in the stage characteristics, and combine with the stage aerodynamic design values of the compressor to calculate the matching margin of each stage and the front and rear stage margin increment matrix FA in the stage characteristics, and the matching margin of each stage , the subscript i represents the i th stage, dp represents the design point, stall represents the near surge point; Front and rear stage margin increment - , m where is the imported 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; S32. According to the axial-flow compressor flow field parameter database, plot the flow coefficient-load coefficient curves of each stage, and numerically fit to obtain the curve function to obtain the change sensitivity FB of the flow coefficient-load coefficient curve, which is used to judge the stall preemptive stage in combination with the matching margin of each stage and the front and rear stage margin increment matrix FA in the stage characteristics; S33. According to the axial-flow compressor flow field parameter database, plot the evolution law curves of the spanwise pressure ratio of each row of rotor / stator with the working condition, and obtain the change sensitivity FC of the spanwise pressure ratio of each row of rotor / stator with the working condition to judge the stall pre-developing spanwise position. The spanwise pressure ratio includes the rotor spanwise pressure ratio and the stator spanwise total pressure recovery coefficient.

6. The axial compressor stall pre-diagnosis analysis method according to claim 5, characterized in that In step S4, the specific steps of judging the stall preemptive stage include: S41. Determine the work capacity and matching position of each stage of the axial compressor rotor based on the matching margins at all levels, the margin increments between the front and rear stages, and the flow coefficient - load coefficient curve, so as to analyze which stage has insufficient work capacity, that is, the stall - first - occurring stage. Therefore, define the stall - first - occurring stage function: ； In the formula, , , , , and are regression coefficients; Substitute the matrix FA of the matching margins at all levels and the margin increments between the front and rear stages in the stage characteristics and the sensitivity FB of the change of the flow coefficient - load coefficient curve at all levels into the stall - first - occurring stage function α; When the first derivative α’ of the stall leading stage function = f 1(FA,FB)’ ≥ 0, it indicates that the work capacity of the current stage rotor has reached the limit and the work capacity is insufficient, so it is determined that the current stage rotor is the stall leading stage.

7. The axial flow compressor stall pre-diagnosis analysis method according to claim 6, characterized in that, In the step S4, the specific steps for judging the stall - first - developing direction and position include: S42. Determine the work capacity of each spanwise position of each row of rotor / stator based on the evolution law curve of the spanwise pressure ratio of each row of rotor / stator changing with the working condition, so as to determine the specific spanwise position with insufficient work capacity, and then locate the stall - first - developing direction and position. Therefore, define the stall - first - developing direction and position function: ； In the formula, , , , , and are regression coefficients, span represents the relative spanwise height cross-section position and its value ranges from [0 to 1]; Substitute the sensitivity FC of the change of the spanwise pressure ratio of each row of rotor / stator with the working condition into the stall - first - developing direction and position function; When β < 0, it indicates that this rotor is the stall - first - developing direction and position at the spanwise height section of span, and it is the position that needs to be optimized in design with key emphasis when further increasing the margin.

8. An axial compressor stall pre-diagnosis and analysis device, characterized in that, Including: A numerical simulation module for performing high - fidelity numerical simulation on the axial compressor according to the standardized flow field simulation process and simulation method; A database establishment module for establishing a multi - working - condition high - fidelity axial compressor flow field parameter database based on the simulation results; A flow field characteristic parameter acquisition module for extracting and mining three key flow field characteristic parameters from the multi - working - condition high - fidelity axial compressor flow field parameter database, including the matrix FA of the matching margins at all levels and the margin increments between the front and rear stages in the stage characteristics, the sensitivity FB of the change of the flow coefficient - load coefficient curve, and the sensitivity FC of the change of the spanwise pressure ratio with the working condition; A stall - first - occurring stage and spanwise position judgment module for performing a comprehensive pre - diagnosis based on the matrix FA of the matching margins at all levels and the margin increments between the front and rear stages in the stage characteristics, the sensitivity FB of the change of the flow coefficient - load coefficient curve, and the sensitivity FC of the change of the spanwise pressure ratio with the working condition, judging the stall - first - occurring stage and the stall - first - developing direction and position, and finally outputting the stall - first - occurring stage and its spanwise position of the axial compressor.

9. An electronic device, comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, When the processor executes the computer program, it realizes the steps of the axial compressor stall - first - occurring diagnosis and analysis method according to any one of claims 1 to 7.

10. A storage medium, the storage medium includes a stored program, and when the program runs, it controls the device where the storage medium is located to execute the steps of the axial compressor stall - first - occurring diagnosis and analysis method according to any one of claims 1 to 7.

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