Stall boundary prediction method and device of gas compressor, electronic equipment and storage medium

Abstract

The invention provides a stall boundary prediction method and device of a gas compressor, electronic equipment and a storage medium, and relates to the technical field of pneumatic design of gas compressors. The method comprises the steps that through-flow calculation is conducted on the gas compressor, and a through-flow calculation result is obtained; according to the through-flow calculation result, stage static pressure rise coefficients and diffusion factors of different blade height sections of the gas compressor are determined; according to the stage static pressure rise coefficients and the diffusion factors of the different blade height sections, the first stall section is determined from the different blade height sections; determining a limit value which can be reached by the stage static pressure rise coefficient of the first stall section; and in response to the fact that the stage static pressure rise coefficient of one stage on the first stall section reaches the limit value, it is predicted that the compressor reaches the stall boundary. Therefore, according to the scheme, the prediction precision and the prediction speed of the stall boundary of the gas compressor are improved, so that rapid and accurate prediction of the stall boundary of the gas compressor is realized.

Description

Technical Field

[0001] The present application relates to the technical field of compressor aerodynamic design, and particularly to a method, device, electronic device and storage medium for predicting the stall boundary of a compressor. Background Art

[0002] In order to ensure the safety of the working process of a gas turbine, a compressor needs to have a sufficient stable working range and not enter unstable working states such as rotating stall and surge. For this purpose, it is necessary to accurately evaluate the stall boundary of the compressor. Summary of the Invention

[0003] An object of the present application is to solve at least one of the technical problems in the related art to some extent.

[0004] To this end, a first object of the present application is to propose a method for predicting the stall boundary of a compressor to achieve rapid and accurate prediction of the stall boundary.

[0005] A second object of the present application is to propose a device for predicting the stall boundary of a compressor.

[0006] A third object of the present application is to propose an electronic device.

[0007] A fourth object of the present application is to propose a computer-readable storage medium.

[0008] A fifth object of the present application is to propose a computer program product.

[0009] To achieve the above object, an embodiment of the first aspect of the present application proposes a method for predicting the stall boundary of a compressor, including: performing a through-flow calculation on the compressor to obtain a through-flow calculation result; Determining the stage static pressure rise coefficient and diffusion factor of different blade height sections of the compressor according to the through-flow calculation result; Determining the first-stall section from the different blade height sections according to the stage static pressure rise coefficient and diffusion factor of the different blade height sections; Determining the limit value that the stage static pressure rise coefficient of the first-stall section can reach; In response to the stage static pressure rise coefficient of one of the levels on the first-stall section reaching the limit value, predicting that the compressor reaches the stall boundary.

[0010] To achieve the above object, an embodiment of the second aspect of the present application proposes a device for predicting the stall boundary of a compressor, including: a calculation module for performing a through-flow calculation on the compressor to obtain a through-flow calculation result; A first determination module for determining the stage static pressure rise coefficient and diffusion factor of different blade height sections of the compressor according to the through-flow calculation result; A second determination module, configured to determine a first stall section from the different blade height sections according to the stage static pressure rise coefficient and the diffusion factor of the different blade height sections; A third determination module, configured to determine a limit value that the stage static pressure rise coefficient of the first stall section can reach; A prediction module, configured to predict that the compressor reaches a stall boundary in response to the stage static pressure rise coefficient of one of the levels on the first stall section reaching the limit value.

[0011] To achieve the above object, an embodiment of the third aspect of the present application provides an electronic device, including: a processor; and a memory communicatively connected to the processor; the memory stores computer-executable instructions; the processor executes the computer-executable instructions stored in the memory, so that the processor can execute the compressor stall boundary prediction method described in the first aspect embodiment above.

[0012] To achieve the above object, an embodiment of the fourth aspect of the present application provides a computer-readable storage medium, on which a computer program is stored, and the computer instructions are used to make the computer execute the compressor stall boundary prediction method described in the above embodiment of one aspect.

[0013] To achieve the above object, an embodiment of the fifth aspect of the present application provides a computer program product, including a computer program, and when the computer program is executed by a processor, it implements the compressor stall boundary prediction method described in the above embodiment of one aspect.

[0014] The compressor stall boundary prediction method, device, electronic device and storage medium provided by the present application obtain the through-flow calculation result of the compressor, and determine the stage static pressure rise coefficient and the diffusion factor of different blade height sections of the compressor according to the through-flow calculation result, so that the first stall section can be determined from different blade height sections according to the stage static pressure rise coefficient and the diffusion factor. Further, it can be predicted whether the compressor reaches the stall boundary according to whether the stage static pressure rise coefficient on the first stall section reaches the limit value of the stage static pressure rise coefficient. Thus, according to the through-flow calculation result, the stall boundary of the compressor is predicted, improving the accuracy and prediction speed of the compressor stall boundary prediction, thereby achieving a fast and accurate prediction of the compressor stall boundary.

[0015] The additional aspects and advantages of the present application will be partially given in the following description, partially become obvious from the following description, or be understood through the practice of the present application. Description of the Drawings

[0016] The above and / or additional aspects and advantages of the present application will become obvious and easy to understand from the following description of the embodiments in conjunction with the drawings, where: Figure 1Schematic flowchart of a method for predicting the stall boundary of a compressor provided by an embodiment of the present application; Figure 2 Schematic diagram of the first stall cross-section provided by an embodiment of the present application; Figure 3 Schematic flowchart of another method for predicting the stall boundary of a compressor provided by an embodiment of the present application; Figure 4 Schematic flowchart of another method for predicting the stall boundary of a compressor provided by an embodiment of the present application; Figure 5 Schematic flowchart of another method for predicting the stall boundary of a compressor provided by an embodiment of the present application; Figure 6 Schematic flowchart of a method for predicting the stall boundary of a compressor provided by an embodiment of the present application; Figure 7 Schematic diagram of the structure of a device for predicting the stall boundary of a compressor provided by an embodiment of the present application. Detailed implementation manners

[0017] The embodiments of the present application are described in detail below. Examples of the embodiments are shown in the accompanying drawings, where the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present application and should not be construed as limiting the present application.

[0018] The method and device for predicting the stall boundary of a compressor according to an embodiment of the present application are described below with reference to the accompanying drawings.

[0019] Figure 1 is a flowchart of a method for predicting the stall boundary of a compressor according to an embodiment of the present application. As Figure 1 shown, the method for predicting the stall boundary of a compressor according to an embodiment of the present application includes, but is not limited to, the following steps: S101, perform through-flow calculation on the compressor to obtain the through-flow calculation result.

[0020] It should be noted that the execution subject of the stall boundary prediction method for the compressor provided in the embodiments of the present application is an electronic device, and this electronic device may be a terminal device. Optionally, the terminal device may be a mobile electronic device or a non-mobile electronic device. Exemplarily, the mobile electronic device may be a mobile phone, a tablet computer, a laptop computer, a handheld computer, a vehicle-mounted electronic device, a wearable device, an ultra-mobile personal computer (UMPC), a netbook, or a personal digital assistant (PDA), etc., and the non-mobile electronic device may be a personal computer (PC), a television, etc. The embodiments of the present application do not make specific limitations.

[0021] It can be understood that the through-flow calculation is a numerical simulation method in the aerodynamic design of a compressor, which is used to quickly predict the flow characteristics of the fluid in the blade passage and the aerodynamic performance of the device. The through-flow calculation solves the distribution law of the basic flow parameters (such as pressure, velocity, temperature) of the fluid in the axial (or radial) flow passage through numerical simulation, so as to evaluate the aerodynamic performance of the compressor.

[0022] In some embodiments, performing a through-flow calculation on the compressor may be to perform a numerical simulation on the compressor to obtain the distribution law of the basic flow parameters of the internal flow field of the compressor along the flow passage, and obtain the through-flow calculation result according to the distribution law of the parameters.

[0023] For example, the streamline curvature method is adopted for the through-flow calculation, a trailing angle model and a loss model are added, and the radial mixing effect and the mixing model are considered. During the calculation process, the total temperature, total pressure, and inlet flow direction are given at the inlet, and the compressor flow rate is given, and the flow rate is gradually reduced to approach the stall boundary.

[0024] Optionally, the through-flow calculation results include but are not limited to: characteristic parameters, the distribution of flow parameters, aerodynamic performance parameters, and blade load parameters. Among them, the flow parameters include pressure parameters, temperature parameters, velocity parameters, etc.

[0025] S102. According to the through-flow calculation result, determine the stage static pressure rise coefficient and diffusion factor of different blade height sections of the compressor.

[0026] In some embodiments, the stage static pressure rise coefficient of each blade height section of the compressor can be calculated according to the through-flow calculation result. Optionally, the aerodynamic parameters corresponding to each blade height section can be obtained from the through-flow calculation result, and the stage static pressure rise coefficient can be calculated based on the aerodynamic parameters.

[0027] In some embodiments, parameters related to the diffusion factor can be obtained based on the through-flow calculation results, and the diffusion factor can be calculated based on these parameters. Optionally, the diffusion factor includes the diffusion factor of the moving blade and the diffusion factor of the stationary blade.

[0028] Optionally, the blade solidity, the change in the circumferential velocity at the inlet and outlet, and the relative velocity at the inlet and outlet in the through-flow calculation results can be used as the parameters related to the diffusion factor.

[0029] S103. Determine the first-stall section from different blade-height sections according to the stage static pressure rise coefficient and the diffusion factor of different blade-height sections.

[0030] In some embodiments, the load corresponding to the blade-height section can be determined according to the stage static pressure rise coefficient and the diffusion factor of different blade-height sections, and the first-stall section can be determined from different blade-height sections according to the load corresponding to the blade-height section. As shown in the schematic diagram of the first-stall section. Figure 2 The schematic diagram of the first-stall section shown.

[0031] In some embodiments, it can be determined whether the blade-height section meets the set conditions according to the load corresponding to the blade-height section, and the blade-height section that meets the set conditions can be used as the first-stall section. Optionally, the set conditions can be determined according to the magnitude of the load. For example, taking the load being greater than the set threshold as meeting the set conditions. That is to say, when the load corresponding to the blade-height section is greater than the set threshold, it is determined that the set conditions are met.

[0032] S104. Determine the limit value that the stage static pressure rise coefficient of the first-stall section can reach.

[0033] In some embodiments, the mapping relationship between the dimensionless diffuser length and the maximum stage static pressure rise coefficient can be obtained, and this mapping relationship can be queried according to the dimensionless diffuser length of the first-stall section, so as to determine the maximum stage static pressure rise coefficient that the stage static pressure rise coefficient of the first-stall section can reach, and take the maximum stage static pressure rise coefficient as the limit value.

[0034] In some embodiments, the dimensionless diffuser length is the ratio of the diffuser length of the blade-height section to the outlet width. The diffuser length and the outlet width of the first-stall section can be determined from the through-flow calculation results, and further calculate the ratio of the diffuser length of the first-stall section to the outlet width as the dimensionless diffuser length of the first-stall section.

[0035] In some embodiments, in order to improve the accuracy of the limit value, the maximum stage static pressure rise coefficient can also be corrected, and the corrected maximum stage static pressure rise coefficient can be taken as the limit value.

[0036] Optionally, the maximum stage static pressure rise coefficient can be corrected based on the Reynolds number of the compressor. The maximum stage static pressure rise coefficient can also be corrected based on the tip clearance of the compressor blades. The maximum stage static pressure rise coefficient can also be corrected based on the axial clearance of the compressor blade rows.

[0037] S105. In response to the stage static pressure rise coefficient of one of the stages on the leading stall section reaching the limit value, predict that the compressor reaches the stall boundary.

[0038] In some embodiments, by obtaining the stage static pressure rise coefficient of each stage on the leading stall section and determining whether the stage static pressure rise coefficient of each stage reaches the limit value, and when the stage static pressure rise coefficient of one of the stages on the leading stall section reaches the limit value, it is possible to predict that the compressor reaches the stall boundary.

[0039] In some embodiments, the stage static pressure rise coefficient of one of the stages on the leading stall section reaching the limit value can also be used as a prediction condition for predicting that the compressor reaches the stall boundary. When the leading stall section meets the prediction condition, it is possible to predict that the compressor reaches the stall boundary.

[0040] In the compressor stall boundary prediction method provided by the embodiments of the present application, by obtaining the through-flow calculation result of the compressor and determining the stage static pressure rise coefficient and diffusion factor of different blade height sections of the compressor according to the through-flow calculation result, the leading stall section can be determined from different blade height sections according to the stage static pressure rise coefficient and diffusion factor. Further, it is possible to predict whether the compressor reaches the stall boundary according to whether the stage static pressure rise coefficient on the leading stall section reaches the limit value of the stage static pressure rise coefficient. Thus, according to the through-flow calculation result, the stall boundary of the compressor is predicted, improving the accuracy and prediction speed of the prediction of the compressor stall boundary, thereby achieving a fast and accurate prediction of the compressor stall boundary.

[0041] Figure 3 is a flowchart of a compressor stall boundary prediction method provided by the embodiments of the present application. As Figure 3 shown, the compressor stall boundary prediction method of the embodiments of the present application includes but is not limited to the following steps: S301. Perform a through-flow calculation on the compressor to obtain the through-flow calculation result.

[0042] In the embodiments of the present application, the implementation manner of step S301 can be implemented by any one of the embodiments of the present application respectively, and no limitation is made here and no further description is given.

[0043] S302. For each blade height section, determine the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section according to the through-flow calculation result.

[0044] S303. Determine the stage static pressure rise coefficient of the blade height section based on the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section.

[0045] In some embodiments, the aerodynamic parameters of each blade height section and the characteristic parameters of the compressor can be obtained from the through-flow calculation results, so that the stage static pressure rise coefficient of the blade height section can be calculated based on the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section.

[0046] Optionally, the through-flow calculation can perform numerical simulation on the characteristic parameters of the compressor to obtain the characteristic curve of the compressor as the through-flow calculation result, and obtain the characteristic parameters of the compressor according to the characteristic curve.

[0047] Optionally, the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section include but are not limited to: constant pressure specific heat ratio, specific heat ratio, stage inlet static temperature, stage inlet static pressure, stage outlet static pressure, circumferential velocity at the inlet of the rotor blade, circumferential velocity at the outlet of the rotor blade.

[0048] In some embodiments, according to the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section, the following formula can be used to determine the stage static pressure rise coefficient of the blade height section:

[0049] where, C h_ef is the stage static pressure rise coefficient, c p is the constant pressure specific heat, k is the specific heat ratio, T 1 is the stage inlet static temperature, p 1 is the stage inlet static pressure, p 2 is the stage outlet static pressure, U 1 is the circumferential velocity at the inlet of the rotor blade, U 2 is the circumferential velocity at the outlet of the rotor blade, W 1_ef is the effective dynamic pressure head velocity of the rotor blade, V 1_ef is the effective dynamic pressure head velocity of the stator blade.

[0050] In some embodiments, W 1_ef being the effective dynamic pressure head velocity of the rotor blade, the effective dynamic pressure head velocity of the rotor blade can be calculated based on the minimum possible relative velocity at the inlet of the rotor blade and the relative velocity at the inlet of the rotor blade. Optionally, the following formula can be used to determine the effective dynamic pressure head velocity of the rotor blade W 1_ef :

[0051] where, W minis the minimum possible relative velocity at the inlet of the moving blade, W 1 is the relative velocity at the inlet of the moving blade.

[0052] In some embodiments, the minimum possible relative velocity at the inlet of the moving blade W min can be calculated according to the velocity triangle relationship under the condition of keeping the direction of the outlet velocity of the upstream stationary blade unchanged. Optionally, to calculate the minimum possible relative velocity at the inlet of the moving blade W min The formula is as follows:

[0053] where, α 2 is the absolute flow angle at the outlet of the stationary blade, β 1 is the relative flow angle at the inlet of the moving blade.

[0054] In some embodiments, V 1_ef is the effective dynamic head velocity of the stationary blade, and the effective dynamic head velocity of the stationary blade can be calculated based on the minimum possible relative velocity at the inlet of the stationary blade and the relative velocity at the inlet of the stationary blade. Optionally, the effective dynamic head velocity of the stationary blade can be determined by the following formula V 1_ef :

[0055] where, V min is the minimum possible relative velocity at the inlet of the stationary blade, V 1 is the relative velocity at the inlet of the stationary blade.

[0056] In some embodiments, the minimum possible relative velocity at the inlet of the stationary blade V min can be calculated according to the velocity triangle relationship under the condition of keeping the direction of the outlet velocity of the upstream moving blade unchanged. Optionally, to calculate the minimum possible relative velocity at the inlet of the stationary blade V min The formula is as follows:

[0057] where, α 1 is the absolute flow angle at the inlet of the stationary blade, β 2 is the relative flow angle at the outlet of the moving blade.

[0058] S304. According to the through-flow calculation results, determine the diffusion factors of different blade height sections of the compressor.

[0059] In some embodiments, the diffusion factors of different blade heights in the compressor include the diffusion factor of the rotor blade and the diffusion factor of the stator blade. Parameters such as the solidity of the rotor blade and the stator blade, the change in the circumferential velocity at the inlet and outlet of the rotor blade and the stator blade, the relative velocity at the inlet and outlet of the rotor blade, and the absolute velocity at the inlet and outlet of the stator blade can be obtained respectively from the through-flow calculation results. Based on the above parameters, the diffusion factor of the rotor blade and the diffusion factor of the stator blade are calculated.

[0060] Optionally, the following formula can be used to calculate the diffusion factor of the rotor blade DF r :

[0061] Wherein, τ r is the solidity of the rotor blade, Δ W u is the change in the circumferential velocity at the inlet and outlet of the rotor blade, W 1 is the relative velocity at the inlet of the rotor blade, W 2 is the relative velocity at the outlet of the rotor blade.

[0062] Optionally, the following formula can be used to calculate the diffusion factor of the stator blade DF s :

[0063] Wherein, τ s is the solidity of the stator blade, Δ V u is the change in the circumferential velocity at the inlet and outlet of the stator blade, V 1 is the absolute velocity at the inlet of the stator blade, V 2 is the absolute velocity at the outlet of the stator blade.

[0064] In some embodiments, the stage static pressure rise coefficient and the diffusion factor of the set partial blade height section of the compressor can also be obtained, and interpolation is performed on the stage static pressure rise coefficient and the diffusion factor of the set partial blade height section, so as to obtain the stage static pressure rise coefficient and the diffusion factor of different blade height sections of the compressor.

[0065] In some embodiments, according to the through-flow calculation results, the stage static pressure rise coefficient and the diffusion factor of the set partial blade height section of the compressor can be determined, and interpolation calculation is performed on the stage static pressure rise coefficient and the diffusion factor of the partial blade height section to obtain the stage static pressure rise coefficient and the diffusion factor of different blade height sections of the compressor.

[0066] S305. Determine the first stall section from different blade height sections according to the stage static pressure rise coefficient and the diffusion factor of different blade height sections.

[0067] S306. Determine the limit value that the static pressure rise coefficient of the first stalled section can reach.

[0068] S307. In response to the stage static pressure rise coefficient of one of the stages on the first stalled section reaching the limit value, predict that the compressor reaches the stall boundary.

[0069] In the embodiments of the present application, the implementation manners of steps S305 - S307 can be respectively implemented by any one of the embodiments of the present application. No limitation is made here and no further description is given.

[0070] In some embodiments, after predicting that the compressor reaches the stall boundary, the first stalled stage of the compressor can also be determined. By determining the stage among the stage static pressure rise coefficients on the first stalled section that first reaches the limit value as the first stalled stage of the compressor.

[0071] In some embodiments, after predicting that the compressor reaches the stall boundary, the accuracy of the stall boundary can also be verified. Optionally, the stall boundary can be verified according to three - dimensional computational fluid dynamics (CFD).

[0072] In some embodiments, by performing CFD calculations on the compressor to obtain the CFD calculation results, and based on the CFD calculation results of the compressor, determine the reference stall boundary of the compressor. That is, the stall boundary of the compressor can be determined from the CFD calculation results and used as the reference stall boundary, so that the stall boundary reached by the compressor can be verified based on the reference stall boundary.

[0073] Optionally, it can be verified whether there is an error between the reference stall boundary and the stall boundary reached by the compressor. If there is an error, determine whether the error is less than the error threshold. In response to the error between the reference stall boundary and the stall boundary reached by the compressor being less than the error threshold, determine that the stall boundary reached by the compressor passes the verification.

[0074] In the stall boundary prediction method of the compressor provided by the embodiments of the present application, by determining the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section from the through - flow calculation results, and calculating the stage static pressure rise coefficient of the blade height section according to the characteristic parameters and the aerodynamic parameters. Thus, determining the stage static pressure rise coefficient of the blade height section according to the through - flow calculation results can provide data support for subsequent prediction of the compressor stall boundary, thereby improving the accuracy of predicting the stall boundary.

[0075] Figure 4 is a flowchart of a method for predicting the stall boundary of a compressor provided by the embodiments of the present application. As Figure 4 shown, the method for predicting the stall boundary of the compressor in the embodiments of the present application includes but is not limited to the following steps: S401. Perform a through-flow calculation on the compressor to obtain the through-flow calculation results.

[0076] S402. Determine the stage static pressure rise coefficient and diffusion factor of different blade height sections of the compressor according to the through-flow calculation results.

[0077] In the embodiments of the present application, the implementation manners of steps S401 - S402 can be respectively implemented by any one of the embodiments of the present application. No limitation is made here and no further elaboration is provided.

[0078] S403. Determine the spanwise distribution of the stage static pressure rise coefficient and diffusion factor of different blade height sections.

[0079] In some embodiments, determining the spanwise distribution of the stage static pressure rise coefficient and diffusion factor of different blade height sections refers to analyzing the changes in the stage static pressure rise coefficient and diffusion factor at different spanwise height positions of the blade. Among them, the spanwise direction can be the direction from the blade root to the blade tip.

[0080] In some embodiments, by obtaining the stage static pressure rise coefficient and diffusion factor at different spanwise positions of different blade height sections, and analyzing the changes in the stage static pressure rise coefficient and diffusion factor according to the stage static pressure rise coefficient and diffusion factor at different spanwise positions, the spanwise distribution is obtained.

[0081] S404. Determine the axial distribution of the stage static pressure rise coefficient and diffusion factor of different blade height sections.

[0082] In some embodiments, determining the axial distribution of the stage static pressure rise coefficient and diffusion factor of different blade height sections refers to determining the changes in the stage static pressure rise coefficient and diffusion factor in the axial direction of the compressor. Among them, the axial direction can be the air flow direction. For example, different axial positions from the inlet to the outlet, such as guide vanes, rotor blades, and bladeless regions.

[0083] In some embodiments, by obtaining the stage static pressure rise coefficient and diffusion factor at different axial positions of different blade height sections, and analyzing the changes in the stage static pressure rise coefficient and diffusion factor according to the stage static pressure rise coefficient and diffusion factor at different axial positions, the axial distribution is obtained.

[0084] S405. Determine the load conditions of the blade height sections along the spanwise distribution and axial distribution.

[0085] In some embodiments, the load conditions of the blade height sections can be analyzed along the spanwise distribution and axial distribution. Optionally, the first load distribution on the blade height section can be determined along the spanwise distribution, and the second load distribution on the blade height section can be determined along the axial distribution, so as to determine the load conditions of the blade height section according to the first load distribution and the second load distribution.

[0086] For example, the first load distribution of the blade height section can be determined according to mechanical parameters such as stress and strain distributed along the spanwise direction of the blade height section. The change curve of the load of the blade height section at different axial positions over time or rotation angle can be obtained to determine the second load distribution.

[0087] Optionally, the load magnitude of the blade height section can be determined based on the first load distribution and the second load distribution, and the load magnitude can be used as the load condition of the blade height section.

[0088] S406. Select the blade height section whose load condition meets the set conditions as the first stall section.

[0089] In some embodiments, the set conditions can be determined in advance, and it can be determined whether the load conditions of different blade height sections meet the set conditions. For example, if the load condition is the load magnitude, the load magnitude being greater than the load threshold can be used as meeting the set conditions, so that it can be determined whether the load magnitudes of different blade height sections are greater than the load threshold to select the blade height section whose load condition meets the set conditions as the first stall section.

[0090] In some embodiments, after determining the first stall section, the effectiveness of the first stall section can also be verified. Optionally, the blade height range where the load meets the set conditions can be obtained, and the effectiveness of the first stall section can be verified according to the blade height range.

[0091] In some embodiments, by obtaining the CFD calculation results of the compressor and determining the blade height range where the load meets the set conditions according to the CFD calculation results.

[0092] In some embodiments, the blade height positions with severe flow separation and blockage and high load can be analyzed based on the CFD calculation results, and the blade height positions with severe flow separation and blockage and high load can be used as the blade height range where the load meets the set conditions. In some embodiments, verifying the effectiveness of the first stall section according to the blade height range can be to determine whether the blade height position of the first stall section is within the blade height range. If it is within the blade height range, it is determined that the first stall section is effective.

[0093] S407. Determine the limit value that the static pressure rise coefficient of the first stall section can reach.

[0094] S408. In response to the stage static pressure rise coefficient of one of the stages on the first stall section reaching the limit value, predict that the compressor reaches the stall boundary.

[0095] In the embodiments of the present application, the implementation manners of steps S407 - S408 can be respectively implemented in any one of the embodiments of the present application. No limitation is made here and no further elaboration is provided.

[0096] In the stall boundary prediction method of the compressor provided by the embodiments of the present application, by determining the spanwise distribution and axial distribution of the stage static pressure rise coefficient and the diffusion factor of different blade height sections, and determining the load conditions of the blade height sections according to the spanwise distribution and axial distribution, blade height sections whose load conditions meet the set conditions can be selected as the first stalled sections. Thus, by determining the first stalled sections according to the load conditions of the blade height sections, the stall boundary can be predicted more accurately based on the first stalled sections.

[0097] Figure 5 is a flowchart of a stall boundary prediction method of a compressor provided by the embodiments of the present application. As Figure 5 shown, the stall boundary prediction method of the compressor in the embodiments of the present application includes but is not limited to the following steps: S501, perform a through-flow calculation on the compressor to obtain the through-flow calculation results.

[0098] S502, determine the stage static pressure rise coefficient and the diffusion factor of different blade height sections of the compressor according to the through-flow calculation results.

[0099] S503, determine the first stalled section from different blade height sections according to the stage static pressure rise coefficient and the diffusion factor of different blade height sections.

[0100] In the embodiments of the present application, the implementation manners of steps S501 - S503 can be implemented respectively by any one of the embodiments of the present application. No limitation is made here and no further elaboration is given.

[0101] S504, determine the diffuser length and the outlet width of the first stalled section, and determine the target non-dimensional diffuser length according to the diffuser length and the outlet width.

[0102] S505, query the mapping relationship between the maximum stage static pressure rise coefficient and the non-dimensional diffuser length, and obtain the target maximum stage static pressure rise coefficient that has a mapping with the target non-dimensional diffuser length.

[0103] S506, determine the limit value according to the target maximum stage static pressure rise coefficient.

[0104] In some embodiments, the non-dimensional diffuser length is the ratio of the diffuser length of the blade height section to the outlet width. The diffuser length and the outlet width of different blade height sections can be determined from the through-flow calculation results, so that the diffuser length and the outlet width of the first stalled section can be determined. Further, the target non-dimensional diffuser length of the first stalled section can be calculated according to the diffuser length and the outlet width.

[0105] Optionally, the formula for calculating the non-dimensional diffuser length is as follows: L / g 2= L / (t ·cos β 2)(8) Wherein, L / g 2 represents the dimensionless diffuser length, L represents the diffuser length, g 2 represents the outlet width. Wherein, g 2 = t ·cos β 2, t is the characteristic length, β 2 is the angle at the outlet.

[0106] That is to say, by substituting the diffuser length and the outlet width of the first stall section into the above formula (8), the target dimensionless diffuser length can be calculated.

[0107] In some embodiments, the mapping relationship between the maximum stage static pressure rise coefficient and the dimensionless diffuser length can be obtained, and according to the target dimensionless diffuser length, by querying this mapping relationship, the maximum stage static pressure rise coefficient mapped to the target dimensionless diffuser length can be determined as the target maximum stage static pressure rise coefficient.

[0108] In some embodiments, the target maximum stage static pressure rise coefficient can be corrected to obtain a limit value to improve the accuracy of the limit value. By determining the Reynolds number, tip clearance, and axial clearance of the blade row corresponding to the first stall section, and according to the Reynolds number, tip clearance, and axial clearance of the blade row, the target maximum stage static pressure rise coefficient is corrected to obtain a limit value.

[0109] Optionally, the Reynolds number, tip clearance, and axial clearance of the blade row corresponding to the first stall section can be determined from the through-flow calculation results.

[0110] S507. In response to the stage static pressure rise coefficient of one of the stages on the first stall section reaching the limit value, it is predicted that the compressor reaches the stall boundary.

[0111] In the embodiments of the present application, the implementation manner of step S507 can be implemented by any one of the embodiments of the present application respectively, and no limitation is made here and no further description is given.

[0112] In the stall boundary prediction method of the compressor provided by the embodiments of the present application, by determining the target dimensionless diffuser length of the first stall section, according to the target dimensionless diffuser length, the target maximum stage static pressure rise coefficient of the first stall section is determined, and the target maximum stage static pressure rise coefficient is corrected to obtain a limit value. Thus, according to the limit value and the stage static pressure rise coefficient, the stall boundary of the compressor is predicted, and the stall boundary of the compressor can be predicted quickly and accurately.

[0113] Figure 6The figure shows a schematic flow chart for predicting the stall boundary of a compressor. By performing a through-flow calculation on the compressor and determining the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section based on the through-flow calculation results, the stage static pressure rise coefficient of different blade height sections is calculated according to the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section, and the diffusion factor of different blade height sections is determined according to the through-flow calculation results, so that the first-stall section can be determined based on the stage static pressure rise coefficient and the diffusion factor.

[0114] Optionally, the spanwise distribution of the stage static pressure rise coefficient and the diffusion factor of different blade height sections can be analyzed, and the axial distribution of the stage static pressure rise coefficient and the diffusion factor of different blade height sections can be analyzed. Further, along the spanwise distribution and the axial distribution, the loading conditions of the blade height section are determined, so as to select the blade height section whose loading conditions meet the set conditions as the first-stall section.

[0115] Further, the target dimensionless diffuser length of the first-stall section is determined, and according to the mapping relationship between the maximum stage static pressure rise coefficient and the dimensionless diffuser length, the target maximum stage static pressure rise coefficient corresponding to the target dimensionless diffuser length is determined, and the limit value is obtained by correcting the target maximum stage static pressure rise coefficient. It is judged whether the stage static pressure rise coefficient of one of the levels on the first-stall section reaches the limit value, and when it reaches the limit value, it is predicted that the compressor reaches the stall boundary, and the level of the first stage static pressure rise coefficient on the first-stall section that first reaches the limit value is determined as the first-stall stage of the compressor.

[0116] Corresponding to the compressor stall boundary prediction methods proposed in the above several embodiments, an embodiment of the present application also proposes a compressor stall boundary prediction device. Since the compressor stall boundary prediction device proposed in the embodiment of the present application corresponds to the compressor stall boundary prediction methods proposed in the above several embodiments, the implementation manners of the above compressor stall boundary prediction methods are also applicable to the compressor stall boundary prediction device proposed in the embodiment of the present application, and will not be described in detail in the following embodiments.

[0117] To implement the above embodiments, the present application also proposes a compressor stall boundary prediction device.

[0118] Figure 7 FIG. is a schematic structural diagram of a compressor stall boundary prediction device provided by an embodiment of the present application.

[0119] As Figure 7 shown, the compressor stall boundary prediction device 700 includes: A calculation module 701, configured to perform a through-flow calculation on the compressor and obtain the through-flow calculation result; A first determination module 702, configured to determine the stage static pressure rise coefficient and the diffusion factor of different blade height sections of the compressor according to the through-flow calculation result; A second determination module 703, configured to determine a first-stall cross-section from different blade-height cross-sections according to the stage static pressure rise coefficient and diffusion factor of different blade-height cross-sections; A third determination module 704, configured to determine a limit value that the stage static pressure rise coefficient of the first-stall cross-section can reach; A prediction module 705, configured to predict that the compressor reaches the stall boundary in response to the stage static pressure rise coefficient of one of the levels on the first-stall cross-section reaching the limit value.

[0120] In a possible implementation manner of the embodiment of the present application, the prediction module 705 is further configured to: determine the level at which the stage static pressure rise coefficient of each level on the first-stall cross-section first reaches the limit value, as the first-stall stage of the compressor.

[0121] In a possible implementation manner of the embodiment of the present application, the first determination module 702 is further configured to: for each blade-height cross-section, determine the characteristic parameters of the compressor and the aerodynamic parameters of the blade-height cross-section according to the through-flow calculation result; determine the stage static pressure rise coefficient of the blade-height cross-section according to the characteristic parameters of the compressor and the aerodynamic parameters of the blade-height cross-section.

[0122] In a possible implementation manner of the embodiment of the present application, the following formula is used to determine the stage static pressure rise coefficient of the blade-height cross-section:

[0123] wherein, c p is the specific heat at constant pressure; k is the specific heat ratio; T 1 is the static temperature at the inlet of the stage; p 1 is the static pressure at the inlet of the stage; p 2 is the static pressure at the outlet of the stage; U 1 is the circumferential velocity at the inlet of the rotor blade; U 2 is the circumferential velocity at the outlet of the rotor blade; W 1_ef is the effective dynamic head velocity of the rotor blade; V 1_ef is the effective dynamic head velocity of the stator blade.

[0124] In a possible implementation manner of the embodiment of the present application, the second determination module 703 is further configured to: determine the spanwise distribution of the stage static pressure rise coefficient and diffusion factor of different blade-height cross-sections; determine the axial distribution of the stage static pressure rise coefficient and diffusion factor of different blade-height cross-sections; determine the load condition of the blade-height cross-section along the spanwise distribution and axial distribution; select the blade-height cross-section whose load condition meets the set condition as the first-stall cross-section.

[0125] In a possible implementation manner of the embodiment of the present application, the second determination module 703 is further configured to: obtain the three-dimensional computational fluid dynamics (CFD) calculation result of the compressor, and determine the blade height range in which the load meets the set conditions according to the CFD calculation result; verify the effectiveness of the first stall section according to the blade height range.

[0126] In a possible implementation manner of the embodiment of the present application, the third determination module 704 is further configured to: determine the diffuser length and the outlet width of the first stall section, and determine the target dimensionless diffuser length according to the diffuser length and the outlet width; query the mapping relationship between the maximum stage static pressure rise coefficient and the dimensionless diffuser length, and obtain the target maximum stage static pressure rise coefficient that has a mapping with the target dimensionless diffuser length; determine the limit value according to the target maximum stage static pressure rise coefficient.

[0127] In a possible implementation manner of the embodiment of the present application, the third determination module 704 is further configured to: determine the Reynolds number, the tip clearance, and the axial clearance of the blade row corresponding to the first stall section, and correct the target maximum stage static pressure rise coefficient according to the Reynolds number, the tip clearance, and the axial clearance of the blade row to obtain the limit value.

[0128] In a possible implementation manner of the embodiment of the present application, the prediction module 705 is further configured to: determine the reference stall boundary of the compressor based on the CFD calculation result of the compressor; verify the stall boundary reached by the compressor based on the reference stall boundary.

[0129] In a possible implementation manner of the embodiment of the present application, the first determination module 702 is further configured to: determine the stage static pressure rise coefficient and the diffusion factor of the partial blade height section set by the compressor according to the through-flow calculation result; perform interpolation calculation on the stage static pressure rise coefficient and the diffusion factor of the partial blade height section to obtain the stage static pressure rise coefficient and the diffusion factor of different blade height sections of the compressor.

[0130] In the stall boundary prediction device of the compressor provided by the embodiment of the present application, by obtaining the through-flow calculation result of the compressor and determining the stage static pressure rise coefficient and the diffusion factor of different blade height sections of the compressor according to the through-flow calculation result, the first stall section can be determined from different blade height sections according to the stage static pressure rise coefficient and the diffusion factor. Further, it is possible to predict whether the compressor reaches the stall boundary according to whether the stage static pressure rise coefficient on the first stall section reaches the limit value of the stage static pressure rise coefficient. Thus, according to the through-flow calculation result, the stall boundary of the compressor is predicted, improving the accuracy and prediction speed of the prediction of the stall boundary of the compressor, thereby realizing the fast and accurate prediction of the stall boundary of the compressor.

[0131] It should be noted that the foregoing explanation of the embodiment of the stall boundary prediction method of the compressor is also applicable to the stall boundary prediction device of the compressor in this embodiment, and will not be elaborated here.

[0132] To implement the above embodiments, the present application further provides an electronic device, including: a processor, and a memory communicatively connected to the processor; the memory stores computer-executable instructions; the processor executes the computer-executable instructions stored in the memory to implement the method provided in the foregoing embodiments. To implement the above embodiments, the present application further provides a computer-readable storage medium storing computer-executable instructions, which are used to implement the method provided in the foregoing embodiments when executed by a processor.

[0133] To implement the above embodiments, the present application further provides a computer program product including a computer program, which implements the method provided in the foregoing embodiments when executed by a processor.

[0134] In the description of the foregoing embodiments, the descriptions with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, without conflict, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0135] In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present application, "a plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0136] Any process or method description in the flowchart or described in other ways herein may be understood to represent a module, segment, or portion of code including one or more executable instructions for implementing a customized logic function or process, and the scope of the preferred embodiments of the present application includes additional implementations, where the functions may be executed in a substantially simultaneous manner or in a reverse order according to the involved functions, rather than in the order shown or discussed, which should be understood by those skilled in the art to which the embodiments of the present application pertain.

[0137] The logic and / or steps represented in the flowchart or otherwise described herein, for example, can be considered as a definable sequence list of executable instructions for implementing logical functions, and can be specifically implemented in any computer-readable medium for use by an instruction execution system, apparatus, or device (such as a computer-based system, a system including a processor, or other systems that can fetch and execute instructions from the instruction execution system, apparatus, or device), or used in combination with these instruction execution systems, apparatus, or devices. For the purposes of this specification, a "computer-readable medium" can be any device that can contain, store, communicate, propagate, or transmit a program for use by or in combination with an instruction execution system, apparatus, or device. More specific examples (a non-exhaustive list) of the computer-readable medium include the following: an electrical connection portion with one or more wirings (electronic device), a portable computer disk cartridge (magnetic device), a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber device, and a portable compact disc read-only memory (CDROM). Additionally, the computer-readable medium can even be paper or other suitable media on which the program can be printed, because the program can be obtained electronically, for example, by optically scanning the paper or other media, followed by editing, interpretation, or other suitable processing as necessary, and then storing it in a computer memory.

[0138] It should be understood that various parts of the present application can be implemented by hardware, software, firmware, or a combination thereof. In the above-described embodiments, multiple steps or methods can be implemented by software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented in hardware, as in another embodiment, any one or a combination of the following techniques well known in the art can be used: discrete logic circuits having logic gate circuits for implementing logical functions on data signals, application-specific integrated circuits having appropriate combinational logic gate circuits, programmable gate arrays (PGAs), field programmable gate arrays (FPGAs), etc.

[0139] Those of ordinary skill in the art of this technology can understand that all or part of the steps carried by the method of implementing the above embodiments can be completed by a program instructing relevant hardware, and the program can be stored in a computer-readable storage medium. When the program is executed, it includes one or a combination of the steps of the method embodiments.

[0140] In addition, each functional unit in various embodiments of the present application may be integrated into one processing module, may exist separately as individual physical units, or two or more units may be integrated into one module. The above-mentioned integrated module may be implemented in the form of hardware or in the form of a software functional module. When the integrated module is implemented in the form of a software functional module and sold or used as an independent product, it may also be stored in a computer-readable storage medium.

[0141] The above-mentioned storage medium may be a read-only memory, a magnetic disk, an optical disc, etc. Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present application. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present application.

Claims

1. A method for predicting the stall boundary of a compressor, characterized in that The method includes: Performing a through-flow calculation on the compressor to obtain the through-flow calculation result; Determining the stage static pressure rise coefficient and diffusion factor of different blade height sections of the compressor according to the through-flow calculation result; Determining the first stall section from the different blade height sections according to the stage static pressure rise coefficient and diffusion factor of the different blade height sections; Determining the limit value that the stage static pressure rise coefficient of the first stall section can reach; In response to the stage static pressure rise coefficient of one of the stages on the first stall section reaching the limit value, predicting that the compressor reaches the stall boundary.

2. The method according to claim 1, wherein After predicting that the compressor reaches the stall boundary, it further includes: Determining the stage with the first stage static pressure rise coefficient reaching the limit value among the stage static pressure rise coefficients of each stage on the first stall section as the first stall stage of the compressor.

3. The method according to claim 1, wherein The determining the stage static pressure rise coefficient of different blade height sections of the compressor according to the through-flow calculation result includes: For each blade height section, determining the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section according to the through-flow calculation result; Determining the stage static pressure rise coefficient of the blade height section according to the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section.

4. The method according to claim 3, wherein The stage static pressure rise coefficient of the blade height section is determined by using the following formula: Among them, c p is the specific heat at constant pressure; k is the specific heat ratio; T $T_1$ is the static temperature at the inlet of the stage; p $p_1$ is the static pressure at the inlet of the stage; p $p_2$ is the static pressure at the outlet of the stage; U $u_1$ is the circumferential velocity at the inlet of the moving blade; U $u_2$ is the circumferential velocity at the outlet of the moving blade; W 1_ef $w_1$ is the effective dynamic head velocity of the moving blade; V 1_ef $c_1$ is the effective dynamic head velocity of the stationary blade. Note: In the translation, for the sake of clarity in expressing physical quantities, some subscripts are added with dollar signs ($) in the English translation. You can adjust this according to your actual needs. Also, the specific physical quantity symbols should be determined according to the unified regulations in the relevant technical field. Here is just a general translation example.

5. The method according to any one of claims 1-4, characterized in that, The determining the first stall section from the different blade height sections according to the stage static pressure rise coefficient and diffusion factor of the different blade height sections includes: Determining the spanwise distribution of the stage static pressure rise coefficient and diffusion factor of the different blade height sections; Determining the axial distribution of the stage static pressure rise coefficient and diffusion factor of the different blade height sections; Determining the load condition of the blade height section along the spanwise distribution and the axial distribution; Selecting the blade height section whose load condition meets the set condition as the first stall section.

6. The method according to any one of claims 1 to 4, characterized in that The method further includes: Obtaining the three-dimensional computational fluid dynamics (CFD) calculation result of the compressor and determining the blade height range with the load meeting the set condition according to the CFD calculation result; Validating the effectiveness of the first stall section according to the blade height range.

7. The method according to any one of claims 1 to 4, characterized in that, The determining the limit value that the stage static pressure rise coefficient of the first stall section can reach includes: Determining the diffuser length and outlet width of the first stall section and determining the target dimensionless diffuser length according to the diffuser length and outlet width; Querying the mapping relationship between the maximum stage static pressure rise coefficient and the dimensionless diffuser length to obtain the target maximum stage static pressure rise coefficient mapped to the target dimensionless diffuser length; Determining the limit value according to the target maximum stage static pressure rise coefficient.

8. The method according to claim 7, wherein The determining the limit value according to the target maximum stage static pressure rise coefficient includes: Determining the Reynolds number, tip clearance, and blade row axial clearance corresponding to the first stall section and correcting the target maximum stage static pressure rise coefficient according to the Reynolds number, tip clearance, and blade row axial clearance to obtain the limit value.

9. The method according to any one of claims 1 to 4, characterized in that, After predicting that the compressor reaches the stall boundary, it further includes: Determining the reference stall boundary of the compressor based on the CFD calculation result of the compressor; Validating the stall boundary reached by the compressor based on the reference stall boundary.

10. The method according to any one of claims 1-4, characterized in that, Determining the stage static pressure rise coefficient and diffusion factor of different blade height sections of the compressor according to the through-flow calculation result includes: Determining the stage static pressure rise coefficient and diffusion factor of the set partial blade height sections of the compressor according to the through-flow calculation result; Performing interpolation calculation on the stage static pressure rise coefficient and diffusion factor of the partial blade height sections to obtain the stage static pressure rise coefficient and diffusion factor of different blade height sections of the compressor.

11. A stall boundary prediction device for a compressor, characterized in that, The device includes: A calculation module for performing through-flow calculation on the compressor to obtain the through-flow calculation result; A first determination module for determining the stage static pressure rise coefficient and diffusion factor of different blade height sections of the compressor according to the through-flow calculation result; A second determination module for determining the first stall section from the different blade height sections according to the stage static pressure rise coefficient and diffusion factor of the different blade height sections; A third determination module for determining the limit value that the stage static pressure rise coefficient of the first stall section can reach; A prediction module for predicting that the compressor reaches the stall boundary in response to the stage static pressure rise coefficient of one of the levels on the first stall section reaching the limit value.

12. An electronic device, characterized in that, Includes: A processor and a memory communicatively connected to the processor; The memory stores computer execution instructions; The processor executes the computer execution instructions stored in the memory to implement the method according to any one of claims 1-10.

13. A computer-readable storage medium, characterized in that, Computer execution instructions are stored in the computer-readable storage medium, and when the computer execution instructions are executed by the processor, they are used to implement the method according to any one of claims 1-10.

14. A computer program product, characterized in that, Includes a computer program, and when the computer program is executed by the processor, it implements the method according to any one of claims 1-10.

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