Compressor stall boundary prediction method, device, electronic device and storage medium

Abstract

The present application proposes a method, device, electronic device, and storage medium for predicting the stall boundary of a compressor, relating to the technical field of compressor aerodynamic design. The method comprises: performing flow calculations on the compressor to obtain flow calculation results; determining the stage static pressure lift coefficients and diffusion factors of different blade height sections of the compressor based on the flow calculation results; determining the first stall section from the different blade height sections based on the stage static pressure lift coefficients and diffusion factors of the different blade height sections; determining the limit value that the stage static pressure lift coefficient of the first stall section can reach; and predicting that the compressor has reached the stall boundary in response to the stage static pressure lift coefficient of one level on the first stall section reaching the limit value. As a result, the present solution improves the accuracy and speed of predicting the compressor stall boundary, thereby achieving rapid and accurate prediction of the compressor stall boundary.

Description

Technical Field

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

[0002] To ensure the safety of gas turbine operation, the compressor must have a sufficient stable operating range to avoid unstable operating states such as rotating stall and surge. To this end, an accurate assessment of the compressor's stall boundary is necessary. Summary of the Invention

[0003] The purpose of this application is to solve one of the technical problems in the related art at least to a certain extent.

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

[0005] The second objective of this application is to provide a stall boundary prediction device for a compressor.

[0006] The third objective of this application is to provide an electronic device.

[0007] The fourth object of this application is to provide a computer-readable storage medium.

[0008] A fifth object of this application is to provide a computer program product.

[0009] To achieve the above-mentioned purpose, a first embodiment of the present application provides a method for predicting the stall boundary of a compressor, comprising: performing a throughflow calculation on the compressor to obtain a throughflow calculation result;

[0010] Determining the stage static pressure lift coefficient and diffusion factor of the compressor at different blade height sections according to the throughflow calculation results;

[0011] Determining the first stall section from the sections with different blade heights according to the stage static pressure lift coefficient and diffusion factor of the sections with different blade heights;

[0012] Determining the limit value that the stage static pressure lift coefficient of the first-to-stall section can reach;

[0013] In response to the stage static pressure lift coefficient of one of the stages on the first-to-stall section reaching the limit value, it is predicted that the compressor reaches a stall boundary.

[0014] To achieve the above-mentioned purpose, a second embodiment of the present application provides a stall boundary prediction device for a compressor, comprising: a calculation module, configured to perform throughflow calculation on the compressor and obtain a throughflow calculation result;

[0015] A first determination module is configured to determine the stage static pressure lift coefficient and diffusion factor of the compressor at different blade height sections based on the throughflow calculation result;

[0016] A second determining module is configured to determine a first stall section from the sections with different blade heights according to the stage static pressure lift coefficient and the diffusion factor of the sections with different blade heights;

[0017] A third determining module is used to determine a limit value that the stage static pressure lift coefficient of the first stall section can reach;

[0018] The prediction module is configured to predict that the compressor has reached a stall boundary in response to the stage static lift coefficient of one of the stages on the first stall section reaching the limit value.

[0019] To achieve the above-mentioned purpose, the third aspect embodiment of the present application proposes an electronic device, comprising: 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 stall boundary prediction method of the compressor described in the first aspect embodiment above.

[0020] To achieve the above-mentioned purpose, the fourth embodiment of the present application proposes a computer-readable storage medium having a computer program stored thereon, wherein the computer instructions are used to enable the computer to execute the stall boundary prediction method for the compressor described in the first embodiment above.

[0021] To achieve the above-mentioned purpose, the fifth embodiment of the present application proposes a computer program product, including a computer program, which, when executed by a processor, implements the stall boundary prediction method of the compressor described in the first embodiment above.

[0022] The present application provides a compressor stall boundary prediction method, device, electronic device, and storage medium. By obtaining compressor flow calculation results and determining the stage static pressure rise coefficient and diffusion factor of compressor sections at different blade heights based on the flow calculation results, the first stalling section can be determined from sections at different blade heights based on the stage static pressure rise coefficient and diffusion factor. Furthermore, whether the compressor has reached the stall boundary can be predicted based on whether the stage static pressure rise coefficient on the first stalling section has reached its limit. Thus, by predicting the compressor stall boundary based on the flow calculation results, the accuracy and speed of compressor stall boundary prediction are improved, thereby enabling rapid and accurate prediction of the compressor stall boundary.

[0023] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become apparent from the description below, or will be learned through practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0025] Figure 1 A schematic flow chart of a method for predicting the stall boundary of a compressor provided in an embodiment of the present application;

[0026] Figure 2 A schematic diagram of the first stall section provided in an embodiment of the present application;

[0027] Figure 3 A schematic flow chart of another compressor stall boundary prediction method provided in an embodiment of the present application;

[0028] Figure 4 A schematic flow chart of another compressor stall boundary prediction method provided in an embodiment of the present application;

[0029] Figure 5 A schematic flow chart of another compressor stall boundary prediction method provided in an embodiment of the present application;

[0030] Figure 6 A schematic diagram of a flow chart for predicting the stall boundary of a compressor provided in an embodiment of the present application;

[0031] Figure 7 A schematic structural diagram of a stall boundary prediction device for a compressor provided in an embodiment of the present application. DETAILED DESCRIPTION

[0032] The following describes in detail embodiments of the present application, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present application, and should not be construed as limiting the present application.

[0033] The following describes a method and apparatus for predicting the stall boundary of a compressor according to an embodiment of the present application with reference to the accompanying drawings.

[0034] Figure 1 : is a flow chart of a compressor stall boundary prediction method provided in accordance with an embodiment of the present application, such as Figure 1 As shown, the stall boundary prediction method of the compressor of the embodiment of the present application includes but is not limited to the following steps:

[0035] S101, performing flow calculation on the compressor to obtain flow calculation results.

[0036] It should be noted that the compressor stall boundary prediction method provided in the embodiments of the present application is performed by an electronic device, which 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, tablet computer, laptop computer, PDA, in-vehicle electronic device, wearable device, ultra-mobile personal computer (UMPC), netbook, or personal digital assistant (PDA), while the non-mobile electronic device may be a personal computer (PC), television, etc. This embodiment of the present application does not impose any specific limitations.

[0037] It's understood that throughflow calculation is a numerical simulation method used in compressor aerodynamic design. It's used to quickly predict the flow characteristics of fluids within blade passages and the aerodynamic performance of the equipment. Throughflow calculation uses numerical simulation to determine the distribution of basic flow parameters (such as pressure, velocity, and temperature) within the axial (or radial) flow path, thereby evaluating the compressor's aerodynamic performance.

[0038] In some embodiments, the flow calculation of the compressor can be performed by numerically simulating the compressor to obtain the distribution pattern of basic flow parameters of the internal flow field of the compressor along the flow channel, and obtaining the flow calculation result based on the distribution pattern of the parameters.

[0039] For example, the flow calculation uses the streamline curvature method, incorporates a lagging angle model and a loss model, and considers radial mixing effects with a mixing model. The calculation is based on a given inlet total temperature, total pressure, and inlet direction, along with a given compressor flow rate, and approaches the stall boundary by gradually reducing the flow rate.

[0040] Optionally, the flow calculation results include, but are not limited to, characteristic parameters, distribution of flow parameters, aerodynamic performance parameters, and blade load parameters. Flow parameters include pressure parameters, temperature parameters, velocity parameters, and the like.

[0041] S102: Determine the stage static pressure lift coefficient and diffusion factor of the compressor at different blade height sections based on the flow calculation results.

[0042] In some embodiments, the stage static pressure lift coefficient for each blade height section of the compressor can be calculated based on the throughflow calculation results. Alternatively, aerodynamic parameters corresponding to each blade height section can be obtained from the throughflow calculation results, and the stage static pressure lift coefficient can be calculated based on the aerodynamic parameters.

[0043] In some embodiments, parameters related to the diffusion factor can be obtained based on the throughflow calculation results, and the diffusion factor can be calculated based on the parameters. Optionally, the diffusion factor includes the diffusion factor of the moving blade and the diffusion factor of the stationary blade.

[0044] Optionally, the density of the blades, the variation of the inlet and outlet circumferential velocities, and the relative velocities of the inlet and outlet in the throughflow calculation results may be used as parameters related to the diffusion factor.

[0045] S103, determining the first stall section from the sections with different blade heights based on the stage static pressure lift coefficient and diffusion factor of the sections with different blade heights.

[0046] In some embodiments, the load corresponding to the blade height section can be determined based on the stage static pressure rise coefficient and diffusion factor of different blade height sections, and the first stall section can be determined from the different blade height sections based on the load corresponding to the blade height section. Figure 2 Schematic diagram of the first stall section shown.

[0047] In some embodiments, the load corresponding to the blade-height section can be used to determine whether the blade-height section meets a predetermined condition, and the blade-height section that meets the predetermined condition is used as the first stall section. Alternatively, the predetermined condition can be determined based on the load. For example, a load exceeding a predetermined threshold can be used as the predetermined condition. In other words, the predetermined condition is determined to be met when the load corresponding to the blade-height section exceeds the predetermined threshold.

[0048] S104, determine the maximum value that the stage static pressure rise coefficient of the first stall section can reach.

[0049] In some embodiments, a mapping relationship between the dimensionless expansion length and the maximum stage static pressure lift coefficient can be obtained, and the mapping relationship can be queried based on the dimensionless expansion length of the first-to-stall section to determine the maximum stage static pressure lift coefficient that the first-to-stall section can achieve, and the maximum stage static pressure lift coefficient is used as the limit value.

[0050] In some embodiments, the dimensionless expansion length is the ratio of the expansion length of the blade height section to the outlet width. The expansion length and outlet width of the first-to-stall section can be determined from throughflow calculation results, and the ratio of the expansion length of the first-to-stall section to the outlet width can be further calculated to serve as the dimensionless expansion length of the first-to-stall section.

[0051] In some embodiments, in order to improve the accuracy of the limit value, the maximum stage static pressure rise coefficient may be corrected, and the corrected maximum stage static pressure rise coefficient may be used as the limit value.

[0052] Optionally, the maximum stage static pressure lift coefficient may be corrected based on the Reynolds number of the compressor, the tip clearance of the compressor blades, or the axial clearance between the compressor blade rows.

[0053] S105 , in response to the stage static pressure lift coefficient of one of the stages on the first stall section reaching a limit value, predicting that the compressor has reached a stall boundary.

[0054] In some embodiments, by obtaining the stage static pressure rise coefficient of each level on the first-to-stall section and determining whether the stage static pressure rise coefficient of each level has reached a limit value, and when the stage static pressure rise coefficient of one of the levels on the first-to-stall section reaches the limit value, it can be predicted that the compressor has reached the stall boundary.

[0055] In some embodiments, the static pressure lift coefficient of one of the levels on the first stall section reaching a limit value can also be used as a prediction condition for predicting whether the compressor has reached the stall boundary. When the first stall section meets the prediction condition, it can be predicted that the compressor has reached the stall boundary.

[0056] In the stall boundary prediction method for a compressor provided in an embodiment of the present application, by obtaining the flow calculation results of the compressor and determining the stage static pressure rise coefficient and diffusion factor of the compressor sections at different blade heights based on the flow calculation results, the first stall section can be determined from the sections at different blade heights based on the stage static pressure rise coefficient and diffusion factor. Furthermore, whether the compressor has reached the stall boundary can be predicted based on whether the stage static pressure rise coefficient on the first stall section has reached the limit value of the stage static pressure rise coefficient. Thus, the stall boundary of the compressor is predicted based on the flow calculation results, which improves the accuracy and speed of the compressor stall boundary prediction, thereby achieving a fast and accurate prediction of the compressor stall boundary.

[0057] Figure 3 : is a flow chart of a compressor stall boundary prediction method provided in accordance with an embodiment of the present application, such as Figure 3 As shown, the stall boundary prediction method of the compressor of the embodiment of the present application includes but is not limited to the following steps:

[0058] S301, performing flow calculation on the compressor to obtain flow calculation results.

[0059] In the embodiment of the present application, the implementation method of step S301 can be implemented by any method in the various embodiments of the present application, which is not limited here and will not be repeated.

[0060] 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 throughflow calculation result.

[0061] S303: Determine the stage static pressure lift coefficient of the blade height section according to characteristic parameters of the compressor and aerodynamic parameters of the blade height section.

[0062] In some embodiments, the aerodynamic parameters of each blade height section and the characteristic parameters of the compressor can be obtained from the flow calculation results, so that the stage static pressure lift 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.

[0063] Optionally, the throughflow calculation may perform numerical simulation on characteristic parameters of the compressor, obtain a characteristic curve of the compressor as a result of the throughflow calculation, and obtain the characteristic parameters of the compressor according to the characteristic curve.

[0064] Optionally, the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section include but are not limited to: constant pressure heat ratio, specific heat ratio, stage inlet static temperature, stage inlet static pressure, stage outlet static pressure, blade inlet circumferential speed, blade outlet circumferential speed.

[0065] In some embodiments, based on the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section, the stage static pressure lift coefficient of the blade height section can be determined using the following formula:

[0066]

[0067] in, C h_ef is the static pressure rise coefficient, c p is the specific heat at constant pressure, k is the specific heat ratio, T 1 is the static temperature of the inlet, p 1 is the static pressure at the inlet of the stage, p 2 is the static pressure at the stage outlet, U 1 is the circumferential speed of the moving blade inlet, U 2 is the circumferential speed of the moving blade outlet, W 1_ef is the effective dynamic pressure head velocity of the moving blade, V 1_ef is the effective dynamic head velocity of the stationary blade.

[0068] In some embodiments, W 1_ef is the effective dynamic pressure head velocity of the moving blade, which can be calculated based on the minimum possible relative velocity of the moving blade inlet and the relative velocity of the moving blade inlet. Alternatively, the effective dynamic pressure head velocity of the moving blade can be determined using the following formula: W 1_ef :

[0069]

[0070] in,W min is the minimum possible relative velocity at the rotor blade inlet, W 1 is the relative velocity at the moving blade inlet.

[0071] In some embodiments, the minimum possible relative velocity at the bucket inlet is W min It can be calculated based on the velocity triangle relationship while keeping the upstream stationary blade outlet velocity direction unchanged. Optionally, the minimum possible relative velocity at the moving blade inlet is calculated. W min The formula is as follows:

[0072]

[0073] in, α 2 is the absolute airflow angle at the stator blade outlet, β 1 is the relative airflow angle at the moving blade inlet.

[0074] In some embodiments, V 1_ef is the effective dynamic pressure head velocity of the stator blade, which can be calculated based on the minimum possible relative velocity of the stator blade inlet and the relative velocity of the stator blade inlet. Alternatively, the effective dynamic pressure head velocity of the stator blade can be determined using the following formula: V 1_ef :

[0075]

[0076] in, V min is the minimum possible relative velocity at the stator inlet, V 1 is the relative velocity at the stator inlet.

[0077] In some embodiments, the minimum possible relative velocity at the vane inlet is V min It can be calculated based on the velocity triangle relationship while keeping the upstream moving blade outlet velocity direction unchanged. Optionally, the minimum possible relative velocity at the stationary blade inlet is calculated as V min The formula is as follows:

[0078]

[0079] in, α 1 is the absolute airflow angle at the stator inlet, β 2 is the relative airflow angle at the moving blade outlet.

[0080] S304: Determine the diffusion factors of different blade height sections of the compressor based on the flow calculation results.

[0081] In some embodiments, the compressor's diffusion factors for different blade heights include the diffusion factors of moving blades and stator blades. Parameters such as the density of the moving and stator blades, the change in the circumferential velocity at the inlet and outlet of the moving and stator blades, the relative velocity of the moving blade inlet and outlet, and the absolute velocity of the stator blade inlet and outlet can be obtained from the throughflow calculation results. The diffusion factors of the moving and stator blades can be calculated based on these parameters.

[0082] Alternatively, the diffusion factor of the moving blade can be calculated using the following formula: DF r :

[0083]

[0084] in, τ r is the density of the moving blade, Δ W u is the change in the circumferential velocity of the moving blade inlet and outlet, W 1 is the relative speed at the moving blade inlet, W 2 is the relative velocity at the moving blade outlet.

[0085] Alternatively, the diffusion factor of the stationary blade can be calculated using the following formula: DF s :

[0086]

[0087] in, τ s is the density of the stationary blade, Δ V u is the change in the circumferential velocity of the stator inlet and outlet, V 1 is the absolute velocity at the stator inlet, V 2 is the absolute velocity at the stator blade outlet.

[0088] In some embodiments, the stage static pressure rise coefficient and diffusion factor of the partial blade height section set by the compressor can also be obtained, and the stage static pressure rise coefficient and diffusion factor of the set partial blade height section can be interpolated to obtain the stage static pressure rise coefficient and diffusion factor of the compressor with different blade height sections.

[0089] In some embodiments, the stage static pressure rise coefficient and diffusion factor of the partial blade height section set by the compressor can be determined based on the flow calculation results, and the stage static pressure rise coefficient and diffusion factor of the partial blade height section can be interpolated to obtain the stage static pressure rise coefficient and diffusion factor of the compressor with different blade height sections.

[0090] S305 , determining the first stall section from the sections with different blade heights based on the stage static pressure lift coefficient and the diffusion factor of the sections with different blade heights.

[0091] S306, determining the maximum value that the static pressure lift coefficient of the first-to-stall section can reach.

[0092] S307 : In response to the stage static pressure lift coefficient of one of the stages on the first stall section reaching a limit value, predicting that the compressor has reached a stall boundary.

[0093] In the embodiment of the present application, the implementation method of steps S305-S307 can be implemented by any method in the embodiments of the present application, which is not limited here and will not be repeated.

[0094] In some embodiments, after predicting that the compressor has reached a stall boundary, the first stall stage of the compressor may be determined. The first stage of the compressor to reach a limit value among the static pressure rise coefficients of the stages on the first stall section is determined as the first stall stage of the compressor.

[0095] In some embodiments, after predicting that the compressor has reached a stall boundary, the accuracy of the stall boundary may be verified. Optionally, the stall boundary may be verified using three-dimensional computational fluid dynamics (CFD).

[0096] In some embodiments, a CFD calculation is performed on the compressor to obtain CFD calculation results. A reference stall boundary of the compressor is determined based on the CFD calculation results. In other words, the stall boundary of the compressor can be determined from the CFD calculation results and used as the reference stall boundary. Thus, the stall boundary reached by the compressor can be verified based on the reference stall boundary.

[0097] Optionally, it may be verified whether there is an error between the reference stall boundary and the stall boundary reached by the compressor. If an error exists, it is determined whether the error is less than an 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, it is determined that the stall boundary reached by the compressor has passed the verification.

[0098] In the compressor stall boundary prediction method provided in the embodiments of the present application, the compressor characteristic parameters and aerodynamic parameters of the blade height section are determined from the flow calculation results. The stage static pressure lift coefficient of the blade height section is then calculated based on the characteristic parameters and aerodynamic parameters. Thus, determining the stage static pressure lift coefficient of the blade height section based on the flow calculation results provides data support for subsequent prediction of the compressor stall boundary, thereby improving the accuracy of the stall boundary prediction.

[0099] Figure 4 : is a flow chart of a compressor stall boundary prediction method provided in accordance with an embodiment of the present application, such as Figure 4As shown, the stall boundary prediction method of the compressor of the embodiment of the present application includes but is not limited to the following steps:

[0100] S401: Perform flow calculation on the compressor to obtain flow calculation results.

[0101] S402: Determine the static pressure lift coefficient and diffusion factor of the compressor stage at different blade height sections based on the flow calculation results.

[0102] In the embodiment of the present application, the implementation method of steps S401-S402 can be implemented by any method in the embodiments of the present application, which is not limited here and will not be repeated.

[0103] S403, determining the spanwise distribution of the stage static pressure lift coefficient and the diffusion factor of the sections with different blade heights.

[0104] In some embodiments, determining the spanwise distribution of the stage static pressure lift coefficient and the diffusion factor at different blade height sections refers to analyzing the variations in the stage static pressure lift coefficient and the diffusion factor at different blade height positions along the span. The spanwise direction may be the direction from the blade root to the blade tip.

[0105] In some embodiments, the spanwise distribution is obtained by obtaining the stage static pressure lift coefficient and diffusion factor of different blade height sections at different spanwise positions, and analyzing the changes in the stage static pressure lift coefficient and diffusion factor based on the stage static pressure lift coefficient and diffusion factor at different spanwise positions.

[0106] S404: Determine the axial distribution of the stage static pressure lift coefficient and diffusion factor at different blade height sections.

[0107] In some embodiments, determining the axial distribution of the stage static pressure lift coefficient and diffusion factor at different blade height sections refers to determining the variation of the stage static pressure lift coefficient and diffusion factor in the compressor axial direction, where the axial direction can be the airflow direction. For example, different axial positions from the inlet to the outlet, such as guide vanes, rotor blades, and vaneless areas, can be determined.

[0108] In some embodiments, the axial distribution is obtained by obtaining the stage static pressure rise coefficient and diffusion factor of different blade height sections at different axial positions, and analyzing the changes in the stage static pressure rise coefficient and diffusion factor based on the stage static pressure rise coefficient and diffusion factor at different axial positions.

[0109] S405 , determining the load condition of the blade height section along the spanwise distribution and the axial distribution.

[0110] In some embodiments, the load condition of the blade height cross section can be analyzed along the spanwise distribution and the axial distribution. Alternatively, a first load distribution on the blade height cross section can be determined along the spanwise distribution, and a second load distribution on the blade height cross section can be determined along the axial distribution. Thus, the load condition of the blade height cross section can be determined based on the first and second load distributions.

[0111] For example, a first load distribution on the blade height section can be determined based on mechanical parameters such as stress and strain distributed along the span direction of the blade height section. A second load distribution can be determined by obtaining a curve of load variation over time or rotation angle at different axial positions on the blade height section.

[0112] Optionally, the load magnitude of the blade height section may be determined according to the first load distribution and the second load distribution, and the load magnitude may be used as the load condition of the blade height section.

[0113] S406 , selecting a blade height section whose load condition meets the set conditions as the first stall section.

[0114] In some embodiments, a predetermined condition can be determined, and a determination can be made as to whether the load conditions of sections at different blade heights meet the predetermined condition. For example, if the load condition is a load magnitude, the load magnitude being greater than a load threshold can be used as the condition for meeting the predetermined condition. This allows a determination as to whether the load magnitudes of sections at different blade heights are greater than the load threshold, and the section at the blade height that meets the predetermined condition can be selected as the first-to-stall section.

[0115] In some embodiments, after determining the first-to-stall cross section, the validity of the first-to-stall cross section may be verified. Alternatively, a blade height range in which the load meets a set condition may be obtained, and the validity of the first-to-stall cross section may be verified based on the blade height range.

[0116] In some embodiments, CFD calculation results of the compressor are obtained, and the blade height range in which the load meets the set conditions is determined based on the CFD calculation results.

[0117] In some embodiments, the blade height position where flow separation and blockage are serious and load is high can be analyzed based on CFD calculation results, and the blade height position where flow separation and blockage are serious and load is high can be used as the blade height range where load meets the set conditions.

[0118] In some embodiments, the effectiveness of the first-to-stall section is verified according to the blade height range, which may be to determine whether the blade height position of the first-to-stall section is within the blade height range. If it is within the blade height range, the first-to-stall section is determined to be effective.

[0119] S407, determine the maximum value that the static pressure lift coefficient of the first stall section can reach.

[0120] S408 : In response to the stage static pressure lift coefficient of one of the stages on the first stall section reaching a limit value, predicting that the compressor has reached a stall boundary.

[0121] In the embodiment of the present application, the implementation method of steps S407-S408 can be implemented by any method in the embodiments of the present application, which is not limited here and will not be repeated.

[0122] In the compressor stall boundary prediction method provided in the embodiments of the present application, by determining the spanwise and axial distributions of the stage static pressure lift coefficient and expansion factor for different blade height sections, and determining the load condition of the blade height section based on the spanwise and axial distributions, the blade height section whose load condition meets the set conditions can be selected as the first stall section. Thus, by determining the first stall section based on the load condition of the blade height section, the stall boundary can be more accurately predicted based on the first stall section.

[0123] Figure 5 : is a flow chart of a compressor stall boundary prediction method provided in accordance with an embodiment of the present application, such as Figure 5 As shown, the stall boundary prediction method of the compressor of the embodiment of the present application includes but is not limited to the following steps:

[0124] S501: Perform flow calculation on the compressor to obtain flow calculation results.

[0125] S502: Determine the static pressure lift coefficient and diffusion factor of the compressor stage at different blade height sections based on the flow calculation results.

[0126] S503: Determine the first stall section from the sections with different blade heights based on the stage static pressure lift coefficient and the diffusion factor of the sections with different blade heights.

[0127] In the embodiment of the present application, steps S501-S503 can be implemented by any of the methods in the embodiments of the present application, which is not limited here and will not be described in detail.

[0128] S504 , determining the diffuser length and outlet width of the first stall section, and determining a target dimensionless diffuser length based on the diffuser length and outlet width.

[0129] S505 , querying a mapping relationship between a maximum stage static pressure rise coefficient and a dimensionless expansion length, and obtaining a target maximum stage static pressure rise coefficient that is mapped to a target dimensionless expansion length.

[0130] S506: Determine a limit value according to the target maximum stage static pressure rise coefficient.

[0131] In some embodiments, the dimensionless expansion length is the ratio of the expansion length of the blade height section to the outlet width. The expansion lengths and outlet widths of sections with different blade heights can be determined from the throughflow calculation results, thereby determining the expansion length and outlet width of the first-to-stall section. Furthermore, the target dimensionless expansion length of the first-to-stall section can be calculated based on the expansion length and outlet width.

[0132] Alternatively, the formula for calculating the dimensionless diffuser length is as follows:

[0133] L / g 2= L / ( t ·cos β 2) (8)

[0134] in, L / g 2 represents the dimensionless expansion length, L represents the expansion length, g 2 represents the outlet width. g 2= t ·cos β 2, t is the characteristic length, β 2 is the angle at the exit.

[0135] That is to say, by substituting the diffusion length and outlet width of the first stall section into the above formula (8), the target dimensionless diffusion length can be calculated.

[0136] In some embodiments, a mapping relationship between the maximum stage static pressure lift coefficient and the dimensionless diffusion length can be obtained, and based on the target dimensionless diffusion length, the mapping relationship can be queried to determine the maximum stage static pressure lift coefficient that is mapped to the target dimensionless diffusion length as the target maximum stage static pressure lift coefficient.

[0137] In some embodiments, the target maximum stage static pressure lift coefficient may be corrected to obtain a limit value to improve the accuracy of the limit value. The limit value is obtained by determining the Reynolds number, blade tip clearance, and blade row axial clearance corresponding to the first stall section, and then correcting the target maximum stage static pressure lift coefficient based on the Reynolds number, blade tip clearance, and blade row axial clearance.

[0138] Optionally, the Reynolds number, blade tip clearance, and blade row axial clearance corresponding to the first stall section may be determined from the throughflow calculation results.

[0139] S507 : In response to the stage static pressure lift coefficient of one of the stages on the first stall section reaching a limit value, predicting that the compressor has reached a stall boundary.

[0140] In the embodiment of the present application, the implementation method of step S507 can be implemented by any method in the various embodiments of the present application, which is not limited here and will not be repeated.

[0141] In the compressor stall boundary prediction method provided in the embodiments of the present application, a target dimensionless expansion length for the first-to-stall section is determined. Based on this target dimensionless expansion length, a target maximum stage static pressure rise coefficient for the first-to-stall section is determined. This target maximum stage static pressure rise coefficient is then corrected to obtain a limiting value. Thus, based on the limiting value and the stage static pressure rise coefficient, the compressor stall boundary is predicted, enabling rapid and accurate prediction of the compressor stall boundary.

[0142] Figure 6 The figure shows a flow chart for predicting the stall boundary of a compressor. By calculating the compressor flow through the compressor and determining the compressor's characteristic parameters and the aerodynamic parameters of the blade-height section based on the flow calculation results, the stage static pressure lift coefficients for sections of different blade heights are calculated. Furthermore, the diffusion factors for sections of different blade heights are determined based on the flow calculation results. The first stall section can then be determined based on the stage static pressure lift coefficients and the diffusion factors.

[0143] Optionally, the spanwise distribution of the stage static pressure lift coefficient and diffusion factor for sections at different blade heights can be analyzed, as well as the axial distribution of the stage static pressure lift coefficient and diffusion factor for sections at different blade heights. Furthermore, the load conditions of the sections at the blade heights can be determined based on the spanwise and axial distributions. The sections at the blade heights that meet the specified load conditions can then be selected as the first-to-stall sections.

[0144] Furthermore, a target dimensionless expansion length for the first-to-stall section is determined. Based on the mapping relationship between the maximum stage static pressure lift coefficient and the dimensionless expansion length, a target maximum stage static pressure lift coefficient mapped to the target dimensionless expansion length is determined, and the target maximum stage static pressure lift coefficient is corrected to obtain a limit value. A determination is made as to whether the stage static pressure lift coefficient of one of the stages on the first-to-stall section has reached the limit value. If the limit value is reached, it is predicted that the compressor has reached the stall boundary, and the stage whose static pressure lift coefficient on the first-to-stall section first reaches the limit value is determined as the first-to-stall stage of the compressor.

[0145] Corresponding to the stall boundary prediction methods for a compressor proposed in the above-mentioned embodiments, an embodiment of the present application further proposes a stall boundary prediction device for a compressor. Since the stall boundary prediction device for a compressor proposed in the embodiment of the present application corresponds to the stall boundary prediction methods for a compressor proposed in the above-mentioned embodiments, the implementation method of the stall boundary prediction method for a compressor is also applicable to the stall boundary prediction device for a compressor proposed in the embodiment of the present application, and will not be described in detail in the following embodiments.

[0146] In order to implement the above embodiment, the present application also proposes a stall boundary prediction device for a compressor.

[0147] Figure 7 A schematic structural diagram of a stall boundary prediction device for a compressor provided in an embodiment of the present application.

[0148] like Figure 7 As shown, the stall boundary prediction device 700 of the compressor includes:

[0149] A calculation module 701 is used to perform flow calculation on the compressor and obtain flow calculation results;

[0150] A first determination module 702 is configured to determine the static pressure lift coefficient and diffusion factor of the compressor stage at different blade height sections based on the throughflow calculation results;

[0151] The second determining module 703 is configured to determine the first stall section from the sections with different blade heights according to the stage static pressure lift coefficient and diffusion factor of the sections with different blade heights;

[0152] The third determining module 704 is used to determine the limit value that the stage static pressure lift coefficient of the first stall section can reach;

[0153] The prediction module 705 is configured to predict that the compressor has reached a stall boundary in response to the stage static pressure lift coefficient of one of the stages on the first stall section reaching a limit value.

[0154] In a possible implementation of the embodiment of the present application, the prediction module 705 is further configured to determine the first level of the static pressure lift coefficients of the various levels on the first stall section that reaches the limit value as the first stall level of the compressor.

[0155] In a possible implementation of an embodiment of the present application, the first determination module 702 is also used to: for each blade height section, determine the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section based on the flow calculation results; determine the stage static pressure lift coefficient of the blade height section based on the characteristic parameters of the compressor and the aerodynamic parameters of the blade height section.

[0156] In a possible implementation of the embodiment of the present application, the following formula is used to determine the stage static pressure lift coefficient of the blade height section:

[0157]

[0158] in, c p is the specific heat at constant pressure; k is the specific heat ratio; T 1 is the static temperature at the stage inlet; p 1 is the static pressure at the stage inlet; p 2 is the static pressure at the stage outlet; U1 is the circumferential speed of the moving blade inlet; U 2 is the circumferential speed of the moving blade outlet; W 1_ef is the effective dynamic head velocity of the moving blade; V 1_ef is the effective dynamic head velocity of the stationary blade.

[0159] In a possible implementation of an embodiment of the present application, the second determination module 703 is further used to: determine the spanwise distribution of the stage static pressure lift coefficient and the diffusion factor of different blade height sections; determine the axial distribution of the stage static pressure lift coefficient and the diffusion factor of different blade height sections; determine the load condition of the blade height section along the spanwise distribution and the axial distribution; and select the blade height section whose load condition meets the set conditions as the first stall section.

[0160] In a possible implementation of an embodiment of the present application, the second determination module 703 is further used to: obtain the three-dimensional computational fluid dynamics (CFD) calculation results of the compressor, and determine the blade height range in which the load meets the set conditions based on the CFD calculation results; and verify the effectiveness of the first stall section based on the blade height range.

[0161] In one possible implementation of the embodiment of the present application, the third determination module 704 is further used to: determine the diffusion length and outlet width of the first-to-stall section, and determine a target dimensionless diffusion length based on the diffusion length and outlet width; query the mapping relationship between the maximum stage static pressure lift coefficient and the dimensionless diffusion length to obtain a target maximum stage static pressure lift coefficient that is mapped to the target dimensionless diffusion length; and determine a limit value based on the target maximum stage static pressure lift coefficient.

[0162] In a possible implementation of an embodiment of the present application, the third determination module 704 is further used to: determine the Reynolds number, blade tip clearance and blade row axial clearance corresponding to the first stall section, and correct the target maximum stage static pressure lift coefficient based on the Reynolds number, blade tip clearance and blade row axial clearance to obtain a limit value.

[0163] In a possible implementation of the embodiment of the present application, the prediction module 705 is further used to: determine a reference stall boundary of the compressor based on the CFD calculation results of the compressor; and verify the stall boundary reached by the compressor based on the reference stall boundary.

[0164] In a possible implementation of an embodiment of the present application, the first determination module 702 is also used to: determine the stage static pressure rise coefficient and diffusion factor of the partial blade height section set by the compressor based on the flow calculation results; perform interpolation calculation on the stage static pressure rise coefficient and diffusion factor of the partial blade height section to obtain the stage static pressure rise coefficient and diffusion factor of different blade height sections of the compressor.

[0165] In the stall boundary prediction device for a compressor provided in an embodiment of the present application, by obtaining the flow calculation results of the compressor and determining the stage static pressure rise coefficient and diffusion factor of the compressor sections at different blade heights based on the flow calculation results, the first stall section can be determined from the sections at different blade heights based on the stage static pressure rise coefficient and diffusion factor. Furthermore, it is possible to predict whether the compressor has reached the stall boundary based on whether the stage static pressure rise coefficient on the first stall section has reached the limit value of the stage static pressure rise coefficient. Thus, the stall boundary of the compressor is predicted based on the flow calculation results, thereby improving the accuracy and speed of the prediction of the compressor stall boundary, thereby achieving a fast and accurate prediction of the compressor stall boundary.

[0166] It should be noted that the above explanation of the embodiment of the stall boundary prediction method for a compressor is also applicable to the stall boundary prediction device for a compressor in this embodiment, and will not be repeated here.

[0167] In order to implement the above embodiments, the present application also proposes an electronic device, comprising: 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 by the above embodiments.

[0168] In order to implement the above embodiments, the present application also proposes a computer-readable storage medium, in which computer-executable instructions are stored. When the computer-executable instructions are executed by a processor, they are used to implement the methods provided by the above embodiments.

[0169] In order to implement the above embodiments, the present application also proposes a computer program product, including a computer program, which implements the methods provided by the above embodiments when executed by a processor.

[0170] In the descriptions of the foregoing embodiments, the reference terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic expressions 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, those skilled in the art may combine and combine different embodiments or examples described in this specification and features of different embodiments or examples, unless they are mutually inconsistent.

[0171] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of such features. Throughout the description of this application, "plurality" means at least two, for example, two, three, etc., unless otherwise specifically defined.

[0172] Any process or method description in a flowchart or otherwise described herein may be understood to represent a module, segment or portion of code comprising one or more executable instructions for implementing the steps of a custom logical function or process, and the scope of the preferred embodiments of the present application includes alternative implementations in which functions may be performed out of the order shown or discussed, including performing functions in a substantially simultaneous manner or in the reverse order depending on the functions involved, which should be understood by those skilled in the art to which the embodiments of the present application belong.

[0173] The logic and / or steps represented in a flowchart or otherwise described herein, for example, can be considered a sequenced list of executable instructions for implementing the logical functions, and can be embodied in any computer-readable medium for use by, or in conjunction with, an instruction execution system, apparatus, or device (e.g., a computer-based system, a system including a processor, or other system that can fetch and execute instructions from an instruction execution system, apparatus, or device). For purposes of this specification, a "computer-readable medium" is any device that can contain, store, communicate, propagate, or transport a program for use by, or in conjunction with, an instruction execution system, apparatus, or device. More specific examples (not exhaustive) of computer-readable media include: an electrical connection with one or more wires (electronic devices), a portable computer disk cartridge (magnetic device), random access memory (RAM), read-only memory (ROM), erasable and programmable read-only memory (EPROM or flash memory), fiber optic devices, and a portable compact disc read-only memory (CDROM). Furthermore, the computer-readable medium may even be paper or other suitable medium on which the program is printed, since the program may be obtained electronically, for example, by optically scanning the paper or other medium and then editing, interpreting or processing it in another suitable manner if necessary, and then storing it in a computer memory.

[0174] It should be understood that various parts of this application can be implemented using hardware, software, firmware, or a combination thereof. In the above-described embodiments, multiple steps or methods can be implemented using software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented using hardware, as in another embodiment, any one of the following technologies known in the art or a combination thereof can be used: a discrete logic circuit having logic gate circuits for implementing logical functions on data signals, an application-specific integrated circuit having suitable combinational logic gate circuits, a programmable gate array (PGA), a field-programmable gate array (FPGA), etc.

[0175] Those skilled in the art will understand that all or part of the steps in the method of the above embodiment can be completed by instructing related hardware through a program, 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 embodiment.

[0176] In addition, the functional units in the various embodiments of the present application may be integrated into a processing module, or each unit may exist physically separately, or two or more units may be integrated into a module. The above-mentioned integrated module may be implemented in the form of hardware or in the form of a software functional module. If 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.

[0177] The storage medium mentioned above may be a read-only memory, a magnetic disk, or an optical disk, etc. Although the embodiments of the present application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present application. Persons skilled in the art may 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 comprises: Perform flow calculation on the compressor and obtain flow calculation results; Determining the stage static pressure lift coefficient and diffusion factor of the compressor at different blade height sections according to the throughflow calculation results; Determining the first stall section from the sections with different blade heights according to the stage static pressure lift coefficient and diffusion factor of the sections with different blade heights; Determining the limit value that the stage static pressure lift coefficient of the first-to-stall section can reach; In response to a stage static pressure lift coefficient of one of the stages on the first-to-stall section reaching the limit value, predicting that the compressor has reached a stall boundary; Determining the first stall section from the sections with different blade heights according to the stage static pressure lift coefficient and diffusion factor of the sections with different blade heights includes: Determining the spanwise distribution of the stage static pressure lift coefficient and diffusion factor for 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; Determine the load condition of the blade height section along the spanwise distribution and the axial distribution; A blade height section whose load condition meets set conditions is selected as the first stall section.

2. The method according to claim 1, characterized in that After predicting that the compressor reaches the stall boundary, the method further includes: The first level of the static pressure rise coefficients of each level on the first-stall section that reaches the limit value is determined as the first-stall level of the compressor.

3. The method according to claim 1, characterized in that Determining the stage static pressure lift coefficient of the compressor at different blade height sections based on the throughflow calculation result includes: For each blade height section, determining characteristic parameters of the compressor and aerodynamic parameters of the blade height section according to the throughflow calculation result; The stage static pressure lift coefficient of the blade height section is determined according to characteristic parameters of the compressor and aerodynamic parameters of the blade height section.

4. The method according to claim 3, characterized in that The following formula is used to determine the stage static pressure rise coefficient of the blade height section: in, c p is the specific heat at constant pressure; k is the specific heat ratio; T 1 is the static temperature at the stage inlet; p 1 is the static pressure at the stage inlet; p 2 is the static pressure at the stage outlet; U 1 is the circumferential speed of the moving blade inlet; U 2 is the circumferential speed of the moving blade outlet; W 1_ef is the effective dynamic head velocity of the moving blade; V 1_ef is the effective dynamic head velocity of the stationary blade.

5. The method according to any one of claims 1 to 4, characterized in that The method further comprises: Obtaining three-dimensional computational fluid dynamics (CFD) calculation results of the compressor, and determining a blade height range in which the load meets a set condition based on the CFD calculation results; The effectiveness of the first-to-stall cross section is verified according to the blade height range.

6. The method according to any one of claims 1 to 4, characterized in that The determination of the limit value that can be achieved by the stage static pressure lift coefficient of the first stall section includes: determining a diffusion length and an outlet width of the first-to-stall section, and determining a target dimensionless diffusion length based on the diffusion length and the outlet width; querying a mapping relationship between a maximum stage static pressure rise coefficient and a dimensionless expansion length to obtain a target maximum stage static pressure rise coefficient that is mapped to the target dimensionless expansion length; The limit value is determined according to the target maximum stage static pressure rise coefficient.

7. The method according to claim 6, characterized in that Determining the limit value according to the target maximum stage static pressure rise coefficient includes: The Reynolds number, blade tip clearance, and blade row axial clearance corresponding to the first stall section are determined, and the target maximum stage static pressure lift coefficient is corrected based on the Reynolds number, blade tip clearance, and blade row axial clearance to obtain the limit value.

8. The method according to any one of claims 1 to 4, characterized in that After predicting that the compressor reaches the stall boundary, the method further includes: determining a reference stall boundary of the compressor based on CFD calculation results of the compressor; The stall boundary reached by the compressor is verified based on the reference stall boundary.

9. The method according to any one of claims 1 to 4, characterized in that Determining the stage static pressure lift coefficient and diffusion factor of the compressor at different blade height sections based on the throughflow calculation result includes: Determining the stage static pressure lift coefficient and diffusion factor of the set partial blade height section of the compressor according to the throughflow calculation result; Interpolation calculation is performed on the stage static pressure rise coefficient and diffusion factor of the partial blade height section to obtain the stage static pressure rise coefficient and diffusion factor of the compressor section with different blade heights.

10. A compressor stall boundary prediction device, characterized in that: The device comprises: A calculation module, used to perform flow calculation on the compressor and obtain flow calculation results; A first determination module is configured to determine the stage static pressure lift coefficient and diffusion factor of the compressor at different blade height sections based on the throughflow calculation result; A second determining module is configured to determine a first stall section from the sections with different blade heights according to the stage static pressure lift coefficient and the diffusion factor of the sections with different blade heights; A third determining module is used to determine a limit value that the stage static pressure lift coefficient of the first stall section can reach; A prediction module, configured to predict that the compressor has reached a stall boundary in response to the stage static pressure lift coefficient of one of the stages on the first stall section reaching the limit value; The second determination module is used to determine the spanwise distribution of the stage static pressure lift coefficient and the 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; Determine the load condition of the blade height section along the spanwise distribution and the axial distribution; A blade height section whose load condition meets set conditions is selected as the first stall section.

11. An electronic device, characterized in that: include: 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 according to any one of claims 1 to 9.

12. A computer-readable storage medium, characterized in that The computer-readable storage medium stores computer-executable instructions, which are used to implement the method according to any one of claims 1 to 9 when executed by a processor.

13. A computer program product, characterized in that The invention comprises a computer program, which implements the method according to any one of claims 1 to 9 when being executed by a processor.

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