Compressor aerodynamic stability design method and device, electronic equipment and storage medium

Abstract

The present disclosure relates to the technical field of stability prediction, and particularly provides a compressor aerodynamic stability design method and device, electronic equipment and storage medium to solve the problem that the compressor aerodynamic stability in the design process cannot be accurately and quickly predicted in the prior art. The compressor aerodynamic stability design method comprises: obtaining physical parameters of an S2 flow surface in a target compressor, obtaining flow field parameters on a compressor meridian surface satisfying a preset condition according to the physical parameters; determining the stability of the compressor according to the flow field parameters, and obtaining structure parameters of an S1 flow surface in the compressor under the condition that the stability of the compressor satisfies a preset stability. The compressor aerodynamic stability design method, device, electronic equipment and storage medium provided by the present disclosure are used for predicting the stability of the compressor.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the technical field of stability prediction, and particularly relates to a compressor aerodynamic stability design method and device, electronic equipment and storage medium. BACKGROUND

[0002] With the continuous improvement of modern compressor load, the flow stability problem of the compressor is becoming more and more prominent, and predicting the flow stability of the compressor is a key step in the design stage of the compressor. So far, in the actual design process of the compressor, the guarantee of the stability margin of the compressor mainly depends on the empirical relationship, which is obtained by summarizing a large number of cascade and compressor experimental data. And the empirical relationship itself has great uncertainty, and the database it depends on is not suitable for modern more advanced compressors, and it relies too much on the experience of designers, and it is difficult to adapt to the fine design of modern advanced compressors. If the stability margin of the compressor cannot meet the design requirements, it will directly lead to the fact that the compressor has been designed and cannot be used.

[0003] In order to solve the problem that the stability margin of the compressor cannot meet the design requirements, the existing technology usually uses steady numerical simulation to predict the compressor instability point, but the steady numerical simulation method for predicting the flow instability of the compressor has no theoretical basis, and the error of using steady numerical simulation to predict the compressor instability point is large and small, which is difficult to estimate. This is unacceptable in engineering, and is also the root cause of the flow instability failure in the development of domestic and foreign aero-engines. In order to make up for the shortcomings of the steady numerical simulation method, the existing technology mainly uses analytical models and unsteady numerical simulation. The analytical model greatly simplifies the compressor geometry and flow details, simplifies the blade row into a disk or a half-disk, and ignores the non-uniformity of the flow through piecewise averaging. These all limit the accuracy and scope of the model prediction, and it is difficult to meet the "accuracy" requirement of the stability evaluation in the design stage. Unsteady numerical simulation has problems in the selection of turbulence model, the setting of boundary conditions, and whether to introduce initial disturbance or not. Moreover, the huge consumption of computing resources and computing time of unsteady numerical simulation is an important reason for limiting its engineering application, and it is difficult to meet the "fast" requirement of the stability evaluation in the design stage.

[0004] Therefore, how to solve the problem that the existing technology cannot accurately and quickly predict the aerodynamic stability of the compressor in the design process is one of the important problems to be solved in the field. SUMMARY

[0005] Therefore, the present disclosure provides a compressor aerodynamic stability design method and device, electronic equipment and storage medium to solve the problem that the existing technology cannot accurately and quickly predict the aerodynamic stability of the compressor in the design process.

[0006] According to one aspect of the present disclosure, a compressor aerodynamic stability design method is provided, comprising:

[0007] Obtaining physical parameters of an S2 flow surface in a target compressor, and obtaining flow field parameters on a compressor meridian surface satisfying a preset condition according to the physical parameters;

[0008] Determining the stability of the compressor according to the flow field parameters, and obtaining structure parameters of an S1 flow surface in the compressor when the stability of the compressor meets a first preset stability;

[0009] Obtaining a stability margin of the compressor according to the structure parameters, and determining a three-dimensional model of the target compressor according to the structure parameters and the flow field parameters when the stability margin of the compressor meets a preset stability margin;

[0010] After three-dimensional steady numerical simulation is performed on the three-dimensional model of the target compressor, obtaining an instability flow point of the target compressor and a stability margin corresponding to the instability flow point;

[0011] When the stability margin corresponding to the instability flow point meets a second preset condition, determining that the stability margin of the target compressor is the stability margin of the compressor, and evaluating the aerodynamic stability of the compressor according to the stability margin of the compressor, and determining design parameters of the target compressor based on the aerodynamic stability of the compressor.

[0012] In addition, the compressor aerodynamic stability design method according to one aspect of the present disclosure further comprises obtaining physical parameters of an S2 flow surface in a target compressor, and obtaining flow field parameters on a compressor meridian surface satisfying a preset condition according to the physical parameters, which comprises:

[0013] Determining flow field parameters on the S2 flow surface based on the physical parameters of the S2 flow surface;

[0014] Determining a control equation on the S2 flow surface based on the flow field parameters on the S2 flow surface;

[0015] Determining through-flow flow field parameters on the S2 flow surface in the process of solving the control equation on the S2 flow surface;

[0016] Determining the through-flow flow field parameters as the flow field parameters on the compressor meridian surface when the through-flow flow field parameters meet a preset condition.

[0017] The compressor aerodynamic stability design method according to one aspect of the present disclosure further comprises that the control equation on the S2 flow surface comprises any one of an S2 flow surface equation, a state equation, a continuity equation, a momentum equation and an energy equation.

[0018] The compressor aerodynamic stability design method according to one aspect of the present disclosure further comprises determining the stability of the compressor according to the flow field parameters, and obtaining the structural parameters of the S1 flow surface in the compressor under the condition that the stability of the compressor meets the preset stability, which comprises:

[0019] Obtaining the flow angle parameters in the compressor under the condition that the stability of the compressor meets the preset stability;

[0020] Determining the angle parameters of the S1 flow surface in the compressor based on the flow angle parameters;

[0021] Determining the structural parameters of the S1 flow surface in the compressor based on the angle parameters of the S1 flow surface.

[0022] The compressor aerodynamic stability design method according to one aspect of the present disclosure further comprises that determining the structural parameters of the S1 flow surface in the compressor based on the angle parameters of the S1 flow surface further comprises:

[0023] Determining the thickness distribution parameters of the compressor blade according to the working condition requirements of different compressors;

[0024] Determining the corresponding thickness distribution superimposed on each base element arc line in the S1 flow surface based on the thickness distribution parameters;

[0025] Determining the structural parameters of the S1 flow surface in the compressor according to the thickness distribution.

[0026] The compressor aerodynamic stability design method according to one aspect of the present disclosure further comprises that after performing three-dimensional steady numerical simulation on the three-dimensional model of the target compressor, obtaining the instability flow point of the target compressor and the stability margin corresponding to the instability flow point comprises:

[0027] Determining the three-dimensional model of the compressor based on the flow field parameters on the compressor meridian surface and the structural parameters of the S1 flow surface in the compressor;

[0028] Obtaining the three-dimensional steady flow field of the compressor under different flow points after performing three-dimensional steady numerical simulation on the three-dimensional model of the compressor;

[0029] Obtaining the instability flow point of the compressor and the stability margin corresponding to the instability flow point according to the three-dimensional steady flow field under different flow points.

[0030] The compressor aerodynamic stability design method according to one aspect of the present disclosure, under the condition that the stability margin corresponding to the instability flow point meets the second preset condition, determines that the stability margin of the target compressor is the stability margin of the compressor, and evaluates the compressor aerodynamic stability according to the stability margin of the compressor, and determining the design parameters of the target compressor based on the compressor aerodynamic stability comprises:

[0031] Obtaining the two-dimensional steady flow field under the condition of reducing the dimension of the three-dimensional steady flow field;

[0032] obtaining an instability flow point of the compressor and a stable margin corresponding to the instability flow point based on a two-dimensional steady flow field;

[0033] determining an actual stable margin of the compressor according to the stable margin corresponding to each instability flow point;

[0034] if the actual stable margin satisfies a second preset condition, determining that the stable margin of the target compressor is the stable margin of the compressor;

[0035] if the actual stable margin parameter does not satisfy the second preset condition, modifying the design parameter of the compressor until the actual stable margin parameter of the compressor satisfies the second preset condition, and determining the aerodynamic stability of the compressor;

[0036] determining the design parameter of the target compressor based on the aerodynamic stability of the compressor.

[0037] According to another aspect of the present disclosure, there is provided a compressor aerodynamic stability prediction device applied to the compressor aerodynamic stability design method provided in the first aspect, the device comprising: a first obtaining module configured to obtain physical parameters of an S2 flow surface in a target compressor, and obtain flow field parameters on a compressor meridian surface satisfying a first preset condition according to the physical parameters; a second obtaining module configured to determine a stability of the compressor according to the flow field parameters, and obtain structure parameters of an S1 flow surface in the compressor in a case where the stability of the compressor satisfies a preset stability; a first determining module configured to obtain a stable margin of the compressor according to the structure parameters, and determine a three-dimensional model of the target compressor according to the structure parameters and the flow field parameters in a case where the stable margin of the compressor satisfies a preset stable margin; a third obtaining module configured to obtain an instability flow point of the target compressor and a stable margin corresponding to the instability flow point after performing three-dimensional steady numerical simulation on the three-dimensional model of the target compressor; and a fourth obtaining module configured to determine that the stable margin of the target compressor is the stable margin of the compressor in a case where the stable margin corresponding to the instability flow point satisfies a second preset condition, and predict the aerodynamic stability of the compressor according to the stable margin of the compressor, and determine the design parameter of the target compressor based on the aerodynamic stability of the compressor.

[0038] According to yet another aspect of the present disclosure, there is provided an electronic device comprising at least one processor, and a memory for storing at least one processor-executable instruction, wherein the at least one processor is configured to execute the instructions to implement the steps of the compressor aerodynamic stability design method.

[0039] According to yet another aspect of the present disclosure, there is provided a computer-readable storage medium, which, when instructions in the computer-readable storage medium are executed by a processor of an electronic device, enables the electronic device to perform the steps of the compressor aerodynamic stability design method.

[0040] The at least one technical scheme adopted by the embodiments of the present disclosure can achieve the following beneficial effects: the physical parameters of the S2 flow surface in the compressor of the target compressor are obtained, the flow field parameters on the meridian surface of the compressor satisfying the first preset condition are obtained according to the physical parameters, the stability of the compressor is determined according to the flow field parameters, the structural parameters of the S1 flow surface in the compressor are obtained in the case that the stability of the compressor satisfies the preset stability, the stability margin of the compressor is obtained according to the structural parameters, the three-dimensional model of the target compressor is determined according to the structural parameters and the flow field parameters in the case that the stability margin of the compressor satisfies the preset stability margin, and the instability flow point of the target compressor and the stability margin corresponding to the instability flow point are obtained after the three-dimensional steady numerical simulation of the three-dimensional model of the target compressor. On this basis, the compressor aerodynamic stability design method of the present application can ensure the stability margin of the compressor in the design stage, thereby reducing the problem that the stability margin of the compressor in the design stage does not meet the standard. At the same time, the above method integrates the parameter acquisition of the compressor and the prediction of the compressor aerodynamic stability into one, determines the stability margin of the target compressor as the stability margin of the compressor in the case that the stability margin corresponding to the instability flow point meets the second preset condition, evaluates the compressor aerodynamic stability according to the stability margin of the compressor, determines the design parameters of the target compressor based on the compressor aerodynamic stability, can quickly improve the accuracy of predicting the compressor aerodynamic stability, and significantly improves the compressor aerodynamic stability compared with the prediction method in the original design system, thereby effectively solving the problem that the compressor aerodynamic stability in the design process cannot be accurately and quickly predicted in the prior art. BRIEF DESCRIPTION OF DRAWINGS

[0041] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are only some embodiments of the present disclosure, and other drawings can also be obtained by those skilled in the art without any creative effort.

[0042] Figure 1 FIG. 1 is a schematic diagram illustrating the flow of the compressor aerodynamic stability design method according to the embodiments of the present disclosure;

[0043] Figure 2 FIG. 2 is a flow chart illustrating the acquisition of the flow field parameters on the meridian surface of the compressor according to the embodiments of the present disclosure;

[0044] Figure 3 FIG. 3 is a flow chart further illustrating the acquisition of the structural parameters of the S1 flow surface in the compressor according to the embodiments of the present disclosure;

[0045] Figure 4 FIG. 4 is a flow chart further illustrating the determination of the structural parameters of the S1 flow surface in the compressor according to the thickness distribution according to the embodiments of the present disclosure;

[0046] Figure 5 FIG. 2 is a flowchart further illustrating obtaining an unstable flow point of a target compressor and a stability margin corresponding to the unstable flow point according to an embodiment of the present disclosure;

[0047] Figure 6 FIG. 3 is a schematic diagram of a compressor test rig with a detachable rotor disc according to an embodiment of the present disclosure;

[0048] Figure 7 FIG. 4 is a structural diagram of the detachable rotor disc according to an embodiment of the present disclosure;

[0049] Figure 8 FIG. 5 is a structural diagram of a front-loaded blade of the detachable rotor disc according to an embodiment of the present disclosure;

[0050] Figure 9 FIG. 6 is a structural diagram of a uniformly-loaded blade of the detachable rotor disc according to an embodiment of the present disclosure;

[0051] Figure 10 FIG. 7 is a structural diagram of a rear-loaded blade of the detachable rotor disc according to an embodiment of the present disclosure;

[0052] Figure 11 FIG. 8 is a result diagram of unstable points of a front-loaded blade compressor, a uniformly-loaded blade compressor, and a rear-loaded blade compressor according to an embodiment of the present disclosure;

[0053] Figure 12 FIG. 9 is a result diagram of unstable points of a front-loaded blade compressor, a uniformly-loaded blade compressor, and a rear-loaded blade compressor according to an embodiment of the present disclosure;

[0054] Figure 13 FIG. 10 is a result diagram of unstable points of a front-loaded blade compressor, a uniformly-loaded blade compressor, and a rear-loaded blade compressor according to an embodiment of the present disclosure;

[0055] Figure 14 FIG. 11 is a structural schematic diagram of a compressor aerodynamic stability prediction device according to an embodiment of the present disclosure;

[0056] Figure 15 FIG. 12 is a structural schematic diagram of an electronic device according to an embodiment of the present disclosure;

[0057] Figure 16 FIG. 13 is a structural schematic diagram of a computer system according to an embodiment of the present disclosure.

[0058] Reference Signs:

[0059] 601 - rotor, 602 - stator, 603 - vane, 604 - motor. DETAILED DESCRIPTION

[0060] Embodiments of the present disclosure will be described in more detail with reference to the drawings. While certain embodiments of the present disclosure are shown in the drawings, it is understood that the present disclosure can be embodied in various forms and should not be interpreted as being limited to the embodiments set forth herein; rather, these embodiments are provided so that the present disclosure can be more thoroughly and completely understood. It should be understood that the drawings of the present disclosure are only for illustrative purposes and are not intended to limit the scope of protection of the present disclosure.

[0061] It should be understood that each step recited in the method embodiments of the present disclosure can be executed in different order and / or in parallel. In addition, the method embodiments can include additional steps and / or omit the steps shown. The scope of the present disclosure is not limited in this respect.

[0062] The term "comprising" and variations thereof as used herein are open-ended, and mean "including but not limited to". The term "based on" means "based, at least in part, on". The term "one embodiment" means "at least one embodiment". The term "another embodiment" means "at least one additional embodiment". The term "some embodiments" means "at least some embodiments". Related terms are defined as follows. It should be noted that reference herein to "first", "second" and the like concepts only serve to distinguish different apparatuses, modules or units, and are not intended to limit the order or interdependence of the functions performed by these apparatuses, modules or units.

[0063] It should be noted that the terms "one", "multiple" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that, unless otherwise explicitly indicated in the context, it should be understood as "one or more".

[0064] The names of the messages or information exchanged between the plurality of apparatuses in the embodiments of the present disclosure are only for illustrative purposes, and are not intended to limit the scope of the messages or information.

[0065] With the continuous increase of modern compressor load, the compressor flow stability problem is more and more prominent, and the prediction of the flow stability of the compressor is a key step in the design stage of the compressor. So far, in the actual design process of the compressor, the guarantee of the stability margin of the compressor mainly depends on the empirical relationship, which is obtained by summarizing a large number of cascade and compressor experimental data. And the empirical relationship itself has great uncertainty, and the database it depends on is not suitable for modern more advanced compressors, and it is difficult to adapt to the fine design of modern advanced compressors, and once the stability margin of the compressor cannot meet the design requirements, it will directly lead to the fact that the compressor has been designed and cannot be used.

[0066] In order to solve the problem that the stability margin of the compressor cannot meet the design requirements, the existing technology usually uses steady numerical simulation to predict the compressor instability point, but the steady numerical simulation method for predicting the flow instability of the compressor has no theoretical basis, and the error of predicting the compressor instability point by using the steady numerical simulation is large and small, which is difficult to estimate, which is unacceptable in engineering, and is the fundamental reason for the flow instability failure in the development of domestic and foreign aero-engines. In order to make up for the deficiency of the steady numerical simulation method, the existing technology mainly uses analytical model and unsteady numerical simulation, the analytical model greatly simplifies the compressor geometry and flow details, simplifies the blade row into a disk or a half-disk, and ignores the non-uniformity of the flow by piecewise averaging, which limits the prediction accuracy and application range of the model, and it is difficult to meet the "accuracy" requirement of the stability evaluation in the design stage. There are problems in the selection of turbulence model, the setting of boundary conditions and whether initial disturbance needs to be introduced in the unsteady numerical simulation, and the huge consumption of calculation resources and calculation time in the unsteady numerical simulation is an important reason for limiting its engineering application, which is difficult to meet the "fast" requirement of the stability evaluation in the design stage.

[0067] In view of the above problems, the present disclosure exemplary embodiments provide a compressor aerodynamic stability design method, device, electronic equipment and storage medium to solve the problem that the compressor aerodynamic stability cannot be accurately and quickly predicted in the design process in the prior art.

[0068] A compressor aerodynamic stability design method according to an embodiment of the present disclosure will be described in detail below with reference to the accompanying drawings.

[0069] Figure 1 The schematic diagram of the flow of the compressor aerodynamic stability design method according to the embodiment of the present disclosure is shown in the figure. As shown in the figure, the compressor aerodynamic stability design method comprises the following steps: Figure 1

[0070] ​S101: Obtain the physical parameters of the S2 flow surface in the target compressor, and obtain the flow field parameters on the meridian plane of the compressor satisfying a first preset condition according to the physical parameters. It can be understood that the first preset condition is a preset flow rate, a preset pressure ratio and a preset efficiency in the compressor.

[0071] S102: Determine the stability of the compressor according to the flow field parameters, and obtain the structure parameters of the S1 flow surface in the compressor when the stability of the compressor meets a preset stability.

[0072] S103: Obtain the stability margin of the compressor according to the structure parameters, and determine the three-dimensional model of the target compressor according to the structure parameters and the flow field parameters when the stability margin of the compressor meets a preset stability margin.

[0073] S104: After three-dimensional steady numerical simulation is performed on the three-dimensional model of the target compressor, obtain the instability flow point of the target compressor and the stability margin corresponding to the instability flow point.

[0074] S105: When the stability margin corresponding to the instability flow point meets a second preset condition, determine that the stability margin of the target compressor is the stability margin of the compressor, evaluate the aerodynamic stability of the compressor according to the stability margin of the compressor, and determine the design parameters of the target compressor based on the aerodynamic stability of the compressor. It can be understood that the second preset condition is a preset flow rate, a preset pressure ratio, a preset efficiency and a preset stability margin.

[0075] The physical parameters of the S2 flow surface in the compressor of the target compressor are acquired, the flow field parameters on the compressor meridian surface satisfying a first preset condition are acquired according to the physical parameters, the stability of the compressor is determined according to the flow field parameters, the structure parameters of the S1 flow surface in the compressor are acquired in the case that the stability of the compressor satisfies a preset stability, the three-dimensional model of the target compressor is determined according to the structure parameters and the flow field parameters in the case that the stability margin of the compressor satisfies a preset stability margin, and the instability flow point of the target compressor and the stability margin corresponding to the instability flow point are acquired after three-dimensional steady numerical simulation is performed on the three-dimensional model of the target compressor. On this basis, the compressor aerodynamic stability design method can guarantee the stability margin of the compressor in the design stage, reduces the problem that the stability margin does not meet the standard in the design stage of the compressor, and integrates the parameter acquisition of the compressor and the prediction of the compressor aerodynamic stability into one, determines the stability margin of the target compressor as the stability margin of the compressor in the case that the stability margin corresponding to the instability flow point satisfies a second preset condition, evaluates the compressor aerodynamic stability according to the stability margin of the compressor, determines the design parameters of the target compressor based on the compressor aerodynamic stability, can quickly improve the accuracy of predicting the compressor aerodynamic stability, obviously improves the prediction method of the compressor aerodynamic stability in the original design system, and effectively solves the problem that the compressor aerodynamic stability in the design process cannot be accurately and quickly predicted in the prior art.

[0076] Figure 2 is a flow chart illustrating acquisition of the flow field parameters on the compressor meridian surface according to an embodiment of the present disclosure, as Figure 2 shown, preferably, the physical parameters of the S2 flow surface in the compressor of the target compressor are acquired, the flow field parameters on the compressor meridian surface satisfying a preset condition are acquired according to the physical parameters, and the flow field parameters on the compressor meridian surface satisfying a preset condition are acquired according to the physical parameters.

[0077] S201: determining the flow field parameters on the S2 flow surface based on the physical parameters of the S2 flow surface;

[0078] S202: determining the control equation on the S2 flow surface based on the flow field parameters on the S2 flow surface;

[0079] S203: determining the through-flow flow field parameters on the S2 flow surface in the process of solving the control equation on the S2 flow surface;

[0080] S204: determining the through-flow flow field parameters as the flow field parameters on the compressor meridian surface in the case that the through-flow flow field parameters satisfy a preset condition.

[0081] Exemplarily, the control equation on the S2 flow surface includes any one of the S2 flow surface equation, the state equation, the continuity equation, the momentum equation and the energy equation.

[0082] In practical applications, the control equations on the S2 stream surface are mainly established by the center stream surface method. The so-called center stream surface is an S2 stream surface located in the middle of adjacent blades, and the flow field parameters on the S2 stream surface represent the circumferential average flow field of the current blade passage. The control equations for solving the through-flow calculation are shown below, mainly including the S2 stream surface equation, the state equation, the continuity equation, the momentum equation and the energy equation.

[0083] The S2 stream surface equation is as follows:

[0084] The spatial coordinates on the S2 stream surface satisfy θ=θ(r,z), wherein r, θ and z represent the radial, circumferential and axial coordinates in the cylindrical coordinate system, respectively, and the geometric relationship satisfied by the spatial coordinates on the S2 stream surface is shown. The unit normal vector of any point on the S2 stream surface is denoted as k=(k r ,kθ,k z ), and the relative velocity W of the airflow on the S2 stream surface satisfies k·W=0, that is, k r W r +k θ W θ +k z W z =0, wherein W r represents the component of the relative velocity in the radial direction, W θ represents the component of the relative velocity in the circumferential direction, and W z represents the component of the relative velocity in the axial direction. The above S2 stream surface equation illustrates the relationship between the geometric parameters and the physical parameters, and provides a geometric constraint condition for the physical parameters.

[0085] The state equation is as follows:

[0086] The flow working medium satisfies the ideal gas state equation, that is, p=ρR g T, wherein p represents the static pressure, ρ represents the ideal gas density, T represents the static temperature, and R g represents the gas constant.

[0087] The continuity equation is as follows:

[0088] The continuity equation of the steady flow in the relative coordinate system can be written as

[0089] The momentum equation is as follows:

[0090] The inviscid momentum equation of the steady flow in the relative coordinate system can be written as wherein ω represents the angular velocity vector, and the unit is rad / s.

[0091] The energy equation is as follows:

[0092] The energy equation of the inviscid steady adiabatic flow in the relative coordinate system is i.e. wherein, represents the rotor enthalpy, h represents the static enthalpy, and Ω represents the rotating speed, with the unit of r / min.

[0093] The control equations on the S2 flow surface are all based on the assumption of no viscosity, and in order to consider the viscous loss, the entropy increase along the streamline also needs to be considered. By giving the design parameters and solving the above five equations simultaneously, the through-flow design can be completed, and the through-flow flow field on the S2 flow surface can be obtained.

[0094] Exemplarily, Figure 3 is a flowchart further illustrating the process of obtaining the structural parameters of the S1 flow surface in the compressor according to the embodiments of the present disclosure, as Figure 3 shown, the stability of the compressor is determined according to the flow field parameters, and in the case that the stability of the compressor meets the preset stability, the structural parameters of the S1 flow surface in the compressor include:

[0095] S301: obtaining the flow angle parameters in the compressor in the case that the stability of the compressor meets the preset stability;

[0096] S302: determining the angle parameters of the S1 flow surface in the compressor based on the flow angle parameters, it should be understood that the above-mentioned flow angle parameters are the flow angle distribution of each spanwise position element from the leading edge to the trailing edge (for the rotor, it is the relative flow angle, and for the stator, it is the absolute flow angle).

[0097] S303: determining the structural parameters of the S1 flow surface in the compressor based on the angle parameters of the S1 flow surface, it should be understood that the above-mentioned angle parameters of the S1 flow surface are the flow angle distribution of each spanwise position element from the leading edge to the trailing edge, the leading edge angle of attack of each element, the trailing edge lag angle and the internal deorbit angle of the blade.

[0098] Exemplarily, Figure 4 is a flowchart further illustrating the process of determining the structural parameters of the S1 flow surface in the compressor according to the thickness distribution according to the embodiments of the present disclosure, as Figure 4 shown, determining the structural parameters of the S1 flow surface in the compressor blade based on the angle parameters of the S1 flow surface further includes:

[0099] S401: determining the thickness distribution parameters of the compressor blade according to the working condition requirements of different compressor blades. In actual application, the thickness distribution parameters of the corresponding classical blade profile are directly used according to the working condition requirements of the blade profile, for example: C4 blade profile, BC6 blade profile and NACA65 blade profile, in addition, by giving the front and rear small circle radii, the maximum thickness of the blade profile and the relative position of the maximum thickness, the thickness distribution of each element blade profile is constructed by a cubic polynomial.

[0100] S402: superimpose the thickness distribution on the camber line in each base element to obtain the base element airfoil at each spanwise position based on the thickness distribution parameter in the S1 flow surface. That is, after the camber line and the thickness distribution are determined, the corresponding thickness distribution is superimposed on the camber line in each base element to obtain the base element airfoil at each spanwise position.

[0101] S403: determine the structural parameters of the S1 flow surface in the compressor according to the thickness distribution. It can be understood that after the base element airfoil is obtained, the three-dimensional blade can be obtained by spanwise stacking according to the centroid or the leading edge / trailing edge given the stacking axis and its reference point. Finally, the structural parameters of the S1 flow surface are determined based on the three-dimensional blade.

[0102] Exemplarily, Figure 5 is a flowchart further illustrating the process of obtaining the instability flow point of the target compressor and the stability margin corresponding to the instability flow point according to an embodiment of the present disclosure, as Figure 5 shown, after the three-dimensional steady numerical simulation of the three-dimensional model of the target compressor, obtaining the instability flow point of the target compressor and the stability margin corresponding to the instability flow point comprises:

[0103] S501: determine the three-dimensional model of the compressor based on the flow field parameters on the compressor meridional plane and the structural parameters of the S1 flow surface in the compressor.

[0104] S502: obtain the three-dimensional steady flow field of the compressor at different flow points after the three-dimensional steady numerical simulation of the three-dimensional model of the compressor. It should be understood that after the three-dimensional steady numerical simulation of the three-dimensional model of the compressor, the three-dimensional steady flow field of the compressor at different flow points is obtained, and whether the compressor meets the preset conditions, such as flow rate, pressure ratio, and efficiency, is determined according to the three-dimensional steady flow field at different flow points.

[0105] S503: obtain the instability flow point of the compressor and the stability margin corresponding to the instability flow point according to the three-dimensional steady flow field at different flow points.

[0106] For example, when the stability margin corresponding to the unstable flow point meets the second preset condition, the stability margin of the target compressor is determined as the stability margin of the compressor, and the aerodynamic stability of the compressor is evaluated based on the stability margin of the compressor. Determining the design parameters of the target compressor based on the compressor aerodynamic stability includes: obtaining a two-dimensional steady flow field after dimensionality reduction of the three-dimensional steady flow field; obtaining the unstable flow point of the compressor and the stability margin corresponding to the unstable flow point based on the two-dimensional steady flow field; determining the actual stability margin of the compressor based on the stability margin corresponding to each unstable flow point; if the actual stability margin meets the second preset condition, determining the stability margin of the target compressor as the stability margin of the compressor; if the actual stability margin parameter does not meet the second preset condition, modifying the design parameters of the compressor until the actual stability margin parameter of the compressor meets the second preset condition, and determining the compressor aerodynamic stability; and determining the design parameters of the target compressor based on the compressor aerodynamic stability.

[0107] In practical applications, the surface boundary of a fluid can be replaced by distributed force source terms. Therefore, by removing the blade geometry inside the compressor and introducing distributed blade force source terms, the master governing equations satisfied by the flow inside the entire compressor in a stationary coordinate system can be constructed:

[0108]

[0109] Where f is the blade force vector per unit flow rate, V is the velocity vector, and π is the second-order stress tensor containing normal and shear stresses, expressed as: μ is the dynamic viscosity coefficient, I is the third-order identity matrix, and e is the internal energy, under the ideal gas assumption. γ is the specific heat ratio, which is generally taken as 1.40 for room temperature air under constant specific heat capacity conditions. ρf·V is the work done by the blade force. Indicates heat conduction, This represents heat generation; under the adiabatic assumption, both heat conduction and heat generation are zero.

[0110] When performing stability analysis on a compressor, it is necessary to reasonably reduce the dimensionality of the aforementioned governing equations. During the compressor aerodynamic design phase, the inlet flow is uniform, and the compressor geometry is periodic in the circumferential direction. Therefore, considering the assumption of circumferentially uniform fluid flow, only the axial and radial flow nonuniformity is considered in the governing equations. The influence of circumferential nonuniformity in the blade region is then considered in the blade force source term. Ignoring heat conduction and heat generation, and removing the viscous shear stress term, combined with the ideal gas law, the aforementioned governing equations can be expanded in cylindrical coordinates as follows:

[0111]

[0112] In the formula, fr represents the radial component of the blade force, f θ represents the circumferential component of the blade force and f z represents the axial component of the blade force, u is the radial component of the flow velocity in the stationary coordinate system, v is the circumferential component of the flow velocity in the stationary coordinate system, w is the axial component of the flow velocity in the stationary coordinate system, Ω is the rotational speed of the rotor, and f θ πΩr / 30 represents the work done by the blade force, h * is the stagnation enthalpy, and its expression under the ideal gas assumption is

[0113] For example, since the stall inception phase of the compressor is concerned, a linear stability analysis method can be used to write the transient quantity q of the flow parameter as the sum of the time-averaged quantity and the unsteady small perturbation quantity q', that is:

[0114]

[0115] In the formula, r represents the radial coordinate in the cylindrical coordinate system, θ represents the circumferential coordinate in the cylindrical coordinate system, and z represents the axial coordinate in the cylindrical coordinate system, and q represents any physical parameter ρ, u, v, w, p, f r , f θ , and f z .

[0116] Since the flow field is assumed to be circumferentially uniform, each order of the circumferential mode of the perturbation quantity can be regarded as decoupled, and the perturbation quantity is Fourier expanded in time and circumferentially, that is:

[0117]

[0118] In the formula, ω represents a complex eigenvalue, m c is the circumferential wave number of the perturbation quantity.

[0119] The blade force source term acts to depict the influence of the blade geometry on the flow field, and thus it is often expressed as a function of the local flow parameters in the blade force modeling process, that is, f = f(ρ, u, v, w, p). The perturbation quantity of the blade force can be represented by a first-order Taylor expansion. Considering that the blade force cannot change instantaneously with the local flow field parameters, but needs a certain response time, a first-order delay equation is introduced on the basis of the first-order Taylor expansion to represent the size of the blade force perturbation quantity, that is:

[0120]

[0121] In the formula, τ is the delay time, which is equivalent to the time of the flow passing through the blade passage.

[0122] Subtracting the zero-order equation satisfied by the steady background flow, ignoring the second-order and higher-order small quantities, and rearranging, the control equation in matrix form is obtained:

[0123]

[0124] In the formula, A, B, C, E, G and F are all 5-order coefficient matrices composed of the time average of the background flow and the spatial partial derivative thereof, the F matrix is composed of the blade force source term, and the specific expression thereof depends on the specific form of the blade force model f = f (p, u, v, w, p) established. There are many ways to model the blade, and the present application does not specify a specific blade force model. In addition, appropriate boundary conditions are supplemented on the inlet and outlet boundaries and the wall boundaries, which are reflected in the above coefficient matrix, so that the established compressor flow stability prediction method conforms to the current physical problem.

[0125] On this basis, the singular value decomposition method SVD or the generalized eigenvalue theory method is used to solve the control equation in the above matrix form to obtain the system eigenvalue ω. Through Fourier expansion of the disturbance in time and circumferential direction, it can be seen that the imaginary part of the eigenvalue directly reflects the evolution trend of the disturbance with time: if the imaginary part is greater than zero, the disturbance grows with time until the system is unstable, and therefore the system is unstable; if the imaginary part is less than zero, the disturbance decays with time until it disappears, and at this time the system is stable. Therefore, according to the positive and negative of the imaginary part of the eigenvalue obtained by solving, it can be judged whether the current compressor flow state is stable.

[0126] For example, in order to judge whether the compressor stability and stability margin meet the requirements, the above compressor aerodynamic stability design method is verified by the following experiment, Figure 6 is a further schematic diagram of a compressor test bench with a detachable rotor blade disc according to an embodiment of the present disclosure, as Figure 6 shown, the above compressor test bench includes a row of rotor 601 blades and a row of stator 602 blades, wherein the row of rotor 601 blades is connected with a motor 604, in order to support the test bench to maintain the original shape during the experiment, a support plate 603 is also provided near the outlet of the row of stator 602 blades. Figure 7 is a further structural diagram of a detachable rotor blade disc according to an embodiment of the present disclosure, Figure 8 is a further structural diagram of a detachable rotor blade disc according to an embodiment of the present disclosure, Figure 9 is a further structural diagram of a detachable rotor blade disc according to an embodiment of the present disclosure, Figure 10 is a further structural diagram of a detachable rotor blade disc according to an embodiment of the present disclosure, as Figures 7 to 10It can be seen that the above three loading modes of the detachable rotor blade are front-loaded blades, uniformly loaded blades and rear-loaded blades. It should be noted that the stator blades are unchanged, i.e. the rotor blades of the three loading modes and the same stator blades constitute three different compressors.

[0127] Figure 11 is a further illustration of the instability point result diagram of the front-loaded blade form compressor, the uniformly loaded blade form compressor and the rear-loaded blade form compressor of the detachable rotor blade according to the embodiment of the present disclosure using the method of the present disclosure, Figure 12 is a further illustration of the instability point result diagram of the front-loaded blade form compressor, the uniformly loaded blade form compressor and the rear-loaded blade form compressor of the detachable rotor blade according to the embodiment of the present disclosure using the traditional constant value simulation method, Figure 13 is a further illustration of the instability point result diagram of the front-loaded blade form compressor, the uniformly loaded blade form compressor and the rear-loaded blade form compressor of the detachable rotor blade according to the embodiment of the present disclosure using the experimental method, as shown in Figures 11 to 13 , wherein 1 represents the front-loaded blade form compressor, 2 represents the uniformly loaded blade form compressor, and 3 represents the rear-loaded blade form compressor. The abscissa flow rate (kg / s) represents different flow rate points of the compressor, and the ordinate is the characteristic value imaginary part. The imaginary part less than 0 indicates that the compressor flow is stable, and the imaginary part greater than 0 indicates that the compressor flow is unstable. From the large flow point to the small flow point, the working condition changes are the throttling processes of the compressor. It can be seen that in the process, the characteristic value experiences a process from less than 0 to greater than 0, that is, the compressor flow experiences a process from stable to unstable, and the flow point corresponding to the characteristic value equal to 0 is the instability flow point of the compressor predicted by the compressor flow stability prediction method of the present application. From Figure 11 It can be seen that the instability flow points of the front-loaded, uniformly loaded and rear-loaded three compressors predicted by the above method are 5.01 kg / s, 5.17 kg / s and 5.34 kg / s, respectively.

[0128] Figure 12 is the calculation result of the traditional constant value simulation method. The abscissa flow rate (kg / s) represents different flow rate points of the compressor, and the ordinate static pressure rise coefficient is the pressure increase capacity index of the compressor. Each compressor corresponds to a characteristic line, and the minimum flow point is the instability point of the compressor calculated by the method, which is the last converged flow point before the constant value simulation diverges. From Figure 12 It can be seen that the instability flow points of the front-loaded, uniformly loaded and rear-loaded three compressors calculated by the constant value simulation method are 4.88 kg / s, 4.90 kg / s and 5.15 kg / s, respectively. Figure 13is the experimental test result. It can be seen that the experimental measured unstable flow points of the three compressors under the front loading, uniform loading and rear loading are 5.07 kg / s, 5.18 kg / s and 5.38 kg / s respectively.

[0129] By comparing the unstable points of the compressors in the above Figures 11 to 13 , taking the experimental measured unstable flow points of the three compressors as the benchmark, the relative error of the unstable points of the compressors calculated by the steady numerical simulation method.

[0130] Table 1 Relative error of unstable points of compressors obtained by steady simulation method

[0131]

[0132] Table 2 is the relative error of the unstable points of the compressors evaluated by the compressor flow stability prediction method of the present application, taking the experimental measured unstable flow points of the three compressors as the benchmark.

[0133] Table 2 Relative error of unstable points of compressors obtained by compressor aerodynamic stability design method

[0134]

[0135] Comparing Table 1 and Table 2, it can be seen that the calculation error of the traditional steady numerical simulation method is > 5%, which does not meet the precision requirement of error ≤ 5 required in engineering; the evaluation error of the compressor aerodynamic stability design method is < 1.5%, which completely meets the engineering needs, and the reliability of the compressor aerodynamic stability design method of the present application can be proved by the above experiments.

[0136] In the case of dividing each functional module corresponding to each function, the present application exemplary embodiment provides a compressor aerodynamic stability prediction device, which can be a server or a chip applied to a server. Figure 14 Further, the structure schematic diagram of the compressor aerodynamic stability prediction device according to the embodiment of the present application is illustrated. As shown in Figure 14 , the compressor aerodynamic stability prediction device 1400 comprises:

[0137] The first acquisition module 1401 acquires the physical parameters of the S2 flow surface in the target compressor, and acquires the flow field parameters on the compressor meridian surface satisfying the first preset condition according to the physical parameters;

[0138] The second acquisition module 1402 determines the stability of the compressor according to the flow field parameters, and acquires the structure parameters of the S1 flow surface in the compressor under the condition that the stability of the compressor satisfies the preset stability;

[0139] The first determining module 1403 obtains the stability margin of the compressor based on the structural parameters. If the stability margin of the compressor meets the preset stability margin, it determines the three-dimensional model of the target compressor based on the structural parameters and the flow field parameters.

[0140] The third acquisition module 1404, after performing a three-dimensional steady-state numerical simulation on the three-dimensional model of the target compressor, acquires the unstable flow point of the target compressor and the stability margin corresponding to the unstable flow point.

[0141] The fourth acquisition module 1405 determines the stability margin of the target compressor as the stability margin of the compressor when the stability margin corresponding to the unstable flow point meets the second preset condition, evaluates the aerodynamic stability of the compressor based on the stability margin of the compressor, and determines the design parameters of the target compressor based on the aerodynamic stability of the compressor.

[0142] Figure 15 Further illustrations show schematic diagrams of the structure of an electronic device according to embodiments of the present disclosure. For example... Figure 15 As shown, the electronic device 1500 includes at least one processor 1501 and a memory 1502 coupled to the processor 1501. The processor 1501 can perform the corresponding steps in the methods disclosed in the embodiments of this disclosure.

[0143] The processor 1501 described above can also be referred to as a Central Processing Unit (CPU), which can be an integrated circuit chip with signal processing capabilities. Each step in the method disclosed in this embodiment can be implemented by the integrated logic circuitry in the hardware of the processor 1501 or by instructions in software form. The processor 1501 can be a general-purpose processor, a digital signal processor (DSP), an ASIC, a field-programmable gate array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components. The general-purpose processor can be a microprocessor or any conventional processor. The steps of the method disclosed in this embodiment can be directly implemented by a hardware decoding processor, or implemented by a combination of hardware and software modules in the decoding processor. The software modules can be located in the memory 1502, such as random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, registers, or other mature storage media in the art. The processor 1501 reads information from the memory 1502 and, in conjunction with its hardware, completes the steps of the method described above.

[0144] Furthermore, various operations / processes according to this disclosure, implemented via software and / or firmware, can be transmitted from a storage medium or network to a computer system with a dedicated hardware architecture, for example, Figure 16 The computer system 1600 shown is equipped with the programs that constitute the software. When various programs are installed, the computer system is able to perform various functions, including functions such as those mentioned above. Figure 16 Further illustrations show a schematic diagram of the structure of a computer system according to an embodiment of the present disclosure.

[0145] Computer system 1600 is intended to represent various forms of digital electronic computer devices, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. Electronic devices may also represent various forms of mobile devices, such as personal digital processors, cellular phones, smartphones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely illustrative and are not intended to limit the implementation of the present disclosure described and / or claimed herein.

[0146] like Figure 16 As shown, the computer system 1600 includes a computing unit 1601, which can perform various appropriate actions and processes based on a computer program stored in a read-only memory (ROM) 1602 or a computer program loaded from a storage unit 1608 into a random access memory (RAM) 1603. The RAM 1603 may also store various programs and data required for the operation of the computer system 1600. The computing unit 1601, ROM 1602, and RAM 1603 are interconnected via a bus 1604. An input / output (I / O) interface 1605 is also connected to the bus 1604.

[0147] The plurality of components in the computer system 1600 are connected to the I / O interface 1605, including: an input unit 1606, an output unit 1607, a storage unit 1608, and a communication unit 1609. The input unit 1606 can be any type of device capable of inputting information to the computer system 1600, and can receive inputted digital or character information, and generate key signal inputs related to user settings and / or function controls of the electronic device. The output unit 1607 can be any type of device capable of presenting information, and can include, but is not limited to, a display, a speaker, a video / audio output terminal, a vibrator, and / or a printer. The storage unit 1608 can include, but is not limited to, a magnetic disk, an optical disk. The communication unit 1609 allows the computer system 1600 to exchange information / data with other devices through a network such as the Internet, and can include, but is not limited to, a modem, a network card, an infrared communication device, a wireless communication transceiver, and / or a chipset, for example, a Bluetooth™ device, a WiFi device, a WiMax device, a cellular communication device, and / or the like.

[0148] The computing unit 1601 can be various general and / or special-purpose processing components with processing and computing capabilities. Some examples of the computing unit 1601 include, but are not limited to, a central processing unit (CPU), a graphics processing unit (GPU), various special-purpose artificial intelligence (AI) computing chips, various computing units running machine learning model algorithms, a digital signal processor (DSP), and any appropriate processor, controller, microcontroller, etc. The computing unit 1601 performs various methods and processes described above. For example, in some embodiments, the above-described methods disclosed by the embodiments of the present disclosure can be implemented as a computer software program, which is tangibly contained in a machine-readable medium, for example, the storage unit 1608. In some embodiments, part or all of the computer program can be loaded and / or installed on the electronic device 1500 via the ROM 1602 and / or the communication unit 1609. In some embodiments, the computing unit 1601 can be configured to perform the above-described methods disclosed by the embodiments of the present disclosure by any other appropriate means, for example, by means of firmware.

[0149] The embodiments of the present disclosure also provide a computer-readable storage medium, wherein when instructions in the computer-readable storage medium are executed by a processor of an electronic device, the electronic device is enabled to perform the above-described methods disclosed by the embodiments of the present disclosure.

[0150] The computer readable storage medium in the embodiments of the present disclosure can be a tangible medium, which can contain or store a program for use by or in connection with an instruction execution system, apparatus, or device. The computer readable storage medium can include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the above. More specifically, the computer readable storage medium can include an electrical connection based on one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above.

[0151] The computer readable medium can be included in the above-mentioned electronic device, or can exist separately and not be assembled into the electronic device.

[0152] The embodiments of the present disclosure also provide a computer program product, including a computer program, wherein the computer program is executed by a processor to implement the above-mentioned method disclosed by the embodiments of the present disclosure.

[0153] In the embodiments of the present disclosure, the computer program code for performing the operations of the present disclosure can be written in one or more programming languages or a combination thereof, including an object-oriented programming language, such as Java, Smalltalk, C++, and a conventional procedural programming language, such as "C" language or a similar programming language. The program code can be executed completely on a user computer, partially on the user computer and partially on a remote computer, as a separate software package, partially on the user computer and partially on a remote computer, or completely on a remote computer or server. In the case involving a remote computer, the remote computer can be connected to the user computer through any kind of network, including a local area network (LAN) or a wide area network (WAN), or can be connected to an external computer.

[0154] The flow diagrams and the block diagrams in the drawings are illustrations of architectures, functionalities, and operations of possible implementations of systems, methods, and computer program products according to various embodiments of present disclosure. In this regard, each block in the flow diagrams or block diagrams can represent a module, a segment, or a portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that in some alternative implementations, the functions noted in the block can occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and / or flow diagrams, and combinations thereof, can be implemented by special purpose hardware-based systems that perform the specified functions or operations, or combinations of special purpose hardware and computer instructions.

[0155] The modules, components or units described in the embodiments of the present disclosure can be implemented by software or by hardware. In some cases, the name of the module, component or unit does not constitute a limitation on the module, component or unit itself.

[0156] The functions described in this specification can be implemented in part or in whole by one or more hardware logic components. For example, and without limitation, illustrative types of hardware logic components that can be used include Field-programmable Gate Arrays (FPGAs), Program-specific Integrated Circuits (ASICs), Program-specific Standard Products (ASSPs), System-on-a-chip systems (SOCs), Complex Programmable Logic Devices (CPLDs), etc.

[0157] The above description is merely illustrative of the embodiments of the present disclosure and the principles of the technology involved. It is understood that the disclosure scope of the present disclosure is not limited to the technical solutions formed by the specific combinations of the above technical features, and should also cover other technical solutions formed by the combinations of the above technical features or equivalent features thereof without departing from the above disclosure concept. For example, the technical solutions formed by the mutual replacement of the above features and the technical features disclosed in the present disclosure (but not limited to) having similar functions.

[0158] Although some specific embodiments of the present disclosure have been described in detail by way of examples, one skilled in the art should understand that the above examples are only for illustration, and are not intended to limit the scope of the present disclosure. One skilled in the art should understand that the above embodiments can be modified without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.

Claims

1. A method of compressor aerodynamic stability design, characterized by, The method comprises the following steps: acquiring physical parameters of an S2 flow surface in a target compressor, and acquiring flow field parameters on a compressor meridian surface satisfying a first preset condition according to the physical parameters; determining the stability of the compressor according to the flow field parameters, and acquiring structure parameters of an S1 flow surface in the compressor under the condition that the stability of the compressor satisfies a preset stability, which comprises the following steps: acquiring an airflow angle parameter in the compressor under the condition that the stability of the compressor satisfies the preset stability; determining an angle parameter of the S1 flow surface in the compressor based on the airflow angle parameter; determining the structure parameters of the S1 flow surface in the compressor based on the angle parameter of the S1 flow surface, which further comprises the following steps: determining a thickness distribution parameter of a compressor blade according to the working condition requirement of different compressors; determining a corresponding thickness distribution on each base element camber in the S1 flow surface based on the thickness distribution parameter; determining the structure parameters of the S1 flow surface in the compressor according to the thickness distribution; acquiring a stability margin of the compressor according to the structure parameters, and determining a three-dimensional model of the target compressor according to the structure parameters and the flow field parameters under the condition that the stability margin of the compressor satisfies a preset stability margin; acquiring an instability flow point of the target compressor and a stability margin corresponding to the instability flow point after performing three-dimensional steady numerical simulation on the three-dimensional model of the target compressor; determining that the stability margin of the target compressor is the stability margin of the compressor and evaluating the aerodynamic stability of the compressor based on the stability margin of the compressor under the condition that the stability margin corresponding to the instability flow point satisfies a second preset condition, and determining the design parameters of the target compressor based on the aerodynamic stability of the compressor, which comprises the following steps: acquiring a two-dimensional steady flow field under the condition of reducing the dimension of a three-dimensional steady flow field; acquiring an instability flow point of the compressor and a stability margin corresponding to the instability flow point based on the two-dimensional steady flow field; determining an actual stability margin of the compressor according to the stability margin corresponding to each instability flow point; determining that the stability margin of the target compressor is the stability margin of the compressor if the actual stability margin satisfies the second preset condition; modifying the design parameters of the compressor until the actual stability margin parameter of the compressor satisfies the second preset condition and determining the aerodynamic stability of the compressor if the actual stability margin parameter does not satisfy the second preset condition; determining the design parameters of the target compressor based on the aerodynamic stability of the compressor.

2. The method for compressor aerodynamic stability design according to claim 1, wherein, The method comprises the following steps: acquiring physical parameters of an S2 flow surface in a target compressor, and acquiring flow field parameters on a compressor meridian surface satisfying a first preset condition according to the physical parameters, which comprises the following steps: determining flow field parameters on the S2 flow surface based on the physical parameters of the S2 flow surface; determining a control equation on the S2 flow surface based on the flow field parameters on the S2 flow surface; determining a through-flow flow field parameter on the S2 flow surface in the process of solving the control equation on the S2 flow surface; 3. The method for compressor aerodynamic stability design of claim 1, wherein, determining that the through-flow flow field parameter is the flow field parameter on the compressor meridian surface under the condition that the through-flow flow field parameter satisfies a preset condition. The control equation on the S2 flow surface comprises any one of the following equations: an S2 flow surface equation, a state equation, a continuity equation, a momentum equation and an energy equation.

4. The method for compressor aerodynamic stability design of claim 1, wherein, After three-dimensional steady numerical simulation is performed on the three-dimensional model of the target compressor, the instability flow point of the target compressor and the stability margin corresponding to the instability flow point are obtained, which comprises: determining the three-dimensional model of the compressor based on the flow field parameters on the compressor meridian plane and the structural parameters of the S1 flow surface in the compressor blade; After three-dimensional steady numerical simulation is performed on the three-dimensional model of the compressor, the three-dimensional steady flow field of the compressor at different flow points is obtained; According to the three-dimensional steady flow field at different flow points, the instability flow point of the compressor and the stability margin corresponding to the instability flow point are obtained.

5. A compressor aerodynamic stability prediction device applied to the compressor aerodynamic stability design method according to any one of claims 1 to 4, characterized by, Comprise: The first acquisition module acquires the physical parameters of the S2 flow surface in the target compressor, and acquires the flow field parameters on the compressor meridian plane that meet the preset conditions according to the physical parameters; The second acquisition module determines the stability of the compressor according to the flow field parameters, and acquires the structural parameters of the S1 flow surface in the compressor under the condition that the stability of the compressor meets the preset stability, which comprises: acquiring the flow angle parameter in the compressor under the condition that the stability of the compressor meets the preset stability; determining the angle parameter of the S1 flow surface in the compressor based on the flow angle parameter; determining the structural parameters of the S1 flow surface in the compressor based on the angle parameter of the S1 flow surface further comprises: determining the thickness distribution parameter of the compressor blade according to the working condition requirement of different compressors; determining the thickness distribution superimposed on each base element arc line in the S1 flow surface based on the thickness distribution parameter; determining the structural parameters of the S1 flow surface in the compressor according to the thickness distribution; The first determination module acquires the stability margin of the compressor according to the structural parameters, and determines the three-dimensional model of the target compressor according to the structural parameters and the flow field parameters under the condition that the stability margin of the compressor meets the preset stability margin; The third acquisition module acquires the instability flow point of the target compressor and the stability margin corresponding to the instability flow point after three-dimensional steady numerical simulation is performed on the three-dimensional model of the target compressor; The fourth acquisition module determines the stability margin of the target compressor as the stability margin of the compressor and evaluates the aerodynamic stability of the compressor according to the stability margin of the compressor under the condition that the stability margin corresponding to the instability flow point meets the preset condition, and determines the design parameters of the target compressor based on the aerodynamic stability of the compressor, which comprises: acquiring the two-dimensional steady flow field under the condition that the three-dimensional steady flow field is reduced in dimension; acquiring the instability flow point of the compressor and the stability margin corresponding to the instability flow point based on the two-dimensional steady flow field; determining the actual stability margin of the compressor according to the stability margin corresponding to each instability flow point; if the actual stability margin meets the second preset condition, determining the stability margin of the target compressor as the stability margin of the compressor; if the actual stability margin parameter does not meet the second preset condition, modifying the design parameters of the compressor until the actual stability margin parameter of the compressor meets the second preset condition, and determining the aerodynamic stability of the compressor; determining the design parameters of the target compressor based on the aerodynamic stability of the compressor.

6. An electronic device, comprising: Comprise: at least one processor; a memory for storing the instructions executable by the at least one processor; wherein the at least one processor is configured to execute the instructions to implement the method for compressor aerodynamic stability design according to any one of claims 1-4.

7. A computer readable storage medium characterized by, When the instructions in the computer-readable storage medium are executed by the processor of the electronic device, the electronic device is enabled to implement the method for compressor aerodynamic stability design according to any one of claims 1-4.

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