Gas compressor aerodynamic stability design method and device, electronic equipment and storage medium

Abstract

The invention relates to the technical field of stability prediction, in particular to a method and device for designing aerodynamic stability of a gas compressor, electronic equipment and a storage medium, and aims to solve the problem that the aerodynamic stability of the gas compressor in the design process cannot be accurately and quickly predicted in the prior art. The air compressor aerodynamic stability design method comprises the steps that physical parameters of an S2 flow surface in an air compressor of a target air compressor are obtained, and flow field parameters, meeting preset conditions, on a meridian plane of the air compressor are obtained according to the physical parameters; and the stability of the gas compressor is determined according to the flow field parameters, and under the condition that the stability of the gas compressor meets preset stability, structural parameters of the S1 flow surface in the gas compressor are obtained. The gas compressor aerodynamic stability design method and device, the electronic equipment and the storage medium are used for predicting the stability of the gas compressor.

Description

Technical Field

[0001] The present disclosure relates to the technical field of stability prediction, and in particular to a method, device, electronic device and storage medium for designing aerodynamic stability of a compressor. Background Art

[0002] With the continuous increase of modern compressor load, the problem of compressor flow stability has become more and more prominent. Predicting the compressor flow stability is a key step in the compressor design stage. So far, in the actual design process of the compressor, the guarantee of the compressor stability margin mainly relies on empirical relationships, which are obtained by summarizing a large amount of blade and compressor experimental data. In addition, there is a lot of uncertainty in the empirical relationship itself. The database it relies on is not applicable to modern more advanced compressors. It is overly dependent on the experience of designers and is difficult to adapt to the refined design of modern advanced compressors. Once the compressor stability margin cannot meet the design requirements, it will directly lead to the unusability of the designed compressor.

[0003] In order to solve the problem that the stability margin of the above-mentioned compressor does not meet the design requirements, the prior art usually uses steady-state numerical simulation to predict the compressor instability point. However, there is no theoretical basis for predicting compressor flow instability using this method. The error of predicting the compressor instability point using steady-state numerical simulation fluctuates and is difficult to estimate. This is unacceptable in engineering and is also the root cause of flow instability failures in the development of domestic and foreign aircraft engines. In order to make up for the shortcomings of the steady-state numerical simulation method, the prior art mainly uses analytical models and unsteady numerical simulation. The analytical model greatly simplifies the geometry and flow details of the compressor, simplifies the blade row into a disk or a semi-disk, and ignores the non-uniformity of the flow by means of segmented averaging. These limit the accuracy and scope of model prediction, and it is difficult to meet the "accurate" requirements of stability evaluation in the design stage. Unsteady numerical simulation has problems in the selection of turbulence models, the setting of boundary conditions, and whether it is necessary to introduce initial disturbances. In addition, the huge consumption of computing resources and computing time in unsteady numerical simulation is an important reason that limits its engineering application, and it is difficult to meet the "fast" requirements of stability evaluation in the design stage.

[0004] Therefore, how to solve the problem in the prior art that the aerodynamic stability of the compressor cannot be accurately and quickly predicted during the design process is one of the important issues that need to be urgently solved in this field. Summary of the invention

[0005] In view of this, the embodiments of the present disclosure provide a compressor aerodynamic stability design method, device, electronic device and storage medium to solve the problem in the prior art that the compressor aerodynamic stability cannot be accurately and quickly predicted during 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 the S2 flow surface in the compressor of the target compressor, and obtaining flow field parameters on the compressor meridian surface that meet preset conditions according to the physical parameters;

[0008] Determine the stability of the compressor according to the flow field parameters, and obtain the structural parameters of the S1 flow surface in the compressor when the stability of the compressor meets the first preset stability;

[0009] The stability margin of the compressor is obtained according to the structural parameters, and when the stability margin of the compressor satisfies the preset stability margin, the three-dimensional model of the target compressor is determined according to the structural parameters and the flow field parameters;

[0010] After performing a three-dimensional constant numerical simulation on the three-dimensional model of the target compressor, the unstable flow point of the target compressor and the stability margin corresponding to the unstable flow point are obtained;

[0011] When the stability margin corresponding to the unstable flow point satisfies 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, and the design parameters of the target compressor are determined 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 includes obtaining physical parameters of the S2 flow surface in the compressor of the target compressor, and obtaining flow field parameters on the compressor meridian surface that meet preset conditions according to the physical parameters includes:

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

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

[0015] In the process of solving the control equations on the S2 flow surface, the flow field parameters on the S2 flow surface are determined;

[0016] When the flow field parameters satisfy preset conditions, the flow field parameters are determined to be flow field parameters on the compressor meridian plane.

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

[0018] The compressor aerodynamic stability design method according to one aspect of the present disclosure further includes determining the stability of the compressor according to the flow field parameters. When the stability of the compressor meets the preset stability, obtaining the structural parameters of the S1 flow surface in the compressor includes:

[0019] When the stability of the compressor satisfies the preset stability, an airflow angle parameter in the compressor is obtained;

[0020] Determine the angle parameter of the S1 flow surface in the compressor based on the airflow angle parameter;

[0021] The structural parameters of the S1 flow surface in the compressor are determined 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 includes determining the structural parameters of the S1 flow surface in the compressor based on the angle parameters of the S1 flow surface, and further includes:

[0023] Determine the thickness distribution parameters of compressor blades according to the working conditions of different compressors;

[0024] Determine the thickness distribution corresponding to each primitive arc in the S1 flow surface based on the thickness distribution parameter;

[0025] The structural parameters of the S1 flow surface in the compressor are determined based on the thickness distribution.

[0026] The compressor aerodynamic stability design method according to one aspect of the present disclosure further includes obtaining an unstable flow point of the target compressor and a stability margin corresponding to the unstable flow point after performing a three-dimensional constant numerical simulation on a three-dimensional model of the target compressor, including:

[0027] Determine 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;

[0028] After performing three-dimensional steady numerical simulation on the three-dimensional model of the compressor, the three-dimensional steady flow field of the compressor at different flow points is obtained;

[0029] According to the three-dimensional steady flow field at different flow points, the unstable flow point of the compressor and the stability margin corresponding to the unstable flow point are obtained.

[0030] According to a compressor aerodynamic stability design method according to one aspect of the present disclosure, when the stability margin corresponding to the unstable flow point satisfies 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 according to the stability margin of the compressor. Determining the design parameters of the target compressor based on the aerodynamic stability of the compressor includes:

[0031] Obtain a two-dimensional steady flow field by reducing the dimension of a three-dimensional steady flow field;

[0032] Based on the two-dimensional steady flow field, the unstable flow point of the compressor and the stability margin corresponding to the unstable flow point are obtained;

[0033] The actual stability margin of the compressor is determined according to the stability margin corresponding to each unstable flow point;

[0034] If the actual stability margin satisfies the second preset condition, determining the stability margin of the target compressor as the stability margin of the compressor;

[0035] If the actual stability margin parameter does not satisfy the second preset condition, modify the design parameters of the compressor until the actual stability margin parameter of the compressor satisfies the second preset condition, and determine the compressor aerodynamic stability of the compressor;

[0036] The design parameters of the target compressor are determined based on the compressor aerodynamic stability.

[0037] According to another aspect of the present disclosure, a compressor aerodynamic stability prediction device is provided, which is applied to the compressor aerodynamic stability design method provided in the first aspect, and the device includes: a first acquisition module, which acquires physical parameters of the S2 flow surface in the compressor of the target compressor, and acquires flow field parameters on the compressor meridian surface that meet the first preset condition according to the physical parameters; a second acquisition module, which 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 when the stability of the compressor meets the preset stability; a first determination module, which acquires the stability margin of the compressor according to the structural parameters, and acquires the flow field parameters on the compressor meridian surface that meet the first preset condition according to the physical parameters; When the stability margin of the compressor meets the preset stability margin, the three-dimensional model of the target compressor is determined according to the structural parameters and the flow field parameters; the third acquisition module obtains the unstable flow point of the target compressor and the stability margin corresponding to the unstable flow point after performing a three-dimensional steady-state numerical simulation on the three-dimensional model of the target compressor; the fourth acquisition module determines that the stability margin of the target compressor is the stability margin of the compressor when the stability margin corresponding to the unstable flow point meets the second preset condition, predicts the aerodynamic stability of the compressor according to the stability margin of the compressor, and determines the design parameters of the target compressor based on the aerodynamic stability of the compressor.

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

[0039] According to another aspect of the present disclosure, a computer-readable storage medium is provided. When instructions in the computer-readable storage medium are executed by a processor of an electronic device, the electronic device is enabled to execute the steps of the above-mentioned compressor aerodynamic stability design method.

[0040] At least one of the above-mentioned technical solutions adopted in the embodiments of the present disclosure can achieve the following beneficial effects: obtaining the physical parameters of the S2 flow surface in the compressor of the target compressor, and obtaining the flow field parameters on the compressor meridian plane that meets the first preset condition based on the physical parameters; determining the stability of the compressor based on the flow field parameters, and obtaining the structural parameters of the S1 flow surface in the compressor when the stability of the compressor meets the preset stability; obtaining the stability margin of the compressor based on the structural parameters, and determining the three-dimensional model of the target compressor based on the structural parameters and the flow field parameters when the stability margin of the compressor meets the preset stability margin; and obtaining the unstable flow point of the target compressor and the stability margin corresponding to the unstable flow point after performing a three-dimensional constant numerical simulation on 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, reducing the problem of substandard stability margin in the compressor design stage. At the same time, the above method integrates the parameter acquisition of the compressor with the prediction of the compressor aerodynamic stability. 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. The design parameters of the target compressor are determined based on the aerodynamic stability of the compressor, which can quickly improve the accuracy of predicting the aerodynamic stability of the compressor, so that the aerodynamic stability of the compressor is significantly improved compared with the prediction method in the original design system, and effectively solves the problem that the prior art cannot accurately and quickly predict the aerodynamic stability of the compressor during the design process. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0042] Figure 1 A schematic diagram illustrating a process of applying a compressor aerodynamic stability design method according to an embodiment of the present disclosure;

[0043] Figure 2 is a flowchart illustrating obtaining flow field parameters on a compressor meridian plane according to an embodiment of the present disclosure;

[0044] Figure 3 is a flowchart further illustrating obtaining structural parameters of the S1 flow surface in the compressor according to an embodiment of the present disclosure;

[0045] Figure 4 is a flow chart further illustrating determining structural parameters of the S1 flow surface in the compressor according to the thickness distribution according to an embodiment of the present disclosure;

[0046] Figure 5 is a flow chart 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 is a schematic diagram further illustrating a compressor test bench with a detachable rotor blade disk according to an embodiment of the present disclosure;

[0048] Figure 7 is a structural diagram further illustrating a detachable rotor blade disk according to an embodiment of the present disclosure;

[0049] Figure 8 is a diagram further illustrating a front loading blade structure of a detachable rotor blade disk according to an embodiment of the present disclosure;

[0050] Fig. 9 is a diagram further illustrating a detachable rotor blade disk uniformly loaded with blades according to an embodiment of the present disclosure;

[0051] Fig.10 is a diagram further illustrating a detachable rotor blade rear loading blade structure according to an embodiment of the present disclosure;

[0052] Fig.11 is a diagram further illustrating the prediction of the instability point result of the front-loaded blade type compressor, the uniformly loaded blade type compressor and the rear-loaded blade type compressor of the detachable rotor blade disk according to the embodiment of the present disclosure using the method of the present disclosure;

[0053] Fig.12 is a diagram further illustrating the instability point result calculated by the traditional steady-state numerical simulation method for the front-loaded blade type compressor, the uniformly loaded blade type compressor and the rear-loaded blade type compressor of the detachable rotor blade disk according to the embodiment of the present disclosure;

[0054] Fig.13 is a diagram further illustrating the instability point result obtained by using an experimental method for a detachable rotor blade disk front-loaded blade type compressor, a uniformly loaded blade type compressor, and a rear-loaded blade type compressor according to an embodiment of the present disclosure;

[0055] Fig.14 Further illustrating a schematic structural diagram of a compressor aerodynamic stability prediction device according to an embodiment of the present disclosure;

[0056] Fig.15 A schematic diagram of the structure of an electronic device according to an embodiment of the present disclosure is further illustrated;

[0057] Fig.16 The following is a schematic diagram of the structure of a computer system according to an embodiment of the present disclosure.

[0058] Reference numerals:

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

[0060] Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although certain embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as being limited to the embodiments described herein, which are instead provided for a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are only for exemplary purposes and are not intended to limit the scope of protection of the present disclosure.

[0061] It should be understood that the various steps described in the method embodiments of the present disclosure may be performed in different orders and / or in parallel. In addition, the method embodiments may include additional steps and / or omit the steps shown. The scope of the present disclosure is not limited in this respect.

[0062] The term "including" and its variations used in this document are open inclusions, that is, "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 other embodiment"; the term "some embodiments" means "at least some embodiments". Relevant definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc. mentioned in this disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

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

[0064] The names of the messages or information exchanged between multiple devices in the embodiments of the present disclosure are only used for illustrative purposes and are not used to limit the scope of these messages or information.

[0065] With the continuous increase of modern compressor load, the problem of compressor flow stability has become more and more prominent. Predicting the compressor flow stability is a key step in the compressor design stage. So far, in the actual design process of the compressor, the guarantee of the compressor stability margin mainly relies on empirical relationships, which are obtained by summarizing a large amount of blade and compressor experimental data. In addition, there is a lot of uncertainty in the empirical relationship itself. The database it relies on is not applicable to modern more advanced compressors. It is overly dependent on the experience of designers and is difficult to adapt to the refined design of modern advanced compressors. Once the compressor stability margin cannot meet the design requirements, it will directly lead to the unusability of the designed compressor.

[0066] In order to solve the problem that the stability margin of the above-mentioned compressor does not meet the design requirements, the prior art usually uses steady-state numerical simulation to predict the compressor instability point. However, there is no theoretical basis for predicting compressor flow instability using this method. The error of predicting the compressor instability point using steady-state numerical simulation fluctuates and is difficult to estimate. This is unacceptable in engineering and is also the root cause of flow instability failures in the development of domestic and foreign aircraft engines. In order to make up for the shortcomings of the steady-state numerical simulation method, the prior art mainly uses analytical models and unsteady numerical simulation. The analytical model greatly simplifies the geometry and flow details of the compressor, simplifies the blade row into a disk or a semi-disk, and ignores the non-uniformity of the flow by means of segmented averaging. These limit the accuracy and scope of model prediction, and it is difficult to meet the "accurate" requirements of stability evaluation in the design stage. Unsteady numerical simulation has problems in the selection of turbulence models, the setting of boundary conditions, and whether it is necessary to introduce initial disturbances. In addition, the huge consumption of computing resources and computing time in unsteady numerical simulation is an important reason that limits its engineering application, and it is difficult to meet the "fast" requirements of stability evaluation in the design stage.

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

[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 FIG. 1 is a schematic diagram of the process of applying the compressor aerodynamic stability design method according to an embodiment of the present disclosure. Figure 1 As shown, the compressor aerodynamic stability design method includes the following steps:

[0070] S101: Obtain physical parameters of the S2 flow surface in the compressor of the target compressor, and obtain flow field parameters on the compressor meridian plane that meet the first preset condition according to the physical parameters. It can be understood that the above-mentioned 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 when the stability of the compressor meets the preset stability, obtain the structural parameters of the S1 flow surface in the compressor.

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

[0073] S104: After performing a three-dimensional steady-state numerical simulation on the three-dimensional model of the target compressor, an unstable flow point of the target compressor and a stability margin corresponding to the unstable flow point are obtained.

[0074] S105: When the stability margin corresponding to the unstable flow point satisfies 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 according to the stability margin of the compressor, and the design parameters of the target compressor are determined based on the aerodynamic stability of the compressor. It can be understood that the above-mentioned 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 obtained, and the flow field parameters on the compressor meridian plane that meet the first preset condition are obtained according to the physical parameters; the stability of the compressor is determined according to the flow field parameters, and when the stability of the compressor meets the preset stability, the structural parameters of the S1 flow surface in the compressor are obtained; the stability margin of the compressor is obtained according to the structural parameters, and when the stability margin of the compressor meets the preset stability margin, the three-dimensional model of the target compressor is determined according to the structural parameters and the flow field parameters; after performing a three-dimensional steady-state numerical simulation on the three-dimensional model of the target compressor, the unstable flow point of the target compressor and the stability margin corresponding to the unstable flow point are obtained. 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, reducing the problem of substandard stability margin in the compressor design stage. At the same time, the above method integrates the parameter acquisition of the compressor with the prediction of the compressor aerodynamic stability. 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. The design parameters of the target compressor are determined based on the aerodynamic stability of the compressor, which can quickly improve the accuracy of predicting the aerodynamic stability of the compressor, so that the aerodynamic stability of the compressor is significantly improved compared with the prediction method in the original design system, and effectively solves the problem that the prior art cannot accurately and quickly predict the aerodynamic stability of the compressor during the design process.

[0076] Figure 2 FIG. 1 is a flowchart illustrating a method for obtaining flow field parameters on a compressor meridian plane according to an embodiment of the present disclosure. Figure 2 As shown, preferably, obtaining the physical parameters of the S2 flow surface in the compressor of the target compressor, and obtaining the flow field parameters on the compressor meridian surface that meet the preset conditions according to the physical parameters includes:

[0077] S201: Determine flow field parameters on the S2 flow surface based on 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 flow field parameters on the S2 flow surface in the process of solving the control equation on the S2 flow surface;

[0080] S204: When the flow field parameters satisfy a preset condition, the flow field parameters are determined to be flow field parameters on the compressor meridian plane.

[0081] Exemplarily, the control equations on the S2 flow surface include: 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 surface are mainly established using the center surface method. The so-called center surface refers to the S2 surface located between adjacent blades. The flow field parameters on the S2 surface represent the circumferential average flow field of the current blade channel. The control equations solved by the throughflow calculation are shown below, which mainly include the S2 surface equation, state equation, continuity equation, momentum equation, and energy equation.

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

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

[0085] The state equation is as follows:

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

[0087] The continuity equation is as follows:

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

[0089] The momentum equation is as follows:

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

[0091] The energy equation is as follows:

[0092] The energy equation for inviscid steady adiabatic flow in relative coordinate system is: Right now In the formula, represents rotor enthalpy, h represents static enthalpy, and Ω represents rotational speed, the unit is r / min.

[0093] The control equations on the above S2 flow surface are all based on the inviscid assumption. In order to consider the viscous loss, the entropy increase along the streamline also needs to be taken into account. By giving the design parameters and solving the above five equations in parallel, the flow design can be completed and the flow field on the S2 flow surface can be obtained.

[0094] For example, Figure 3 is a flowchart further illustrating the acquisition of structural parameters of the S1 flow surface in the compressor according to an embodiment of the present disclosure, such as Figure 3 As shown, the stability of the compressor is determined according to the flow field parameters. When the stability of the compressor meets the preset stability, the structural parameters of the S1 flow surface in the compressor are obtained, including:

[0095] S301: acquiring an airflow angle parameter in the compressor when the stability of the compressor meets a preset stability;

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

[0097] S303: Determine the structural parameters of the S1 flow surface in the compressor based on the angle parameters of the S1 flow surface. It can be understood that the angle parameters of the S1 flow surface are the airflow angle distribution from the leading edge to the trailing edge of each spanwise position primitive, the leading edge attack angle of each primitive, the trailing edge lagging angle and the internal derailment angle of the blade.

[0098] For example, Figure 4 is a flowchart further illustrating determining the structural parameters of the S1 flow surface in the compressor according to the thickness distribution according to an embodiment of the present disclosure, such as Figure 4 As shown, the structural parameters of the S1 flow surface in the compressor blade are determined based on the angle parameters of the S1 flow surface, and further include:

[0099] S401: Determine the thickness distribution parameters of the compressor blades according to the working conditions of different compressor blades. In practical applications, the thickness distribution parameters of the corresponding classic blades are directly used according to the working conditions of the blades, such as C4 blades, BC6 blades and NACA65 blades. In addition, by giving the front and rear small circle radii, the maximum thickness of the blade and the relative position of the maximum thickness, the thickness distribution of each primitive blade is constructed by a cubic polynomial.

[0100] S402: Determine the corresponding thickness distribution superimposed on the mid-camber line of each primitive in the S1 flow surface based on the thickness distribution parameter. That is, after the mid-camber line and thickness distribution are determined, the corresponding thickness distribution is superimposed on the mid-camber line of each primitive to obtain the primitive blade profile 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 primitive blade profile is obtained, the stacking axis and its reference point are given, and the spanwise stacking is performed according to the center of gravity or the leading / trailing edge to obtain a three-dimensional blade, and finally the structural parameters of the S1 flow surface are determined based on the three-dimensional blade.

[0102] For example, Figure 5 is a flowchart further illustrating obtaining the unstable flow point of the target compressor and the stability margin corresponding to the unstable flow point according to an embodiment of the present disclosure, such as Figure 5 As shown, after performing a three-dimensional constant numerical simulation on the three-dimensional model of the target compressor, the unstable flow point of the target compressor and the stability margin corresponding to the unstable flow point are obtained, including:

[0103] S501: Determine a 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.

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

[0105] S503: Obtaining unstable flow points of the compressor and stability margins corresponding to the unstable flow points according to the three-dimensional steady flow fields at different flow points.

[0106] Exemplarily, when the stability margin corresponding to the unstable flow point satisfies the second preset condition, the stability margin of the target compressor is determined to be 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 aerodynamic stability of the compressor includes: obtaining a two-dimensional steady flow field when reducing the dimension 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 according to the stability margin corresponding to each unstable flow point; if the actual stability margin satisfies 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 satisfy 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 compressor aerodynamic stability of the compressor; determining the design parameters of the target compressor based on the aerodynamic stability of the compressor.

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

[0108]

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

[0110] When analyzing the stability of the compressor, it is necessary to reasonably reduce the dimension of the above main control equations. In the aerodynamic design stage of the compressor, the inlet flow is uniform, and the compressor geometry is periodic in the circumferential direction. Therefore, considering the assumption that the fluid flow is uniform in the circumferential direction, only the flow non-uniformity in the axial and radial dimensions is considered in the control equation, and the impact of the circumferential non-uniformity of the flow in the blade area is considered in the blade force source term. Ignoring heat conduction and heat generation, removing the viscous shear stress term, and combining the ideal gas state equation, the above main control equation can be expanded in the cylindrical coordinate system 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 airflow velocity in the stationary coordinate system, v is the circumferential component of the airflow velocity in the stationary coordinate system, and w is the axial component of the airflow velocity in the stationary coordinate system. Ω is the rotor rotation speed in r / min; f θ πΩr / 30 represents the work done by the blade force, h * is the stagnation enthalpy, which is expressed as follows under the ideal gas assumption:

[0113] For example, since we are concerned about the stall initiation stage of the compressor, we can use the linear stability analysis method to write the transient quantity q of the flow parameter as the time-averaged quantity and the sum of the unsteady small disturbance q′, that is:

[0114]

[0115] Where 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. q represents any physical parameters ρ, u, v, w, p, f r 、f θ and f z .

[0116] Since the flow field is assumed to be circumferentially uniform, the circumferential modes of the disturbance can be regarded as decoupled, and the disturbance is Fourier expanded in time and circumferential direction, that is:

[0117]

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

[0119] The role of the blade force source term is to characterize the influence of blade geometry on the flow field. Therefore, in the process of blade force modeling, it is often expressed as a function of local flow parameters, that is, f = f(ρ,u,v,w,p). The disturbance of the blade force can be expressed by a first-order Taylor expansion. Considering that the blade force cannot change with the local flow field parameters immediately, but requires a certain response time, a first-order delay equation is introduced on the basis of the first-order Taylor expansion to express the magnitude of the blade force disturbance, that is:

[0120]

[0121] Where τ is the delay time, which is equivalent to the time it takes for the airflow to flow through the blade channel.

[0122] Subtract the zero-order equation satisfied by the steady background flow, ignore the second-order and above small quantities, and get the control equation in matrix form:

[0123]

[0124] Wherein, A, B, C, E, G and F are all fifth-order coefficient matrices composed of the time-averaged quantities of the background flow and their spatial partial derivatives. The F matrix is ​​composed of blade force source terms, and its specific expression depends on the established blade force model, that is, the specific form of f = f(ρ, u, v, w, p). Blade force modeling can be done in many ways, and this application does not specify a specific blade force model. In addition, appropriate boundary conditions are added on the inlet and outlet boundaries and wall boundaries, which are reflected in the above coefficient matrix, so that the established compressor flow stability prediction method conforms to the current physical problems.

[0125] On this basis, the singular value decomposition (SVD) or generalized eigenvalue theory is used to solve the control equation in the above matrix form to obtain the system eigenvalue ω. By performing Fourier expansion on 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 over time: if the imaginary part is greater than zero, the disturbance increases with time until the system becomes unstable, so the system is unstable; if the imaginary part is less than zero, the disturbance decays with time until it disappears, and the system is stable. Therefore, the positive or negative imaginary part of the eigenvalue obtained can be used to determine whether the current compressor flow state is stable.

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

[0127] Fig.11 is a diagram further illustrating the prediction of the instability point result of the front-loaded blade type compressor, the uniformly loaded blade type compressor and the rear-loaded blade type compressor of the detachable rotor blade disk according to the embodiment of the present disclosure using the method of the present disclosure, Fig.12 is a diagram further illustrating the instability point result calculated by the traditional steady-state numerical simulation method for the front-loaded blade type compressor, the uniformly loaded blade type compressor and the rear-loaded blade type compressor of the detachable rotor blade disk according to the embodiment of the present disclosure, Fig.13 1 is a diagram further illustrating the instability point result diagram measured by the experimental method for the detachable rotor blade disk front-loaded blade type compressor, the uniformly loaded blade type compressor and the rear-loaded blade type compressor according to the embodiment of the present disclosure, such as Figures 11 to 13 As shown, 1 represents a compressor with front-loaded blades, 2 represents a compressor with uniformly loaded blades, and 3 represents a compressor with rear-loaded blades. The horizontal axis flow rate (kg / s) represents the operating conditions of the compressor at different flow points, and the vertical axis is the imaginary part of the eigenvalue. An imaginary part less than 0 indicates that the compressor flow is stable, and an imaginary part greater than 0 indicates that the compressor flow is unstable. The change in operating conditions from a large flow point to a small flow point is the throttling process of the compressor. It can be seen that in this process, the eigenvalue has undergone a process from less than 0 to greater than 0, that is, the compressor flow has undergone a process from stable to unstable, and the flow point corresponding to the eigenvalue equal to 0 is the compressor instability flow point predicted by the compressor flow stability prediction method of this application. From Fig.11 It can be seen that the unstable flow points of the three compressors with front loading, uniform loading and back loading predicted by the above method are 5.01kg / s, 5.17kg / s and 5.34kg / s respectively.

[0128] Fig.12 It is the result of the traditional steady-state numerical simulation method. The horizontal axis flow rate (kg / s) represents the working conditions of different flow points of the compressor, and the vertical axis static pressure rise coefficient is the compressor boost capacity indicator. Each compressor corresponds to a characteristic line. The minimum flow point is the compressor instability point calculated by this method, which is the last convergent flow point before the steady-state value diverges. Fig.12 It can be seen that the unstable flow points of the three compressors with front loading, uniform loading and back loading calculated by the steady-state numerical simulation method are 4.88kg / s, 4.90kg / s and 5.15kg / s respectively. Fig.13It is the experimental test result. It can be seen that the unstable flow points of the three compressors with front loading, uniform loading and rear loading measured in the experiment are 5.07kg / s, 5.18kg / s and 5.38kg / s respectively.

[0129] Through the above Figures 11 to 13 The relative error of the compressor instability point calculated by the constant numerical simulation method is compared with the instability flow points of the three compressors measured experimentally.

[0130] Table 1 Relative error of compressor instability point obtained by steady-state simulation method

[0131]

[0132] Table 2 shows the relative errors of the compressor instability points evaluated by the compressor flow stability prediction method of the present application, based on the experimentally measured instability flow points of three compressors.

[0133] Table 2 Relative error of compressor instability point obtained by compressor aerodynamic stability design method

[0134]

[0135] By comparing Table 1 and Table 2, it can be seen that the calculation error of the traditional steady-state numerical simulation method is greater than 5%, which does not meet the accuracy requirement of error ≤ 5 required in engineering; the evaluation error of the compressor aerodynamic stability design method is less than 1.5%, which fully meets the engineering needs. The above experiments can prove the reliability of the compressor aerodynamic stability design method disclosed in the present invention.

[0136] In the case of dividing each functional module according to each function, an exemplary embodiment of the present disclosure provides a compressor aerodynamic stability prediction device, which may be a server or a chip applied to a server. Fig.14 The following is a schematic diagram of the structure of the compressor aerodynamic stability prediction device according to an embodiment of the present disclosure. Fig.14 As shown, the compressor aerodynamic stability prediction device 1400 includes:

[0137] A first acquisition module 1401 is configured to acquire physical parameters of a flow surface S2 in a compressor of a target compressor, and acquire flow field parameters on a meridian surface of the compressor that meet a first preset condition according to the physical parameters;

[0138] A second acquisition module 1402 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 when the stability of the compressor meets the preset stability;

[0139] A first determination module 1403 is configured to obtain a stability margin of the compressor according to the structural parameters, and determine a three-dimensional model of the target compressor according to the structural parameters and the flow field parameters when the stability margin of the compressor satisfies a preset stability margin;

[0140] A third acquisition module 1404, after performing a three-dimensional constant numerical simulation on the three-dimensional model of the target compressor, acquires an unstable flow point of the target compressor and a 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 satisfies the second preset condition, evaluates the aerodynamic stability of the compressor according to the stability margin of the compressor, and determines the design parameters of the target compressor based on the aerodynamic stability of the compressor.

[0142] Fig.15 The following is a schematic diagram of the structure of an electronic device according to an embodiment of the present disclosure. Fig.15 As shown, the electronic device 1500 includes at least one processor 1501 and a memory 1502 coupled to the processor 1501 , and the processor 1501 can execute corresponding steps in the above method disclosed in the embodiment of the present disclosure.

[0143] The processor 1501 may also be referred to as a central processing unit (CPU), which may be an integrated circuit chip having signal processing capabilities. Each step in the method disclosed in the embodiment of the present disclosure may be completed by an integrated logic circuit of hardware in the processor 1501 or by instructions in the form of software. The processor 1501 may be a general-purpose processor, a digital signal processor (DSP), an ASIC, a field-programmable gate array (FPGA) or other programmable logic device, a discrete gate or transistor logic device, or a discrete hardware component. A general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc. The steps of the method disclosed in the embodiment of the present disclosure may be directly embodied as being executed by a hardware decoding processor, or may be executed by a combination of hardware and software modules in a decoding processor. The software module may be located in a memory 1502, such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory, or an electrically erasable programmable memory, a register, or other mature storage media in the art. The processor 1501 reads the information in the memory 1502 and completes the steps of the method in combination with its hardware.

[0144] In addition, when various operations / processes according to the present disclosure are implemented by software and / or firmware, they can be transmitted from a storage medium or a network to a computer system having a dedicated hardware structure, for example, Fig.16 The computer system 1600 shown installs the programs constituting the software, and when the various programs are installed, the computer system can execute various functions, including the functions described above. Fig.16 The following is 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 can also represent various forms of mobile devices, such as personal digital processing, cellular phones, smart phones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely examples and are not intended to limit the implementation of the present disclosure described and / or claimed herein.

[0146] like Fig.16 As shown, the computer system 1600 includes a computing unit 1601, which can perform various appropriate actions and processes according to 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. In the RAM 1603, various programs and data required for the operation of the computer system 1600 can also be stored. The computing unit 1601, the ROM 1602, and the RAM 1603 are connected to each other via a bus 1604. An input / output (I / O) interface 1605 is also connected to the bus 1604.

[0147] A 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 may be any type of device capable of inputting information to the computer system 1600, and the input unit 1606 may receive input digital or character information, and generate key signal inputs related to user settings and / or function control of the electronic device. The output unit 1607 may be any type of device capable of presenting information, and may 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 may include, but is not limited to, a disk, an optical disk. The communication unit 1609 allows the computer system 1600 to exchange information / data with other devices over a network such as the Internet, and may 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 may be a variety of general and / or special 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 dedicated artificial intelligence (AI) computing chips, various computing units running machine learning model algorithms, digital signal processors (DSPs), and any appropriate processors, controllers, microcontrollers, etc. The computing unit 1601 performs the various methods and processes described above. For example, in some embodiments, the above methods disclosed in the embodiments of the present disclosure may be implemented as a computer software program, which is tangibly included in a machine-readable medium, such as a storage unit 1608. In some embodiments, part or all of the computer program may be loaded and / or installed on the electronic device 1500 via ROM 1602 and / or communication unit 1609. In some embodiments, the computing unit 1601 may be configured to perform the above methods disclosed in the embodiments of the present disclosure in any other appropriate manner (e.g., by means of firmware).

[0149] The embodiment of the present disclosure also provides a computer-readable storage medium, wherein when the instructions in the computer-readable storage medium are executed by a processor of an electronic device, the electronic device is enabled to execute the above method disclosed in the embodiment of the present disclosure.

[0150] The computer-readable storage medium in the embodiments of the present disclosure may be a tangible medium that may contain or store a program for use by or in conjunction with an instruction execution system, device, or apparatus. The computer-readable storage medium may include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, devices, or equipment, or any suitable combination of the above. More specifically, the computer-readable storage medium may include an electrical connection based on one or more lines, 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 may be included in the electronic device, or may exist independently without being incorporated 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 implements the above method disclosed in the embodiments of the present disclosure when executed by a processor.

[0153] In embodiments of the present disclosure, computer program codes for performing the operations of the present disclosure may be written in one or more programming languages ​​or combinations thereof, including but not limited to object-oriented programming languages, such as Java, Smalltalk, C++, and conventional procedural programming languages, such as "C" language or similar programming languages. The program code may be executed entirely on a user's computer, partially on a user's computer, as an independent software package, partially on a user's computer, partially on a remote computer, or entirely on a remote computer or server. In the case of a remote computer, the remote computer may be connected to the user's computer via any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computer.

[0154] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present disclosure. In this regard, each square box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some implementations as replacements, the functions marked in the square box can also occur in a sequence different from that marked in the accompanying drawings. For example, two square boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each square box in the block diagram and / or flow chart, and the combination of the square boxes in the block diagram and / or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0155] The modules, components or units involved in the embodiments described in the present disclosure may be implemented by software or hardware, wherein the names of the modules, components or units do not, in some cases, limit the modules, components or units themselves.

[0156] The functions described above herein may be performed at least in part by one or more hardware logic components. For example, without limitation, exemplary hardware logic components that may be used include: field programmable gate arrays (FPGAs), application specific integrated circuits (ASICs), application specific standard products (ASSPs), systems on chip (SOCs), complex programmable logic devices (CPLDs), and the like.

[0157] The above descriptions are only some embodiments of the present disclosure and an explanation of the technical principles used. Those skilled in the art should understand that the scope of disclosure involved in the present disclosure is not limited to the technical solutions formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above disclosed concept. For example, a technical solution formed by replacing the above features with the technical features with similar functions disclosed in the present disclosure (but not limited to).

[0158] Although some specific embodiments of the present disclosure have been described in detail by way of example, it should be understood by those skilled in the art that the above examples are for illustration only and are not intended to limit the scope of the present disclosure. It should be understood by those skilled in the art that the above embodiments may 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 compressor aerodynamic stability design method, characterized in that: include: Acquire physical parameters of the S2 flow surface in the compressor of the target compressor, and acquire flow field parameters on the compressor meridian plane that meets the first preset condition according to the physical parameters; 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 when the stability of the compressor meets the preset stability; Acquire the stability margin of the compressor according to the structural parameters, and determine the three-dimensional model of the target compressor according to the structural parameters and the flow field parameters when the stability margin of the compressor satisfies a preset stability margin; After performing a three-dimensional constant numerical simulation on the three-dimensional model of the target compressor, an unstable flow point of the target compressor and a stability margin corresponding to the unstable flow point are obtained; When the stability margin corresponding to the unstable flow point satisfies 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, and the design parameters of the target compressor are determined based on the aerodynamic stability of the compressor.

2. The compressor aerodynamic stability design method according to claim 1, characterized in that: Obtaining physical parameters of the S2 flow surface in the compressor of the target compressor, and obtaining flow field parameters on the compressor meridian surface that meet preset conditions according to the physical parameters includes: Determine the flow field parameters on the S2 flow surface based on the physical parameters of the S2 flow surface; Determine the control equation on the S2 flow surface based on the flow field parameters on the S2 flow surface; In the process of solving the control equations on the S2 flow surface, the flow field parameters on the S2 flow surface are determined; When the through-flow flow field parameters meet preset conditions, the through-flow flow field parameters are determined to be flow field parameters on the compressor meridian plane.

3. The compressor aerodynamic stability design method according to claim 1, characterized in that: The control equations on the S2 flow surface include: any one of the S2 flow surface equation, state equation, continuity equation, momentum equation and energy equation.

4. The compressor aerodynamic stability design method according to claim 1, characterized in that: Determining the stability of the compressor according to the flow field parameters, and when the stability of the compressor meets the preset stability, obtaining the structural parameters of the S1 flow surface in the compressor includes: When the stability of the compressor satisfies a preset stability, an airflow angle parameter in the compressor is obtained; Determining the angle parameter of the S1 flow surface in the compressor based on the airflow angle parameter; The structural parameters of the S1 flow surface in the compressor are determined based on the angle parameters of the S1 flow surface.

5. The compressor aerodynamic stability design method according to claim 4, characterized in that: Determining the structural parameters of the S1 flow surface in the compressor based on the angle parameters of the S1 flow surface also includes: Determine the thickness distribution parameters of compressor blades according to the working conditions of different compressors; Determine the corresponding thickness distribution superimposed on each primitive arc in the S1 flow surface based on the thickness distribution parameter; The structural parameters of the S1 flow surface in the compressor are determined according to the thickness distribution.

6. The compressor aerodynamic stability design method according to claim 1, characterized in that: After performing a three-dimensional constant numerical simulation on the three-dimensional model of the target compressor, obtaining the unstable flow point of the target compressor and the stability margin corresponding to the unstable flow point includes: The three-dimensional model of the compressor is determined 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 performing a three-dimensional steady numerical simulation on the three-dimensional model of the compressor, a three-dimensional steady flow field at different flow points of the compressor is obtained; According to the three-dimensional steady flow field at different flow points, the unstable flow point of the compressor and the stability margin corresponding to the unstable flow point are obtained.

7. The compressor aerodynamic stability design method according to claim 1, characterized in that: When the stability margin corresponding to the unstable flow point satisfies the second preset condition, determining the stability margin of the target compressor as the stability margin of the compressor, and evaluating the aerodynamic stability of the compressor according to the stability margin of the compressor, and determining the design parameters of the target compressor based on the aerodynamic stability of the compressor includes: Obtain a two-dimensional steady flow field by reducing the dimension of a three-dimensional steady flow field; Based on the two-dimensional steady flow field, the unstable flow point of the compressor and the stability margin corresponding to the unstable flow point are obtained; The actual stability margin of the compressor is determined according to the stability margin corresponding to each unstable flow point; If the actual stability margin satisfies 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 satisfy the second preset condition, modify the design parameters of the compressor until the actual stability margin parameter of the compressor satisfies the second preset condition, and determine the compressor aerodynamic stability of the compressor; The design parameters of the target compressor are determined based on the aerodynamic stability of the compressor.

8. A compressor aerodynamic stability prediction device, characterized in that: include: A first acquisition module is used to acquire physical parameters of the S2 flow surface in the compressor of the target compressor, and to acquire flow field parameters on the compressor meridian surface that meet preset conditions according to the physical parameters; A 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 when the stability of the compressor meets the preset stability; A first determination module, which obtains a stability margin of the compressor according to the structural parameters, and determines a three-dimensional model of the target compressor according to the structural parameters and the flow field parameters when the stability margin of the compressor satisfies a preset stability margin; A third acquisition module, after performing a three-dimensional constant numerical simulation on the three-dimensional model of the target compressor, acquires an unstable flow point of the target compressor and a stability margin corresponding to the unstable flow point; The fourth acquisition module 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 preset conditions, evaluates the aerodynamic stability of the compressor according to the stability margin of the compressor, and determines the design parameters of the target compressor based on the aerodynamic stability of the compressor.

9. An electronic device, characterized in that: include: at least one processor; a memory for storing the at least one processor-executable instruction; Wherein, the at least one processor is used to execute the instructions to implement the compressor aerodynamic stability design method as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that: When the instructions in the computer-readable storage medium are executed by a processor of an electronic device, the electronic device is enabled to execute the compressor aerodynamic stability design method according to any one of claims 1 to 7.

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