Analytical method and apparatus for assessing compressor flow stability under circumferential distortion

Abstract

The present disclosure relates to the technical field of compressor analysis, and particularly provides a method and device for evaluating the flow stability of a compressor under circumferential distortion, the method comprising: constructing Euler control equations of a compressor to be evaluated; obtaining small perturbation equations of the compressor based on small perturbation assumption and the Euler control equations, and solving the small perturbation equations based on flow field data at multiple circumferential points to obtain small perturbation solutions of the compressor; determining boundary conditions of blades in the compressor based on a cascade model and parallel compressor theory, and determining a system stability characteristic equation of the compressor under circumferential flow field unevenness according to the boundary conditions and the small perturbation solutions; and determining a flow stability evaluation result of the compressor according to a solving result of the system stability characteristic equation; the present disclosure can improve the accuracy of the flow stability evaluation result of a high-load compressor with circumferential flow field unevenness.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the technical field of compressor analysis, and particularly relates to a method and device for evaluating flow stability of a compressor under circumferential distortion. BACKGROUND

[0002] As an important device of an engine, a compressor is limited by actual conditions under a working scene, and there is non-uniformity in space and time at the inlet of the compressor, which is referred to as inlet distortion in the field of an aero-engine. The circumferential distortion is a typical form of spatial distortion, which causes greater threat to the performance and stability of the compressor by destroying the uniformity of the inlet flow of the compressor.

[0003] In the related art, in order to study the flow stability problem in the compressor, a Moore-Greitzer model can be used to model and analyze the compressor to determine the stability analysis result of the compressor.

[0004] However, the Moore-Greitzer model is a two-dimensional incompressible model, and in the process of analyzing the stability of the compressor, the flow field of the compressor is assumed to be incompressible, which does not conform to the actual working condition of the high-load compressor, resulting in poor accuracy of the analysis result of the high-load compressor based on the Moore-Greitzer model. SUMMARY

[0005] The present disclosure is proposed in view of the above problems. The present disclosure provides a method and device for evaluating flow stability of a compressor under circumferential distortion, which improves the accuracy of the flow stability evaluation result of the high-load compressor with circumferential flow field non-uniformity.

[0006] According to an aspect of the present disclosure, a method for evaluating flow stability of a compressor under circumferential distortion is provided, comprising:

[0007] constructing Euler control equations of the compressor to be evaluated, wherein a flow field parameter in the Euler control equations is a function of a circumferential coordinate of the compressor;

[0008] obtaining a small disturbance equation of the compressor based on a small disturbance assumption and the Euler control equations, and solving the small disturbance equation based on flow field data at a plurality of circumferential points to obtain a small disturbance solution of the compressor;

[0009] determining boundary conditions of blades in the compressor based on a cascade model and a parallel compressor theory, and determining a system stability characteristic equation of the compressor under circumferential flow field non-uniformity according to the boundary conditions and the small disturbance solution;

[0010] According to a solving result of the system stability characteristic equation, a flow stability evaluation result of the compressor is determined.

[0011] According to another aspect of the present disclosure, there is provided a compressor flow stability evaluation analysis device under circumferential distortion, comprising:

[0012] A construction module is configured to construct an Euler control equation of a compressor to be evaluated, wherein a flow field parameter in the Euler control equation is a function of a circumferential coordinate of the compressor;

[0013] An acquisition module is configured to obtain a small disturbance equation of the compressor based on a small disturbance assumption and the Euler control equation, and solve the small disturbance equation based on flow field data at a plurality of circumferential points to obtain a small disturbance solution of the compressor;

[0014] A first determination module is configured to determine a boundary condition of a blade in the compressor based on a cascade model and a parallel compressor theory, and determine a system stability characteristic equation of the compressor under circumferential flow field non-uniformity according to the boundary condition and the small disturbance solution;

[0015] A second determination module is configured to determine a flow stability evaluation result of the compressor according to a solving result of the system stability characteristic equation.

[0016] According to still another aspect of the present disclosure, there is provided an electronic device comprising a memory, a processor, and a computer program stored on the memory, wherein the processor executes the computer program to implement the compressor flow stability evaluation analysis method under circumferential distortion.

[0017] According to yet another aspect of the present disclosure, there is provided a computer readable storage medium having a computer program stored thereon, wherein the computer program is executed by a processor to implement the compressor flow stability evaluation analysis method under circumferential distortion.

[0018] The compressor flow stability evaluation analysis method and device under circumferential distortion provided by the present disclosure, on the one hand, the flow field parameter in the constructed Euler control equation of the compressor is a function of the circumferential coordinate of the compressor, which can make the small disturbance equation obtained based on the small disturbance assumption and the Euler control equation of the compressor more accurately represent the small disturbance of the circumferential wave in the compressor under circumferential flow field non-uniformity; on the other hand, by solving the small disturbance equation based on the flow field data at a plurality of circumferential points, a small disturbance solution considering circumferential non-uniform flow field is obtained, and based on the small disturbance solution and the boundary condition of the blade in the compressor, a solving result of the system stability characteristic equation of the compressor under circumferential flow field non-uniformity is obtained, and the stability of the compressor is analyzed, thereby improving the accuracy of the flow stability evaluation result of the high-load compressor under circumferential flow field non-uniformity.

[0019] It is to be understood that both the foregoing general description and the following detailed description are exemplary and intended to provide further explanation of the subject technology claimed. BRIEF DESCRIPTION OF DRAWINGS

[0020] The foregoing and other objects, features, and advantages of the present disclosure will become more apparent from the following detailed description, which proceeds with reference to the accompanying drawings. The drawings are intended to provide a further understanding, but are not intended for limitation of the present disclosure. The drawings illustrate examples for the present disclosure and, together with the description, serve to explain the principles of the present disclosure. In the drawings:

[0021] Figure 1 is a flow chart illustrating a method for evaluating and analyzing compressor flow stability under circumferential distortion according to an embodiment of the present disclosure.

[0022] Figure 2 is a block diagram illustrating an apparatus for evaluating and analyzing compressor flow stability under circumferential distortion according to an embodiment of the present disclosure.

[0023] Figure 3 is a schematic diagram illustrating a computer program product according to an embodiment of the present disclosure.

[0024] Figure 4 is a hardware block diagram of an electronic device according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0025] To make the objectives, technical solutions and advantages of the present disclosure more apparent, the following will describe example embodiments according to the present disclosure in detail with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all the embodiments of the present disclosure, and it should be understood that the present disclosure is not limited by the example embodiments described herein.

[0026] To solve the above problems, the present embodiment provides a scheme for evaluating and analyzing compressor flow stability under circumferential distortion, as shown in Figure 1 Figure 1 a flow chart of a method for evaluating and analyzing compressor flow stability under circumferential distortion according to an example embodiment of the present disclosure is shown, which can be applied in a terminal device, which can be a computer, a notebook or a tablet computer, etc. As shown in Figure 1 the method according to the present embodiment can include:

[0027] Step S101, constructing Euler control equations of a compressor to be evaluated;

[0028] wherein the flow field parameters in the Euler control equations are functions of the circumferential coordinates of the compressor.​

[0029] Step S102: Based on the small perturbation assumption and the Euler control equation, the small perturbation equation of the compressor is obtained, and the small perturbation equation is solved based on the flow field data at multiple circumferential points to obtain the small perturbation solution of the compressor.

[0030] Step S103: Based on the excitation disk model and parallel compressor theory, determine the boundary conditions of the blades inside the compressor, and determine the system stability characteristic equation of the compressor under the condition of non-uniform circumferential flow field according to the boundary conditions and small disturbance solution.

[0031] Step S104: Determine the flow stability assessment result of the compressor based on the solution result of the system stability characteristic equation.

[0032] In summary, the analytical method for evaluating compressor flow stability under circumferential distortion provided in this disclosure has two advantages. First, in the constructed Euler control equations of the compressor, the flow field parameters are functions of the compressor's circumferential coordinates. This allows the small perturbation equations, obtained based on the small perturbation assumption and the compressor's Euler control equations, to more accurately characterize the small perturbation of circumferential waves within the compressor under non-uniform circumferential flow fields. Second, by considering flow field data at multiple circumferential points to solve the small perturbation equations, a small perturbation solution considering the non-uniform circumferential flow field is obtained. Based on this small perturbation solution and the solution results of the compressor's system stability characteristic equation under non-uniform circumferential flow fields, constructed using the boundary conditions of the compressor blades, the stability of the compressor is analyzed, thus improving the accuracy of the flow stability evaluation results for high-load compressors with non-uniform circumferential flow fields.

[0033] The following are Figure 1 The specific implementation methods of each step in the illustrated embodiment are described in detail below:

[0034] In step S101, the terminal device can construct the Euler control equations for the compressor to be evaluated.

[0035] In this embodiment of the disclosure, the Euler control equation refers to the control equation of the compressor determined by combining the Euler formula, wherein the flow field parameters in the Euler control equation are functions of the circumferential coordinates of the compressor.

[0036] In one optional implementation, the process of constructing the Euler control equations for the compressor to be evaluated by the terminal device may include: determining the flow field parameters in the Euler equations as functions of the circumferential coordinates of the compressor, wherein the flow field parameters include fluid density, fluid velocity, and fluid pressure; and assuming that the process inside the single channel in the circumferential direction is isentropic, replacing the energy equation in the Euler equations with the sound velocity equation to obtain the Euler control equations for the compressor, wherein the Euler control equations for the compressor are:

[0037]

[0038] In formula 1, ρ is fluid density, is fluid velocity, p is fluid pressure, γ is specific heat ratio, and θ is circumferential coordinate under cylindrical coordinate system; is mass continuity equation, is momentum equation, is sound speed equation. The Euler control equation of the compressor can be constructed by determining the flow field parameters as functions of the circumferential coordinate, so as to facilitate the system stability analysis of the compressor with circumferential flow unevenness based on flow field data at multiple circumferential points.

[0039] It can be understood that, in the embodiments of the present disclosure, ρ θ is a function of fluid density with respect to circumferential coordinate, is a function of fluid velocity with respect to circumferential coordinate, p θ is a function of fluid pressure with respect to circumferential coordinate; and γ is specific heat ratio, which is generally taken as 1.4 for air.

[0040] In step S102, the terminal device obtains a small disturbance equation of the compressor based on the small disturbance assumption and the Euler control equation, and solves the small disturbance equation based on flow field data at multiple circumferential points to obtain a small disturbance solution of the compressor.

[0041] In the embodiments of the present disclosure, the small disturbance assumption determines the flow field parameters as a sum of flow field parameter average and flow field parameter small disturbance; and the flow field data at multiple circumferential points are obtained by simulating the working process of the compressor by a simulation software model.

[0042] In an optional implementation, the process in which the terminal device obtains the small disturbance equation of the compressor based on the small disturbance assumption and the Euler control equation can include: determining, based on the small disturbance assumption, the flow field parameters in the Euler control equation as a sum of flow field parameter average and flow field parameter small disturbance to obtain the flow field parameter characterization equation, wherein the flow field parameter average is:

[0043]

[0044] In formula 2, is flow field parameter average, r and z are respectively radial coordinate and axial coordinate under cylindrical coordinate system, n is the number of circumferential selected points on the circumferential wave number of the circumferential distortion disturbance, m is the circumferential wave number of the disturbance, and N is the truncated Fourier series, which can be determined based on actual needs, and the embodiments of the present disclosure do not limit this;

[0045] The flow field parameter small disturbance is:

[0046]

[0047] In formula 3, q' is a small disturbance quantity of the flow field parameter, ω is a complex characteristic frequency, and τ is a virtual time.

[0048] The flow field parameter equation is:

[0049]

[0050] Further, based on the flow field parameter representation equation and the Euler control equation, the small disturbance equation of the compressor is obtained.

[0051] In formula 4, q is the flow field parameter. The flow field parameter representation equation can be determined based on the small disturbance assumption through the average quantity and the small disturbance quantity of the flow field parameter, and the small disturbance equation of the compressor is obtained. Since the average quantity and the small disturbance quantity of the flow field parameter are related to the number of circumferential sampling points on the circumferential wave number of the circumferential distortion disturbance, the circumferential wave number and / or the circumferential coordinate, the small disturbance of the compressor under the circumferential flow field unevenness can be more accurately represented.

[0052] It can be understood that, in the case where q is the fluid density, formula 4 is Similarly, in the case where q is the fluid velocity and the fluid density, the form of formula 4 is similar to that in the case where q is the fluid density; therefore, the function of the flow field parameter in the compressor with respect to the circumferential coordinate of the compressor can be obtained by substituting formula 2 and formula 3 into formula 4.

[0053] It should be noted that, in the embodiments of the present disclosure, the process of constructing the Euler control equation of the compressor by the terminal device is implemented in response to the Euler control equation construction operation of the compressor; similarly, the process of constructing the flow field parameter representation equation in the compressor by the terminal device is implemented in response to the flow field parameter representation equation construction operation in the compressor.

[0054] In an optional implementation, the terminal device obtains the small perturbation equation of the compressor based on the flow field parameter representation equation and the Euler control equation, which can include: assuming that the average amount of the flow field parameter satisfies the Euler equation, updating the flow field parameter in the Euler equation based on the average amount of the flow field parameter to obtain an updated Euler equation; and determining the difference between the Euler control equation and the updated Euler equation as the small perturbation equation of the compressor according to the flow field parameter representation equation. In the process of determining the small perturbation equation of the compressor according to the difference between the Euler control equation and the updated Euler equation, it is assumed that the flow field parameter in a small range (mainly a single blade passage) in the circumferential direction is still averaged according to the parallel compressor assumption, and then the circumferential non-average amount and the high-order small amount can be omitted to obtain the small perturbation equation of the compressor. The small perturbation equation is a single passage small perturbation equation, and the small perturbation equation of the compressor is:

[0055]

[0056] In formula 5, ρ' is the fluid density perturbation, is the fluid velocity perturbation, and p' is the fluid pressure perturbation. Based on the linear stability analysis method, it can be determined that the average amount of the flow field parameter also satisfies the equation characteristics in the control equation of the compressor. Then, the average amount of the flow field parameter can be used to replace the flow field parameter in the Euler equation to obtain an updated Euler equation. The difference between the Euler control equation of the compressor and the updated Euler equation is determined as the small perturbation equation of the compressor based on the relationship between the average amount of the flow field parameter, the small perturbation amount of the flow field parameter, and the flow field parameters in the flow field parameter representation equation, so as to ensure that the obtained small perturbation equation of the compressor has high accuracy in representing the perturbation in the compressor.

[0057] In an optional implementation, the terminal device solves the small perturbation equation based on the flow field data at multiple circumferential points to obtain the small perturbation solution of the compressor, which can include: performing Helmholtz decomposition on the small perturbation equation to obtain a pressure perturbation equation in a non-rotational field; further, solving the pressure perturbation equation based on the flow field data at multiple circumferential points to obtain a pressure perturbation solution; then, substituting the pressure perturbation solution into the small perturbation equation to obtain a density perturbation solution and a velocity perturbation solution in the non-rotational field, wherein the velocity perturbation solution includes a circumferential velocity perturbation solution and an axial velocity perturbation solution; and finally, determining the pressure perturbation solution, the density perturbation solution, the circumferential velocity perturbation solution, and the axial velocity perturbation solution as the small perturbation solution of the compressor. The flow field data at multiple circumferential points can be considered to solve the small perturbation equation to obtain the small perturbation solution considering the circumferential non-uniform flow field, so as to realize accurate evaluation of the stability of the compressor under the circumferential non-uniform flow field.

[0058] It should be noted that, in the embodiments of this disclosure, the density perturbation solution and the velocity perturbation solution in the divergence-free field and the zero velocity field can also be solved separately. It can be found that the form of their solution is consistent with the homogeneous ordinary differential equation of the perturbation solution in the irrotational field. Therefore, the form of the solution can be merged into the density perturbation solution and the velocity perturbation solution. Since the pressure perturbation solution in the divergence-free field and the zero velocity field is 0, the final pressure perturbation solution usually includes the pressure perturbation solution in the irrotational field.

[0059] The terminal device performs Helmholtz decomposition on the small perturbation equation to obtain the pressure perturbation equation in the irrotational field as follows:

[0060]

[0061] It should be noted that, in the embodiments of this disclosure, during the process of determining the pressure perturbation equation in an irrotational field, since there is a velocity potential in the irrotational field, it can be assumed that the circumferential perturbation velocity of the fluid is... The axial disturbance velocity of the fluid is in, Let the velocity potential be denoted by , and the velocity vectors of the fluid circumferential disturbance velocity and the fluid axial disturbance velocity be denoted by . The number of circumferential selection points n on the circumferential wavenumber of the circumferential distortion perturbation can be determined based on actual needs, and the embodiments disclosed herein do not limit this.

[0062] The solution to the pressure disturbance is:

[0063]

[0064] In Equation 7, p′ is the pressure disturbance value matrix, Y F2 Let Λ be the left eigenvector of the characteristic matrix of the pressure disturbance equation system, and let a be the pressure wave amplitude matrix. Fz For matrix e Fz The eigenvalues ​​are arranged diagonally, e Fz Let z be the matrix exponent, where z is the axial distance.

[0065] In matrix F, D = (IW 2 A)M,

[0066] in,

[0067] It should be noted that 'a' is the pressure amplitude matrix vector, which can be divided into two parts, a1 and a2. a1 is related to the ascending wave of the pressure wave, and its characteristic is that Λ corresponds to a1. Fz The eigenvalue is e iλz(λ is the eigenvalue of the matrix F), and the real part of λ is the same as the sign of the real part of ω solved below; a2 is related to the downward wave of the pressure wave, and Λ Fz the real part of λ is opposite to the sign of the real part of ω below.

[0068] The density disturbance solution is:

[0069]

[0070] The circumferential velocity disturbance solution is:

[0071]

[0072] The axial velocity disturbance solution is:

[0073]

[0074] In formula 8, formula 9 and formula 10, ρ' is the density disturbance matrix, v' is the circumferential velocity disturbance matrix, w' is the axial velocity disturbance matrix, b is the density wave amplitude matrix, c is the velocity wave amplitude matrix, and Y Hz is the left eigenvector matrix of the matrix e Hz , Λ Hz is the eigenvalue of e Hz , e Hz = Y Hz Λ Hz Y Hz -1 , Λ -Hs is the eigenvalue of e -Hz , N is the total circumferential wave number of the circumferential distortion disturbance, Y F1 is the submatrix in , Λ Fs is the eigenvalue of the matrix e Hs , wherein s is the integral quantity.

[0075] In step S103, the terminal device can determine the boundary condition of the blade in the compressor based on the actuator disk model and the parallel compressor theory, and determine the system stability characteristic equation of the compressor under the circumferential flow field uneven condition according to the boundary condition and the small disturbance solution.

[0076] In the embodiment of the present disclosure, the actuator disk model can assume that the blade of the compressor is an actuator disk without thickness, and the parallel compressor theory is used in the circumferential direction, so that the flow characteristics of the air flow on the front and back sides of the blade in the compressor can be determined, including the mass conservation, the total pressure lumped loss condition, the Kutta condition, and other flow characteristics. The other flow characteristics can be determined based on the actual situation, and the present disclosure is not limited thereto.

[0077] In an alternative embodiment, the process of determining the boundary conditions of the blade in the compressor based on the actuator disk model and the parallel compressor theory can include: determining the flow characteristics of the front and back side air flows of the blade in the compressor based on the actuator disk model and the parallel compressor theory; further, constructing the flow characteristic equation of the front and back side air flows of the blade to obtain the boundary conditions of the blade in the compressor; wherein the flow characteristics include the mass conservation, the total pressure lumped loss condition, the Kutta condition and the conservation of the rotational enthalpy; the flow characteristics of the air flows on both sides of the blade in the compressor can be determined based on the actuator disk model and the parallel compressor theory, and the flow characteristic equation of the blade is constructed based on the flow characteristics as the boundary conditions, so as to construct a more accurate characteristic equation of the system stability of the compressor under the condition of the non-uniform circumferential flow field.

[0078] wherein the mass conservation equation constructed under the mass conservation condition is:

[0079] (ρw′+wρ′) - =(ρw′+wρ′) + ; (equation 11)

[0080] The rotational enthalpy conservation equation constructed under the rotational enthalpy conservation condition is:

[0081]

[0082] In equation 12, Ω is the rotational speed of the compressor, and the direction is from the inlet to the outlet according to the right-hand rule. The Kutta condition equation constructed under the Kutta condition is:

[0083] (wv′-(v-Ωr)w′) + =0; (equation 13)

[0084] wherein the process of constructing the total pressure lumped loss condition equation under the total pressure lumped loss condition can include:

[0085] The total pressure loss coefficient ζ is defined as:

[0086] ζ=p t - -p t + ; (equation 14)

[0087] In equation 14, wherein R is the average radius of the compressor.

[0088] and, assuming that the relative total pressure loss coefficient ζ is equal to the tangent value of the relative inlet air flow angle β1, then:

[0089] ζ=ζ(tanβ1); (equation 15)

[0090] In equation 15, The small perturbation of the tangent value of the relative inlet flow angle is

[0091] Further, since there is a response delay between the total pressure instantaneous loss coefficient ζ' disturbance and the inlet velocity disturbance, it is assumed that a first-order delay equation is satisfied between them, and then:

[0092]

[0093] Next, formula 14 is substituted into formula 16, and formula 15 is combined to obtain the initial total pressure lumped loss condition equation as:

[0094]

[0095] Further, the initial total pressure lumped loss condition equation is moved to obtain the total pressure lumped loss condition equation as:

[0096]

[0097] In an optional implementation, the flow characteristics include mass conservation, total enthalpy conservation, total pressure lumped loss condition, and Courant condition, and the process in which the terminal device determines the system stability characteristic equation of the compressor under the circumferential flow field inhomogeneity according to the boundary condition and the small perturbation solution can include:

[0098] The small perturbation solution is substituted into the boundary condition, and an inlet and outlet parameter condition is added to obtain the system stability characteristic equation of the compressor under the circumferential flow field inhomogeneity, wherein the system stability characteristic equation is:

[0099]

[0100] In formula 19, 0 I 0 0[0] 1×4n is the downward pressure wave matrix of the inlet, 0 0 I 0[0] 1×4n is the downward density wave matrix of the inlet, 0 0 0 I[0] 1×4n is the downward velocity wave matrix of the inlet, [0] 1×4nI 0000 is an outlet upstream pressure wave matrix, A1 is a pressure amplitude matrix of the front side of the blade under the mass conservation condition, B1 is a density amplitude matrix of the front side of the blade under the mass conservation condition, C1 is a velocity amplitude matrix of the front side of the blade under the mass conservation condition, E1 is a pressure amplitude matrix of the back side of the blade under the mass conservation condition, F1 is a density amplitude matrix of the back side of the blade under the mass conservation condition, G1 is a velocity amplitude matrix of the back side of the blade under the mass conservation condition, A2 is a pressure amplitude matrix of the front side of the blade under the total enthalpy conservation condition, B2 is a density amplitude matrix of the front side of the blade under the total enthalpy conservation condition, C2 is a velocity amplitude matrix of the front side of the blade under the total enthalpy conservation condition, E2 is a pressure amplitude matrix of the back side of the blade under the total enthalpy conservation condition, F2 is a density amplitude matrix of the back side of the blade under the total enthalpy conservation condition, G2 is a velocity amplitude matrix of the back side of the blade under the total enthalpy conservation condition, A3 is a pressure amplitude matrix of the front side of the blade under the total pressure lumping loss condition, B3 is a density amplitude matrix of the front side of the blade under the total pressure lumping loss condition, C3 is a velocity amplitude matrix of the front side of the blade under the total pressure lumping loss condition, E3 is a pressure amplitude matrix of the back side of the blade under the total pressure lumping loss condition, F3 is a density amplitude matrix of the back side of the blade under the total pressure lumping loss condition, G3 is a velocity amplitude matrix of the back side of the blade under the total pressure lumping loss condition, A4 is a pressure amplitude matrix of the front side of the blade under the Kutta condition, B4 is a density amplitude matrix of the front side of the blade under the Kutta condition, C4 is a velocity amplitude matrix of the front side of the blade under the Kutta condition, E4 is a pressure amplitude matrix of the back side of the blade under the Kutta condition, F4 is a density amplitude matrix of the back side of the blade under the Kutta condition, G4 is a velocity amplitude matrix of the back side of the blade under the Kutta condition, a1 is a pressure amplitude matrix of the downward pressure wave inside the compressor, a2 is a pressure amplitude matrix of the upward pressure wave inside the compressor, b is a density amplitude matrix, c is a velocity amplitude matrix, - represents the front side of the blade, and + represents the back side of the blade. The flow characteristics of the two sides of the blade in the compressor represented by the mass conservation, the total enthalpy conservation, the total pressure lumping loss condition, and the Kutta condition are used to construct the system stability characteristic equation of the compressor under the circumferential flow field non-uniformity, so as to improve the matching degree of the system state represented by the system stability characteristic equation of the compressor under the circumferential flow field non-uniformity and the actual state of the circumferential flow field non-uniform compressor system, and improve the accuracy of the flow stability evaluation result of the determined compressor.

[0101] It should be noted that in the embodiments of the present disclosure, the inlet and outlet parameter conditions can include: downward pressure waves at the inlet, downward density waves at the inlet, downward velocity waves at the inlet, and upward pressure waves at the outlet.

[0102] In step S104, the terminal device determines the flow stability evaluation result of the compressor according to the solution result of the system stability characteristic equation.

[0103] In an alternative implementation, the process of determining the flow stability evaluation result of the compressor according to the solution of the system stability eigen-equation can include:

[0104] The system stability eigen-equation belonging to the closed equation is simplified into an updated system stability eigen-equation, which is:

[0105] X(ω)δ=0; (Equation 20)

[0106] In Equation 20, δ is the unknown in Equation 19, that is, the matrix X(ω) is the coefficient matrix, that is, the matrix

[0107] Then, the updated system stability eigen-equation is solved based on the singular value decomposition method to obtain the value of the complex characteristic frequency. Further, if the imaginary part of the complex characteristic frequency is less than zero, it is determined that the system of the compressor is unstable; or if the imaginary part of the complex characteristic frequency is greater than zero, it is determined that the system of the compressor is stable.

[0108] It should be noted that in the embodiments of the present disclosure, the updated system stability eigen-equation is a homogeneous equation set, and the necessary and sufficient condition for the existence of small perturbations of the compressor system is det(X(ω))=0, and the complex characteristic frequency is solved by the singular value decomposition method, and the imaginary part of the complex characteristic frequency can represent whether the flow state of the compressor is stable.

[0109] The exemplary embodiments of the present disclosure provide a compressor flow stability evaluation analytic device under circumferential distortion, which can be a server or a chip applied to a server. Figure 2 A functional module schematic block diagram of the compressor flow stability evaluation analytic device under circumferential distortion according to the exemplary embodiments of the present disclosure is shown. As shown in Figure 2 The compressor flow stability evaluation analytic device under circumferential distortion 200 includes:

[0110] The construction module 201 is configured to construct the Euler control equation of the compressor to be evaluated, and the flow field parameters in the Euler control equation are functions of the circumferential coordinates of the compressor;

[0111] The acquisition module 202 is configured to obtain the small perturbation equation of the compressor based on the small perturbation assumption and the Euler control equation, and solve the small perturbation equation based on the flow field data at a plurality of circumferential points to obtain the small perturbation solution of the compressor;

[0112] The first determining module 203 is configured to determine the boundary condition of the blade in the compressor based on the disk model and the parallel compressor theory, and determine the system stability characteristic equation of the compressor under the condition of the non-uniform circumferential flow field according to the boundary condition and the small disturbance solution.

[0113] The second determining module 204 is configured to determine the flow stability evaluation result of the compressor according to the solution result of the system stability characteristic equation.

[0114] Optionally, the constructing module 201 is configured to:

[0115] determine the flow field parameters in the Euler equation as functions of the circumferential coordinate of the compressor, wherein the flow field parameters include fluid density, fluid velocity and fluid pressure;

[0116] replace the energy equation in the Euler equation with the sound speed equation assuming that the single-channel interior in the circumferential direction is an isentropic process, to obtain the Euler control equation of the compressor, wherein the Euler control equation of the compressor is:

[0117]

[0118] wherein ρ is the fluid density, is the fluid velocity, p is the fluid pressure, γ is the specific heat ratio, and θ is the circumferential coordinate in the cylindrical coordinate system.

[0119] Optionally, the obtaining module 202 is configured to:

[0120] determine the flow field parameters in the Euler control equation as the sum of the average amount of the flow field parameters and the small disturbance amount of the flow field parameters based on the small disturbance assumption, to obtain the flow field parameter representation equation, wherein the average amount of the flow field parameters is:

[0121]

[0122] wherein, is the average amount of the flow field parameters, r and z are respectively the radial coordinate and the axial coordinate in the cylindrical coordinate system, n is the circumferential selected point number on the circumferential wave number of the circumferential distortion disturbance, m is the circumferential wave number of the disturbance amount, and N is the truncated Fourier series.

[0123] the small disturbance amount of the flow field parameters is:

[0124]

[0125] wherein q′ is the small disturbance amount of the flow field parameters, ω is the complex characteristic frequency, and τ is the virtual time:

[0126]

[0127] wherein q is a flow field parameter;

[0128] Based on the flow field parameter representation equation and the Euler control equation, a small disturbance equation of the compressor is obtained.

[0129] Optionally, the obtaining module 202 is configured to:

[0130] In a case where it is determined that the flow field parameter average quantity satisfies the Euler equation, a flow field parameter in the Euler equation is updated based on the flow field parameter average quantity, to obtain an updated Euler equation;

[0131] According to the flow field parameter representation equation, a difference between the Euler control equation and the updated Euler equation is determined as the small disturbance equation of the compressor, and the small disturbance equation of the compressor is:

[0132]

[0133] wherein ρ′ is a fluid density disturbance, is a fluid velocity disturbance, and p′ is a fluid pressure disturbance.

[0134] Optionally, the obtaining module 202 is configured to:

[0135] The small disturbance equation is subjected to Helmholz decomposition to obtain a pressure disturbance equation in a non-rotational field;

[0136] Based on flow field data at a plurality of circumferential points, the pressure disturbance equation is solved to obtain a pressure disturbance solution;

[0137] The pressure disturbance solution is substituted into the small disturbance equation to obtain a density disturbance solution and a velocity disturbance solution in a non-rotational field, a non-divergent field and a zero velocity field, wherein the velocity disturbance solution includes a circumferential velocity disturbance solution and an axial velocity disturbance solution;

[0138] The pressure disturbance solution, the density disturbance solution, the circumferential velocity disturbance solution and the axial velocity disturbance solution are determined as the small disturbance solution of the compressor.

[0139] Optionally, the first determining module 203 is configured to:

[0140] Based on a cascade model and a parallel compressor theory, flow characteristics of front and back side airflows of a blade in the compressor are determined, wherein the flow characteristics include mass conservation, total enthalpy conservation, total pressure lumped loss condition and Kutta condition;

[0141] Flow characteristic equations of the front and back side airflows of the blade are constructed to obtain boundary conditions of the blade in the compressor.

[0142] Optionally, the first determining module 203 is configured to:

[0143] The small perturbation solution is substituted into the boundary conditions and added to the import and export parameter conditions to obtain a system stability characteristic equation of the compressor under the condition of circumferential flow field unevenness, and the system stability characteristic equation is:

[0144]

[0145] Wherein, 0 I 0 0[0] 1×4n is a down-transmitted pressure wave matrix of the import, 0 0 I 0[0] 1×4n is a down-transmitted density wave matrix of the import, 0 0 0 I[0] 1×4n is a down-transmitted velocity wave matrix of the import, [0] 1×4n I 0 0 0 is an up-transmitted pressure wave matrix of the export, A1 is a pressure amplitude matrix of the front side of the blade under the mass conservation condition, B1 is a density amplitude matrix of the front side of the blade under the mass conservation condition, C1 is a velocity amplitude matrix of the front side of the blade under the mass conservation condition, E1 is a pressure amplitude matrix of the back side of the blade under the mass conservation condition, F1 is a density amplitude matrix of the back side of the blade under the mass conservation condition, G1 is a velocity amplitude matrix of the back side of the blade under the mass conservation condition, A2 is a pressure amplitude matrix of the front side of the blade under the total enthalpy conservation condition, B2 is a density amplitude matrix of the front side of the blade under the total enthalpy conservation condition, C2 is a velocity amplitude matrix of the front side of the blade under the total enthalpy conservation condition, E2 is a pressure amplitude matrix of the back side of the blade under the total enthalpy conservation condition, F2 is a density amplitude matrix of the back side of the blade under the total enthalpy conservation condition, G2 is a velocity amplitude matrix of the back side of the blade under the total enthalpy conservation condition, A3 is a pressure amplitude matrix of the front side of the blade under the total pressure lumped loss condition, B3 is a density amplitude matrix of the front side of the blade under the total pressure lumped loss condition, C3 is a velocity amplitude matrix of the front side of the blade under the total pressure lumped loss condition, E3 is a pressure amplitude matrix of the back side of the blade under the total pressure lumped loss condition, F3 is a density amplitude matrix of the back side of the blade under the total pressure lumped loss condition, G3 is a velocity amplitude matrix of the back side of the blade under the total pressure lumped loss condition, A4 is a pressure amplitude matrix of the front side of the blade under the Kutta condition, B4 is a density amplitude matrix of the front side of the blade under the Kutta condition, C4 is a velocity amplitude matrix of the front side of the blade under the Kutta condition, E4 is a pressure amplitude matrix of the back side of the blade under the Kutta condition, F4 is a density amplitude matrix of the back side of the blade under the Kutta condition, G4 is a velocity amplitude matrix of the back side of the blade under the Kutta condition, a1 is a pressure amplitude matrix of the down-transmitted pressure wave inside the compressor, a2 is a pressure amplitude matrix of the up-transmitted pressure wave inside the compressor, b is a density amplitude matrix, c is a velocity amplitude matrix, - indicates the front side of the blade, and + indicates the back side of the blade.

[0146] The exemplary embodiments of the present disclosure further provide an electronic device, comprising: at least one processor; and a memory connected with the at least one processor in communication. The memory stores a computer program capable of being executed by the at least one processor, and the computer program, when executed by the at least one processor, is configured to cause the electronic device to perform the method according to the embodiments of the present disclosure.

[0147] The exemplary embodiments of the present disclosure further provide a non-transitory computer readable storage medium storing a computer program, wherein the computer program, when executed by a processor of a computer, is configured to cause the computer to perform the method according to the embodiments of the present disclosure.

[0148] As shown in Figure 3 The exemplary embodiments of the present disclosure further provide a computer program product 300, comprising a computer program 301, wherein the computer program, when executed by a processor of a computer, is configured to cause the computer to perform the method according to the embodiments of the present disclosure.

[0149] Referring to Figure 4 , a block diagram of the structure of an electronic device 400 that can be a terminal device of the present disclosure will now be described, which is an example of a hardware device that can be applied to various aspects of the present disclosure. The electronic device is intended to represent a wide variety of digital electronic computer devices, such as laptops, desktops, workstations, personal digital assistants, servers, blade servers, mainframes, and other suitable computers. The electronic device can also represent a wide variety 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 meant to be examples only, and are not meant to limit implementations of the present disclosure described and / or claimed in this document.

[0150] As shown in Figure 4 The electronic device 400 includes a computing unit 401 that can perform various appropriate actions and processes in accordance with a computer program stored in a read-only memory (ROM) 402 or a computer program loaded into a random access memory (RAM) 403 from a storage unit 408. In the RAM 403, various programs and data required for the operation of the electronic device 400 can also be stored. The computing unit 401, the ROM 402, and the RAM 403 are connected to each other through a bus 404. An input / output (I / O) interface 405 is also connected to the bus 404.

[0151] A plurality of components in the electronic device 400 are connected to the I / O interface 405, including: an input unit 406, an output unit 407, a storage unit 408, and a communication unit 409. The input unit 406 can be any type of device that can input information to the electronic device 400, 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 407 can be any type of device that can present 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 408 can include, but is not limited to, a magnetic disk, an optical disk. The communication unit 409 allows the electronic device 400 to exchange information / data with other devices through a computer network such as the Internet and / or various telecommunication networks, 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, such as a Bluetooth™ device, a WiFi device, a WiMax device, a cellular communication device, and / or the like.

[0152] The computing unit 401 can be various general and / or special purpose processing components having processing and computing capabilities. Some examples of the computing unit 401 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 401 performs various methods and processes described above. For example, in some embodiments, the methods of the present embodiments can be implemented as a computer software program tangibly embodied in a machine-readable medium, such as the storage unit 408. In some embodiments, portions or all of the computer program can be loaded and / or installed onto the electronic device 400 via the ROM 402 and / or the communication unit 409. In some embodiments, the computing unit 401 can be configured to perform the methods of the present embodiments by any other appropriate means, such as by means of firmware.

[0153] Program code for carrying out methods of the present disclosure can be written in any combination of one or more programming languages. The program code can be provided to a processor or controller of a general purpose computer, special purpose computer, or other programmable data processing apparatus to produce a machine, such that the program code, when executed by the processor or controller, produces a function / operation specified in the flowchart and / or block diagram. The program code can be executed entirely on a machine, partially on a machine, partially on a machine as a stand-alone software package, and partially on a remote machine or a server.

[0154] In the context of this disclosure, a machine-readable medium can be a tangible medium that contains or stores a program for use by or in connection with an instruction execution system, apparatus, or device. The machine-readable medium can be a machine-readable signal medium or a machine-readable storage medium. A machine-readable 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 foregoing. More specific examples of a machine-readable storage medium will include one or more lines of electrical connections, portable computer disks, hard disk drives, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or Flash memory), optical fibers, portable compact disc read-only memories (CD-ROMs), optical storage devices, magnetic storage devices, or any suitable combination of the foregoing.

[0155] As used in this disclosure, the terms "machine-readable medium" and "computer- readable medium" refer to any computer program product, apparatus and / or device (e.g., magnetic discs, optical disks, memory, Programmable Logic Devices (PLDs)) used to provide machine instructions and / or data to a programmable processor, including a machine-readable medium that receives machine instructions as a machine-readable signal. The term "machine-readable signal" refers to any signal used to provide machine instructions and / or data to a programmable processor.

[0156] To provide for interaction with a user, the systems and techniques described here can be implemented on a computer having a display device (e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor) for displaying information to the user and a keyboard and a pointing device (e.g., a mouse or a trackball) by which the user can provide input to the computer. Other kinds of devices can be used to provide for interaction with a user as well; for example, feedback provided to the user can be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user can be received in any form, including acoustic, speech, or tactile input.

[0157] The systems and techniques described here can be implemented in a computing system that includes a back end component, e.g., as a data server, or that includes a middleware component, e.g., an application server, or that includes a front end component, e.g., a user computer having a graphical user interface or a Web browser through which a user can interact with an implementation of the systems and techniques described here, or any combination of such back end, middleware, or front end components. The components of the system can be interconnected by any form or medium of digital data communication, e.g., a communication network. Examples of communication networks include a local area network (LAN), a wide area network (WAN), and the Internet.

[0158] The computer system can include clients and servers. A client and server are generally remote from each other and typically interact through a communication network. The relationship of client and server arises by virtue of computer programs running on the respective computers and having a client-server relationship to each other.

[0159] In the embodiments described above, all or some of the steps can be implemented by software, hardware or firmware, or any combination thereof. When implemented by software, all or some of the steps can be implemented by one or more computer program or instructions. When loaded on a computer, the computer program or instructions can execute on the computer and perform all or some of the steps described in the embodiments of the present disclosure. The computer can be a general purpose computer, a special purpose computer, a computer network, a terminal, user equipment, or other programmable apparatus. The computer program or instructions can be stored in a computer readable storage medium or transmitted from one computer readable storage medium to another, e.g., from a website, a computer, a server or a data center to another website, computer, server or data center through a wired or wireless way. The computer readable storage medium can be any available medium or a combination of one or more of the available media that is accessible by a computer. The available medium can be a magnetic medium, e.g., a floppy diskette, a hard disk, a magnetic tape; an optical medium, e.g., a compact disk (CD), a digital video disk (DVD); a semiconductor medium, e.g., a solid state disk (SSD).

[0160] Although the present disclosure has been described in connection with certain specific features and embodiments thereof, it is to be understood that it is provided as an exemplification of the principles of the present disclosure and the features set forth herein are intended to be illustrative rather than limiting, and that numerous modifications and variations therein can be expected by those skilled in the art. Accordingly, it should be understood that the description and drawings are illustrative of the present disclosure and are not intended to be limiting. It should be understood that various changes can be made to the implementations described and the embodiments presented herein without departing from the spirit and scope of the present disclosure. It is intended that all such changes be considered as within the scope of the present disclosure.

Claims

1. An analytical method for assessing compressor flow stability under circumferential distortion, characterized in that, The method comprises the following steps: constructing an Euler control equation of a compressor to be evaluated, wherein a flow field parameter in the Euler control equation is a function of a circumferential coordinate of the compressor; obtaining a small disturbance equation of the compressor based on a small disturbance assumption and the Euler control equation, and solving the small disturbance equation based on flow field data at a plurality of circumferential points to obtain a small disturbance solution of the compressor; determining a boundary condition of a blade in the compressor based on a disk model and a parallel compressor theory, and determining a system stability characteristic equation of the compressor under a circumferential flow field uneven condition according to the boundary condition and the small disturbance solution; determining a flow stability evaluation result of the compressor according to a solving result of the system stability characteristic equation.

2. The method for assessing compressor flow stability under circumferential distortion according to claim 1, wherein, The method of constructing the Euler control equation of the compressor to be evaluated comprises the following steps: determining the flow field parameter in the Euler equation as a function of the circumferential coordinate of the compressor, wherein the flow field parameter comprises fluid density, fluid velocity and fluid pressure; assuming that a single-channel interior in the circumferential direction is an isentropic process, and replacing an energy equation in the Euler equation with a sound speed equation to obtain the Euler control equation of the compressor, the Euler control equation of the compressor being: ； wherein, is the fluid density, is the fluid velocity, is the fluid pressure, is the specific heat ratio, is the circumferential coordinate in cylindrical coordinates.

3. The method for assessing compressor flow stability under circumferential distortion according to claim 1, wherein The method of obtaining the small disturbance equation of the compressor based on the small disturbance assumption and the Euler control equation comprises the following steps: determining, based on the small disturbance assumption, that the flow field parameter in the Euler control equation is a sum of a flow field parameter average and a flow field parameter small disturbance to obtain a flow field parameter representation equation, the flow field parameter average being: ； wherein is the average value of the flow field parameter, and are the radial coordinate and axial coordinate in cylindrical coordinate system, respectively, is the number of circumferential sampling points on the circumferential wave number of the circumferential distortion disturbance, is the truncated Fourier series, is the circumferential coordinate in cylindrical coordinate system; the flow field parameter small disturbance being: ； wherein, is a small perturbation of the flow field parameter, is a complex eigenfrequency, is a virtual time, is a circumferential wave number of the perturbation. the flow field parameter representation equation being: ； wherein is a flow field parameter; obtaining the small disturbance equation of the compressor based on the flow field parameter representation equation and the Euler control equation.

4. The method for assessing compressor flow stability under circumferential distortion according to claim 3, wherein, The method of obtaining the small disturbance equation of the compressor based on the flow field parameter representation equation and the Euler control equation comprises the following steps: in a case where the flow field parameter average satisfies the Euler equation, updating the flow field parameter in the Euler equation based on the flow field parameter average to obtain an updated Euler equation; determining, according to the flow field parameter representation equation, a difference between the Euler control equation and the updated Euler equation as the small disturbance equation of the compressor, the small disturbance equation of the compressor being: ； wherein, is a fluid density perturbation, is a fluid velocity perturbation, is a fluid pressure perturbation, is a circumferential coordinate in cylindrical coordinates.

5. The method for assessing compressor flow stability under circumferential distortion as recited in claim 1, wherein, The method of solving the small disturbance equation based on the flow field data at the plurality of circumferential points to obtain the small disturbance solution of the compressor comprises the following steps: performing Helmholz decomposition on the small disturbance equation to obtain a pressure disturbance equation in a non-rotation field; solving the pressure disturbance equation based on the flow field data at the plurality of circumferential points to obtain a pressure disturbance solution; substituting the pressure disturbance solution, the density disturbance solution, the circumferential velocity disturbance solution and the axial velocity disturbance solution into the small disturbance equation to obtain a density disturbance solution and a velocity disturbance solution in a non-rotation field, a non-diffusion field and a zero velocity field, wherein the velocity disturbance solution comprises a circumferential velocity disturbance solution and an axial velocity disturbance solution; determining the pressure disturbance solution, the density disturbance solution, the circumferential velocity disturbance solution and the axial velocity disturbance solution as the small disturbance solution of the compressor.

6. The method for assessing compressor flow stability under circumferential distortion according to claim 1, wherein The method of determining the boundary condition of the blade in the compressor based on the disk model and the parallel compressor theory comprises the following steps: Determine flow characteristics of the front and back side air flows of the blade in the compressor based on a disk model and a parallel compressor theory, wherein the flow characteristics include mass conservation, total enthalpy conservation, total pressure lumped loss condition and Kutta condition; Construct flow characteristic equations of the front and back side air flows of the blade to obtain boundary conditions of the blade in the compressor.

7. The method for assessing compressor flow stability under circumferential distortion according to claim 6, wherein Determine a system stability characteristic equation of the compressor under circumferential flow field non-uniformity based on the boundary conditions and the small perturbation solution, wherein the system stability characteristic equation is: Substitute the small perturbation solution into the boundary conditions and add inlet and outlet parameter conditions to obtain the system stability characteristic equation of the compressor under circumferential flow field non-uniformity, wherein the system stability characteristic equation is: ； wherein, is the down-going pressure wave matrix at the inlet, is the down-going density wave matrix at the inlet, is the down-going velocity wave matrix at the inlet, is the up-going pressure wave matrix at the outlet, is the pressure amplitude matrix at the front side of the blade under mass conservation condition, is the density amplitude matrix at the front side of the blade under mass conservation condition, is the velocity amplitude matrix at the front side of the blade under mass conservation condition, is the pressure amplitude matrix at the back side of the blade under mass conservation condition, is the density amplitude matrix at the back side of the blade under mass conservation condition, is the velocity amplitude matrix at the back side of the blade under mass conservation condition, is the pressure amplitude matrix at the front side of the blade under total enthalpy conservation condition, is the density amplitude matrix at the front side of the blade under total enthalpy conservation condition, is the velocity amplitude matrix at the front side of the blade under total enthalpy conservation condition, is the pressure amplitude matrix at the back side of the blade under total enthalpy conservation condition, is the density amplitude matrix at the back side of the blade under total enthalpy conservation condition, is the velocity amplitude matrix at the back side of the blade under total enthalpy conservation condition, is the pressure amplitude matrix at the front side of the blade under total pressure lumped loss condition, is the density amplitude matrix at the front side of the blade under total pressure lumped loss condition, is the velocity amplitude matrix at the front side of the blade under total pressure lumped loss condition, is the pressure amplitude matrix at the back side of the blade under total pressure lumped loss condition, is the density amplitude matrix at the back side of the blade under total pressure lumped loss condition, is the velocity amplitude matrix at the back side of the blade under total pressure lumped loss condition, is the pressure amplitude matrix at the front side of the blade under Kutta condition, is the density amplitude matrix at the front side of the blade under Kutta condition, is the velocity amplitude matrix at the front side of the blade under Kutta condition, is the pressure amplitude matrix at the back side of the blade under Kutta condition, is the density amplitude matrix at the back side of the blade under Kutta condition, is the velocity amplitude matrix at the back side of the blade under Kutta condition, is the pressure amplitude matrix of the down-going pressure wave inside the compressor, is the pressure amplitude matrix of the up-going pressure wave inside the compressor, is the density amplitude matrix, is the velocity amplitude matrix, - denotes the front side of the blade and + denotes the back side of the blade.

8. An analytical device for assessing the stability of a flow in a compressor with circumferential distortion, characterized in that Comprise: A constructing module configured to construct Euler control equations of a compressor to be evaluated, wherein flow field parameters in the Euler control equations are functions of circumferential coordinates of the compressor; An obtaining module configured to obtain small perturbation equations of the compressor based on small perturbation assumptions and the Euler control equations, and solve the small perturbation equations based on flow field data at a plurality of circumferential points to obtain small perturbation solutions of the compressor; A first determining module configured to determine boundary conditions of the blade in the compressor based on a disk model and a parallel compressor theory, and determine a system stability characteristic equation of the compressor under circumferential flow field non-uniformity based on the boundary conditions and the small perturbation solutions; A second determining module configured to determine a flow stability evaluation result of the compressor based on a solution result of the system stability characteristic equation.

9. An electronic device comprising a memory, a processor, and a computer program stored on the memory, wherein the computer program, when executed by the processor, is arranged to perform the method of any one of claims 1 to 8. The processor executes the computer program to implement the circumferential distortion under compressor flow stability evaluation analytic method of any one of claims 1 to 7.

10. A computer-readable storage medium having stored thereon a computer program, characterized in that, The computer program is executed by the processor to implement the circumferential distortion under compressor flow stability evaluation analytic method of any one of claims 1 to 7.

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