Method and device for evaluating and analyzing flow stability of gas compressor under circumferential distortion

Abstract

The invention relates to the technical field of gas compressor analysis, and particularly provides a gas compressor flow stability evaluation and analysis method and device under circumferential distortion, and the method comprises the steps: constructing an Euler control equation of a to-be-evaluated gas compressor; obtaining a small disturbance equation of the gas compressor based on a small disturbance hypothesis and the Euler control equation, and solving the small disturbance equation based on the flow field data at the plurality of circumferential points to obtain a small disturbance solution of the gas compressor; determining boundary conditions of blades in the gas compressor based on an excitation disc model and a parallel gas compressor theory, and determining a system stability characteristic equation of the gas compressor under the condition of non-uniform circumferential flow field according to the boundary conditions and a small disturbance solution; determining a flow stability evaluation result of the gas compressor according to a solving result of the system stability characteristic equation; the accuracy of the flow stability evaluation result of the high-load gas compressor with the uneven circumferential flow field can be improved.

Description

Technical Field

[0001] The present disclosure relates to the technical field of compressor analysis, and in particular to a compressor flow stability evaluation and analysis method and device under circumferential distortion. Background Art

[0002] As an important component of the engine, the compressor is limited by the actual conditions in its working scenario. There will be spatial and temporal unevenness at the compressor inlet, which is called intake distortion in the field of aircraft engines. Among them, circumferential distortion is a typical form of spatial distortion. It destroys the uniform flow at the compressor inlet, posing a greater threat to the compressor performance and stability.

[0003] In the related art, in order to study the flow stability problem inside the compressor, the compressor can usually be modeled and analyzed based on the Moore-Greitzer model to determine the stability analysis result of the compressor.

[0004] However, the Moore-Greitzer model is a two-dimensional incompressible model. In the process of analyzing the stability of the compressor, the compressor flow field is assumed to be incompressible, which does not conform to the actual working conditions of the high-load compressor. As a result, the analysis results determined when performing stability analysis on the high-load compressor based on the Moore-Greitzer model are of poor accuracy. Summary of the invention

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

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

[0007] Constructing the Euler control equation of the compressor to be evaluated, wherein the flow field parameters in the Euler control equation are functions of the circumferential coordinates of the compressor;

[0008] Based on the small disturbance hypothesis and the Euler control equation, a small disturbance equation of the compressor is obtained, and the small disturbance equation is solved based on flow field data at multiple circumferential points to obtain a small disturbance solution of the compressor;

[0009] Based on the excitation disk model and the parallel compressor theory, the boundary conditions of the blades in the compressor are determined, and according to the boundary conditions and the small disturbance solution, the system stability characteristic equation of the compressor under the condition of non-uniform circumferential flow field is determined;

[0010] The flow stability evaluation result of the compressor is determined according to the solution result of the system stability characteristic equation.

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

[0012] A construction module, 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, configured to obtain a small disturbance equation of the compressor based on a small disturbance hypothesis 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 the boundary conditions of the blades in the compressor based on the excitation disk model and the parallel compressor theory, 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 the small disturbance solution;

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

[0016] According to another aspect of the present disclosure, an electronic device is provided, comprising a memory, a processor, and a computer program stored in the memory, wherein the processor executes the computer program to implement the above-mentioned analytical method for evaluating compressor flow stability under circumferential distortion.

[0017] According to yet another aspect of the present disclosure, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the analytical method for evaluating compressor flow stability under circumferential distortion is implemented.

[0018] The present invention provides an analytical method and device for evaluating compressor flow stability under circumferential distortion. On the one hand, in the Euler control equation of the compressor constructed, the flow field parameters are functions of the circumferential coordinates of the compressor, so that the small perturbation equation obtained based on the small perturbation hypothesis and the Euler control equation of the compressor can more accurately characterize the small perturbation of the circumferential waves in the compressor under the condition of uneven circumferential flow field; on the other hand, the small perturbation equation is solved by considering the flow field data at multiple circumferential points, and the small perturbation solution considering the circumferential uneven flow field is obtained, and the solution result of the system stability characteristic equation of the compressor under the condition of uneven circumferential flow field constructed based on the small perturbation solution and the boundary conditions of the blades in the compressor is used to analyze the stability of the compressor, thereby improving the accuracy of the flow stability evaluation results of high-load compressors with uneven circumferential flow fields.

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

[0020] The above and other purposes, features and advantages of the present disclosure will become more apparent by describing the embodiments of the present disclosure in more detail in conjunction with the accompanying drawings. The accompanying drawings are used to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and do not constitute a limitation of the present disclosure. In the accompanying drawings, the same reference numerals generally represent the same components or steps.

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

[0022] Figure 2 is a block diagram illustrating an analytical device for evaluating 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 illustrating an electronic device according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0025] In order to make the purpose, technical solution and advantages of the present disclosure more obvious, the exemplary embodiments according to the present disclosure will be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are only 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 to the exemplary embodiments described here.

[0026] In order to solve the above problems, the embodiment of the present disclosure provides an analytical solution for evaluating compressor flow stability under circumferential distortion, such as Figure 1 As shown, Figure 1 A flowchart of a compressor flow stability evaluation and analysis method under circumferential distortion according to an exemplary embodiment of the present disclosure is shown. The method can be applied to a terminal device, which can be a computer, a notebook, or a tablet computer. Figure 1 As shown, the method of the embodiment of the present disclosure may include:

[0027] Step S101, constructing the Euler control equation of the compressor to be evaluated;

[0028] The flow field parameters in the Euler control equation are functions of the circumferential coordinates of the compressor.

[0029] Step S102, based on the small disturbance hypothesis and the Euler control equation, a small disturbance equation of the compressor is obtained, and the small disturbance equation is solved based on the flow field data at multiple circumferential points to obtain a small disturbance solution of the compressor;

[0030] Step S103, based on the excitation disk model and the parallel compressor theory, the boundary conditions of the blades in the compressor are determined, and according to the boundary conditions and the small disturbance solution, the system stability characteristic equation of the compressor under the condition of non-uniform circumferential flow field is determined;

[0031] Step S104, determining the compressor flow stability evaluation result according to the solution result of the system stability characteristic equation.

[0032] In summary, the analytical method for evaluating compressor flow stability under circumferential distortion provided by the embodiment of the present disclosure, on the one hand, in the constructed Euler control equation of the compressor, the flow field parameters are functions of the circumferential coordinates of the compressor, so that the small perturbation equation obtained based on the small perturbation assumption and the Euler control equation of the compressor can more accurately characterize the small perturbation of circumferential waves in the compressor under the condition of uneven circumferential flow field; on the other hand, the small perturbation equation is solved by considering the flow field data at multiple circumferential points, and the small perturbation solution considering the circumferential uneven flow field is obtained, and the system stability characteristic equation of the compressor under the condition of uneven circumferential flow field is constructed based on the small perturbation solution and the boundary conditions of the blades in the compressor. The stability of the compressor is analyzed, thereby improving the accuracy of the flow stability evaluation results of high-load compressors with uneven circumferential flow fields.

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

[0034] In step S101 , the terminal device may construct the Euler control equation of the compressor to be evaluated.

[0035] In the embodiment of the present disclosure, the Euler control equation refers to a control equation of a compressor determined in combination with the Euler formula, and the flow field parameters in the Euler control equation are functions of the circumferential coordinates of the compressor.

[0036] In an optional implementation, the process of constructing the Euler control equation of the compressor to be evaluated by the terminal device may include: determining the flow field parameters in the Euler equation 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 interior of the single channel in the circumferential direction is an isentropic process, replacing the energy equation in the Euler equation with the sound speed equation to obtain the Euler control equation of the compressor, and the Euler control equation of the compressor is:

[0037]

[0038] In formula 1, 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; is the mass continuity equation, is the momentum equation, The Euler control equation of the compressor can be constructed by determining the flow field parameters as functions of the circumferential coordinates, so as to analyze the system stability of the compressor with uneven circumferential flow based on the flow field data at multiple circumferential points.

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

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

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

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

[0043]

[0044] In formula 2, is the average value of the flow field parameters, r and z are the radial coordinate and axial coordinate in the cylindrical coordinate system, respectively, 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. Specifically, it can be determined based on actual needs, and the embodiments of the present disclosure are not limited to this;

[0045] The small disturbance of flow field parameters is:

[0046]

[0047] In Formula 3, q′ is the small perturbation of the flow field parameters, ω is the complex characteristic frequency, and τ is the virtual time.

[0048] The flow field parameter equation is:

[0049]

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

[0051] In formula 4, q is a flow field parameter. Based on the small disturbance hypothesis, the flow field parameter characterization equation can be determined by the average amount and the small disturbance amount of the flow field parameters, and the small disturbance equation of the compressor can be obtained. Since the average amount and the small disturbance amount of the flow field parameters are related to the number of circumferential selected points on the circumferential wave number of the circumferential distortion disturbance, the circumferential wave number and / or the circumferential coordinates of the disturbance amount, the small disturbance of the compressor under the condition of uneven circumferential flow field can be more accurately characterized.

[0052] It can be understood that when q is the fluid density, Formula 4 is Similarly, when q is the fluid velocity and fluid density, the form of Formula 4 is similar to the form of Formula 4 when q is the fluid density; therefore, the function of the flow field parameters in the compressor with respect to the circumferential coordinates of the compressor can be obtained by substituting Formulas 2 and 3 into Formula 4.

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

[0054] In an optional embodiment, the process of obtaining the small perturbation equation of the compressor by the terminal device based on the flow field parameter characterization equation and the Euler control equation may include: assuming that the average amount of the flow field parameters satisfies the Euler equation, updating the flow field parameters in the Euler equation based on the average amount of the flow field parameters 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 characterization equation, wherein, 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, the parallel compressor assumption is that the flow field parameters in a small range (mainly a single blade channel range) in the circumferential direction are still average, then the circumferential uneven amount can be ignored, and after ignoring the high-order small amount, the small perturbation equation of the compressor can be obtained, and the small perturbation equation is the small perturbation equation of a single channel, and the small perturbation equation of the compressor is:

[0055]

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

[0057] In an optional embodiment, 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 may include: performing Helmholz decomposition on the small perturbation equation to obtain the pressure perturbation equation in the irrotational field; further, solving the pressure perturbation equation based on the flow field data at multiple circumferential points to obtain the pressure perturbation solution; then, substituting the pressure perturbation solution into the small perturbation equation to obtain the density perturbation solution and the velocity perturbation solution of the irrotational field, wherein the velocity perturbation solution includes the circumferential velocity perturbation solution and the axial velocity perturbation solution; 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 may be considered to solve the small perturbation equation to obtain the small perturbation solution that considers the circumferential non-uniform flow field, so as to achieve an accurate evaluation of the stability of the compressor under the condition of non-uniform circumferential flow field.

[0058] It should be noted that in the embodiments of the present disclosure, the density perturbation solution and the velocity perturbation solution in the field without dispersion and zero velocity can also be solved separately, and it can be found that the form of the solution is consistent with the homogeneous ordinary differential equation of the irrotational field perturbation solution. Therefore, the form of the solution can be merged into the density perturbation solution and the velocity perturbation solution; and the pressure perturbation solution in the field without dispersion and zero velocity is 0, so 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:

[0060]

[0061] It should be noted that in the embodiment of the present disclosure, in the process of determining the pressure perturbation equation in the 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, is the velocity potential, and the velocity vectors of the fluid circumferential disturbance velocity and the fluid axial disturbance velocity are The number n of circumferential selected points on the circumferential wave number of the circumferential distortion disturbance can be determined based on actual needs, and the embodiments of the present disclosure do not limit this.

[0062] The pressure perturbation solution is:

[0063]

[0064] In formula 7, p′ is the pressure disturbance value matrix, Y F2 is the left eigenvector of the characteristic matrix of the pressure perturbation equations, a is the pressure wave amplitude matrix, Λ Fz is the matrix e Fz The eigenvalues ​​of are arranged along the diagonal, e Fz is the matrix index, where z is the axial distance,

[0065] In the 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. Among them, a1 is related to the upstream wave of the pressure wave. The characteristic is that the Λ corresponding to a1 Fz The eigenvalue of iλz(λ is the eigenvalue of matrix F), and the real part of λ has the same sign as the real part of ω solved in the following passage; a2 is related to the downward propagation of the pressure wave, and the Λ corresponding to a2 is Fz In the eigenvalues ​​of , the real part of λ has the opposite sign to the real part of ω in the following text.

[0068] The density perturbation solution is:

[0069]

[0070] The circumferential velocity perturbation solution is:

[0071]

[0072] The axial velocity perturbation solution is:

[0073]

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

[0075] In step S103, the terminal device may determine the boundary conditions of the blades in the compressor based on the excitation disk model and the parallel compressor theory, 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 the small disturbance solution;

[0076] In the embodiment of the present disclosure, the disk model can assume that the compressor blades are disks without thickness, and adopt the parallel compressor theory in the circumferential direction. The flow characteristics of the airflow on the front and rear sides of the blades in the compressor can be determined, including mass conservation, conversion enthalpy conservation, total pressure lumped loss conditions, Kutta conditions, and other flow characteristics. Among them, other flow characteristics can be determined based on actual conditions, and the embodiment of the present disclosure is not limited to this.

[0077] In an optional embodiment, the process of determining the boundary conditions of the blades in the compressor by the terminal device based on the disk model and the parallel compressor theory may include: determining the flow characteristics of the front and rear airflows of the blades in the compressor based on the disk model and the parallel compressor theory; further, constructing the flow characteristic equations of the front and rear airflows of the blades to obtain the boundary conditions of the blades in the compressor; wherein the flow characteristics include mass conservation, enthalpy conservation, total pressure lumped loss conditions and Kutta conditions; the flow characteristics of the airflows on both sides of the blades in the compressor can be determined based on the disk model and the parallel compressor theory, and the flow characteristic equations of the blades can be constructed as boundary conditions based on the flow characteristics, so as to construct a more accurate characteristic equation that characterizes the system stability of the compressor under the condition of uneven circumferential flow field.

[0078] Among them, the mass conservation equation constructed under the condition of mass conservation is:

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

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

[0081]

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

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

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

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

[0086] ζ=p t - -p t + ;(Formula 14)

[0087] In formula 14, Where 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 intake air flow angle β1, then:

[0089] ζ=ζ(tanβ1); (Formula 15)

[0090] In formula 15, The small perturbation of the tangent value of the relative intake air flow angle is

[0091] Furthermore, since there is a response delay between the total pressure instantaneous loss coefficient ζ′ disturbance and the intake speed disturbance, it is assumed that the first-order delay equation between the two is satisfied, then:

[0092]

[0093] Next, substitute Formula 14 into Formula 16 and combine it with Formula 15 to obtain the initial total pressure lumped loss condition equation:

[0094]

[0095] Furthermore, by shifting the terms of the initial total pressure lumped loss condition equation, the total pressure lumped loss condition equation can be obtained as follows:

[0096]

[0097] In an optional implementation, the flow characteristics include mass conservation, transfer enthalpy conservation, total pressure lumped loss condition, and Kutta condition, and the process of determining, by the terminal device according to the boundary conditions and the small disturbance solution, the system stability characteristic equation of the compressor under the condition of non-uniform circumferential flow field may include:

[0098] Substituting the small disturbance solution into the boundary conditions and adding the inlet and outlet parameter conditions, the system stability characteristic equation of the compressor under the condition of non-uniform circumferential flow field is obtained, 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 imported downlink density wave matrix, 0 0 0 I[0] 1×4n is the imported downlink velocity wave matrix, [0] 1×4nI 0 0 0 is the outlet upstream pressure wave matrix, A1 is the pressure amplitude matrix of the front side of the blade under the condition of mass conservation, B1 is the density amplitude matrix of the front side of the blade under the condition of mass conservation, C1 is the velocity amplitude matrix of the front side of the blade under the condition of mass conservation, E1 is the pressure amplitude matrix of the rear side of the blade under the condition of mass conservation, F1 is the density amplitude matrix of the rear side of the blade under the condition of mass conservation, G1 is the velocity amplitude matrix of the rear side of the blade under the condition of mass conservation, A2 is the pressure amplitude matrix of the front side of the blade under the condition of transfer enthalpy conservation, B2 is the density amplitude matrix of the front side of the blade under the condition of transfer enthalpy conservation, C2 is the velocity amplitude matrix of the front side of the blade under the condition of transfer enthalpy conservation, E2 is the pressure amplitude matrix of the rear side of the blade under the condition of transfer enthalpy conservation, F2 is the density amplitude matrix of the rear side of the blade under the condition of transfer enthalpy conservation, G2 is the velocity amplitude matrix of the rear side of the blade under the condition of transfer enthalpy conservation, A3 is the pressure amplitude matrix of the front side of the blade under the condition of total pressure lumped loss, B3 is the total pressure lumped loss The density amplitude matrix of the front side of the blade under the condition of total pressure lumped loss, C3 is the velocity amplitude matrix of the front side of the blade under the condition of total pressure lumped loss, E3 is the pressure amplitude matrix of the rear side of the blade under the condition of total pressure lumped loss, F3 is the density amplitude matrix of the rear side of the blade under the condition of total pressure lumped loss, G3 is the velocity amplitude matrix of the rear side of the blade under the condition of total pressure lumped loss, A4 is the pressure amplitude matrix of the front side of the blade under the Kutta condition, B4 is the density amplitude matrix of the front side of the blade under the Kutta condition, C4 is the velocity amplitude matrix of the front side of the blade under the Kutta condition, E4 is the pressure amplitude matrix of the rear side of the blade under the Kutta condition, F4 is the density amplitude matrix of the rear side of the blade under the Kutta condition, G4 is the velocity amplitude matrix of the rear side of the blade under the Kutta condition, a1 is the pressure amplitude matrix of the downward pressure wave inside the compressor, a2 is the pressure amplitude matrix of the upward pressure wave inside the compressor, b is the density amplitude matrix, c is the velocity amplitude matrix, - represents the front side of the blade, + represents the rear side of the blade. By using the airflow characteristics on both sides of the compressor blades characterized by the conservation of mass, conservation of transfer enthalpy, total pressure lumped loss conditions, and Kutta conditions, a system stability characteristic equation of the compressor under the condition of uneven circumferential flow field is constructed. The matching degree between the compressor system state characterized by the system stability characteristic equation of the compressor under the condition of uneven circumferential flow field and the actual condition of the compressor system with uneven circumferential flow field can be improved, so as to improve the accuracy of the flow stability evaluation results of the determined compressor.

[0101] It should be noted that, in the embodiment of the present disclosure, the inlet and outlet parameter conditions may include: a downward pressure wave at the inlet, a downward density wave at the inlet, a downward velocity wave at the inlet, and an upward pressure wave 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 optional implementation manner, the process of determining the flow stability evaluation result of the compressor by the terminal device according to the solution result of the system stability characteristic equation may include:

[0104] The system stability characteristic equation belonging to the closed equation is simplified to the updated system stability characteristic equation. The updated system stability characteristic equation is:

[0105] X(ω)δ=0;(Formula 20)

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

[0107] Next, the updated system stability characteristic 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 compressor system is unstable; or, if the imaginary part of the complex characteristic frequency is greater than zero, it is determined that the compressor system is stable.

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

[0109] An exemplary embodiment of the present disclosure provides a compressor flow stability evaluation and analysis device under circumferential distortion. The compressor flow stability evaluation and analysis device under circumferential distortion may be a server or a chip applied to a server. Figure 2 FIG. 1 is a schematic block diagram of the functional modules of a compressor flow stability evaluation and analysis device under circumferential distortion according to an exemplary embodiment of the present disclosure. Figure 2 As shown, the compressor flow stability evaluation and analysis device 200 under circumferential distortion includes:

[0110] A construction module 201 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;

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

[0112] The first determination module 203 is configured to determine the boundary conditions of the blades in the compressor based on the excitation disk model and the parallel compressor theory, 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 the small disturbance solution;

[0113] The second determination 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 construction module 201 is configured to:

[0115] Determine the flow field parameters in the Euler equation as a function of the circumferential coordinates of the compressor, wherein the flow field parameters include fluid density, fluid velocity and fluid pressure;

[0116] Assuming that the interior of the single channel in the circumferential direction is an isentropic process, the energy equation in the Euler equation is replaced by the sound speed equation to obtain the Euler control equation of the compressor:

[0117]

[0118] Where 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 acquisition module 202 is configured to:

[0120] Based on the small disturbance hypothesis, the flow field parameters in the Euler control equation are determined to be the average flow field parameters and the sum of the small disturbance values ​​of the flow field parameters, and the flow field parameter characterization equation is obtained. The average flow field parameters are:

[0121]

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

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

[0124]

[0125] Among them, q′ is the small perturbation of the flow field parameters, ω is the complex characteristic frequency, and τ is the virtual time:

[0126]

[0127] Among them, q is the flow field parameter;

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

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

[0130] When it is determined that the average amount of the flow field parameters satisfies the Euler equation, the flow field parameters in the Euler equation are updated based on the average amount of the flow field parameters to obtain an updated Euler equation;

[0131] According to the flow field parameter characterization equation, the difference between the Euler control equation and the updated Euler equation is determined as the small perturbation equation of the compressor. The small perturbation equation of the compressor is:

[0132]

[0133] Where ρ′ is the fluid density disturbance, is the fluid velocity disturbance, and p′ is the fluid pressure disturbance.

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

[0135] Performing Helmholz decomposition on the small perturbation equation to obtain a pressure perturbation equation in an irrotational field;

[0136] Solving the pressure disturbance equation based on flow field data at a plurality of circumferential points to obtain a pressure disturbance solution;

[0137] Substituting the pressure perturbation solution into the small perturbation equation, obtaining the density perturbation solution and the velocity perturbation solution in the irrotational field, the dispersion-free field and the zero velocity field, wherein the velocity perturbation solution includes the circumferential velocity perturbation solution and the axial velocity perturbation 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 the excitation disk model and the parallel compressor theory, the flow characteristics of the airflow on the front and rear sides of the blades in the compressor are determined, wherein the flow characteristics include mass conservation, transfer enthalpy conservation, total pressure lumped loss condition and Kutta condition;

[0141] The flow characteristic equations of the airflow on the front and rear sides of the blade are constructed to obtain the boundary conditions of the blades in the compressor.

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

[0143] Substituting the small disturbance solution into the boundary conditions and adding the inlet and outlet parameter conditions, the system stability characteristic equation of the compressor under the condition of uneven circumferential flow field is obtained. The system stability characteristic equation is:

[0144]

[0145] Where, 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 imported downlink density wave matrix, 0 0 0 I[0] 1×4n is the imported downlink velocity wave matrix, [0] 1×4n I 0 0 0 is the outlet upstream pressure wave matrix, A1 is the pressure amplitude matrix of the front side of the blade under the condition of mass conservation, B1 is the density amplitude matrix of the front side of the blade under the condition of mass conservation, C1 is the velocity amplitude matrix of the front side of the blade under the condition of mass conservation, E1 is the pressure amplitude matrix of the rear side of the blade under the condition of mass conservation, F1 is the density amplitude matrix of the rear side of the blade under the condition of mass conservation, G1 is the velocity amplitude matrix of the rear side of the blade under the condition of mass conservation, A2 is the pressure amplitude matrix of the front side of the blade under the condition of transfer enthalpy conservation, B2 is the density amplitude matrix of the front side of the blade under the condition of transfer enthalpy conservation, C2 is the velocity amplitude matrix of the front side of the blade under the condition of transfer enthalpy conservation, E2 is the pressure amplitude matrix of the rear side of the blade under the condition of transfer enthalpy conservation, F2 is the density amplitude matrix of the rear side of the blade under the condition of transfer enthalpy conservation, G2 is the velocity amplitude matrix of the rear side of the blade under the condition of transfer enthalpy conservation, A3 is the pressure amplitude matrix of the front side of the blade under the condition of total pressure lumped loss, B3 is the total pressure lumped loss The density amplitude matrix of the front side of the blade under the condition of total pressure lumped loss, C3 is the velocity amplitude matrix of the front side of the blade under the condition of total pressure lumped loss, E3 is the pressure amplitude matrix of the rear side of the blade under the condition of total pressure lumped loss, F3 is the density amplitude matrix of the rear side of the blade under the condition of total pressure lumped loss, G3 is the velocity amplitude matrix of the rear side of the blade under the condition of total pressure lumped loss, A4 is the pressure amplitude matrix of the front side of the blade under the Kutta condition, B4 is the density amplitude matrix of the front side of the blade under the Kutta condition, C4 is the velocity amplitude matrix of the front side of the blade under the Kutta condition, E4 is the pressure amplitude matrix of the rear side of the blade under the Kutta condition, F4 is the density amplitude matrix of the rear side of the blade under the Kutta condition, G4 is the velocity amplitude matrix of the rear side of the blade under the Kutta condition, a1 is the pressure amplitude matrix of the downward pressure wave inside the compressor, a2 is the pressure amplitude matrix of the upward pressure wave inside the compressor, b is the density amplitude matrix, c is the velocity amplitude matrix, - represents the front side of the blade, + represents the rear side of the blade.

[0146] The exemplary embodiment of the present disclosure also provides an electronic device, comprising: at least one processor; and a memory connected to the at least one processor in communication. The memory stores a computer program that can be executed by the at least one processor, and the computer program is used to cause the electronic device to perform the method according to the embodiment of the present disclosure when executed by the at least one processor.

[0147] The exemplary embodiments of the present disclosure also 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 used to cause the computer to perform the method according to the embodiments of the present disclosure.

[0148] like Figure 3 As shown, the exemplary embodiment of the present disclosure further provides a computer program product 300, including a computer program 301, wherein when the computer program is executed by a processor of a computer, it is used to enable the computer to perform the method according to the embodiment of the present disclosure.

[0149] refer to Figure 4 , a block diagram of an electronic device 400 that can be used as 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 various forms of digital electronic computer devices, such as laptop computers, desktop computers, workbenches, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device 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 required herein.

[0150] like Figure 4 As shown, the electronic device 400 includes a computing unit 401, which can perform various appropriate actions and processes according to a computer program stored in a read-only memory (ROM) 402 or a computer program loaded from a storage unit 408 into a random access memory (RAM) 403. 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 via 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 may be any type of device capable of inputting information to the electronic device 400, and the input unit 406 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 407 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 408 may include, but is not limited to, a disk, an optical disk. The communication unit 409 allows the electronic device 400 to exchange information / data with other devices via a computer network such as the Internet and / or various telecommunication networks, 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, such as a Bluetooth™ device, a WiFi device, a WiMax device, a cellular communication device, and / or the like.

[0152] The computing unit 401 may be a variety of general and / or special processing components with 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 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 401 performs the various methods and processes described above. For example, in some embodiments, the method of the exemplary embodiment 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 408. In some embodiments, part or all of the computer program may be loaded and / or installed on the electronic device 400 via ROM 402 and / or communication unit 409. In some embodiments, the computing unit 401 may be configured to perform the method of the exemplary embodiment of the present disclosure by any other appropriate means (e.g., by means of firmware).

[0153] The program code for implementing the method of the present disclosure may be written in any combination of one or more programming languages. These program codes may be provided to a processor or controller of a general-purpose computer, a special-purpose computer, or other programmable data processing device, so that the program code, when executed by the processor or controller, enables the functions / operations specified in the flow chart and / or block diagram to be implemented. The program code may be executed entirely on the machine, partially on the machine, partially on the machine and partially on a remote machine as a stand-alone software package, or entirely on a remote machine or server.

[0154] In the context of the present disclosure, a machine-readable medium 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 equipment. A machine-readable medium may be a machine-readable signal medium or a machine-readable storage medium. A machine-readable medium may include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, device, or equipment, or any suitable combination of the foregoing. A more specific example of a machine-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 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., disk, optical disk, memory, programmable logic device (PLD)) for providing 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 for providing machine instructions and / or data to a programmable processor.

[0156] To provide interaction with a user, the systems and techniques described herein 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 pointing device (e.g., a mouse or trackball) through which the user can provide input to the computer. Other types of devices can also be used to provide interaction with the user; for example, the 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 input, voice input, or tactile input).

[0157] The systems and techniques described herein may be implemented in a computing system that includes back-end components (e.g., as a data server), or a computing system that includes middleware components (e.g., an application server), or a computing system that includes front-end components (e.g., a user computer with a graphical user interface or a web browser through which a user can interact with implementations of the systems and techniques described herein), or a computing system that includes any combination of such back-end components, middleware components, or front-end components. The components of the system may 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] A computer system may include clients and servers. Clients and servers are generally remote from each other and usually interact through a communication network. The relationship of client and server is generated by computer programs running on respective computers and having a client-server relationship to each other.

[0159] In the above embodiments, it can be implemented in whole or in part by software, hardware, firmware or any combination thereof. When implemented by software, it can be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer programs or instructions. When the computer program or instruction is loaded and executed on a computer, the process or function described in the embodiment of the present disclosure is executed in whole or in part. The computer may be a general-purpose computer, a special-purpose computer, a computer network, a terminal, a user device or other programmable device. The computer program or instruction may be stored in a computer-readable storage medium, or transmitted from one computer-readable storage medium to another computer-readable storage medium, for example, the computer program or instruction may be transmitted from one website site, computer, server or data center to another website site, computer, server or data center by wired or wireless means. The computer-readable storage medium may be any available medium that a computer can access or a data storage device such as a server, data center, etc. that integrates one or more available media. The available medium may be a magnetic medium, for example, a floppy disk, a hard disk, a tape; it may also be an optical medium, for example, a digital video disc (DVD); it may also be a semiconductor medium, for example, a solid state drive (SSD).

[0160] Although the present disclosure has been described in conjunction with specific features and embodiments thereof, it is apparent that various modifications and combinations may be made thereto without departing from the spirit and scope of the present disclosure. Accordingly, this specification and the drawings are merely exemplary illustrations of the present disclosure as defined by the appended claims, and are deemed to have covered any and all modifications, variations, combinations or equivalents within the scope of the present disclosure. Obviously, those skilled in the art may make various modifications and variations to the present disclosure without departing from the spirit and scope of the present disclosure. Thus, if these modifications and variations of the present disclosure fall within the scope of the claims of the present disclosure and their equivalents, the present disclosure is also intended to include these modifications and variations.

Claims

1. An analytical method for evaluating compressor flow stability under circumferential distortion, characterized in that: include: Constructing the Euler control equation of the compressor to be evaluated, wherein the flow field parameters in the Euler control equation are functions of the circumferential coordinates of the compressor; Based on the small disturbance hypothesis and the Euler control equation, a small disturbance equation of the compressor is obtained, and the small disturbance equation is solved based on flow field data at multiple circumferential points to obtain a small disturbance solution of the compressor; Based on the excitation disk model and the parallel compressor theory, the boundary conditions of the blades in the compressor are determined, and according to the boundary conditions and the small disturbance solution, the system stability characteristic equation of the compressor under the condition of non-uniform circumferential flow field is determined; The flow stability evaluation result of the compressor is determined according to the solution result of the system stability characteristic equation.

2. The analytical method for evaluating compressor flow stability under circumferential distortion according to claim 1, characterized in that: The Euler control equation of the compressor to be evaluated is constructed, including: Determine the flow field parameters in the Euler equation as a function of the circumferential coordinates of the compressor, wherein the flow field parameters include fluid density, fluid velocity and fluid pressure; Assuming that the interior of the single channel in the circumferential direction is an isentropic process, the energy equation in the Euler equation is replaced by the sound speed equation to obtain the Euler control equation of the compressor, which is: Where 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.

3. The analytical method for evaluating compressor flow stability under circumferential distortion according to claim 1, characterized in that: The small disturbance equation of the compressor is obtained based on the small disturbance assumption and the Euler control equation, including: Based on the small disturbance hypothesis, the flow field parameters in the Euler control equation are determined to be the average flow field parameters and the sum of the small disturbance values ​​of the flow field parameters, and the flow field parameter characterization equation is obtained. The average flow field parameters are: in, is the average value of flow field parameters, r and z are the radial coordinate and axial coordinate in the cylindrical coordinate system, n is the number of circumferential selected points on the circumferential wave number of circumferential distortion disturbance, m is the circumferential wave number of disturbance, and N is the truncated Fourier series; The small disturbance amount of the flow field parameter is: Among them, q′ is the small perturbation of flow field parameters, ω is the complex characteristic frequency, and τ is the virtual time; The flow field parameter characterization equation is: Among them, q is the flow field parameter; Based on the flow field parameter characterization equation and the Euler control equation, the small disturbance equation of the compressor is obtained.

4. The analytical method for evaluating compressor flow stability under circumferential distortion according to claim 3, characterized in that: The small disturbance equation of the compressor is obtained based on the flow field parameter characterization equation and the Euler control equation, including: When it is determined that the average amount of the flow field parameters satisfies the Euler equation, the flow field parameters in the Euler equation are updated based on the average amount of the flow field parameters to obtain an updated Euler equation; According to the flow field parameter characterization equation, the difference between the Euler control equation and the updated Euler equation is determined as the small perturbation equation of the compressor. The small perturbation equation of the compressor is: Where ρ′ is the fluid density disturbance, is the fluid velocity disturbance, and p′ is the fluid pressure disturbance.

5. The analytical method for evaluating compressor flow stability under circumferential distortion according to claim 1, characterized in that: Solving the small disturbance equation based on flow field data at a plurality of circumferential points to obtain a small disturbance solution for the compressor includes: Performing Helmholz decomposition on the small perturbation equation to obtain a pressure perturbation equation in an irrotational field; Solving the pressure disturbance equation based on flow field data at a plurality of circumferential points to obtain a pressure disturbance solution; Substituting the pressure perturbation solution into the small perturbation equation, obtaining the density perturbation solution and the velocity perturbation solution in the irrotational field, the dispersion-free field and the zero velocity field, wherein the velocity perturbation solution includes the circumferential velocity perturbation solution and the axial velocity perturbation solution; 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.

6. The analytical method for evaluating compressor flow stability under circumferential distortion according to claim 1, characterized in that: The boundary conditions of the blades in the compressor are determined based on the excitation disk model and the parallel compressor theory, including: Based on the excitation disk model and the parallel compressor theory, the flow characteristics of the airflow on the front and rear sides of the blades in the compressor are determined, wherein the flow characteristics include mass conservation, transfer enthalpy conservation, total pressure lumped loss condition and Kutta condition; The flow characteristic equations of the airflow on the front and rear sides of the blade are constructed to obtain the boundary conditions of the blades in the compressor.

7. The analytical method for evaluating compressor flow stability under circumferential distortion according to claim 6, characterized in that: Determining the system stability characteristic equation of the compressor under the condition of uneven circumferential flow field according to the boundary conditions and the small disturbance solution includes: Substituting the small disturbance solution into the boundary conditions and adding the inlet and outlet parameter conditions, the system stability characteristic equation of the compressor under the condition of uneven circumferential flow field is obtained. The system stability characteristic equation is: Among them, 0I 00[0] 1×4n is the inlet downward pressure wave matrix, 00I 0[0] 1×4n is the imported downlink density wave matrix, 0 0 0 I [0] 1×4n is the imported downlink velocity wave matrix, [0] 1×4n I 0 0 0 is the outlet upstream pressure wave matrix, A1 is the pressure amplitude matrix of the front side of the blade under the condition of mass conservation, B1 is the density amplitude matrix of the front side of the blade under the condition of mass conservation, C1 is the velocity amplitude matrix of the front side of the blade under the condition of mass conservation, E1 is the pressure amplitude matrix of the rear side of the blade under the condition of mass conservation, F1 is the density amplitude matrix of the rear side of the blade under the condition of mass conservation, G1 is the velocity amplitude matrix of the rear side of the blade under the condition of mass conservation, A2 is the pressure amplitude matrix of the front side of the blade under the condition of transfer enthalpy conservation, B2 is the density amplitude matrix of the front side of the blade under the condition of transfer enthalpy conservation, C2 is the velocity amplitude matrix of the front side of the blade under the condition of transfer enthalpy conservation, E2 is the pressure amplitude matrix of the rear side of the blade under the condition of transfer enthalpy conservation, F2 is the density amplitude matrix of the rear side of the blade under the condition of transfer enthalpy conservation, G2 is the velocity amplitude matrix of the rear side of the blade under the condition of transfer enthalpy conservation, A3 is the pressure amplitude matrix of the front side of the blade under the condition of total pressure lumped loss, B3 is the total pressure lumped loss The density amplitude matrix of the front side of the blade under the condition of total pressure lumped loss, C3 is the velocity amplitude matrix of the front side of the blade under the condition of total pressure lumped loss, E3 is the pressure amplitude matrix of the rear side of the blade under the condition of total pressure lumped loss, F3 is the density amplitude matrix of the rear side of the blade under the condition of total pressure lumped loss, G3 is the velocity amplitude matrix of the rear side of the blade under the condition of total pressure lumped loss, A4 is the pressure amplitude matrix of the front side of the blade under the Kutta condition, B4 is the density amplitude matrix of the front side of the blade under the Kutta condition, C4 is the velocity amplitude matrix of the front side of the blade under the Kutta condition, E4 is the pressure amplitude matrix of the rear side of the blade under the Kutta condition, F4 is the density amplitude matrix of the rear side of the blade under the Kutta condition, G4 is the velocity amplitude matrix of the rear side of the blade under the Kutta condition, a1 is the pressure amplitude matrix of the downward pressure wave inside the compressor, a2 is the pressure amplitude matrix of the upward pressure wave inside the compressor, b is the density amplitude matrix, c is the velocity amplitude matrix, - represents the front side of the blade, + represents the rear side of the blade.

8. A compressor flow stability evaluation and analysis device under circumferential distortion, characterized in that: include: A construction module, 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; an acquisition module, configured to obtain a small disturbance equation of the compressor based on a small disturbance hypothesis 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; A first determination module is configured to determine the boundary conditions of the blades in the compressor based on the excitation disk model and the parallel compressor theory, 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 the small disturbance solution; The second determination module is configured to determine the flow stability evaluation result of the compressor according to the solution result of the system stability characteristic equation.

9. An electronic device comprising a memory, a processor and a computer program stored in the memory, characterized in that: The processor executes the computer program to implement the analytical method for evaluating compressor flow stability under circumferential distortion as described in any one of claims 1 to 7.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the analytical method for evaluating compressor flow stability under circumferential distortion as described in any one of claims 1 to 7 is implemented.

Images