Gas-solid two-phase flow-based compressor aerodynamic stability evaluation method and device, electronic equipment and storage medium

Abstract

The present disclosure relates to the technical field of aero-engine compressors, and particularly provides a method and device for evaluating aerodynamic stability of a compressor based on gas-solid two-phase flow, an electronic device and a storage medium. In view of the complex gas-solid two-phase flow inside an aero-compressor, the method for evaluating aerodynamic stability of the compressor based on the gas-solid two-phase flow comprises: constructing a control equation based on the gas-solid two-phase flow, wherein the control equation represents the influence of blade geometry on the flow field through a blade force source term and represents the influence of solid particles on the flow field through a particle force source term; constructing an eigenvalue equation according to the control equation; and evaluating the aerodynamic stability according to the eigenvalue equation. The technical solution of the embodiment of the present disclosure can solve the technical problem of huge calculation amount of aerodynamic stability evaluation under the gas-solid two-phase flow, and quickly and accurately evaluate the aerodynamic stability of the compressor.

Description

Technical Field

[0001] This disclosure relates to the field of aero-engine compressor technology, and in particular to a method, apparatus, electronic device and storage medium for evaluating the aerodynamic stability of a compressor based on gas-solid two-phase flow. Background Technology

[0002] With the development of the aviation industry, the application scenarios of aero engines are becoming increasingly complex. As the power source for aircraft, they will inevitably face challenges from various harsh conditions during operation, such as dust storms, hail, and passing through volcanic clouds. This places higher demands on the stability and safety of aero engines. In the above-mentioned conditions, high-speed solid particles will be drawn into the engine, forming a gas-solid two-phase flow inside the engine.

[0003] The existing method for achieving compressor aerodynamic stability under gas-solid two-phase flow is to use unsteady numerical simulation, which has the following drawbacks: the aerodynamic stability assessment involves a large amount of computation and is slow. Summary of the Invention

[0004] This disclosure is made in view of the above-mentioned problems. This disclosure provides a method, apparatus, electronic equipment, and storage medium for evaluating the aerodynamic stability of a compressor based on gas-solid two-phase flow.

[0005] According to one aspect of this disclosure, a method for evaluating the aerodynamic stability of a compressor based on gas-solid two-phase flow is provided, comprising:

[0006] A control equation based on gas-solid two-phase flow is constructed, wherein the control equation represents the influence of blade geometry on the flow field through the blade force source term, and represents the influence of solid particles on the flow field through the particle force source term;

[0007] Based on the governing equations, construct the eigenvalue equations;

[0008] The aerodynamic stability is evaluated based on the eigenvalue equation.

[0009] Furthermore, according to one aspect of this disclosure, a compressor aerodynamic stability assessment method based on gas-solid two-phase flow includes the following governing equations:

[0010]

[0011] Where ρ represents fluid density, t represents time, V represents gas phase velocity vector, π represents second-order stress tensor containing normal and shear stresses, f represents blade force vector per unit flow rate, and S... p The particle force vector representing unit flow rate, e t Let λ represent the total internal energy, λ represent the thermal conductivity, T represent the temperature, ρf·V represent the work done by the blade forces, and ρS represent the total internal energy. p ·V represents the work done by particle forces. Indicates heat conduction, This indicates heat generation.

[0012] Furthermore, according to a compressor aerodynamic stability assessment method based on gas-solid two-phase flow according to one aspect of this disclosure, the blade force source term and the particle force source term are constructed, including:

[0013] Construct the first-order Taylor expansion equations for the perturbation quantities of the blade force source term and the particle force source term;

[0014] A delay equation is constructed to describe the response of blade force disturbances and particle force disturbances to flow field disturbances;

[0015] A Fourier expansion equation is constructed, which is based on the assumptions of circumferential uniformity and steady flow, and the Fourier expansion of the disturbance in the circumferential direction and time is performed.

[0016] Based on the first-order Taylor expansion equation, the delay equation, and the Fourier expansion equation, the blade force source term and the particle force source term are constructed.

[0017] Furthermore, according to one aspect of this disclosure, a method for evaluating the aerodynamic stability of a compressor based on gas-solid two-phase flow includes constructing eigenvalue equations based on the governing equations, comprising:

[0018] Based on the control equations, construct the cylindrical coordinate expansion equations of the control equations;

[0019] Based on the cylindrical coordinate expansion equation, a linearized small perturbation equation for the flow field with time-averaged flow as the background is constructed.

[0020] Based on the linearized small perturbation equation, the eigenvalue equation is constructed.

[0021] Furthermore, according to one aspect of this disclosure, a method for evaluating the aerodynamic stability of a compressor based on gas-solid two-phase flow includes constructing the cylindrical coordinate expansion equation of the control equation, which comprises:

[0022] Based on the assumptions, the expansion equations of the control equations in cylindrical coordinates are constructed according to the control equations.

[0023] The assumptions include one or more of the following:

[0024] The time-averaged background flow inside the compressor is simplified into a circumferentially uniform, adiabatic gas-solid two-phase flow.

[0025] The influence of circumferential non-uniformity within the blade passage is considered through the blade force source term;

[0026] The governing equations exclude circumferential flow nonuniformity and take into account axial and radial flow nonuniformity.

[0027] The governing equations do not explicitly include viscous terms; losses caused by viscosity are incorporated into the blade force source term.

[0028] And / or,

[0029] The process of constructing linearized small perturbation equations for the flow field with time-averaged flow as the background, based on the cylindrical coordinate expansion equations, includes:

[0030] The transient flow parameters are decomposed into two parts: time-averaged and small disturbance quantities, forming the transient flow parameter decomposition equation;

[0031] Based on the transient flow parameter decomposition equation and the cylindrical coordinate expansion equation, a linearized small perturbation equation for the flow field with time-averaged flow rate as the background is constructed.

[0032] Furthermore, according to one aspect of this disclosure, a compressor aerodynamic stability assessment method based on gas-solid two-phase flow is used to construct the eigenvalue equation based on the linearized small perturbation equation, including:

[0033] Obtain the Fourier expansion equation, which is the equation obtained by performing Fourier expansion of the disturbance in the circumferential direction and time under the assumption of circumferential uniformity and steady flow.

[0034] The eigenvalue equation is constructed based on the linearized small perturbation equation and the Fourier expansion equation.

[0035] Furthermore, according to one aspect of this disclosure, a method for evaluating the aerodynamic stability of a compressor based on gas-solid two-phase flow includes the eigenvalue equation comprising:

[0036]

[0037]

[0038] Where i represents the imaginary unit; ω represents the angular frequency; ρ represents the density; u, v, w represent the radial, circumferential, and axial velocity components of the gas phase velocity vector, respectively; e t h represents total internal energy. t Represents total enthalpy; r, θ, z represent the radial, circumferential, and axial positions in cylindrical coordinates, respectively; m represents the circumferential wavenumber; f r ,f θ ,f z These represent the radial, circumferential, and axial components of the blade force source term, respectively. These represent the radial, circumferential, and axial components of the particle force source term, respectively; p represents pressure; Ω represents angular velocity; the superscript ~ represents the disturbance quantity; and the superscript - represents the time-averaged quantity.

[0039] According to another aspect of this disclosure, a compressor aerodynamic stability assessment device based on gas-solid two-phase flow is provided, comprising:

[0040] The first construction module is used to construct the control equations based on gas-solid two-phase flow. The control equations include distributed blade force source terms and distributed particle force source terms. The distributed blade force source terms are used to express the influence of blade geometry on the flow process, and the distributed particle force source terms are used to express distributed particle forces to represent the influence of solid particle geometry on the flow field.

[0041] The second construction module is used to construct eigenvalue equations based on the control equations;

[0042] An evaluation module is used to evaluate aerodynamic stability based on the eigenvalue equation.

[0043] According to another aspect of this disclosure, an electronic device is provided, including a memory, a processor, and a computer program stored in the memory, the processor executing the computer program to implement the steps of any of the methods described above.

[0044] According to another aspect of this disclosure, a computer-readable storage medium is provided that stores a computer program / instructions thereon, which, when executed by a processor, implement the steps of any of the methods described above.

[0045] As will be described in detail below, a method, apparatus, electronic device, and storage medium for evaluating the aerodynamic stability of a compressor based on gas-solid two-phase flow according to embodiments of this disclosure are provided. By constructing a control equation based on gas-solid two-phase flow, the control equation represents the influence of blade geometry on the flow field through blade force source terms and the influence of solid particles on the flow field through particle force source terms. Based on the control equation, an eigenvalue equation is constructed. Based on the eigenvalue equation, aerodynamic stability is evaluated. This can solve the technical problem of the large amount of calculation required for aerodynamic stability evaluation under gas-solid two-phase flow, and quickly and accurately evaluate aerodynamic stability.

[0046] It should be understood that both the foregoing general description and the following detailed description are exemplary and intended to provide further illustration of the claimed technology. Attached Figure Description

[0047] The above and other objects, features, and advantages of this disclosure will become more apparent from the more detailed description of the embodiments thereof in conjunction with the accompanying drawings. The drawings are provided to further illustrate the embodiments of this disclosure and form part of the specification. They are used together with the embodiments of this disclosure to explain the disclosure and do not constitute a limitation thereof. In the drawings, the same reference numerals generally represent the same components or steps.

[0048] Figure 1This is a flowchart illustrating a compressor aerodynamic stability assessment method based on gas-solid two-phase flow according to an embodiment of the present disclosure.

[0049] Figure 2 This is a flowchart illustrating the construction of the blade force source term and the particle force source term in the compressor aerodynamic stability assessment method based on gas-solid two-phase flow according to an embodiment of the present disclosure.

[0050] Figure 3 This is a flowchart illustrating the construction of eigenvalue equations in the compressor aerodynamic stability assessment method based on gas-solid two-phase flow, which is a further embodiment of the present disclosure.

[0051] Figure 4 This further illustrates the influence region of blade force and particle force in the compressor aerodynamic stability assessment method based on gas-solid two-phase flow according to the embodiments of this disclosure.

[0052] Figure 5 This is a block diagram illustrating a compressor aerodynamic stability evaluation device based on gas-solid two-phase flow according to an embodiment of the present disclosure.

[0053] Figure 6 This is a hardware block diagram illustrating an electronic device according to an embodiment of the present disclosure. Detailed Implementation

[0054] To make the objectives, technical solutions, and advantages of this disclosure more apparent, exemplary embodiments according to this disclosure will now be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are merely some embodiments of this disclosure, and not all embodiments of this disclosure. It should be understood that this disclosure is not limited to the exemplary embodiments described herein.

[0055] See Figure 1 A method for evaluating the aerodynamic stability of a compressor based on gas-solid two-phase flow, comprising:

[0056] S101, construct the control equations based on gas-solid two-phase flow, where the control equations represent the influence of blade geometry on the flow field through the blade force source term, and the influence of solid particles on the flow field through the particle force source term.

[0057] In this embodiment, based on the concept of immersed boundary, the surface boundary immersed in the fluid can be replaced by distributed force source terms. Therefore, after removing the blades inside the compressor, distributed blade force source terms can be used to express the influence of blade geometry on the flow field, and distributed particle force source terms can be used to represent the influence of solid particles on the flow field, ultimately yielding the governing equations. Compared to conventional governing equations, these equations add distributed blade and distributed particle force source terms, allowing the surface boundary immersed in the fluid to be replaced by distributed force source terms, thus reducing subsequent computational load while maintaining accuracy.

[0058] The governing equations are as follows:

[0059]

[0060] Where ρ represents fluid density, t represents time, V represents gas phase velocity vector, π represents second-order stress tensor containing normal and shear stresses, f represents blade force vector per unit flow rate, and S... p The particle force vector representing unit flow rate, e t Let λ represent the total internal energy, λ represent the thermal conductivity, T represent the temperature, ρf·V represent the work done by the blade forces, and ρS represent the total internal energy. p ·V represents the work done by particle forces. Indicates heat conduction, This indicates heat generation.

[0061] The expression for ∏ is: μ is the dynamic viscosity coefficient, and I is a third-order identity matrix. Under the ideal gas assumption, γ is the specific heat ratio, which is typically taken as 1.40 for room temperature air under constant specific heat capacity conditions. Under the adiabatic assumption, and All are zero, which means that the heat conduction term and the heat source term are no longer considered.

[0062] The blade force source terms and particle force source terms in the governing equations can be constructed using relevant methods. Specifically, blade force models and particle force models can be constructed, and then the blade force source terms and particle force source terms can be constructed based on these models. It should be understood that various blade force models and particle force models can be used in the process of constructing the blade force source terms and particle force source terms, and it is not limited to a specific blade force or particle force model.

[0063] In one embodiment, see Figure 2 The specific steps for constructing blade force source terms and particle force source terms include:

[0064] S201, construct the first-order Taylor expansion equations for the perturbation quantities of the blade force source term and the particle force source term.

[0065] The purpose of constructing blade force source terms and particle force source terms is to characterize the influence of blade geometry and solid particles on the flow field. Therefore, during the construction process, it can be expressed as a function of local flow parameters, i.e., f = f1(ρ,u,v,w,p), S p =f2(ρ,u,v,w,p). f represents the blade force vector per unit flow rate, S p The vector represents the particle force per unit flow rate, ρ represents the fluid density, u, v, w represent the radial, circumferential, and axial velocity components of the gas phase velocity vector, respectively, and p represents the pressure.

[0066] The time-averaged value of the source term can be calculated from the time-averaged flow field variables using the above function, while the disturbance quantities of the blade force source term and the particle force source term can be described by a first-order Taylor expansion:

[0067]

[0068] Where f represents the blade force vector per unit flow rate, ρ represents the fluid density, u, v, w represent the radial, circumferential, and axial velocity components of the gas phase velocity vector, respectively, p represents the pressure, and S p The vector represents the particle force per unit flow rate. The superscript ` indicates the disturbance amount, and the superscript - indicates the average value. Equation (2) means that after the flow field is disturbed, the blade force source term and the particle force source term will change instantaneously with the flow field.

[0069] S202, construct a delay equation to describe the response of blade force disturbance and particle force disturbance to flow field disturbance.

[0070] Since the volumetric force source term acts on a fluid mass of finite mass, its change in motion cannot be instantaneous. Therefore, the responses of the blade force source term and the particle force source term to the circumferentially averaged flow field have a time delay. In this step, a first-order delay equation is used to describe the responses of blade force disturbances and particle force disturbances to flow field disturbances.

[0071] The delay equation is as follows:

[0072]

[0073] Where f represents the blade force vector per unit flow rate, the superscript ` indicates the disturbance amount, τ1 represents the delay time, t represents time, and S p τ2 represents the particle force vector per unit flow rate, and τ2 represents the delay time.

[0074] The substitution formula (2) has:

[0075]

[0076] Where τ1 represents the delay time, t represents time, f represents the blade force vector per unit flow rate, the superscript ` indicates the disturbance amount, ρ represents the fluid density, u, v, w represent the radial, circumferential, and axial velocity components of the gas phase velocity vector, respectively, p represents the pressure, τ2 represents the delay time, the superscript - indicates the average value, and S o This represents the particle force vector per unit flow rate.

[0077] S203, Construct the Fourier expansion equation. The Fourier expansion equation is based on the assumptions of circumferential uniformity and steady flow, and performs Fourier expansion of the disturbance in the circumferential direction and time.

[0078] In this step, under the assumption of circumferential uniform and steady flow, the various modes of the disturbance in the circumferential and time directions can be decoupled, and the Fourier expansion equations can be obtained by performing Fourier expansions on them in the circumferential and time directions:

[0079]

[0080] Where q represents any flow parameter, such as The superscript ` indicates the disturbance quantity, ω indicates the complex eigenvalue, and m c The circumferential wavenumber represents the amount of disturbance.

[0081] S204. Based on the first-order Taylor expansion equation, the delay equation, and the Fourier expansion equation, the blade force source term and the particle force source term are constructed.

[0082] Substituting equation (3) into equation (2) yields equation (4), and substituting equation (5) into equation (4) yields the blade force source term. and particulate power source In this embodiment of the disclosure, the blade surface boundary and the particle surface boundary immersed in the fluid are replaced by distributed force source terms, which reduces the amount of computation and improves efficiency.

[0083] S102, Based on the governing equations, construct the eigenvalue equations.

[0084] In this step, eigenvalue equations are constructed based on the governing equations.

[0085] In one embodiment, see Figure 3 Based on the governing equations, eigenvalue equations are constructed, including:

[0086] S301, Based on the governing equations, construct the cylindrical coordinate expansion equations of the governing equations.

[0087] In this step, based on the assumptions, the expansion equations of the governing equations in cylindrical coordinates can be constructed.

[0088] To meet the needs of rapid evaluation in engineering, the time-averaged background flow inside the compressor is simplified into a circumferentially uniform, adiabatic gas-solid two-phase flow. This simplification effectively reduces computational resources and time costs, facilitating rapid stability assessment. Specifically, the circumferential non-uniformity within the blade passage is considered uniformly through the blade force source term. Since engineering studies of sand ingestion problems primarily focus on the radial distribution of particles, the circumferential non-uniform distribution of particles is not considered in this disclosure. Thus, the governing equations only consider flow non-uniformity in the axial and radial dimensions, significantly reducing the computational resources and time required for stability assessment. Furthermore, since the presence of viscous terms would make the momentum and energy equations extremely complex, increasing the computational load for stability assessment, viscous terms are not explicitly included in the governing equations; instead, the losses caused by viscosity are also uniformly considered in the blade force source term. In other words, the assumptions include one or more of the following: simplifying the time-averaged background flow inside the compressor into a circumferentially uniform, adiabatic gas-solid two-phase flow; considering the circumferential non-uniformity within the blade passage through the blade force source term; excluding circumferential flow non-uniformity in the governing equations, and considering axial and radial flow non-uniformity; not explicitly including viscous terms in the governing equations, and incorporating the losses caused by viscosity into the blade force source term.

[0089] Taking the assumption that all the above conditions are included as an example, the expansion equations of the governing equations in cylindrical coordinates are:

[0090]

[0091] Where ρ represents fluid density; t represents time; r, θ, z represent radial, circumferential, and axial coordinates in cylindrical coordinates; u, v, w represent the radial, circumferential, and axial components of the gas phase velocity vector in the absolute coordinate system; f r ,f θ ,f z S represents the radial, circumferential, and axial components of the blade force; p The particle force vector representing a unit flow rate; Represents the radial, circumferential, and axial components of the particle force; p represents pressure; Ω represents the rotor angular velocity in rad / s; ρf θ Ωr represents the work done by the blade force; Indicates work done by particle forces; h t e represents total enthalpy. t The total internal energy, under the ideal gas assumption, is expressed as h. t =γ / (γ-1)×p / ρ+(u 2 +v 2 +w 2 ) / 2,e t =1 / (γ-1)×p / ρ+(u 2 +v 2 +w2 ) / 2, γ represents the specific heat ratio.

[0092] S302, based on the cylindrical coordinate system expansion equation, construct the linearized small perturbation equation for the flow field with time-averaged flow as the background.

[0093] In this step, the transient flow parameters can be decomposed into two parts: time-averaged and small perturbation quantities, forming the transient flow parameter decomposition equation; based on the transient flow parameter decomposition equation and the cylindrical coordinate expansion equation, the linearized small perturbation equation with the time-averaged quantity as the background flow field is constructed.

[0094] The technical solution of this disclosure can focus on the initial stage of instability and uses a linear stability analysis method to simplify the problem. This method decomposes the transient flow parameter q into time-averaged quantities. The two parts q and the small perturbation quantity ′ This forms the transient flow parameter decomposition equation:

[0095]

[0096] Where q represents any flow parameter t represents time; r, θ, and z represent the radial, circumferential, and axial coordinates in cylindrical coordinates, respectively; the superscript - indicates the average value.

[0097] Substituting equation (7) into equation (6), eliminating the zero-order terms in the equation and ignoring small quantities of second order and above, we can obtain the linearized small perturbation equation of the flow field with time-averaged flow as the background.

[0098] S303, based on the linearized small perturbation equation, construct the eigenvalue equation.

[0099] Under the assumption of circumferential uniform and steady flow, the various modes of the disturbance in the circumferential and time directions can be decoupled, and the Fourier expansion of the disturbance in the circumferential and time directions yields the Fourier expansion equation (5):

[0100] Substituting the linearized small perturbation equation into the Fourier expansion and rearranging, we obtain the following eigenvalue equation: Mass equation:

[0101]

[0102] Radial momentum equation:

[0103]

[0104] Circumferential momentum equation:

[0105]

[0106] Axial momentum equation:

[0107]

[0108] Energy equation:

[0109]

[0110] Where i represents the imaginary unit; ω represents the angular frequency; ρ represents the density; u, v, w represent the radial, circumferential, and axial velocity components of the gas phase velocity vector, respectively; e t h represents total internal energy. t Represents total enthalpy; r, θ, z represent the radial, circumferential, and axial positions in cylindrical coordinates, respectively; m represents the circumferential wavenumber; f r ,f θ ,f z These represent the radial, circumferential, and axial components of the blade force source term, respectively. Let represent the radial, circumferential, and axial components of the particle force source term, respectively; p represents pressure; Ω represents angular velocity; the superscript ~ represents the disturbance quantity; and the superscript - represents the time-averaged quantity. After rearranging equations (8-1)-(8-5), we can obtain the eigenvalue equations in matrix form:

[0111]

[0112] For a point within the flow field, A, B, C, E, G, F, and S in equation (9) are all fifth-order coefficient matrices composed of time-averaged flow parameters and their spatial partial derivatives. Specifically, A is the coefficient matrix related to the time-averaged flow of the background flow field; B is the coefficient matrix related to the radial derivative; C is the coefficient matrix related to the circumferential wavenumber and disturbance propagation; E is the coefficient matrix related to the axial derivative; G is the matrix related to the basic linear terms in the background flow field (e.g., background velocity, temperature, density, etc.); and F and S are composed of blade force source terms and particle force source terms, respectively. This represents the amount of disturbance.

[0113] Since the force exerted by the blades on the fluid is limited to the region containing the blade rows, the meridional flow field of the compressor needs to be divided into blade and non-blade regions along the flow direction. The governing equations for the blade region include blade force source terms, while those for the non-blade region do not. In contrast, particle force source terms are distributed throughout the entire meridional flow field, and their magnitude is determined by the particle's physical properties, motion parameters, and flow field parameters. Specific zoning methods and the influence regions of blade and particle forces are discussed below. Figure 4 As shown. In addition, in order to close the eigenvalue equation (9), it is necessary to add boundary conditions on the inlet and outlet boundaries and the hub and casing boundaries, establish corresponding matching conditions in adjacent partitions, and reflect them in the above coefficient matrix so that the eigenvalue equation can reflect the real physical problem.

[0114] S103, Evaluate aerodynamic stability based on eigenvalue equations.

[0115] The complex eigenvalues ​​ω = ω0 of the system can be obtained by solving the above eigenvalue equation using singular value decomposition or the generalized eigenvalue method. r +iω i At this point, based on the imaginary part ω of the eigenvalues... i The sign of ω can be used to evaluate the stability of the system. i When ω > 0, the disturbance increases exponentially with time, inducing system instability. i When the value is less than 0, the system remains stable as the disturbance decays exponentially over time.

[0116] In practical applications, a geometric model of a compressor under sand-swallowing conditions can be obtained. This model can be acquired through 3D mapping or numerical simulation. The time-averaged gas-solid two-phase flow field of this geometric model at different operating flow rates can be obtained. This flow field can be obtained through experimental measurement or steady-state numerical simulation. The obtained time-averaged flow field is the background flow field for the flow instability boundary prediction method developed in this application. The blade geometry and physical quantity information required for the model are extracted from this flow field as input to the model. The geometric information includes: hub, casing, and blade leading and trailing edge profiles, as well as blade geometry information used for blade force modeling. The physical quantity information includes: the rotational angular velocity Ω of each blade row (0 for the stator blade row), and the gas phase physical parameters at each flow rate point. The information includes the corresponding coordinates and solid-phase physical parameters used for particle force modeling, such as average particle volume fraction and particle velocity. By inputting this information into the method of this embodiment, the characteristic value ω of the compression system corresponding to each working flow point can be obtained. Then, based on the sign of the imaginary part of ω, it can be determined whether the compression system is stable at that flow point, i.e., ω... i >0 indicates system instability, ω i <0 indicates system stability.

[0117] See Figure 5 A compressor aerodynamic stability assessment device based on gas-solid two-phase flow, comprising:

[0118] The first construction module 501 is used to construct the control equations based on gas-solid two-phase flow. The control equations include distributed blade force source terms and distributed particle force source terms. The distributed blade force source terms are used to express the influence of blade geometry on the flow process, and the distributed particle force source terms are used to express distributed particle forces to represent the influence of solid particle geometry on the flow field.

[0119] The second construction module 502 is used to construct eigenvalue equations based on the governing equations.

[0120] Evaluation module 503 is used to evaluate aerodynamic stability based on the eigenvalue equation.

[0121] In one embodiment, the first building module is also used to build blade force source terms and particle force source terms;

[0122] Constructing blade force source terms and particle force source terms, including:

[0123] Construct the first-order Taylor expansion equations for the perturbation quantities of the blade force source term and the particle force source term;

[0124] A delay equation is constructed to describe the response of blade force disturbances and particle force disturbances to flow field disturbances;

[0125] The Fourier expansion equation is constructed based on the assumptions of circumferential uniformity and steady flow, and the Fourier expansion of the disturbance in the circumferential and time directions is performed.

[0126] Based on the first-order Taylor expansion equation, the delay equation, and the Fourier expansion equation, the blade force source term and the particle force source term are constructed.

[0127] In one embodiment, the second construction module 502, when constructing the eigenvalue equation based on the governing equation, is specifically used for:

[0128] Based on the governing equations, construct the cylindrical coordinate expansion equations of the governing equations;

[0129] Based on the cylindrical coordinate expansion equation, a linearized small perturbation equation for the flow field with time-averaged flow as the background is constructed.

[0130] Based on the linearized small perturbation equation, eigenvalue equations are constructed.

[0131] In one embodiment, the second construction module 502, when constructing the cylindrical coordinate expansion equations of the control equations based on the control equations, is specifically used for:

[0132] Based on the assumptions, and according to the governing equations, we construct the expansion equations of the governing equations in cylindrical coordinates.

[0133] The assumptions include one or more of the following:

[0134] The time-averaged background flow inside the compressor is simplified into a circumferentially uniform, adiabatic gas-solid two-phase flow.

[0135] The influence of circumferential non-uniformity within the blade passage is considered through the blade force source term;

[0136] The governing equations exclude circumferential flow nonuniformity and consider axial and radial flow nonuniformity.

[0137] The governing equations do not explicitly include viscous terms; losses caused by viscosity are incorporated into the blade force source terms.

[0138] In one embodiment, the second construction module 502, when constructing the linearized small perturbation equations of the flow field with time-averaged flow rate as the background based on the cylindrical coordinate expansion equations, is specifically used for:

[0139] The transient flow parameters are decomposed into two parts: time-averaged and small disturbance quantities, forming the transient flow parameter decomposition equation;

[0140] Based on the transient flow parameter decomposition equation and the cylindrical coordinate expansion equation, a linearized small perturbation equation for the flow field with time-averaged flow rate as the background is constructed.

[0141] In one embodiment, the second construction module 502, when constructing the eigenvalue equation based on the linearized small perturbation equation, is specifically used for:

[0142] Obtain the Fourier expansion equation. The Fourier expansion equation is the equation obtained by performing a Fourier expansion of the disturbance in the circumferential direction and in time under the assumption of circumferential uniform and steady flow.

[0143] Based on the linearized small perturbation equation and the Fourier expansion equation, eigenvalue equations are constructed.

[0144] Exemplary embodiments of this disclosure also provide an electronic device, including: at least one processor; and a memory communicatively connected to the at least one processor. The memory stores a computer program executable by the at least one processor, which, when executed by the at least one processor, causes the electronic device to perform a method according to an embodiment of this disclosure.

[0145] Exemplary embodiments of this disclosure also provide a non-transitory computer-readable storage medium storing a computer program, wherein the computer program, when executed by a computer's processor, is used to cause the computer to perform a method according to embodiments of this disclosure.

[0146] Exemplary embodiments of this disclosure also provide a computer program product, including a computer program, wherein the computer program, when executed by a computer's processor, is used to cause the computer to perform a method according to an embodiment of this disclosure.

[0147] refer to Figure 6 The present invention describes a structural block diagram of an electronic device 600 that can serve as a server or client of the present disclosure, 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, workstations, 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 processors, cellular phones, smartphones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely illustrative and are not intended to limit the implementation of the present disclosure described and / or claimed herein.

[0148] Electronic device 600 includes a computing unit 601, which can perform various appropriate actions and processes based on a computer program stored in read-only memory (ROM) 602 or a computer program loaded into random access memory (RAM) 603 from storage unit 608. The RAM 603 may also store various programs and data required for device operation. The computing unit 601, ROM 602, and RAM 603 are interconnected via bus 604. An input / output (I / O) interface 605 is also connected to bus 604.

[0149] Multiple components in electronic device 600 are connected to I / O interface 605, including: input unit 606, output unit 607, storage unit 608, and communication unit 609. Input unit 606 can be any type of device capable of inputting information to electronic device 600. Input unit 606 can receive input digital or character information and generate key signal inputs related to user settings and / or function control of electronic device. Output unit 607 can be any type of device capable of presenting information and may include, but is not limited to, a display, speaker, video / audio output terminal, vibrator, and / or printer. Storage unit 608 may include, but is not limited to, disks and optical discs. Communication unit 609 allows electronic device 600 to exchange information / data with other devices through computer networks such as the Internet and / or various telecommunications networks, and may include, but is not limited to, modems, network cards, infrared communication devices, wireless communication transceivers, and / or chipsets, such as Bluetooth™ devices, WiFi devices, WiMax devices, cellular communication devices, and / or the like.

[0150] The computing unit 601 can be a variety of general-purpose and / or special-purpose processing components with processing and computing capabilities. Some examples of the computing unit 601 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 suitable processor, controller, microcontroller, etc. The computing unit 601 performs the various methods and processes described above. For example, in some embodiments, the methods of the embodiments of this disclosure can be implemented as a computer software program tangibly contained in a machine-readable medium, such as storage unit 608. In some embodiments, part or all of the computer program can be loaded and / or installed on the electronic device 600 via ROM 602 and / or communication unit 609. In some embodiments, the computing unit 601 can be configured to perform the methods of the embodiments of this disclosure by any other suitable means (e.g., by means of firmware).

[0151] The basic principles of this disclosure have been described above with reference to specific embodiments. However, it should be noted that the advantages, benefits, and effects mentioned in this disclosure are merely examples and not limitations, and should not be considered as essential features of each embodiment of this disclosure. Furthermore, the specific details disclosed above are for illustrative and facilitative purposes only, and are not limitations. These details do not limit the scope of this disclosure to the necessity of employing the aforementioned specific details for implementation.

[0152] The block diagrams of devices, apparatuses, devices, and systems disclosed herein are merely illustrative examples and are not intended to require or imply that they must be connected, arranged, or configured in the manner shown in the block diagrams. As those skilled in the art will recognize, these devices, apparatuses, devices, and systems can be connected, arranged, and configured in any manner. Words such as “comprising,” “including,” “having,” etc., are open-ended terms meaning “including but not limited to,” and are used interchangeably with them. The terms “or” and “and” as used herein refer to the terms “and / or,” and are used interchangeably with them unless the context clearly indicates otherwise. The term “such as” as used herein refers to the phrase “such as but not limited to,” and is used interchangeably with it.

[0153] Additionally, as used herein, the “or” used in a list of items beginning with “at least one” indicates a separate list, such that a list of, for example, “at least one of A, B, or C” means A or B or C, or AB or AC or BC, or ABC (i.e., A and B and C). Furthermore, the word “exemplary” does not imply that the described example is preferred or better than other examples.

[0154] It should also be noted that in the systems and methods of this disclosure, the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered as equivalent solutions to this disclosure.

[0155] Various changes, substitutions, and modifications can be made to the technology described herein without departing from the teachings defined by the appended claims. Furthermore, the scope of the claims of this disclosure is not limited to the specific aspects of the processes, machines, manufactures, events, means, methods, and actions described above. Currently existing or later-developed processes, machines, manufactures, events, means, methods, or actions that perform substantially the same function or achieve substantially the same result as the corresponding aspects described herein can be utilized. Therefore, the appended claims include such processes, machines, manufactures, events, means, methods, or actions within their scope.

[0156] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use this disclosure. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein can be applied to other aspects without departing from the scope of this disclosure. Therefore, this disclosure is not intended to be limited to the aspects shown herein, but rather to be carried out within the widest scope consistent with the principles and novel features disclosed herein.

[0157] The above description has been given for purposes of illustration and description. Furthermore, this description is not intended to limit the embodiments of this disclosure to the forms disclosed herein. Although numerous exemplary aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub-combinations thereof.

Claims

1. A method for evaluating the aerodynamic stability of a compressor based on gas-solid two-phase flow, characterized in that, include: A control equation based on gas-solid two-phase flow is constructed, wherein the control equation represents the influence of blade geometry on the flow field through the blade force source term, and represents the influence of solid particles on the flow field through the particle force source term; Based on the governing equations, construct the eigenvalue equations; Evaluate aerodynamic stability based on the eigenvalue equation; The governing equations include: ； ； ； in, Let t represent fluid density and time. Represents the gas phase velocity vector. This represents the second-order stress tensor that includes both normal and shear stresses. This represents the blade force vector per unit flow rate. Represents the particle force vector per unit flow rate. Represents total internal energy. T represents thermal conductivity, and T represents temperature. This indicates the work done by the blade force. This represents the work done by particle forces. Indicates heat conduction, This indicates heat generation.

2. The method according to claim 1, characterized in that, Constructing the blade force source term and the particle force source term includes: Construct the first-order Taylor expansion equations for the perturbation quantities of the blade force source term and the particle force source term; A delay equation is constructed to describe the response of blade force disturbances and particle force disturbances to flow field disturbances; A Fourier expansion equation is constructed, which is based on the assumptions of circumferential uniformity and steady flow, and the Fourier expansion of the disturbance in the circumferential direction and time is performed. Based on the first-order Taylor expansion equation, the delay equation, and the Fourier expansion equation, the blade force source term and the particle force source term are constructed.

3. The method according to claim 1, characterized in that, The step of constructing eigenvalue equations based on the governing equations includes: Based on the control equations, construct the cylindrical coordinate expansion equations of the control equations; Based on the cylindrical coordinate expansion equation, a linearized small perturbation equation for the flow field with time-averaged flow as the background is constructed. Based on the linearized small perturbation equation, the eigenvalue equation is constructed.

4. The method according to claim 3, characterized in that, The step of constructing the cylindrical coordinate expansion equations of the control equations based on the control equations includes: Based on the assumptions, the expansion equations of the control equations in cylindrical coordinates are constructed according to the control equations. The assumptions include one or more of the following: The time-averaged background flow inside the compressor is simplified into a circumferentially uniform, adiabatic gas-solid two-phase flow. The influence of circumferential non-uniformity within the blade passage is considered through the blade force source term; The governing equations exclude circumferential flow nonuniformity and take into account axial and radial flow nonuniformity. The governing equations do not explicitly include viscous terms; losses caused by viscosity are incorporated into the blade force source term. And / or, The process of constructing linearized small perturbation equations for the flow field with time-averaged flow as the background, based on the cylindrical coordinate expansion equations, includes: The transient flow parameters are decomposed into two parts: time-averaged and small disturbance quantities, forming the transient flow parameter decomposition equation; Based on the transient flow parameter decomposition equation and the cylindrical coordinate expansion equation, a linearized small perturbation equation for the flow field with time-averaged flow rate as the background is constructed.

5. The method according to claim 3, characterized in that, Based on the linearized small perturbation equation, the eigenvalue equation is constructed, including: Obtain the Fourier expansion equation, which is the equation obtained by performing Fourier expansion of the disturbance in the circumferential direction and time under the assumption of circumferential uniformity and steady flow. The eigenvalue equation is constructed based on the linearized small perturbation equation and the Fourier expansion equation.

6. The method according to claim 3, characterized in that, The eigenvalue equation includes: ； ； ； ； ； in, Represents the imaginary unit; Indicates angular frequency; Indicates density; These represent the radial, circumferential, and axial velocity components of the gas phase velocity vector, respectively. Represents total internal energy; Indicates total enthalpy; These represent the radial, circumferential, and axial positions in the cylindrical coordinate system, respectively. Represents the circumferential wave number; These represent the radial, circumferential, and axial components of the blade force source term, respectively. These represent the radial, circumferential, and axial components of the particle force source term, respectively. Indicates pressure; It represents angular velocity; the superscript ~ represents the disturbance quantity; the superscript - represents the time-averaged quantity.

7. A compressor aerodynamic stability evaluation device based on gas-solid two-phase flow, characterized in that, include: The first construction module is used to construct the control equations based on gas-solid two-phase flow. The control equations include distributed blade force source terms and distributed particle force source terms. The distributed blade force source terms are used to express the influence of blade geometry on the flow field, and the distributed particle force source terms are used to represent the influence of solid particle geometry on the flow field using distributed particle forces. The second construction module is used to construct eigenvalue equations based on the control equations; An evaluation module is used to evaluate aerodynamic stability based on the eigenvalue equation; The governing equations include: ； ； ； in, Let t represent fluid density and time. Represents the gas phase velocity vector. This represents the second-order stress tensor that includes both normal and shear stresses. This represents the blade force vector per unit flow rate. Represents the particle force vector per unit flow rate. Represents total internal energy. T represents thermal conductivity, and T represents temperature. This indicates the work done by the blade force. This represents the work done by particle forces. Indicates heat conduction, This indicates heat generation.

8. 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 steps of the method according to any one of claims 1 to 6.

9. A computer-readable storage medium having a computer program / instructions stored thereon, characterized in that, When the computer program / instruction is executed by the processor, it implements the steps of the method described in any one of claims 1 to 6.

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