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

Abstract

The invention relates to the technical field of gas compressor analysis, and particularly provides a gas compressor flow stability evaluation analysis method and device under thermal shock distortion, and the method comprises the steps: constructing an Euler equation of a to-be-evaluated gas compressor; a small disturbance equation of the gas compressor is obtained based on a small disturbance hypothesis and an Euler equation, the small disturbance equation is solved based on flow field data in the thermal shock process, and a small disturbance solution of the gas compressor is obtained, based on the assumption that disturbance amplitude change of small disturbance is consistent with thermal shock distortion disturbance change or the thermal shock distortion disturbance is a periodic disturbance assumption, determining; 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 according to the boundary conditions and the small disturbance solution; and determining a flow stability evaluation result of the gas compressor according to a solving result of the system stability characteristic equation. According to the method, the flow stability evaluation difficulty of the gas compressor under the thermal shock distortion condition is reduced.

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 thermal shock distortion. Background Art

[0002] During short-distance takeoff and landing of aviation equipment, the reverse thrust exhaust gas of the engine in the aviation equipment, or the exhaust gas fired by weapons on the aviation equipment, is inhaled into the compressor, which will cause thermal shock distortion at the compressor inlet of the engine, thereby causing the compressor in the engine to fail to operate at the design point, resulting in a decrease in stability in the compressor; therefore, the flow stability evaluation of the compressor becomes increasingly important during the compressor design stage.

[0003] In the related art, in order to study the flow stability of a compressor, the stability index parameters of the compressor can usually be obtained through experiments, or the stability of the compressor can be evaluated by constructing a compressor model.

[0004] However, the compressor flow stability evaluation scheme provided in the related art not only requires a large amount of experimental data but also has high experimental costs; and this compressor flow stability evaluation scheme based on stability layer index parameters or compressor models is usually suitable for compressor flow stability evaluation under uniform air intake conditions, but is not applicable to compressor flow stability evaluation under thermal shock distortion conditions. 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 thermal shock distortion, which improves the accuracy of the flow stability evaluation results of a high-load compressor under thermal shock distortion.

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

[0007] Construct the Euler equations for the compressor to be evaluated;

[0008] Based on the small perturbation hypothesis and the Euler equation, a small perturbation equation of the compressor is obtained, and the small perturbation equation is solved based on the flow field data during the thermal shock process to obtain a small perturbation solution of the compressor, wherein the small perturbation equation is a first small perturbation equation or a second small perturbation equation, the first small perturbation equation is determined based on the assumption that the change in the disturbance amplitude of the small perturbation is consistent with the change in the thermal shock distortion disturbance at the compressor inlet, and the second small perturbation equation is determined based on the assumption that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance;

[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 thermal shock distortion 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, an electronic device is provided, including 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 thermal shock distortion.

[0012] According to 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 thermal shock distortion is implemented.

[0013] The compressor flow stability evaluation and analysis method and device provided by the present disclosure can construct the Euler equation of the compressor based on the assumption that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance, or based on the assumption that the disturbance amplitude change of the small disturbance is consistent with the thermal shock distortion disturbance change at the compressor inlet, and obtain the small disturbance equation considering thermal shock distortion based on the small disturbance assumption and the Euler equation of the compressor, and solve the small disturbance equation based on the flow field data during the thermal shock process to obtain the small disturbance solution considering the thermal shock distortion. Finally, based on the small disturbance solution and the solution result of the system stability characteristic equation of the compressor under the thermal shock distortion constructed by the boundary conditions of the blades in the compressor, the stability of the compressor is analyzed, and the stability analysis of the compressor under the thermal shock distortion scenario is realized. In addition, in the process of performing the compressor stability analysis based on the two assumptions, a large amount of flow field data during the thermal shock process is not required, and no physical model needs to be constructed, which reduces the difficulty of evaluating and analyzing the compressor flow stability under the thermal shock distortion in the thermal shock distortion scenario.

[0014] 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

[0015] 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.

[0016] Figure 1 is a flow chart illustrating an analytical method for evaluating compressor flow stability under thermal shock distortion according to an embodiment of the present disclosure.

[0017] Figure 2 is a block diagram illustrating a compressor flow stability evaluation and analysis device under thermal shock distortion according to an embodiment of the present disclosure.

[0018] Figure 3 is a schematic diagram illustrating a computer program product according to an embodiment of the present disclosure.

[0019] Figure 4 is a hardware block diagram illustrating an electronic device according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0020] 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.

[0021] In the related art, in order to evaluate the flow stability of the compressor, the stability index parameters of the compressor, such as D factor, dimensionless expansion length, viscosity, aspect ratio, etc., can be determined through experiments, and the compressor can be designed based on these stability index parameters; or, a compressor model can be constructed through experimental data to evaluate the compressor stability to guide the compressor design.

[0022] However, the compressor flow stability evaluation scheme based on stability index parameters and compressor models provided in the related art not only requires the manufacture of related compressor components, but also requires the acquisition and processing of a large amount of experimental data, resulting in high experimental costs and long cycles; at the same time, this compressor flow stability evaluation scheme based on stability index parameters and compressor models is generally suitable for compressor flow stability evaluation under uniform air intake conditions, but is not applicable to compressor flow stability evaluation under thermal shock distortion conditions.

[0023] In order to solve the above problems, the present disclosure provides an analytical solution for evaluating compressor flow stability under thermal shock distortion, such as Figure 1 As shown, Figure 1 A flowchart of a compressor flow stability evaluation and analysis method under thermal shock 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:

[0024] Step S101, constructing the Euler equation of the compressor to be evaluated;

[0025] Step S102, based on the small perturbation hypothesis and the Euler equation, a small perturbation equation of the compressor is obtained, and the small perturbation equation is solved based on the flow field data during the thermal shock process to obtain a small perturbation solution of the compressor;

[0026] Among them, the small perturbation equation is the first small perturbation equation or the second small perturbation equation. The first small perturbation equation is determined based on the assumption that the change in the disturbance amplitude of the small perturbation is consistent with the change in the thermal shock distortion disturbance at the compressor inlet. The second small perturbation equation is determined based on the assumption that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance.

[0027] 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 thermal shock distortion is determined;

[0028] Step S104, determining the compressor flow stability evaluation result according to the solution result of the system stability characteristic equation.

[0029] In summary, the analytical method for evaluating compressor flow stability under thermal shock distortion provided by the embodiment of the present disclosure can construct the Euler equation of the compressor based on the assumption that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance, or based on the assumption that the disturbance amplitude change of the small disturbance is consistent with the thermal shock distortion disturbance change at the compressor inlet, and obtain the small disturbance equation considering thermal shock distortion based on the small disturbance assumption and the Euler equation of the compressor, and solve the small disturbance equation based on the flow field data during the thermal shock process to obtain the small disturbance solution considering the thermal shock distortion. Finally, based on the small disturbance solution and the solution result of the system stability characteristic equation of the compressor under the thermal shock distortion constructed by the boundary conditions of the blades in the compressor, the stability of the compressor is analyzed, and the stability analysis of the compressor under the thermal shock distortion scenario is realized. In addition, in the process of compressor stability analysis based on the two assumptions, a large amount of flow field data during the thermal shock process is not required, and no physical model needs to be constructed, which reduces the difficulty of compressor flow stability evaluation under the thermal shock distortion scenario.

[0030] The following Figure 1 The specific implementation methods of each step in the embodiment shown are described in detail:

[0031] In step S101 , the terminal device constructs the Euler equation of the compressor to be evaluated.

[0032] In the disclosed embodiment, in order to determine the control equation of the compressor under the condition of thermal shock distortion, it can be assumed that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance, so that the compressor stability analysis can be performed using the Euler equation of the compressor constructed by referring to the harmonic balance method; or, the compressor stability analysis can be performed directly based on the assumption that the disturbance amplitude change of small disturbances is consistent with the thermal shock distortion disturbance change at the compressor inlet through the traditional Euler equation.

[0033] In an optional implementation, based on the assumption that the disturbance amplitude change of the small disturbance is consistent with the thermal shock distortion disturbance change at the compressor inlet, the terminal device can determine that the Euler equation of the compressor to be evaluated is a first Euler equation in a conservation form:

[0034]

[0035] In an optional implementation, assuming that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance, a small disturbance will also be affected by this and produce a first-order disturbance growth rate; then the terminal device can construct a second Euler equation in a conservation form of the compressor to be evaluated based on the assumption that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance and the first Euler equation in a conservation form. The second Euler equation in a conservation form is:

[0036]

[0037] In Formula 1 and Formula 2, Q=(Q1 Q2 … Q 2n+1 ) T , F=(F1 F2 … F 2n+1 ) T ,G=(G1 G2 …G 2n+1 ) T , ρ is the fluid density, v is the circumferential fluid velocity, w is the axial fluid velocity, p is the fluid pressure, θ is the circumferential coordinate in the cylindrical coordinate system, r and z are the radial coordinate and axial coordinate in the cylindrical coordinate system respectively, e is the internal energy, h is the enthalpy, E is the time spectrum matrix, t is the tth time point among the 2n+1 time points selected in the periodic thermal shock distortion disturbance, τ is the virtual time; among them, n is the number of series composed of the combination of sine function and cosine function after Fourier transform of the periodic thermal shock distortion disturbance.

[0038] Among them, the time spectrum matrix is ​​based on the assumption that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance. Drawing on the harmonic balance method, the flow field parameters at multiple time points selected in the periodic thermal shock distortion disturbance are expanded in Fourier form, and the inverse matrix of the non-Fourier coefficient part matrix and the product of the derivative matrix of the non-Fourier coefficient part matrix with respect to time are determined; wherein, the multiple time points can be 2n+1 time points.

[0039] In step S102, the terminal device obtains a small perturbation equation of the compressor based on the small perturbation hypothesis and the Euler equation, and solves the small perturbation equation based on the flow field data during the thermal shock process to obtain a small perturbation solution of the compressor.

[0040] In the disclosed embodiment, the flow field data during the thermal shock process is obtained by simulating the working process of the compressor of the software model, and the small perturbation equation of the compressor is determined based on the non-conservative form of the Euler equation corresponding to the conservative form of the Euler equation; the non-conservative form of the Euler equation includes the non-conservative form of the first Euler equation, or the non-conservative form of the second Euler equation.

[0041] Among them, the first Euler equation in non-conservative form is:

[0042]

[0043] In formula 3, is the mean circumferential fluid velocity, w is the mean axial fluid velocity, is the mean fluid density, is the radial coordinate mean, and γ is the specific heat ratio.

[0044] It should be noted that in the non-conservative form of the first Euler equation, is the mass continuity equation, and is the momentum equation, is the speed of sound equation, which is equivalent to the energy equation under isentropic conditions.

[0045] By referring to the second Euler equation in the conservation form, the second Euler equation in the non-conservation form is obtained as follows:

[0046]

[0047] In formula 4, E iis the i-th row in the time spectrum matrix, ρ is the fluid density matrix at multiple time points selected in the periodic thermal shock distortion disturbance, v is the circumferential fluid velocity matrix at multiple time points selected in the periodic thermal shock distortion disturbance, w is the axial fluid velocity matrix at multiple time points selected in the periodic thermal shock distortion disturbance, and p is the fluid pressure matrix at multiple time points selected in the periodic thermal shock distortion disturbance.

[0048] It should be noted that in the non-conservative form of the first Euler equation, is the mass continuity equation, and is the momentum equation, is the energy equation.

[0049] It should be noted that in the embodiment of the present disclosure, the small perturbation equation is the first small perturbation equation or the second small perturbation equation. The first small perturbation equation is determined based on the assumption that the change in the disturbance amplitude of the small perturbation is consistent with the change in the thermal shock distortion disturbance at the compressor inlet. The second small perturbation equation is determined based on the assumption that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance.

[0050] In an optional embodiment, the Euler equation is a first Euler equation in a non-conservative form. The process of obtaining the small perturbation equation of the compressor by the terminal device based on the small perturbation assumption and the Euler equation may include: when it is determined that the average amount of the flow field parameters satisfies the first Euler equation in a non-conservative form, updating the flow field parameters in the first Euler equation in a non-conservative form based on the average amount of the flow field parameters to obtain an updated first equation; further, according to the linearization principle of the flow field parameters, determining the difference between the first Euler equation in a non-conservative form and the updated first equation as the first small perturbation equation of the compressor, and based on the assumption that the disturbance amplitude change of the small perturbation is consistent with the disturbance change of the thermal shock distortion at the compressor inlet, determining the small perturbation amount of the flow field parameter in the first small perturbation equation as:

[0051]

[0052] In Formula 5, k q is the rate of change of the small disturbance amplitude, and the rate of change of the small disturbance amplitude is the same as the rate of change of the thermal shock distortion disturbance at the compressor inlet; wherein, the rate of change of the thermal shock distortion disturbance at the compressor inlet is determined based on the flow field information obtained after modeling the compressor under thermal shock conditions.

[0053] Wherein, the first small perturbation equation is:

[0054]

[0055] In Formula 6, ρt ′ is the fluid density disturbance at the tth time point in the thermal shock distortion disturbance, v t ′ is the circumferential fluid velocity disturbance at the tth time point, w t ′ is the circumferential fluid velocity disturbance at the tth time point, p t ′ is the fluid pressure disturbance at the tth time point, is the mean circumferential fluid velocity at the tth time point, is the mean axial fluid velocity at the tth time point, is the mean value of the fluid density at the tth time point. Based on the assumption that the change in the disturbance amplitude of the small disturbance is consistent with the change in the thermal shock distortion disturbance at the compressor inlet, the flow field parameters in the first small disturbance equation can be updated so that the updated first small disturbance equation can characterize the change in the small disturbance caused by thermal shock through the change in the thermal shock distortion disturbance at the compressor inlet, without increasing the complexity of the small disturbance equation, thereby improving the efficiency of the stability assessment of the compressor under thermal shock distortion.

[0056] It should be noted that, in the embodiments of the present disclosure, the linearization principle of the flow field parameters means that the flow field parameters can be characterized as the sum of the average amount of the flow field parameters and the small disturbance amount of the flow field parameters.

[0057] In an optional embodiment, the process of obtaining the small perturbation equation of the compressor by the terminal device based on the small perturbation hypothesis and the Euler equation may include: assuming that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance, based on the small perturbation hypothesis, determining the flow field parameter in the non-conservative form of the Euler equation as the average value of the flow field parameter and the sum of the small perturbation value of the flow field parameter, obtaining the flow field parameter characterization equation, and then, based on the flow field parameter characterization equation and the non-conservative form of the Euler equation, obtaining the small perturbation equation of the compressor. Wherein, the flow field parameters include fluid density, circumferential fluid velocity, axial fluid velocity, and fluid pressure, and the average value of the flow field parameter is:

[0058]

[0059] In Formula 7, is the average value of flow field parameters, n is multiple time points selected in the periodic thermal shock distortion disturbance, ω t is the periodic frequency of the disturbance, N is the truncated Fourier series;

[0060] The small disturbance amount of the flow field parameter is:

[0061]

[0062] In formula 8, q′ is the small disturbance of flow field parameters, ω is the complex characteristic frequency, τ is the time, and m is the circumferential wave number of the disturbance;

[0063] The flow field parameter characterization equation is:

[0064]

[0065] In Formula 9, q is a flow field parameter. Based on the small perturbation hypothesis, the flow field parameter characterization equation can be determined by assuming that the thermal shock distortion is a periodic disturbance, using the average quantity equation and the small perturbation quantity equation of the flow field parameters. Based on the flow field parameter characterization equation and the non-conservative form of the Euler equation in the case of compressor thermal shock intake distortion, a small perturbation equation that more accurately characterizes the small perturbation of the compressor in the case of thermal shock intake distortion being a periodic distortion can be determined.

[0066] It can be understood that, when q is the fluid density, Formula 9 is Similarly, when q is the fluid velocity and fluid density, the form of Formula 9 is similar to the form of Formula 9 when q is the fluid density, and the present disclosure will not elaborate on this.

[0067] In an optional embodiment, the Euler equation is a second Euler equation in a non-conservative form, and the process of obtaining the small perturbation equation of the compressor based on the flow field parameter characterization equation and the non-conservative form of the Euler equation may include: determining the second Euler equation in a non-conservative form based on the second Euler equation in a conservative form of the compressor to be evaluated, and when it is determined that the average amount of the flow field parameters satisfies the second Euler equation in a non-conservative form, updating the flow field parameters in the second Euler equation in a non-conservative form based on the average amount of the flow field parameters to obtain an updated second equation; then, according to the The flow field parameter characterization equation determines the difference between the second Euler equation in the non-conservative form and the updated Euler equation as the second small perturbation equation of the compressor, wherein the second Euler equation in the conservative form contains the term where the time spectrum matrix is ​​located, and the time spectrum matrix is ​​obtained by determining the first-order derivative matrix of the disturbance amplitude of the small perturbation under the thermal shock distortion condition with respect to time based on the assumption that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance, and drawing on the harmonic balance method, and, among the multiple time points selected in the periodic thermal shock distortion disturbance, the second small perturbation equation in the non-conservative form at the t-th time point is:

[0068]

[0069] In formula 10, E iis the i-th row in the time spectrum matrix, ρ′ is the fluid density perturbation matrix at multiple time points selected in the periodic thermal shock distortion perturbation, v′ is the circumferential fluid velocity perturbation matrix at multiple time points selected in the periodic thermal shock distortion perturbation, w′ is the axial fluid velocity perturbation matrix at multiple time points selected in the periodic thermal shock distortion perturbation, and p′ is the fluid pressure perturbation matrix at multiple time points selected in the periodic thermal shock distortion perturbation; wherein the time spectrum matrix includes 2n+1 rows, E i is the tth row in the 2n+1 rows. The small perturbation equations at different time points can be coupled by selecting the flow field parameter matrix at multiple time points in the periodic thermal shock distortion disturbance to obtain a small perturbation equation that can accurately characterize the small perturbation state in the thermal shock distortion process.

[0070] It should be noted that in the embodiment of the present disclosure, when the terminal device determines the first small perturbation equation or the second small perturbation equation, based on the parallel compressor assumption, it is considered that the flow field parameters in the circumferential direction are still average within a small range (mainly referring to the range of a single blade channel). The circumferential unevenness can be ignored, and after ignoring the high-order small quantities, the small perturbation equation of the compressor can be obtained. The small perturbation equation is the small perturbation equation of a single channel.

[0071] Among them, the process of the terminal device constructing the Euler equation of the compressor is implemented in response to the Euler 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.

[0072] In an optional embodiment, the process of the terminal device solving the small perturbation equation based on the flow field data during the thermal shock process to obtain the small perturbation solution of the compressor 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 during the thermal shock process 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 during the thermal shock process may be considered to solve the small perturbation equation to obtain the small perturbation solution under the condition of thermal shock distortion, so as to realize the accurate evaluation of the stability of the compressor under the condition of thermal shock distortion.

[0073] 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.

[0074] It can be understood that in the embodiment of the present disclosure, the terminal device solves the small perturbation equation based on the flow field data during the thermal shock process. In the process of obtaining the small perturbation solution of the compressor, the small perturbation equation used can be the first small perturbation equation or the second small perturbation equation, and the embodiment of the present disclosure does not limit this.

[0075] In an optional embodiment, when the small perturbation solution of the compressor is determined by using the first small perturbation equation, the small perturbation solution includes a first pressure perturbation solution, a first density perturbation solution, a first circumferential velocity perturbation solution and a first axial velocity perturbation solution; wherein, the terminal device performs Helmholtz decomposition on the small perturbation equation to obtain the pressure perturbation equation in the irrotational field, and the process includes: determining the circumferential perturbation velocity of the fluid in the irrotational field and the axial perturbation velocity of the fluid in the irrotational field based on the velocity potential, and then substituting the circumferential perturbation velocity of the fluid in the irrotational field and the axial perturbation velocity of the fluid in the irrotational field into the momentum equation in the first small perturbation equation to obtain the divergence, and substituting the divergence solution result into the continuity equation and the energy equation for elimination, so as to obtain the first pressure perturbation equation in the irrotational field.

[0076] Among them, the circumferential disturbance velocity of the fluid in the irrotational field is The axial disturbance velocity of the fluid in the irrotational field is For velocity potential.

[0077] The first pressure perturbation equation is:

[0078]

[0079] The process of the terminal device solving the pressure disturbance equation based on the flow field data in the thermal shock process to obtain the pressure disturbance solution may include: solving the first pressure disturbance equation based on the flow field data at the t-th time point in the thermal shock distortion disturbance to obtain the first pressure disturbance solution. The pressure disturbance solution can be obtained through the flow field data at any time point in the thermal shock distortion disturbance, which reduces the data processing complexity of determining the pressure disturbance solution under the assumption that the disturbance amplitude change of the small disturbance is consistent with the thermal shock distortion disturbance change at the compressor inlet, and improves the efficiency of the compressor stability analysis. The first pressure disturbance solution is:

[0080]

[0081] The first density perturbation solution determined by the terminal device is:

[0082]

[0083] The first circumferential velocity perturbation solution is:

[0084]

[0085] The first axial velocity perturbation solution is:

[0086]

[0087] In Formula 12, P 1 is the amplitude of the uploaded pressure wave, P 2 is the amplitude of the downward pressure wave, where the upward pressure wave refers to the pressure from the compressor outlet to the inlet, and the downward pressure wave refers to the pressure from the compressor inlet to the outlet. At the same time, the downward pressure wave at the inlet is 0, and the upward pressure wave at the outlet is 0.

[0088]

[0089] In formula 16,

[0090]

[0091] It should be noted that in Formula 12 to Formula 15, α 1 and α 2 Correlation with the upstream pressure wave and the downstream pressure wave respectively.

[0092] In Formula 13 to Formula 15, D is the first small disturbance amplitude, V is the second small disturbance amplitude, W=(MW)V, and as well as, And, (FMD), (SMD), (FMV), (SMV), (FMW) and (SMW) are constants related to the flow field data.

[0093] in,

[0094] In an optional embodiment, when the small perturbation solution of the compressor is determined by using a second small perturbation equation, the small perturbation solution includes a second pressure perturbation solution, a second density perturbation solution, a second circumferential velocity perturbation solution and a second axial velocity perturbation solution; wherein, the terminal device performs Helmholtz decomposition on the small perturbation equation to obtain the pressure perturbation equation in the irrotational field, and the process includes: determining the circumferential perturbation velocity of the fluid in the irrotational field and the axial perturbation velocity of the fluid in the irrotational field based on the velocity potential, and then substituting the circumferential perturbation velocity of the fluid in the irrotational field and the axial perturbation velocity of the fluid in the irrotational field into the momentum equation in the second small perturbation equation to obtain the divergence, and substituting the divergence solution result into the continuity equation and the energy equation for elimination, so as to obtain the second pressure perturbation equation in the irrotational field.

[0095] Similarly, the circumferential disturbance velocity of the fluid in the irrotational field is The axial disturbance velocity of the fluid in the irrotational field is

[0096] The second pressure perturbation equation is:

[0097]

[0098] The process in which the terminal device solves the pressure perturbation equation based on the flow field data during the thermal shock process to obtain the pressure perturbation solution may include: solving the second pressure perturbation equation based on the flow field data at multiple time points during the thermal shock process to obtain the second pressure perturbation solution. The pressure perturbation solution can be obtained through the flow field data at multiple time points in the thermal shock distortion perturbation. In the process of compressor stability analysis based on the assumption that the thermal shock distortion perturbation at the compressor inlet is a periodic perturbation, the compressor stability analysis can be realized without a large amount of experimental data, thereby reducing the difficulty and complexity of the compressor stability analysis. The second pressure perturbation solution is:

[0099]

[0100] The second density perturbation solution determined by the terminal device is:

[0101]

[0102] The second circumferential velocity perturbation solution is:

[0103]

[0104] The second axial velocity perturbation solution is:

[0105]

[0106] In Formula 17 to Formula 21, P 1 is the amplitude matrix of the uploaded pressure wave, P 2is the amplitude matrix of the downward pressure wave, D is the first small disturbance amplitude matrix, V is the second small disturbance amplitude matrix, and W = (MW) V, and,

[0107]

[0108] In Formula 22,

[0109] in,

[0110] It should be noted that in Formula 19 to Formula 21, α 1 and α 2 Correlation with the upstream pressure wave and the downstream pressure wave respectively.

[0111] Meanwhile, in Formulas 18 to 22, FMD, SMD, FMV, SMV, FMW, and SMW are constant matrices of flow field data, wherein FMD satisfies the first equation, which is:

[0112] (FMD)(FMDC1)+(FMDC2)(FMD)+(FMDC3)=0; (Formula 23)

[0113] In Formula 23, FMDC1 = (Λiα 1 ), as well as,

[0114] It can be understood that the terminal device obtains the constant matrix of FMD by solving the first equation.

[0115] SMD satisfies the second equation, which is:

[0116] (SMD)(SMDC1)+(SMDC2)(SMD)+(SMDC3)=0; (Formula 24)

[0117] In Formula 24, SMDC1=(Λiα 2 ), as well as,

[0118] It can be understood that the terminal device obtains the constant matrix of the SMD by solving the second equation.

[0119] FMV satisfies the third-party procedure, where the third-party procedure is:

[0120] (FMV)(FMVC1)+(FMVC2)(FMV)+(FMVC3)=0; (Formula 25)

[0121] In Formula 25, FMVC1 = (Λiα 1 ), as well as,

[0122] It can be understood that the terminal device obtains the constant matrix of FMV by solving the third equation.

[0123] It should be noted that for SMV, by changing the α 1 Replace with α 2 By solving it, we can get the constant matrix of SMV.

[0124] The FMW satisfies the fourth equation, where the fourth equation is:

[0125] (FMW)(FMWC1)+(FMWC2)(FMW)+(FMWC3)=0; (Formula 26)

[0126] In Formula 26, FMWC1=(Λiα 1 ), as well as,

[0127] It should be noted that for SMW, by replacing α in the fourth equation 1 Replace with α 2 By solving it, we can get the constant matrix of SMW.

[0128] In step S103, the terminal device can 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 thermal shock distortion according to the boundary conditions and the small disturbance solution.

[0129] 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.

[0130] 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 thermal shock intake distortion.

[0131] Among them, the mass conservation equation constructed under the condition of mass conservation is:

[0132] (ρw′+wρ′) - =(ρw′+wρ′) + ;(Formula 27)

[0133] The conversion enthalpy conservation equation constructed under the conversion enthalpy conservation condition is:

[0134]

[0135] In Equation 28, Ω is the compressor speed, and according to the right-hand rule, the direction is from inlet to outlet.

[0136] The Kutta condition equation constructed under the Kutta condition is:

[0137] (wv′-(v-Ωr)w′) + =0; (Formula 29)

[0138] The process of constructing the total pressure lumped loss condition equation under the total pressure lumped loss condition may include:

[0139] The total pressure loss coefficient ζ is defined as:

[0140] ζ=p t - -p t + ;(Formula 30)

[0141] In formula 30, Where R is the average radius of the compressor.

[0142] 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:

[0143] ζ=ζ(tanβ1); (Formula 31)

[0144] In formula 31, The small perturbation of the tangent value of the relative intake air flow angle is

[0145] 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:

[0146]

[0147] Next, substitute Formula 30 into Formula 32 and combine it with Formula 31 to obtain the initial total pressure lumped loss condition equation:

[0148]

[0149] 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:

[0150]

[0151] 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 thermal shock distortion may include:

[0152] Substituting the small perturbation 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 thermal shock distortion is obtained, wherein, when the small perturbation solution is the solution result of the first small perturbation equation, the system stability characteristic equation is:

[0153]

[0154] In Formula 35, 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, H1 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, H2 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 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, H3 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, H4 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, P 1 is the amplitude of the uploaded pressure wave, P 2 is the amplitude of the downward pressure wave, D is the amplitude of the first small disturbance, V is the amplitude of the second small disturbance, - represents the front side of the blade, and + represents the rear side of the blade.

[0155] Wherein, when the small perturbation solution is the solution result of the second small perturbation equation, the system stability characteristic equation is:

[0156]

[0157] In Formula 36, ​​P 1 is the amplitude matrix of the uploaded pressure wave, P 2 is the amplitude matrix of the downward pressure wave, D is the amplitude matrix of the first small disturbance, and V is the amplitude matrix of the second small disturbance.

[0158] 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.

[0159] In an optional embodiment, the process of determining the flow stability evaluation result of the compressor by the terminal device based on the solution result of the system stability characteristic equation may include: simplifying the system stability characteristic equation that is a closed equation into an updated system stability characteristic equation; then, solving the updated system stability characteristic equation based on the singular value decomposition method to obtain the value of the complex characteristic frequency, and 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.

[0160] Among them, the updated system stability characteristic equation is:

[0161] X(ω)δ=0;(Formula 37)

[0162] In formula 37, X(ω) is the coefficient matrix, that is, the matrix δ is the unknown in Equation 18, where if the system stability characteristic equation is the equation in Equation 35, then δ is the matrix If the system stability characteristic equation is the equation in Equation 36, then δ is the matrix

[0163] 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.

[0164] An exemplary embodiment of the present disclosure provides a compressor flow stability evaluation and analysis device under thermal shock distortion. The compressor flow stability evaluation and analysis device under thermal shock distortion may be a server or a chip applied to a server. Figure 2 FIG. 2 shows a schematic block diagram of the functional modules of a compressor flow stability evaluation and analysis device under thermal shock distortion according to an exemplary embodiment of the present disclosure. Figure 2 As shown, the compressor flow stability evaluation and analysis device 200 under thermal shock distortion includes:

[0165] A construction module 201 is configured to construct the Euler equations of the compressor to be evaluated;

[0166] The acquisition module 202 is configured to obtain a small perturbation equation of the compressor based on a small perturbation assumption and the Euler equation, and solve the small perturbation equation based on flow field data during a thermal shock process to obtain a small perturbation solution of the compressor, wherein the small perturbation equation is a first small perturbation equation or a second small perturbation equation, the first small perturbation equation is determined based on an assumption that a change in a disturbance amplitude of the small perturbation is consistent with a change in a thermal shock distortion disturbance at an inlet of the compressor, and the second small perturbation equation is determined based on an assumption that a thermal shock distortion disturbance at an inlet of the compressor is a periodic disturbance;

[0167] 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 thermal shock distortion according to the boundary conditions and the small disturbance solution;

[0168] 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.

[0169] Optionally, the acquisition module 202 is configured to:

[0170] When it is determined that the average amount of the flow field parameters satisfies the first Euler equation in a non-conservative form, the flow field parameters in the first Euler equation in a non-conservative form are updated based on the average amount of the flow field parameters to obtain an updated first equation;

[0171] According to the linearization principle of flow field parameters, the difference between the first Euler equation in non-conservative form and the updated first equation is determined as the first small perturbation equation of the compressor, and based on the assumption that the disturbance amplitude change of the small perturbation is consistent with the thermal shock distortion disturbance change at the compressor inlet, the small perturbation amount of the flow field parameter in the first small perturbation equation is determined as:

[0172] q′=∑q′(z)(1+k q τ)e iωτ+imθ ;

[0173] Among them, k q is the change rate of the small disturbance amplitude, which is the same as the change rate of the thermal shock distortion disturbance at the compressor inlet; the first small disturbance equation is:

[0174]

[0175] Among them, ρ t ′ is the fluid density disturbance at the tth time point in the thermal shock distortion disturbance, v t ′ is the circumferential fluid velocity disturbance at the tth time point, w t′ is the circumferential fluid velocity disturbance at the tth time point, p t ′ is the fluid pressure disturbance at the tth time point, is the mean circumferential fluid velocity at the tth time point, is the mean axial fluid velocity at the tth time point, is the mean fluid density at the tth time point.

[0176] Optionally, the acquisition module 202 is configured to:

[0177] Assuming that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance, based on the small disturbance hypothesis, the flow field parameters in the non-conservative form of the Euler equation are determined to be the average value of the 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 flow field parameters include fluid density, circumferential fluid velocity, axial fluid velocity, and fluid pressure. The average value of the flow field parameters is:

[0178]

[0179] in, is the average value of flow field parameters, n is multiple time points selected in the periodic thermal shock distortion disturbance, ω t is the periodic frequency of the disturbance, N is the truncated Fourier series;

[0180] The small disturbance amount of the flow field parameter is:

[0181]

[0182] Among them, q′ is the small disturbance of flow field parameters, ω is the complex characteristic frequency, τ is the time, and m is the circumferential wave number of the disturbance;

[0183] The flow field parameter characterization equation is:

[0184]

[0185] Among them, q is the flow field parameter;

[0186] Based on the flow field parameter characterization equation and the non-conservative form of the Euler equation, the small disturbance equation of the compressor is obtained.

[0187] Optionally, the acquisition module 202 is configured to:

[0188] Based on the second Euler equation in a conservative form of the compressor to be evaluated, a second Euler equation in a non-conservative form is determined, wherein the second Euler equation in a conservative form contains a term where a time spectrum matrix is ​​located, and the time spectrum matrix is ​​obtained by expanding the flow field parameters at multiple time points selected from the periodic thermal shock distortion disturbance in a Fourier form based on the assumption that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance and drawing on the harmonic balance method, determining the inverse matrix of the non-Fourier coefficient partial matrix and the product of the derivative matrix of the non-Fourier coefficient partial matrix with respect to time;

[0189] When it is determined that the average amount of the flow field parameters satisfies the second Euler equation in a non-conservative form, updating the flow field parameters in the second Euler equation in a non-conservative form based on the average amount of the flow field parameters to obtain an updated second equation;

[0190] According to the flow field parameter characterization equation, the difference between the second Euler equation in non-conservative form and the updated second equation is determined as the second small perturbation equation of the compressor, and the second small perturbation equation is:

[0191]

[0192] Among them, ρ t ′ is the fluid density disturbance at the tth time point among multiple time points selected in the periodic thermal shock distortion disturbance, v t ′ is the circumferential fluid velocity disturbance at the tth time point, w t ′ is the circumferential fluid velocity disturbance at the tth time point, p t ′ is the fluid pressure disturbance at the tth time point, is the mean circumferential fluid velocity at the tth time point, is the mean axial fluid velocity at the tth time point, is the mean fluid density at the tth time point, E i is the i-th row in the time spectrum matrix, ρ′ is the fluid density perturbation matrix at multiple time points selected in the periodic thermal shock distortion disturbance, v′ is the circumferential fluid velocity perturbation matrix at multiple time points selected in the periodic thermal shock distortion disturbance, w′ is the axial fluid velocity perturbation matrix at multiple time points selected in the periodic thermal shock distortion disturbance, and p′ is the fluid pressure perturbation matrix at multiple time points selected in the periodic thermal shock distortion disturbance.

[0193] Optionally, the acquisition module 202 is configured to:

[0194] Performing Helmholz decomposition on the small perturbation equation to obtain a pressure perturbation equation in an irrotational field;

[0195] Solving the pressure disturbance equation based on the flow field data during the thermal shock process to obtain a pressure disturbance solution;

[0196] 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;

[0197] 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.

[0198] Optionally, the first determining module 203 is configured to:

[0199] 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;

[0200] 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.

[0201] Optionally, the small perturbation solution is a solution result of the first small perturbation equation, and the first determining module 203 is configured to:

[0202] 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 thermal shock distortion is obtained. The system stability characteristic equation is:

[0203]

[0204] 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] 1×4nI 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, H1 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, H2 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 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, H3 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, H4 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, P 1 is the amplitude of the uploaded pressure wave, P 2 is the amplitude of the downward pressure wave, D is the amplitude of the first small disturbance, V is the amplitude of the second small disturbance, - represents the front side of the blade, and + represents the rear side of the blade.

[0205] Optionally, the small perturbation solution is a solution result of the second small perturbation equation, and the first determining module 203 is configured to:

[0206] 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 thermal shock distortion is obtained. The system stability characteristic equation is:

[0207]

[0208] Among them, P 1 is the first small perturbation amplitude matrix, P 2 is the second small perturbation amplitude matrix, D is the third small perturbation amplitude matrix, and V is the fourth small perturbation amplitude matrix.

[0209] 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.

[0210] 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.

[0211] 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.

[0212] 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.

[0213] 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.

[0214] 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.

[0215] 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).

[0216] 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.

[0217] 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.

[0218] 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.

[0219] 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).

[0220] 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.

[0221] 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.

[0222] 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).

[0223] 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 thermal shock distortion, characterized in that: include: Construct the Euler equations for the compressor to be evaluated; Based on the small perturbation hypothesis and the Euler equation, a small perturbation equation of the compressor is obtained, and the small perturbation equation is solved based on the flow field data during the thermal shock process to obtain a small perturbation solution of the compressor, wherein the small perturbation equation is a first small perturbation equation or a second small perturbation equation, the first small perturbation equation is determined based on the assumption that the change in the disturbance amplitude of the small perturbation is consistent with the change in the thermal shock distortion disturbance at the compressor inlet, and the second small perturbation equation is determined based on the assumption that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance; 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 thermal shock distortion 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 thermal shock distortion according to claim 1, characterized in that: Based on the small disturbance hypothesis and the Euler equation, the small disturbance equation of the compressor is obtained, including: When it is determined that the average amount of the flow field parameters satisfies the first Euler equation in a non-conservative form, the flow field parameters in the first Euler equation in a non-conservative form are updated based on the average amount of the flow field parameters to obtain an updated first equation; According to the linearization principle of flow field parameters, the difference between the first Euler equation in non-conservative form and the updated first equation is determined as the first small perturbation equation of the compressor, and based on the assumption that the disturbance amplitude change of the small perturbation is consistent with the thermal shock distortion disturbance change at the compressor inlet, the small perturbation amount of the flow field parameter in the first small perturbation equation is determined as: Among them, k q is the change rate of the small disturbance amplitude, which is the same as the change rate of the thermal shock distortion disturbance at the compressor inlet; The first small perturbation equation is: Among them, ρ t ′ is the fluid density disturbance at the tth time point in the thermal shock distortion disturbance, v t ′ is the circumferential fluid velocity disturbance at the tth time point, w t ′ is the circumferential fluid velocity disturbance at the tth time point, p t ′ is the fluid pressure disturbance at the tth time point, is the mean circumferential fluid velocity at the tth time point, is the mean axial fluid velocity at the tth time point, is the mean fluid density at the tth time point.

3. The analytical method for evaluating compressor flow stability under thermal shock distortion according to claim 1, characterized in that: Based on the small disturbance hypothesis and the Euler equation, the small disturbance equation of the compressor is obtained, including: Assuming that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance, based on the small disturbance hypothesis, the flow field parameters in the non-conservative form of the Euler equation are determined to be the average value of the 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 flow field parameters include fluid density, circumferential fluid velocity, axial fluid velocity, and fluid pressure. The average value of the flow field parameters is: in, is the average value of flow field parameters, n is multiple time points selected in the periodic thermal shock distortion disturbance, ω t is the periodic frequency of the disturbance, N is the truncated Fourier series; The small disturbance amount of the flow field parameter is: Among them, q′ is the small disturbance of flow field parameters, ω is the complex characteristic frequency, τ is the time, and m is the circumferential wave number of the disturbance; 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 non-conservative form of the Euler equation, the small disturbance equation of the compressor is obtained.

4. The analytical method for evaluating compressor flow stability under thermal shock 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 non-conservative form of the Euler equation, including: Based on the second Euler equation in a conservative form of the compressor to be evaluated, a second Euler equation in a non-conservative form is determined, wherein the second Euler equation in a conservative form contains a term where a time spectrum matrix is ​​located, and the time spectrum matrix is ​​obtained by expanding the flow field parameters at multiple time points selected from the periodic thermal shock distortion disturbance in a Fourier form based on the assumption that the thermal shock distortion disturbance at the compressor inlet is a periodic disturbance by referring to the harmonic balance method, and then determining the inverse matrix of the non-Fourier coefficient partial matrix and the product of the derivative matrix of the non-Fourier coefficient partial matrix with respect to time; When it is determined that the average amount of the flow field parameters satisfies the second Euler equation in the non-conservative form, the flow field parameters in the second Euler equation in the non-conservative form are updated based on the average amount of the flow field parameters to obtain an updated second equation; According to the flow field parameter characterization equation, the difference between the second Euler equation in non-conservative form and the updated second equation is determined as the second small perturbation equation of the compressor, and the second small perturbation equation is: Among them, ρ t ′ is the fluid density disturbance at the tth time point among multiple time points selected in the periodic thermal shock distortion disturbance, v t ′ is the circumferential fluid velocity disturbance at the tth time point, w t ′ is the circumferential fluid velocity disturbance at the tth time point, p t ′ is the fluid pressure disturbance at the tth time point, is the mean circumferential fluid velocity at the tth time point, is the mean axial fluid velocity at the tth time point, is the mean fluid density at the tth time point, E i is the i-th row in the time spectrum matrix, ρ′ is the fluid density perturbation matrix at multiple time points selected in the periodic thermal shock distortion disturbance, v′ is the circumferential fluid velocity perturbation matrix at multiple time points selected in the periodic thermal shock distortion disturbance, w′ is the axial fluid velocity perturbation matrix at multiple time points selected in the periodic thermal shock distortion disturbance, and p′ is the fluid pressure perturbation matrix at multiple time points selected in the periodic thermal shock distortion disturbance.

5. The analytical method for evaluating compressor flow stability under thermal shock distortion according to claim 1, characterized in that: Solving the small disturbance equation based on the flow field data during the thermal shock process to obtain the small disturbance solution of 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 the flow field data during the thermal shock process 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 thermal shock 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 thermal shock distortion according to claim 6, characterized in that: The small perturbation solution is a solution result of the first small perturbation equation, and the system stability characteristic equation of the compressor under the condition of thermal shock distortion is determined according to the boundary condition and the small perturbation solution, including: 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 thermal shock distortion 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, H1 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, H2 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 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, H3 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, H4 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, P 1 is the amplitude of the uploaded pressure wave, P 2 is the amplitude of the downward pressure wave, D is the amplitude of the first small disturbance, V is the amplitude of the second small disturbance, - represents the front side of the blade, and + represents the rear side of the blade.

8. The analytical method for evaluating compressor flow stability under thermal shock distortion according to claim 6, characterized in that: The small perturbation solution is a solution result of the second small perturbation equation, and the system stability characteristic equation of the compressor under the condition of thermal shock distortion is determined according to the boundary condition and the small perturbation solution, including: 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 thermal shock distortion is obtained. The system stability characteristic equation is: Among them, P 1 is the amplitude matrix of the uploaded pressure wave, P 2 is the amplitude matrix of the downward pressure wave, D is the amplitude matrix of the first small disturbance, and V is the amplitude matrix of the second small disturbance.

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 thermal shock distortion as described in any one of claims 1 to 8.

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 thermal shock distortion as described in any one of claims 1 to 8 is implemented.

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