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CN120008934A - A method for evaluating the stability margin of an aviation gas turbine engine - Google Patents

A method for evaluating the stability margin of an aviation gas turbine engine Download PDF

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CN120008934A
CN120008934A CN202510491298.9A CN202510491298A CN120008934A CN 120008934 A CN120008934 A CN 120008934A CN 202510491298 A CN202510491298 A CN 202510491298A CN 120008934 A CN120008934 A CN 120008934A
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stability margin
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surge
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CN120008934B (en
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刘勇
姜忠峰
李华
王智勇
薛园园
潘信予
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Taicang Dianshi Aviation Power Co ltd
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Abstract

The invention relates to the technical field of aeroengines, and discloses an aero gas turbine engine complete machine stability margin assessment method, which comprises the steps of analyzing physical characteristics and working principles of all parts of a gas turbine engine to construct an engine complete machine model, constructing an engine experiment table to perform experiments, judging whether a gas compressor enters a surge state, recording experimental data, performing numerical simulation and recording the simulated data based on the constructed engine complete machine model, comparing the simulated data with the experimental data, verifying the accuracy of the model, constructing a surge boundary if the model is accurate, optimizing the model if the model is inaccurate, judging whether a stall hysteresis phenomenon occurs in real time, generating a normal operation signal or a stall hysteresis signal, updating the surge boundary if the stall hysteresis signal is generated, calculating the stability margin value of the engine based on the surge boundary, and assessing the engine complete machine stability margin.

Description

Complete machine stability margin assessment method for aviation gas turbine engine
Technical Field
The invention relates to the technical field of aero-engines, in particular to a method for evaluating the complete machine stability margin of an aero-gas turbine engine.
Background
In the aviation field, the aviation gas turbine engine is used as a core power device of an aircraft, the performance of the aviation gas turbine engine is directly related to the flight safety and efficiency, the stable operation of the engine is one of key factors for guaranteeing the reliable flight of the aircraft, the stability margin is an important index for measuring the capability of the engine to maintain stable operation under different working conditions, and the accuracy of evaluating the stability margin of the whole machine of the aviation gas turbine engine is significant for improving the performance of the engine and guaranteeing the flight safety.
The construction of the whole engine model is the basis for evaluating the stability margin, and in the prior art, the modeling method is limited by the limitation of understanding the interior of the engine, and the accuracy and the integrity of modeling data are insufficient, so that the real surge boundary of the engine can not be accurately reflected, and the accuracy of stability margin evaluation is further affected.
On the other hand, in the running process of the engine, the stall hysteresis phenomenon has stronger concealment and complexity, the occurrence of the stall hysteresis phenomenon is difficult to be accurately captured in real time by the existing monitoring technical means, the stall hysteresis characteristics are difficult to be quickly and accurately identified from a large amount of monitoring data, and an effective stall hysteresis signal cannot be timely generated, so that the engine cannot be timely and effectively processed when the stall hysteresis occurs, and the safety risk of the running of the engine is increased.
The operation condition of the aviation gas turbine engine can be changed obviously under different environment conditions, most of the existing stability margin assessment methods are designed based on static conditions or limited working condition ranges, and the real-time tracking and adaptation capability for dynamic changes of the operation condition of the engine is lacking, so that the assessment result is disjointed with the actual stable operation capability of the engine, and powerful guarantee cannot be provided for reliable operation of the engine.
Aiming at the problems, the invention provides a method for evaluating the complete machine stability margin of an aviation gas turbine engine.
Disclosure of Invention
The invention aims to provide an overall stability margin assessment method for an aviation gas turbine engine, which aims to solve at least one of the problems in the prior art.
The invention provides a method for evaluating the complete machine stability margin of an aviation gas turbine engine, which comprises the following steps:
constructing a complete engine model;
Constructing an engine experiment table to perform experiments, performing numerical simulation according to an engine complete machine model, recording experiment and simulation data when a compressor enters a surge state, comparing, verifying the accuracy of the model, if the model is accurate, constructing a surge boundary according to the model, and if the model is inaccurate, optimizing the model;
specifically, in the experimental process, the air inlet flow is reduced by a fixed step;
Acquiring a pressure fluctuation amplitude in the process of reducing the inlet air flow, judging that the air compressor enters a surge state if the pressure fluctuation amplitude is greater than or equal to a pressure fluctuation threshold value, recording the experimental inlet air flow of the air compressor, acquiring an outlet pressure value and an inlet pressure value of the air compressor, and performing data processing to obtain an experimental surge pressure ratio;
Performing numerical simulation according to an engine complete machine model, gradually reducing the air inlet flow with the same step length as the experiment, calculating the Lyapunov index in the air compressor in the air inlet flow reducing process, judging that the air compressor enters a surge state if the Lyapunov index is greater than 0, and recording the simulated air inlet flow of the air compressor and the calculated simulated surge pressure ratio;
Comparing and analyzing the experimental air inlet flow and the experimental surge pressure ratio obtained through experiments with the simulated air inlet flow and the simulated surge pressure ratio obtained through simulation respectively, and calculating to obtain an air inlet flow relative error and a pressure ratio relative error;
If the relative error of the air inlet flow is smaller than or equal to the air inlet flow error threshold value and the relative error of the pressure ratio is smaller than or equal to the pressure ratio error threshold value, generating an analog accurate signal;
Carrying out experiments and simulation on the engine under a plurality of different working conditions, obtaining the times of generating simulation accurate signals, and carrying out data processing to obtain the coincidence ratio of the whole engine model;
If the anastomosis ratio is greater than or equal to the anastomosis ratio threshold, generating a model anastomosis signal, otherwise, generating a model deviation signal;
if the model matching signals are generated, establishing a mathematical model of the surge boundary of the engine by analyzing simulation results under different working conditions, and fitting a large number of simulation results according to a multiple regression analysis method to obtain an analysis expression of the surge boundary;
drawing a surge boundary on a characteristic curve according to the analytical expression;
Whether the engine has stall hysteresis or not is analyzed in real time, if so, a stall hysteresis signal is generated, otherwise, a normal running signal is generated, and a stability margin value of normal running of the engine is calculated;
specifically, in the actual running period of the engine, the inlet and outlet pressure difference of the air compressor is obtained in real time;
performing fast Fourier transform on the obtained pressure difference of the inlet and the outlet of the air compressor, and converting a time domain signal into a frequency domain signal to obtain a pressure difference frequency domain amplitude;
if any discrete frequency point exists, enabling the frequency domain amplitude to be greater than or equal to the frequency domain amplitude threshold value, and generating a suspected stall hysteresis signal;
If a suspected stall delay signal is received, acquiring response time of the intake air flow to an accelerator instruction, and if the response time is smaller than a response time threshold, generating a normal operation signal, otherwise, generating a stall delay signal;
If a normal running signal is received, acquiring the real-time pressure ratio and the air inlet flow of the engine, and combining to obtain a real-time measurement point of the current measurement time point on the air inlet flow-pressure ratio plane;
the method comprises the steps of obtaining the pressure ratio corresponding to the same air inlet flow on a surge boundary as a real-time measuring point, performing data processing, and calculating to obtain a stability margin value of an engine in a normal running state;
If a stall hysteresis signal is generated, updating a surge boundary, and calculating a stability margin value of the engine under the stall hysteresis phenomenon based on the updated surge boundary;
Specifically, if a stall hysteresis signal is received, extracting the inlet and outlet pressure difference of a compressor in a delta t time window before and after the stall hysteresis signal is generated in the actual running period of the engine, analyzing and processing data, expanding a surge boundary analysis expression into a time-varying form, and obtaining a corrected surge boundary;
according to the corrected surge boundary and the real-time measuring point, performing data processing, and calculating to obtain a stability margin value of the engine under the stall hysteresis phenomenon;
and evaluating the stability margin of the whole engine according to the stability margin value.
The invention has the beneficial effects that:
1. According to the invention, the CFD numerical simulation and the component level series model are combined to construct a high-precision engine complete machine model, so that the accuracy of stability margin assessment is improved. The comparison and verification of the experiment table experiment and the numerical simulation ensure the reliability of the model, lay a solid foundation for the subsequent evaluation work, and can timely find the stall hysteresis of the engine based on the real-time measurement and analysis technology, such as the fast Fourier transform analysis of pressure difference, air inlet flow and frequency domain characteristics, thereby improving the real-time performance and accuracy of the evaluation.
2. According to the invention, the surge boundary is dynamically updated through CFD transient simulation and the self-adaptive Kalman filtering algorithm, so that the evaluation method is more suitable for the actual running state of the engine, the adaptability and the robustness of stability margin evaluation are improved, and finally, based on the evaluation result of the stability margin value, a safety signal, an early warning signal or a dangerous signal can be generated, so that a powerful guarantee is provided for the safe running of the engine, the running risk is reduced, and the safety and the reliability of aviation flight are improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of a method for evaluating overall stability margin of an aircraft gas turbine engine according to an embodiment of the present invention;
FIG. 2 is a flowchart illustrating steps for obtaining the model fitting signal and the model deviation signal in the overall stability margin evaluation method of an aero gas turbine engine according to an embodiment of the present invention;
FIG. 3 is a flowchart illustrating steps for obtaining a stability margin value of an aircraft gas turbine engine in a normal state according to a method for evaluating a stability margin of the aircraft gas turbine engine according to an embodiment of the present invention;
fig. 4 is a flowchart of an overall stability margin evaluation system for an aero gas turbine engine according to a second embodiment of the present invention.
Detailed Description
In order that those skilled in the art will better understand the present invention, a technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in which it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present invention without making any inventive effort, shall fall within the scope of the present invention.
Embodiment one as shown in fig. 1, the method for evaluating the stability margin of the whole aircraft gas turbine engine provided by the embodiment of the invention specifically comprises the following steps:
S1, analyzing physical characteristics and working principles of each component of a gas turbine engine, constructing a series of models of each component by combining CFD numerical simulation, integrating the mathematical models of each component into a complete engine model, and realizing simulation calculation through a MATLAB platform;
In some embodiments, corresponding component level mathematical models are built according to physical characteristics and operating principles of components of the gas turbine engine, including the compressor, combustor, turbine, etc.;
Specifically, based on a one-dimensional unsteady flow theory, a partial differential equation describing the internal flow of the compressor is solved by using a characteristic line method, the geometric parameters of the compressor are combined, the geometric parameters comprise blade shape, progression, blade tip clearance and the like, a component level mathematical model of the compressor is constructed, and the component level mathematical model of the compressor is corrected by using a CFD numerical simulation result;
based on a chemical reaction dynamics mechanism, combining CFD simulation analysis of a three-dimensional flow field in a combustion chamber, taking fuel injection, atomization, mixing and combustion processes into consideration, and constructing a component level model of the combustion chamber by solving energy conservation, mass conservation and momentum conservation equations;
based on the working principle of the turbine, a aerodynamic thermodynamic model of the turbine is established, a complex flow field in a turbine blade channel is simulated and analyzed by CFD, and model parameters are corrected by combining experimental data, so that a part level model of the turbine is obtained;
it should be noted that, the function of the component level model of the compressor is to accurately describe the relationship between the pressure ratio, efficiency, intake air flow and rotation speed of the compressor, the component level model of the combustion chamber can determine the temperature and pressure distribution of the outlet of the combustion chamber, and the function of the component level model of the turbine is to accurately describe the relationship between the expansion ratio, efficiency, intake air flow and rotation speed of the turbine;
Connecting and integrating the stage models of all the parts according to the actual structure and the working flow of the gas turbine engine, correlating the parameters of all the parts through mass conservation, energy conservation and momentum conservation equations to construct a complete engine model, constructing a complete engine model platform through system simulation software MATLAB, integrating the stage models of all the parts into the platform in a module form, and realizing the simulation calculation of the overall performance of the engine;
It should be noted that the function of this step is to construct an accurate and reliable complete engine model for simulating the running conditions of the engine under different working conditions so as to analyze and evaluate the performance and stability of the engine;
S2, constructing an engine experiment table for experiments, judging whether a compressor enters a surge state or not by adjusting air inflow and monitoring pressure change, recording experimental data, carrying out numerical simulation based on a constructed engine complete machine model, judging the surge state in the simulation process, recording simulation data, comparing the simulation data with the experimental data, verifying the accuracy of the model, generating a model fit signal or a model deviation signal, constructing a surge boundary if the model fit signal is generated, and optimizing the model if the model deviation signal is generated;
as shown in fig. 2, the specific steps for obtaining the model matching signal and the model deviation signal are as follows;
in some embodiments, a special engine experiment table is constructed, an air inlet flow regulating device and a pressure sensor are provided, the air inlet flow regulating device can accurately regulate and control the air inlet flow of the engine, and the pressure sensor is arranged in a compressor flow passage and at the inlet and outlet positions of the compressor and is used for monitoring the pressure value in the compressor flow passage, the inlet pressure value and the outlet pressure value of the compressor in real time;
according to the design working condition range of the engine, setting the initial air inlet flow as ,The method is characterized in that the method is close to the maximum air inlet flow of normal operation of an engine, in the experimental process, the air inlet flow is gradually reduced by a fixed step delta Q, after the air inlet flow is adjusted each time, the engine is waited to run stably, each parameter is ensured to reach a steady state, and the air inlet flow is adjusted again;
It should be noted that the working conditions refer to the running state and working condition of the engine, and relate to various parameters and conditions of the engine during running, including rotation speed, temperature and pressure;
Taking a plurality of acquisition time points in the boundary analysis time period, wherein the interval duration between adjacent acquisition time points is the same, and acquiring the pressure value in the flow passage through a pressure sensor arranged in the flow passage of the air compressor at the acquisition time points;
it should be noted that the boundary analysis period is a period for collecting and boundary analyzing the experimental data of the engine;
The pressure values acquired at the adjacent acquisition time points are subjected to difference value processing, absolute value processing is taken, a pressure fluctuation amplitude is obtained, and the obtained pressure fluctuation amplitude is compared with a pressure fluctuation threshold;
If the pressure fluctuation amplitude is greater than or equal to the pressure fluctuation threshold, the obvious airflow oscillation appears in the interior of the air compressor, the air compressor is judged to enter a surge state, and the experimental air inlet flow of the air compressor is recorded Collecting the outlet pressure value and the inlet pressure value of the air compressor through pressure sensors arranged at the inlet and outlet positions of the air compressor, and carrying out ratio processing on the obtained outlet pressure value and the obtained inlet pressure value to obtain an experimental surge pressure ratio;
The experiment table is used for carrying out actual experiments to obtain the operation data of the engine under different air inlet flows, and provide an actual basis for judging the surge state and verifying the model;
Based on the obtained engine complete machine model platform, the corresponding working condition of the engine in the experimental process is simulated, and the air inlet flow is set from the experiment Firstly, gradually reducing the step length delta Q as the same as an experiment, performing numerical simulation calculation, under each air inlet flow working condition, obtaining flow field distribution in the air compressor by solving a three-dimensional Reynolds average N-S equation, including parameters such as speed, pressure, temperature and the like, calculating the Lyapunov index in the air compressor based on a nonlinear dynamics theory, when the Lyapunov index is greater than 0, indicating that the air flow in the air compressor is in an unstable state, judging that the air compressor enters a surge state, and recording the simulated air inlet flow of the air compressorCalculated simulated surge pressure ratioIt should be noted that, the effect of judging whether the compressor enters the surge state from the angles of experiment and simulation by using the pressure fluctuation amplitude and the Lyapunov index is to ensure the accuracy of the surge judgment;
for experimental air inlet flow rate obtained by experiment Surge ratio of experimentRespectively and simulatively obtaining simulative air inlet flowAnalog surge pressure ratioComparative analysis was performed by the formula
Calculating to obtain relative error of air inflowRelative error to the pressure ratioComparing the obtained relative air inlet flow error and pressure ratio error with an air inlet flow error threshold and a pressure ratio error threshold respectively;
If the relative error of the air inlet flow is larger than the error threshold of the air inlet flow or the relative error of the pressure ratio is larger than the error threshold of the pressure ratio, the numerical simulation result is larger than the experimental result;
If the relative error of the air inlet flow is smaller than or equal to the air inlet flow error threshold value and the relative error of the pressure ratio is smaller than or equal to the pressure ratio error threshold value, the numerical simulation result is well matched with the experimental result, and a simulation accurate signal is generated;
the method comprises the steps of carrying out experiments and simulation on an engine under a plurality of different working conditions, obtaining the times of generating simulation accurate signals, and carrying out ratio processing on the times and the total times of the experimental and simulated working conditions to obtain the coincidence ratio of the whole engine model;
If the anastomosis ratio is larger than or equal to the anastomosis ratio threshold, judging that the simulation result of the whole engine model is accurate, and generating a model anastomosis signal;
If the anastomosis ratio is smaller than the anastomosis ratio threshold, judging that the simulation result of the whole engine model is inaccurate, and generating a model deviation signal;
Based on the generated model matching signals, through analysis of simulation results under different working conditions and by combining with nonlinear dynamics theory, a mathematical model of an engine surge boundary is established, and the surge boundary is expressed as a function of intake air flow Q and pressure ratio pi Fitting a large number of simulation results according to a multiple regression analysis method to obtain an analytical expression of a surge boundary;
according to the simulation result, drawing an intake air flow-pressure ratio characteristic curve of the engine through a data processing software Origin, and drawing a continuous surge boundary on the characteristic curve according to an analytical expression of the surge boundary;
it should be noted that, the role of establishing a mathematical model of the engine surge boundary and drawing the surge boundary is to provide a reference for the subsequent calculation of the stability margin value;
Based on the generated model deviation signal, adopting a genetic algorithm and sequence quadratic programming mixed optimization strategy, defining an fitness function by taking an experimental surge pressure ratio as an optimization target, setting a parameter search range on an engine complete machine model platform, performing global search through the genetic algorithm, performing local refinement correction through sequence quadratic programming, and updating the engine complete machine model;
Re-performing simulation calculation of a surge boundary based on the updated model, and comparing with an experimental result until the anastomosis ratio of the whole engine model is greater than or equal to the anastomosis ratio threshold;
It should be noted that, the function of this step is to verify the accuracy of the complete engine model, optimize the inaccurate model, and then establish the accurate engine surge boundary according to the simulation data of the complete engine model, provide a reliable basis for the evaluation of the engine stability margin;
S3, calculating a pressure difference and an air inlet flow by measuring inlet and outlet pressures of the air compressor and the air flow speed in the engine in real time, analyzing the frequency domain characteristic of the pressure difference by utilizing fast Fourier transform, judging whether the engine has stall hysteresis, generating a normal operation signal or stall hysteresis signal, and calculating a stability margin value of the engine in a normal state if the normal operation signal is generated;
As shown in fig. 3, the specific acquisition steps of the stability margin value of the engine in the normal state are as follows;
in some embodiments, the compressor inlet pressure is measured in real time by the pressure sensor at a measurement time point during the actual operating cycle of the engine And outlet pressureThe actual running period of the engine represents a period of time in a working state after the engine is actually put into operation, a plurality of measuring time points exist in the actual running period of the engine, the interval duration between the adjacent measuring time points is the same, and t represents the time sequence number of the measuring time points in the actual running period of the engine;
For the measured inlet pressure of the compressor And outlet pressurePerforming differential processing to obtain pressure difference;
Likewise, the air flow velocity in the engine is measured in real time at the measurement time point by the hot wire anemometer during the actual operation period of the engineIn combination with measuring the sectional area A of the section of the engine, the flow formula is adopted
Calculating to obtain the air inlet flow of the engine at the measurement time point;
The method is characterized by measuring the inlet and outlet pressure of the compressor and the air flow speed in the engine in real time, calculating the pressure difference and the air inlet flow, and providing data support for judging the running state of the engine;
for the obtained pressure difference Performing a fast fourier transform by the formula
Converting the time domain signal into a frequency domain signal to obtain a pressure difference frequency domain amplitudeWhere j represents an imaginary unit,N represents the number of discrete frequency points,Is a discrete point of frequency which is a frequency band,=0,1,2......,N-1;
The obtained frequency domain amplitudeComparing with a frequency domain amplitude threshold;
If the frequency domain amplitude of all the discrete frequency points All are smaller than the frequency domain amplitude threshold value, which indicates that the engine is normal in operation at the moment, and generates a normal operation signal;
if any discrete frequency point exists, the frequency domain amplitude value is obtained When the frequency domain amplitude threshold value is larger than or equal to the frequency domain amplitude threshold value, stall hysteresis can occur at the moment, and a suspected stall hysteresis signal is generated;
it should be noted that, performing fast fourier transform on the pressure difference, converting the time domain signal into a frequency domain signal, and comparing the frequency domain amplitude with a threshold value to primarily determine whether the engine may have stall hysteresis;
based on the generated suspected stall hysteresis signal, the intake air flow is obtained Response time to throttle command, which means the intake air flow rate of the engine after receiving the change of throttle commandThe time elapsed from the current state to the state corresponding to the new throttle command;
if the response time is smaller than the response time threshold, judging that the engine does not have stall hysteresis, and generating a normal running signal;
if the response time is greater than or equal to the response time threshold, judging that the engine has stall hysteresis, and generating a stall hysteresis signal;
It should be noted that, for the suspected stall hysteresis, the response time of the intake air flow to the throttle command is analyzed, so as to determine whether the stall hysteresis of the engine actually occurs;
based on the generated normal operation signal, the inlet pressure and the outlet pressure of the compressor at the current measurement time point are obtained and are subjected to ratio processing to obtain a real-time pressure ratio Acquiring the air inlet flow of the engine at the current measurement time pointCombining the obtained intake air flow ratesTo real time pressure ratioObtaining a real-time measurement point of the current measurement time point on an air inlet flow-pressure ratio plane;
Calculating the distance between the real-time measuring point and the surge boundary on the plane of the air inlet flow-pressure ratio, and specifically, obtaining the air inlet flow which is the same as the real-time measuring point on the surge boundary The corresponding pressure ratio isBy the formula
Calculating to obtain a stability margin value SM of the engine in a normal running state;
It should be noted that, the purpose of this step is to monitor the running state of the engine in real time, discover the stall hysteresis phenomenon in time, calculate its stability margin value at the same time when the engine is normally operated, offer the guarantee for safe operation of the engine;
S4, if the generated stall hysteresis signal is received, performing time-frequency characteristic analysis on pressure difference signals before and after the stall hysteresis signal, estimating and updating key parameters in a surge boundary mathematical model by combining CFD transient simulation and a self-adaptive Kalman filtering algorithm, and calculating a stability margin value of the engine under the stall hysteresis phenomenon according to the updated surge boundary;
In some embodiments, if a stall-lag signal is received, the pressure difference in the delta t time window before and after the stall-lag signal is generated in the actual operating cycle of the engine is extracted Analysis of time-frequency characteristics of pressure difference signals by wavelet transform, the formula of wavelet transform is
Wherein, Indicated is the input pressure difference signal,Is a wavelet basis function, a represents a scale parameter, b represents a panning parameter,Representing wavelet coefficients obtained by wavelet transformation;
Wavelet coefficient energy of different frequency bands is calculated based on wavelet coefficients obtained through wavelet transformation, large disc energy distribution characteristics are combined with CFD transient simulation results to obtain simulation data, and pressure difference signals are obtained through a data assimilation technology Fusing the stall hysteresis characteristic data with the simulation data to obtain stall hysteresis characteristic data;
the energy distribution characteristics of the pressure difference before and after the stall hysteresis signal are analyzed by wavelet transformation, so that more comprehensive stall hysteresis characteristic data are obtained;
Based on the fused stall hysteresis characteristic data, estimating key parameters in a surge boundary mathematical model by adopting an adaptive Kalman filtering algorithm, and specifically expanding an intake air flow-pressure ratio coefficient term in a surge boundary analysis expression into a time-varying form:
the coefficients a (t), b (t) and c (t) are all updated through stall hysteresis characteristic data fitting, an objective function is constructed through historical data in a sliding time window, and the coefficients are optimized through a gradient descent method;
It should be noted that, the purpose of estimating and updating the key parameters of the surge boundary mathematical model is to make the revised surge boundary reflect the influence of the engine performance degradation and the component wear;
Integrating a real-time data interface in an Origin platform, dynamically updating an intake air flow-pressure ratio characteristic curve, aiming at a stall hysteresis region, adopting a fractal interpolation algorithm to enhance the resolution of the curve in a nonlinear region, obtaining a corrected surge boundary, calculating the Hausdorff distance between the corrected surge boundary and a real-time measurement point, and quantifying the stability margin value of an engine
Calculating to obtain a stability margin value SM of the engine under the stall hysteresis phenomenon, wherein k is the number of measurement time points in a deltat time window before and after generating a stall hysteresis signal,The real-time pressure ratio of the compressor at the ith measurement time point in the time window is shown,Representing the intake air flow rate at the surge boundary at the ith measured time point in the time windowThe corresponding pressure ratios, i=1, 2,3, &..k;
It should be noted that, the function of this step is to deeply analyze the characteristics of stall hysteresis, correct the surge boundary, and improve the accuracy of calculation of the stability margin value, so as to better evaluate the stability of the engine under the stall hysteresis condition;
S5, based on the obtained engine stability margin value, evaluating the overall engine stability margin, and generating a safety signal, an early warning signal or a danger signal of the engine according to an evaluation result;
in some embodiments, the overall engine stability margin is evaluated according to the calculated engine stability margin value;
Specifically, if the stability margin value of the engine is greater than or equal to the early warning threshold value, evaluating the stability margin of the whole engine as good, and generating a safety signal;
If the stability margin value of the engine is larger than or equal to the danger threshold value and smaller than the early warning threshold value, evaluating the stability margin of the whole engine as common, and generating an early warning signal;
if the stability margin value of the engine is smaller than the danger threshold value, evaluating the stability margin of the whole engine as danger, and generating a danger signal;
It should be noted that, the function of this step is to divide the stable state of the engine into three levels of good, normal and dangerous according to the stability margin value of the engine, and generate corresponding signals, discover the unstable state of the engine in time, and provide decision basis for the operation management and maintenance of the engine;
According to the technical scheme, the physical characteristics and the working principle of all parts of a gas turbine engine are analyzed, the number of stages of the parts are built by combining CFD numerical simulation, the number of stages of the parts is integrated into an engine complete machine model, simulation calculation is achieved through a MATLAB platform, an engine experiment table is built for experiments, whether a gas compressor enters a surge state or not is judged by adjusting the inlet flow and monitoring pressure change, experimental data are recorded, the numerical simulation is conducted on the basis of the built engine complete machine model, the surge state in the simulation process is judged, the simulation data are recorded, the simulation data are compared with the experimental data, the accuracy of the model is verified, if the model is accurate, a surge boundary is built, if the model is inaccurate, the model is optimized, the pressure difference and the inlet flow rate of the gas compressor are measured in real time, the inlet and outlet of the air flow of the engine are calculated, the pressure difference and the inlet flow rate of the engine are analyzed, the frequency domain characteristics of the pressure difference are utilized, whether the engine stall hysteresis phenomenon occurs is judged, a normal running signal or stall hysteresis signal is generated, if the normal running signal is generated, a stability margin value of the engine is calculated, if the stall hysteresis signal is received, the time-frequency characteristic is carried out on the pressure difference signal before and after the stall hysteresis signal is judged, the surge margin signal is calculated, and the stability margin value is calculated, and the engine is estimated, and the safety margin is calculated, and the engine is calculated, and the safety margin is calculated.
In the second embodiment, as shown in fig. 4, the method for evaluating the stability margin of the whole aircraft gas turbine engine provided by the embodiment of the invention specifically comprises the following steps:
the complete machine modeling module is used for constructing a complete machine model of the engine;
According to the physical characteristics and working principles of each component of the gas turbine engine, a corresponding component level mathematical model is established, and each component of the gas turbine engine comprises a gas compressor, a combustion chamber, a turbine and the like;
Specifically, based on a one-dimensional unsteady flow theory, a partial differential equation describing the internal flow of the compressor is solved by using a characteristic line method, the geometric parameters of the compressor are combined, the geometric parameters comprise blade shape, progression, blade tip clearance and the like, a component level mathematical model of the compressor is constructed, and the component level mathematical model of the compressor is corrected by using a CFD numerical simulation result;
based on a chemical reaction dynamics mechanism, combining CFD simulation analysis of a three-dimensional flow field in a combustion chamber, taking fuel injection, atomization, mixing and combustion processes into consideration, and constructing a component level model of the combustion chamber by solving energy conservation, mass conservation and momentum conservation equations;
based on the working principle of the turbine, a aerodynamic thermodynamic model of the turbine is established, a complex flow field in a turbine blade channel is simulated and analyzed by CFD, and model parameters are corrected by combining experimental data, so that a part level model of the turbine is obtained;
Connecting and integrating the stage models of all the parts according to the actual structure and the working flow of the gas turbine engine, correlating the parameters of all the parts through mass conservation, energy conservation and momentum conservation equations to construct a complete engine model, constructing a complete engine model platform through system simulation software MATLAB, integrating the stage models of all the parts into the platform in a module form, and realizing the simulation calculation of the overall performance of the engine;
The boundary analysis module is used for constructing an engine experiment table to perform experiments, performing numerical simulation according to an engine complete machine model, recording experiment and simulation data when the compressor enters a surge state, comparing the experiment with the simulation data, verifying the accuracy of the model, constructing a surge boundary according to the model if the model is accurate, and optimizing the model if the model is inaccurate;
A special engine experiment table is constructed, and an air inlet flow regulating device and a pressure sensor are provided, wherein the air inlet flow regulating device can accurately regulate and control the air inlet flow of the engine, and the pressure sensor is arranged in a flow passage of the air compressor and at an inlet and an outlet of the air compressor and is used for monitoring the pressure value in the flow passage of the air compressor, the inlet pressure value and the outlet pressure value of the air compressor in real time;
according to the design working condition range of the engine, setting the initial air inlet flow as ,The method is characterized in that the method is close to the maximum air inlet flow of normal operation of an engine, in the experimental process, the air inlet flow is gradually reduced by a fixed step delta Q, after the air inlet flow is adjusted each time, the engine is waited to run stably, each parameter is ensured to reach a steady state, and the air inlet flow is adjusted again;
Taking a plurality of acquisition time points in the boundary analysis time period, wherein the interval duration between adjacent acquisition time points is the same, and acquiring the pressure value in the flow passage through a pressure sensor arranged in the flow passage of the air compressor at the acquisition time points;
The pressure values acquired at the adjacent acquisition time points are subjected to difference value processing, absolute value processing is taken, a pressure fluctuation amplitude is obtained, and the obtained pressure fluctuation amplitude is compared with a pressure fluctuation threshold;
If the pressure fluctuation amplitude is greater than or equal to the pressure fluctuation threshold, the obvious airflow oscillation appears in the interior of the air compressor, the air compressor is judged to enter a surge state, and the experimental air inlet flow of the air compressor is recorded Collecting the outlet pressure value and the inlet pressure value of the air compressor through pressure sensors arranged at the inlet and outlet positions of the air compressor, and carrying out ratio processing on the obtained outlet pressure value and the obtained inlet pressure value to obtain an experimental surge pressure ratio;
Based on the obtained engine complete machine model platform, the corresponding working condition of the engine in the experimental process is simulated, and the air inlet flow is set from the experimentFirstly, gradually reducing the step length delta Q as the same as an experiment, performing numerical simulation calculation, under each air inlet flow working condition, obtaining flow field distribution in the air compressor by solving a three-dimensional Reynolds average N-S equation, including parameters such as speed, pressure, temperature and the like, calculating the Lyapunov index in the air compressor based on a nonlinear dynamics theory, when the Lyapunov index is greater than 0, indicating that the air flow in the air compressor is in an unstable state, judging that the air compressor enters a surge state, and recording the simulated air inlet flow of the air compressorCalculated simulated surge pressure ratio;
For experimental air inlet flow rate obtained by experimentSurge ratio of experimentRespectively and simulatively obtaining simulative air inlet flowAnalog surge pressure ratioComparative analysis was performed by the formula
Calculating to obtain relative error of air inflowRelative error to the pressure ratioComparing the obtained relative air inlet flow error and pressure ratio error with an air inlet flow error threshold and a pressure ratio error threshold respectively;
If the relative error of the air inlet flow is larger than the error threshold of the air inlet flow or the relative error of the pressure ratio is larger than the error threshold of the pressure ratio, the numerical simulation result is larger than the experimental result;
If the relative error of the air inlet flow is smaller than or equal to the air inlet flow error threshold value and the relative error of the pressure ratio is smaller than or equal to the pressure ratio error threshold value, the numerical simulation result is well matched with the experimental result, and a simulation accurate signal is generated;
the method comprises the steps of carrying out experiments and simulation on an engine under a plurality of different working conditions, obtaining the times of generating simulation accurate signals, and carrying out ratio processing on the times and the total times of the experimental and simulated working conditions to obtain the coincidence ratio of the whole engine model;
If the anastomosis ratio is larger than or equal to the anastomosis ratio threshold, judging that the simulation result of the whole engine model is accurate, and generating a model anastomosis signal;
If the coincidence ratio is smaller than the coincidence ratio threshold, judging that the simulation result of the whole engine model is inaccurate, and generating a model deviation signal;
Based on the generated model matching signals, through analysis of simulation results under different working conditions and by combining with nonlinear dynamics theory, a mathematical model of an engine surge boundary is established, and the surge boundary is expressed as a function of intake air flow Q and pressure ratio pi Fitting a large number of simulation results according to a multiple regression analysis method to obtain an analytical expression of a surge boundary;
according to the simulation result, drawing an intake air flow-pressure ratio characteristic curve of the engine through a data processing software Origin, and drawing a continuous surge boundary on the characteristic curve according to an analytical expression of the surge boundary;
Based on the generated model deviation signal, adopting a genetic algorithm and sequence quadratic programming mixed optimization strategy, defining an fitness function by taking an experimental surge pressure ratio as an optimization target, setting a parameter search range on an engine complete machine model platform, performing global search through the genetic algorithm, performing local refinement correction through sequence quadratic programming, and updating the engine complete machine model;
Re-performing simulation calculation of a surge boundary based on the updated model, and comparing with an experimental result until the anastomosis ratio of the whole engine model is greater than or equal to the anastomosis ratio threshold;
The hysteresis judging module is used for analyzing whether the engine has stall hysteresis or not in real time, generating stall hysteresis signals if the stall hysteresis occurs, otherwise generating normal running signals, and calculating a stability margin value of normal running of the engine;
during the actual running period of the engine, the inlet pressure of the compressor is measured in real time at a measurement time point by the pressure sensor And outlet pressureThe actual running period of the engine represents a period of time in a working state after the engine is actually put into operation, a plurality of measuring time points exist in the actual running period of the engine, the interval duration between the adjacent measuring time points is the same, and t represents the time sequence number of the measuring time points in the actual running period of the engine;
For the measured inlet pressure of the compressor And outlet pressurePerforming differential processing to obtain pressure difference;
Likewise, the air flow velocity in the engine is measured in real time at the measurement time point by the hot wire anemometer during the actual operation period of the engineIn combination with measuring the sectional area A of the section of the engine, the flow formula is adopted
Calculating to obtain the air inlet flow of the engine at the measurement time point;
For the obtained pressure differencePerforming a fast fourier transform by the formula
Converting the time domain signal into a frequency domain signal to obtain a pressure difference frequency domain amplitudeWhere j represents an imaginary unit,N represents the number of discrete frequency points,Is a discrete point of frequency which is a frequency band,=0,1,2......,N-1;
The obtained frequency domain amplitudeComparing with a frequency domain amplitude threshold;
If the frequency domain amplitude of all the discrete frequency points All are smaller than the frequency domain amplitude threshold value, which indicates that the engine is normal in operation at the moment, and generates a normal operation signal;
if any discrete frequency point exists, the frequency domain amplitude value is obtained When the frequency domain amplitude threshold value is larger than or equal to the frequency domain amplitude threshold value, stall hysteresis can occur at the moment, and a suspected stall hysteresis signal is generated;
based on the generated suspected stall hysteresis signal, the intake air flow is obtained Response time to throttle command, which means the intake air flow rate of the engine after receiving the change of throttle commandThe time elapsed from the current state to the state corresponding to the new throttle command;
if the response time is smaller than the response time threshold, judging that the engine does not have stall hysteresis, and generating a normal running signal;
if the response time is greater than or equal to the response time threshold, judging that the engine has stall hysteresis, and generating a stall hysteresis signal;
based on the generated normal operation signal, the inlet pressure and the outlet pressure of the compressor at the current measurement time point are obtained and are subjected to ratio processing to obtain a real-time pressure ratio Acquiring the air inlet flow of the engine at the current measurement time pointCombining the obtained intake air flow ratesTo real time pressure ratioObtaining a real-time measurement point of the current measurement time point on an air inlet flow-pressure ratio plane;
Calculating the distance between the real-time measuring point and the surge boundary on the plane of the air inlet flow-pressure ratio, and specifically, obtaining the air inlet flow which is the same as the real-time measuring point on the surge boundary The corresponding pressure ratio isBy the formula
Calculating to obtain a stability margin value SM of the engine in a normal running state;
the hysteresis optimization module is used for updating the surge boundary if a stall hysteresis signal is generated, and calculating a stability margin value of the engine under the stall hysteresis phenomenon based on the updated surge boundary;
If the generated stall hysteresis signal is received, extracting the pressure difference in the delta t time window before and after the stall hysteresis signal is generated in the actual running period of the engine Analysis of time-frequency characteristics of pressure difference signals by wavelet transform, the formula of wavelet transform is
Wherein, Indicated is the input pressure difference signal,Is a wavelet basis function, a represents a scale parameter, b represents a panning parameter,Representing wavelet coefficients obtained by wavelet transformation;
Wavelet coefficient energy of different frequency bands is calculated based on wavelet coefficients obtained through wavelet transformation, large disc energy distribution characteristics are combined with CFD transient simulation results to obtain simulation data, and pressure difference signals are obtained through a data assimilation technology Fusing the stall hysteresis characteristic data with the simulation data to obtain stall hysteresis characteristic data;
Based on the fused stall hysteresis characteristic data, estimating key parameters in a surge boundary mathematical model by adopting an adaptive Kalman filtering algorithm, and specifically expanding an intake air flow-pressure ratio coefficient term in a surge boundary analysis expression into a time-varying form:
the coefficients a (t), b (t) and c (t) are all updated through stall hysteresis characteristic data fitting, an objective function is constructed through historical data in a sliding time window, and the coefficients are optimized through a gradient descent method;
Integrating a real-time data interface in an Origin platform, dynamically updating an intake air flow-pressure ratio characteristic curve, aiming at a stall hysteresis region, adopting a fractal interpolation algorithm to enhance the resolution of the curve in a nonlinear region, obtaining a corrected surge boundary, calculating the Hausdorff distance between the corrected surge boundary and a real-time measurement point, and quantifying the stability margin value of an engine
Calculating to obtain a stability margin value SM of the engine under the stall hysteresis phenomenon, wherein k is the number of measurement time points in a deltat time window before and after generating a stall hysteresis signal,The real-time pressure ratio of the compressor at the ith measurement time point in the time window is shown,Representing the intake air flow rate at the surge boundary at the ith measured time point in the time windowThe corresponding pressure ratios, i=1, 2,3, &..k;
the margin evaluation module evaluates the stability margin of the whole engine according to the stability margin value;
According to the calculated engine stability margin value, evaluating the stability margin of the whole engine;
Specifically, if the stability margin value of the engine is greater than or equal to the early warning threshold value, evaluating the stability margin of the whole engine as good, and generating a safety signal;
If the stability margin value of the engine is larger than or equal to the danger threshold value and smaller than the early warning threshold value, evaluating the stability margin of the whole engine as common, and generating an early warning signal;
and if the stability margin value of the engine is smaller than the danger threshold value, evaluating the stability margin of the whole engine as danger, and generating a danger signal.
The foregoing describes one embodiment of the present invention in detail, but the description is only a preferred embodiment of the present invention and should not be construed as limiting the scope of the invention. All equivalent changes and modifications within the scope of the present invention are intended to be covered by the present invention.

Claims (10)

1.一种航空燃气涡轮发动机整机稳定裕度评估方法，其特征在于，包括以下步骤：1. A method for evaluating the stability margin of an aircraft gas turbine engine, comprising the following steps: 构建发动机整机模型；Build the whole engine model; 构建发动机实验台进行实验，同时根据发动机整机模型进行数值模拟，记录压气机进入喘振状态时的实验与模拟数据并进行对比，验证模型的准确性，若准确，则根据模型构建喘振边界，若不准确，对模型进行优化；Construct an engine test bench for experiments, and perform numerical simulation based on the engine model. Record and compare the experimental and simulation data when the compressor enters the surge state to verify the accuracy of the model. If it is accurate, construct the surge boundary based on the model. If it is inaccurate, optimize the model. 实时分析发动机是否出现失速迟滞现象，若出现，则生成失速迟滞信号，反之则生成正常运行信号，并计算发动机正常运行的稳定裕度值；Real-time analysis of whether the engine has stall hysteresis phenomenon. If it does, a stall hysteresis signal is generated. Otherwise, a normal operation signal is generated, and the stability margin value of the normal operation of the engine is calculated; 若生成失速迟滞信号，对喘振边界进行更新，基于更新后的喘振边界计算发动机发生失速迟滞现象下的稳定裕度值；If a stall hysteresis signal is generated, the surge boundary is updated, and a stability margin value of the engine when the stall hysteresis phenomenon occurs is calculated based on the updated surge boundary; 根据稳定裕度值对发动机整机稳定裕度进行评估。The stability margin of the engine is evaluated based on the stability margin value. 2.根据权利要求1所述的一种航空燃气涡轮发动机整机稳定裕度评估方法，其特征在于，所述构建喘振边界的方式为：2. The method for evaluating the stability margin of an aircraft gas turbine engine according to claim 1, wherein the surge boundary is constructed in the following manner: 若生成模型吻合信号，通过对不同工况下模拟结果的分析，建立发动机喘振边界的数学模型，根据多元回归分析方法，对大量模拟结果进行拟合，得到喘振边界的解析表达式；If the model matching signal is generated, the mathematical model of the engine surge boundary is established by analyzing the simulation results under different working conditions. According to the multivariate regression analysis method, a large number of simulation results are fitted to obtain the analytical expression of the surge boundary. 根据解析表达式在特性曲线上绘制出喘振边界。The surge boundary is drawn on the characteristic curve according to the analytical expression. 3.根据权利要求2所述的一种航空燃气涡轮发动机整机稳定裕度评估方法，其特征在于，所述模型吻合信号的获取方式为：3. The method for evaluating the stability margin of an aviation gas turbine engine according to claim 2, wherein the model matching signal is obtained by: 在若干个不同工况下对发动机进行实验与模拟，获取生成模拟准确信号的次数并进行数据处理，得到发动机整机模型的吻合比值；The engine is tested and simulated under several different working conditions, the number of times the simulated accurate signal is generated is obtained and the data is processed to obtain the matching ratio of the engine model; 若吻合比值大于或等于吻合比阈值，生成模型吻合信号，反之，则生成模型偏差信号。If the match ratio is greater than or equal to the match ratio threshold, a model match signal is generated; otherwise, a model deviation signal is generated. 4.根据权利要求3所述的一种航空燃气涡轮发动机整机稳定裕度评估方法，其特征在于，所述模拟准确信号的获取方式为：4. The method for evaluating the stability margin of an aviation gas turbine engine according to claim 3, wherein the analog accurate signal is obtained by: 对实验得到的实验进气流量、实验喘振压比分别与模拟得到的模拟进气流量、模拟喘振压比进行对比分析，计算得到进气流量相对误差与压比相对误差；The experimental intake flow rate and experimental surge pressure ratio obtained by the experiment are compared and analyzed with the simulated intake flow rate and simulated surge pressure ratio obtained by the simulation, and the relative error of the intake flow rate and the relative error of the pressure ratio are calculated; 若进气流量相对误差小于或等于进气流量误差阈值，且压比相对误差小于或等于压比误差阈值，生成模拟准确信号。If the relative error of the intake flow rate is less than or equal to the intake flow rate error threshold, and the relative error of the pressure ratio is less than or equal to the pressure ratio error threshold, a simulated accurate signal is generated. 5.根据权利要求4所述的一种航空燃气涡轮发动机整机稳定裕度评估方法，其特征在于，所述实验进气流量与实验喘振压比的获取方式为：5. The method for evaluating the stability margin of an aircraft gas turbine engine according to claim 4, wherein the experimental intake flow rate and the experimental surge pressure ratio are obtained in the following manner: 在实验过程中，以固定的步长减小进气流量；During the experiment, the intake air flow rate was reduced with a fixed step size; 获取减小进气流量过程中的压力波动幅值，若压力波动幅值大于或等于压力波动阈值，判定压气机进入喘振状态，记录压气机的实验进气流量，并采集压气机出口压力值与进口压力值并进行数据处理，得到实验喘振压比。The pressure fluctuation amplitude in the process of reducing the intake flow rate is obtained. If the pressure fluctuation amplitude is greater than or equal to the pressure fluctuation threshold, it is determined that the compressor enters the surge state. The experimental intake flow rate of the compressor is recorded, and the compressor outlet pressure value and inlet pressure value are collected and processed to obtain the experimental surge pressure ratio. 6.根据权利要求4所述的一种航空燃气涡轮发动机整机稳定裕度评估方法，其特征在于，所述模拟进气流量与模拟喘振压比的获取方式为：6. The method for evaluating the stability margin of an aircraft gas turbine engine according to claim 4, wherein the simulated intake flow rate and the simulated surge pressure ratio are obtained in the following manner: 根据发动机整机模型进行数值模拟，以与实验相同的步长逐步减小进气流量，计算减小进气流量过程中压气机内部李雅普诺夫指数，若李雅普诺夫指数大于0，判定压气机进入喘振状态，记录压气机的模拟进气流量以及计算得到的模拟喘振压比。Numerical simulation is performed based on the engine whole machine model. The intake flow rate is gradually reduced with the same step size as the experiment. The Lyapunov index inside the compressor is calculated during the process of reducing the intake flow rate. If the Lyapunov index is greater than 0, it is determined that the compressor enters a surge state. The simulated intake flow rate of the compressor and the calculated simulated surge pressure ratio are recorded. 7.根据权利要求1所述的一种航空燃气涡轮发动机整机稳定裕度评估方法，其特征在于，所述发动机正常运行的稳定裕度值的获取方式为：7. The method for evaluating the stability margin of an aircraft gas turbine engine according to claim 1, wherein the stability margin value of the normal operation of the engine is obtained by: 若接收到正常运行信号，获取发动机的实时压比与进气流量，结合得到当前测量时间点在进气流量-压比平面上的实时测量点；If a normal operation signal is received, the real-time pressure ratio and intake air flow rate of the engine are obtained, and the real-time measurement point on the intake air flow rate-pressure ratio plane at the current measurement time point is obtained by combining them; 获取喘振边界上与实时测量点相同进气流量所对应的压比并进行数据处理，计算得到发动机在正常运行状态下的稳定裕度值。The pressure ratio corresponding to the same intake flow rate as the real-time measurement point on the surge boundary is obtained and data processing is performed to calculate the stability margin value of the engine under normal operating conditions. 8.根据权利要求7所述的一种航空燃气涡轮发动机整机稳定裕度评估方法，其特征在于，所述正常运行信号的获取方式为：8. The method for evaluating the stability margin of an aviation gas turbine engine as claimed in claim 7, wherein the normal operating signal is obtained by: 若接收到疑似失速迟滞信号，获取进气流量对油门指令的响应时间，若响应时间小于响应时间阈值，生成正常运行信号，反之，生成失速迟滞信号。If a suspected stall hysteresis signal is received, the response time of the intake flow to the throttle command is obtained, and if the response time is less than the response time threshold, a normal operation signal is generated, otherwise, a stall hysteresis signal is generated. 9.根据权利要求8所述的一种航空燃气涡轮发动机整机稳定裕度评估方法，其特征在于，所述疑似失速迟滞信号的获取方式为：9. The method for evaluating the stability margin of an aviation gas turbine engine according to claim 8, wherein the suspected stall hysteresis signal is obtained by: 在发动机实际运行周期内，实时获取压气机进出口压力差；During the actual operation cycle of the engine, the compressor inlet and outlet pressure difference is obtained in real time; 对得到的压气机进出口压力差进行快速傅里叶变换，将时域信号转换为频域信号，得到压力差频域幅值；Perform fast Fourier transform on the compressor inlet and outlet pressure difference, convert the time domain signal into a frequency domain signal, and obtain the frequency domain amplitude of the pressure difference; 若存在任一离散频率点使频域幅值大于或等于频域幅值阈值，生成疑似失速迟滞信号。If there is any discrete frequency point that makes the frequency domain amplitude greater than or equal to the frequency domain amplitude threshold, a suspected stall hysteresis signal is generated. 10.根据权利要求1所述的一种航空燃气涡轮发动机整机稳定裕度评估方法，其特征在于，所述失速迟滞现象下的稳定裕度值的获取方式为：10. The method for evaluating the stability margin of an aircraft gas turbine engine as claimed in claim 1, wherein the stability margin value under the stall hysteresis phenomenon is obtained by: 若接收到失速迟滞信号，提取发动机实际运行周期内生成失速迟滞信号前后Δt时间窗口内的压气机进出口压力差，进行数据分析与处理，将喘振边界解析表达式扩展为时变形式，得到修正后的喘振边界；If a stall hysteresis signal is received, the compressor inlet and outlet pressure difference within the Δt time window before and after the stall hysteresis signal is generated in the actual engine operation cycle is extracted, and data analysis and processing are performed to expand the surge boundary analytical expression into a time-varying form to obtain a corrected surge boundary; 根据修正后的喘振边界与实时测量点进行数据处理，计算得到发动机在发生失速迟滞现象下的稳定裕度值。Data processing is performed based on the corrected surge boundary and the real-time measurement points to calculate the stability margin value of the engine when the stall hysteresis phenomenon occurs.
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