CN109184913B - Stability estimation and prediction-based active compound control method for aerodynamic stability of aircraft engine - Google Patents
Stability estimation and prediction-based active compound control method for aerodynamic stability of aircraft engine Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/04—Antivibration arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
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Abstract
The invention discloses an active compound control method for aerodynamic stability of an aircraft engine based on stability estimation and prediction, which comprises the following steps: (1) a pneumatic instability mechanism and an active control method of the gas compressor; (2) an aircraft engine stability margin estimation and active stability control method; (3) an aircraft engine instability prediction and active anti-surge control method; (4) an active stability compound control method for an aircraft engine. Aiming at the problem of aerodynamic stability of the aero-engine, the aerodynamic stability of the aero-engine is improved through three different angles of stability expansion of a compressor part, utilization of residual stability margin and active anti-surge, a regulation strategy and algorithm which can dynamically regulate and control surge margin along with application requirements, is suitable for the active stability control characteristics and engineering application background of the aero-engine and meets the actual use requirements is obtained.
Description
Technical Field
The invention relates to an active compound control method for aerodynamic stability of an aero-engine based on stability estimation and prediction, and belongs to the technical field of aero-engine stability control.
Background
Five typical technical features of fourth generation fighters are: stealth, supersonic cruise, high maneuverability, comprehensive avionics and autonomous logistics. The advantages are that the use of an S-shaped air inlet channel and a high thrust-weight ratio engine and the application of over-stall maneuver are not separated, but the adverse effect of air inlet distortion on the stability of the air compressor is increased, and a higher requirement is provided for the stability of the engine; the engine faces the comprehensive optimization challenge of high pressure ratio, high efficiency, high stability and high distortion resistance, the contradiction between the performance and the stability of the engine is more and more prominent, the stability problem becomes more prominent for the high-performance engine developed in China and the engine with higher thrust-weight ratio in the future, and the engine is a key problem and a technical bottleneck of the success and failure of the new generation of aero-engines. A difficulty with aero-stability control of an aircraft engine is the uncertainty of the stability boundary. Factors such as intake distortion, degradation of engine component performance, manufacturing and assembly errors, etc., can cause the engine stability margin to shift. The pneumatic stability control method includes a passive control method and an active control method. The current aero-engine pneumatic stability control adopts a passive control method, and the control method is based on a destabilization control line and combines a short-time stability augmentation control system and a destabilization restoration control system to solve the unstable working problem of the engine. The passive control method taking the instability control line, the short-time stability augmentation control system and the instability restoration system as the core is developed more mature, is widely applied to the power device of the third-generation fighter, and well ensures the safety of the engine and the airplane. However, the conservative stability margin of the instability control line, the open loop of the short-time stability augmentation control system and the retrospective nature of the instability restoration control system cause the traditional instability control method to have a plurality of fatal defects, which are mainly reflected in the following aspects: (1) the performance of the engine cannot be fully exerted due to the existence of the instability control line, and the engine with higher performance has to be selected under the same performance requirement, so that the weight of the engine is greatly increased, and the thrust-weight ratio is greatly reduced; (2) the instability control line reduces the working range of the engine, so that the residual surge margin cannot be effectively utilized, and the operability of the engine and the maneuverability of the airplane are reduced; (3) the short-time stability augmentation control system is open-loop control, which means that a pilot can forcibly start the engine regardless of whether the engine really faces instability danger or not, and the conservative control measures can certainly reduce the performance of the engine; (4) when the instability recovery control system is started, the engine is already in a pneumatic instability state, if the 'unrecoverable stall' is entered, the instability recovery control system cannot play a role, and has to be stopped and restarted in the air, and even if the instability state can be successfully exited, the aging of the engine is accelerated due to transient instability, and the service life of the engine is shortened.
Disclosure of Invention
Aiming at the defects in the prior art and the problem of aerodynamic stability of the aero-engine, the aerodynamic stability of the engine is improved through three different angles of stability expansion of a compressor part, utilization of residual stability margin and active anti-surge, a regulation strategy and an algorithm which can dynamically regulate and control surge margin along with application requirements, are suitable for the active stability control characteristics of the aero-engine and engineering application backgrounds and meet the actual use requirements are obtained.
In order to solve the problems, the technical scheme adopted by the invention is as follows:
an active compound control method for aerodynamic stability of an aircraft engine based on stability estimation and prediction, the active compound control method comprising:
(1) pneumatic instability mechanism and active control method of gas compressor
(1.1) dynamic model of aerodynamic stability of gas compressor
On the basis of an MG3 model, the accuracy of the model is improved by considering the dynamic process of a compressor rotor and the influence of rotating stall high-order harmonics, and a new compressor variable-speed over-stall transient model is deduced;
(1.2) method for analyzing instability mechanism of gas compressor and actively controlling instability mechanism of gas compressor
The method comprises the steps of analyzing the occurrence of rotating stall and surge by adopting a bifurcation theory, deeply knowing the mechanism of the occurrence of rotating stall and surge from the viewpoint of system dynamics, providing theoretical guidance for the active stability control of the compressor, and designing an active control method for the pneumatic instability of the compressor according to a conclusion obtained by bifurcation analysis on a stability model of the compressor so as to design a corresponding control algorithm;
(1.3) gas compressor stability output feedback active control based on state estimator
The pressure ratio is controlled by adopting a state estimator, the state estimator estimates the flow coefficient of a pressure system according to an input pressure value, and then an active controller is designed, wherein the active controller consists of the state estimator and a state feedback controller, the state estimator and the state feedback controller form an output feedback controller, and the state feedback controller calculates according to the pressure coefficient and the flow coefficient to obtain a control instruction value;
(2) stability margin estimation and active stability control method for aircraft engine
(2.1) real-time model of aircraft engine surge
The method comprises the steps that an aero-engine surge real-time model is a precondition for developing an aero-engine active stability control simulation test based on a stability margin closed loop, and is established by considering the volumetric dynamics effect of an engine cavity, the stall area characteristic of a gas compressor, the flameout characteristic of a combustion chamber and the inlet distortion of an engine on the basis of an existing aero-engine component level model;
(2.2) Surge margin estimation Algorithm and simulation
Firstly, calculating the correlation for measuring the repeatability of the pressure pulsation signal according to the pressure pulsation signal near the blade obtained by a pressure sensor, and obtaining the times of the correlation value crossing a threshold value according to the off-line analysis of experimental data; secondly, establishing an engine stability margin estimation model according to the inherent characteristic relation between the threshold crossing times and the surge margin value, and accurately estimating the real stability margin of the engine through an interpolation method according to the engine surge margin estimation model;
(2.3) active stability control method for aircraft engine
After the surge margin of the engine is obtained through a surge margin estimation algorithm, namely an active stability control law based on surge margin estimation is designed to form a surge margin closed-loop control loop, wherein the control method mainly comprises a surge margin estimation module and an active stability controller module; wherein, the active stability control method is intended to adopt robust H based on quadratic performance index2/H∞The method is designed, and the robustness of the control system is improved;
(3) method for predicting instability of aircraft engine and controlling active anti-surge
(3.1) simulation model of instability foreboding signal
The method comprises the steps of introducing engine instability prediction into experiments such as full-digital simulation, hardware-in-loop simulation and semi-physical simulation of an engine control system, researching an active anti-surge control method based on the instability prediction without real engine experiments, constructing instability foreboding signals, establishing a simulation model of the instability foreboding signals, adopting a simulation structure based on an MG3 model and a chaotic time sequence to the engine instability foreboding signals according to the characteristics of modal wave type instability foreboding disturbance, and considering the interaction between the instability foreboding signals and pressure pulsation signals generated by circumferential rotation of a compressor rotor blade;
(3.2) Engine instability prediction Algorithm
Detecting generation of a destabilization precursor before engine destabilization, designing an engine destabilization prediction algorithm by adopting a time-frequency analysis based method for modal wave type destabilization precursors according to research results of engine destabilization precursor phenomena, respectively designing algorithms for signals at different sensor positions, and for a sensor far away from a rotor blade of a compressor, adopting lower sampling frequency and directly carrying out frequency analysis to extract the strength of the engine destabilization precursor signals, for the sensor above the rotor blade of the compressor, modulating low-frequency precursor disturbance signals in frequency deviation and amplitude of high-frequency signals, detecting low-frequency components from the amplitude of the high-frequency signals by adopting envelope detection, and then carrying out spectrum analysis to obtain the strength of the destabilization precursor signals;
(3.3) active anti-surge control method
When the engine active stability controller fails, accurate and timely prediction can be carried out based on the instability prediction algorithm, active anti-surge control is implemented based on the prediction result, stable work of the engine can be fundamentally ensured, and the method specifically comprises the following operations:
(3.31) acquiring parameter signals such as engine pressure signals and the like sensitive to rotating stall and surge;
(3.32) identifying an engine instability foreboding signal by using an instability foreboding prediction algorithm, and sending an identification result to an active anti-surge controller, wherein the active anti-surge controller can adopt a traditional proportional-integral controller;
(3.33) the active anti-surge controller calculates a corresponding execution mechanism control instruction according to the recognition result and the control rule, and the execution mechanism moves to enable the working point of the engine to be far away from a surge boundary according to the control instruction;
(4) composite control method for active stability of aircraft engine
A multi-loop active stability composite control method is designed from three different levels of stability expansion, residual stability margin utilization and active anti-surge based on a compressor part, and is used for inhibiting the aerodynamic instability of an engine, and the control method is shown in figure 6: according to the control method, the stable working range of the compressor part is expanded through the compressor active control circuit, the residual stability margin is exerted to the maximum extent through the engine stability margin closed-loop control circuit, and the engine instability when the active stability control fails is avoided through the engine active anti-surge control circuit.
As an improvement of the above technical solution, in the practical application of (2.2), the surge margin estimation model needs to receive the pressure, flow and vibration signals collected by the sensor as input, while in the simulation, the engine model cannot simulate the signals with a certain stability margin, and the simulation experiment of the surge margin closed loop needs to simulate the relationship between the correlation degree "threshold crossing event" and the engine surge margin; adopting a random sequence with the same distribution of the occurrence frequency of the threshold crossing events and the threshold value relation, and carrying out mapping simulation on the exponential relation of the correlation degree threshold crossing events and the surge margin by using a sliding threshold value; inputting the surge margin obtained by the calculation of the engine surge model into a threshold value calculation module to obtain the threshold value size of the real surge margin, generating a random number sequence by a random number generator according to a preset frequency, obtaining a threshold value crossing event sequence according to the threshold value, counting the threshold value crossing events to obtain the frequency of the crossing events, and obtaining the real surge margin through a simulation relation.
Compared with the prior art, the invention has the following implementation effects:
(1) the pressure ratio and the stability margin of the engine can be increased, and the engine can work in a region with higher pressure ratio and efficiency of the compressor; under the same pressure ratio, the number of stages of the air compressor can be reduced, and the thrust-weight ratio of the engine is increased.
(2) The engine can work at a high-performance point with smaller surge margin in the acceleration process, the acceleration performance of the engine is improved, and the maneuverability of the airplane is enhanced.
(3) The effective control is implemented before the engine enters the instability, so that the damage to the engine caused by surge or stall is reduced, the service life of the engine is prolonged, and the maintenance cost is reduced.
Drawings
FIG. 1 is a technical circuit diagram of an active composite control method for aerodynamic stability of an aircraft engine based on stability estimation and prediction according to the present invention;
FIG. 2 is a diagram of a rotating stall and surge output feedback active control scheme based on a state estimator of the present invention;
FIG. 3 is a graph of an aircraft engine active stability control strategy based on stability margin estimation in accordance with the present invention;
FIG. 4 is a block diagram of a robust controller according to the present invention;
FIG. 5 is a block diagram of the active anti-surge control method based on instability prediction according to the present invention;
FIG. 6 is a block diagram of a multi-loop active stability compound control method according to the present invention.
Detailed Description
The present invention will be described with reference to specific examples.
The current aero-engine pneumatic stability control adopts a passive control method, and the control method is based on a destabilization control line and combines a short-time stability augmentation control system and a destabilization restoration control system to solve the unstable working problem of the engine. However, the conservative stability margin of the instability control line, the open loop of the short-time stability augmentation control system and the retrospective nature of the instability restoration control system cause the traditional instability control method to have a plurality of fatal defects.
Aiming at the problem of aerodynamic stability of the aero-engine, the aerodynamic stability of the aero-engine is improved through three angles of part expansion, residual stability margin utilization and active anti-surge through two layers of parts and the whole machine, and a regulation strategy and an algorithm which can dynamically regulate and control the surge margin along with application requirements and are suitable for the active stability control characteristics and the engineering application background of the aero-engine are obtained.
The purpose of the invention is as follows:
(1) the method has the advantages that the accuracy of the compressor model is improved by considering the dynamic process of the compressor rotor and the influence of rotating stall high-order harmonics; the mechanism of the pneumatic instability of the compressor is revealed through a bifurcation theory; by utilizing the conclusion of the bifurcation theory, the rotating stall and surge active controller is designed, the instability phenomenon is inhibited, and the stable working range of the gas compressor is expanded.
(2) On the basis of an aircraft engine component level model, considering surge and inlet distortion to obtain an engine surge real-time model; estimating an engine surge margin in real time through a pressure correlation method; an active stability control law is designed based on a robust controller, a surge margin closed-loop control loop is constructed, the residual surge margin is fully utilized, and the dynamic performance of the engine is improved.
(3) The initial disturbance of the engine instability is detected on line in real time through time-frequency analysis, and the detection result is sent to the active anti-surge controller to form an active anti-surge control loop, so that the stable work of the engine can still be ensured when the active control fails.
The invention makes a technical route according to a research scheme of active control of the pneumatic stability of a gas compressor, active stability control based on stability margin estimation, active anti-surge control based on instability prediction and active stability composite control of an aeroengine, as shown in figure 1:
(1) pneumatic instability mechanism and active control method of gas compressor
(1.1) dynamic model of aerodynamic stability of gas compressor
The rotating stall and surge phenomena in compression systems are the key and theoretical basis for developing active control. Moor and Greitzer combine respective research results to deduce a famous MG model; the MG model is expressed by three partial differential equations, a Galerkin process is used, and a cubic curve is selected as a characteristic curve of the compressor, so that a classical MG3 model expressed by an ordinary differential equation set is obtained; according to the method, on the basis of a classical MG3 model, the accuracy of the model is improved by considering the dynamic process of a compressor rotor and the influence of rotating stall high-order harmonics, and a new transient model of the compressor over stall at the variable rotating speed is deduced. A block diagram of the MG model compression system is shown in fig. 2.
(1.2) method for analyzing instability mechanism of gas compressor and actively controlling instability mechanism of gas compressor
The research on the mechanism of the rotating stall and surge of the compression system has important significance on the prevention and active control of the rotating stall and surge; because the compression system test is restricted by factors such as higher cost and risk, larger test result difference caused by equipment difference and the like, the theoretical analysis obtains considerable attention, the essence of a plurality of compression system instability phenomena is disclosed, and the instability model of the compression system provides a foundation for the theoretical analysis. The invention adopts the bifurcation theory to analyze the occurrence of rotating stall and surge, deeply knows the mechanism of the occurrence of rotating stall and surge from the viewpoint of system dynamics and provides theoretical guidance for the active stability control of the compressor. According to the conclusion obtained by the bifurcation analysis of the stability model of the gas compressor, an active control method for the pneumatic instability of the gas compressor can be designed, and a corresponding control algorithm is further designed.
(1.3) gas compressor stability output feedback active control based on state estimator
Most of the current active control algorithms for the compressor need to use the flow or stall amplitude as an input parameter, however, only the pressure ratio in the compressor is a quantity which is easy to measure, so that the output feedback control using the pressure ratio as a measurable parameter has more important practical significance. Therefore, the invention adopts a state estimator to solve the problem, the state estimator estimates the flow coefficient of the pressure system according to the input pressure value, and then the design of the active controller is carried out. The control method to be employed is shown in fig. 2: the controller is composed of a state estimator and a state feedback controller, the state estimator and the state feedback controller form an output feedback controller, and the state feedback controller calculates according to the pressure coefficient and the flow coefficient to obtain a control instruction value.
2 aircraft engine stability margin estimation and active stability control method
(2.1) real-time model of aircraft engine surge
The invention relates to an aero-engine surge real-time model, which is a precondition for developing a stability margin closed-loop-based aero-engine active stability control simulation test.
(2.2) Surge margin estimation Algorithm and simulation
The surge margin of an engine is generally not measurable, so that the surge margin cannot be directly controlled. Therefore, the real-time estimation of the surge margin is a precondition for carrying out closed-loop control on the surge margin, and the method adopts a method for measuring the pressure correlation degree to solve the problem; the specific study scheme is as follows: firstly, calculating the correlation degree for measuring the repeatability of the pressure pulsation signal according to the pressure pulsation signal near the blade obtained by a pressure sensor, and obtaining the times of the correlation value crossing a threshold value according to the off-line analysis of experimental data; secondly, establishing an engine stability margin estimation model according to the inherent characteristic relation between the threshold crossing times and the surge margin value. According to the engine surge margin estimation model, the real stability margin of the engine can be accurately estimated through an interpolation method.
In practical application, a surge margin estimation model needs to receive signals such as pressure, flow and vibration collected by a sensor as input; in simulation, the engine model cannot simulate a signal with a certain stability margin. In order to develop a simulation experiment of a surge margin closed loop, the relationship between a correlation degree threshold crossing event and an engine surge margin needs to be simulated; the invention adopts a random sequence with the same distribution of the relationship between the occurrence frequency of the threshold crossing event and the threshold value, and uses a sliding threshold value to carry out mapping simulation on the exponential relationship between the correlation degree threshold crossing event and the surge margin; the specific scheme is shown in figure 3: inputting the surge margin obtained by the calculation of the engine surge model into a threshold value calculation module to obtain the threshold value size of the real surge margin, generating a random number sequence by a random number generator according to a preset frequency, obtaining a threshold value crossing event sequence according to the threshold value, counting the threshold value crossing events to obtain the frequency of the crossing events, and obtaining the real surge margin through a simulation relation.
(2.3) active stability control law for aircraft engine
After the surge margin of the engine is obtained through a surge margin estimation algorithm, an active stability control law based on surge margin estimation can be designed to form a surge margin closed-loop control loop. The control method of the invention is shown in figure 3: mainly comprises a surge margin estimation module and an active stability controller module, wherein the active stability controller module is intended to adopt a robust H based on quadratic performance index2/H∞The method is designed to improve the robustness of the control system, and a structural block diagram of the robust controller is shown in FIG. 4.
3-aircraft engine instability prediction and active anti-surge control method
(3.1) simulation model of instability foreboding signal
In order to introduce the engine instability prediction into the experiments of full-digital simulation, hardware-in-loop simulation, semi-physical simulation and the like of an engine control system, and research an active anti-surge control method based on the instability prediction without carrying out a real engine experiment, the instability foreboding signal needs to be constructed, and a simulation model of the instability foreboding signal is established; according to the characteristics of modal wave type instability foreboding disturbance, the invention adopts a simulation structure based on an MG model and a chaos time sequence to carry out on an engine instability foreboding signal, and considers the interaction between the instability foreboding signal and a pressure pulsation signal generated by the circumferential rotation of a rotor blade of a gas compressor.
(3.2) Engine instability prediction Algorithm
The generation of a destabilization precursor is detected before the engine is destabilized, which is a precondition for carrying out active anti-surge control based on the destabilization prediction, and the research result of the engine destabilization precursor phenomenon shows that for the modal wave type destabilization precursor, a continuous increasing process exists in the modal wave disturbance amplitude before the engine is completely destabilized. Before the initial disturbance of the modal wave is developed into rotating stall, the amplitude is small, the disturbance is submerged in system noise and measurement noise, and the disturbance of the modal wave is difficult to distinguish from a time domain; and reflected in the frequency domain, the generation and development of the modal wave are represented by a certain frequency component from nothing to nothing, and accompanied by a process of gradually increasing amplitude. Therefore, the engine instability prediction algorithm is designed by adopting a time-frequency analysis-based method, the algorithms are respectively designed aiming at signals of different sensor positions, for the sensor far away from the rotor blade of the compressor, the influence of the rotor blade on the precursor information contained in the signals is small, the lower sampling frequency can be adopted, the frequency analysis can be directly carried out, and the strength of the engine instability precursor signal is extracted. For a sensor above a rotor blade of the compressor, a low-frequency precursor disturbance signal is modulated in frequency deviation and amplitude of a high-frequency signal, a low-frequency component can be detected from the amplitude of the high-frequency signal by adopting envelope detection, and then frequency spectrum analysis is carried out to obtain the intensity of a destabilization precursor signal, wherein the destabilization prediction scheme adopted by the invention is shown in figure 5.
(3.3) active anti-surge control method
When the engine active stability controller fails, if accurate and timely prediction can be carried out based on the instability prediction algorithm and active anti-surge control is implemented based on the prediction result, the stable work of the engine can be fundamentally ensured. The invention adopts an active anti-surge control method based on instability prediction, and the structural block diagram is shown in figure 5: the specific scheme is as follows: (1) collecting parameter signals such as engine pressure and the like sensitive to rotating stall and surge; (2) using a destabilization foreboding prediction algorithm to identify an engine destabilization foreboding signal and sending an identification result to an active anti-surge controller, wherein the active anti-surge controller can adopt a traditional proportional-integral controller; (3) and the active anti-surge controller calculates a corresponding execution mechanism control instruction according to the recognition result and the control rule, and the execution mechanism acts according to the control instruction to enable the working point of the engine to be far away from a surge boundary.
(4) Composite control method for active stability of aircraft engine
Aiming at the problem of aerodynamic stability of an aeroengine, the invention aims to design a multi-loop active stability composite control method based on three different levels of stability expansion of a compressor part, utilization of residual stability margin and active anti-surge to inhibit aerodynamic instability of the engine, and the control method is shown as the following figure 6: according to the control method, the stable working range of the compressor part is expanded through the compressor active control circuit, the residual stability margin is exerted to the maximum extent through the engine stability margin closed-loop control circuit, and the engine instability when the active stability control fails is avoided through the engine active anti-surge control circuit.
The foregoing is a detailed description of the invention with reference to specific embodiments, and the practice of the invention is not to be construed as limited thereto. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (2)
1. An active compound control method for aerodynamic stability of an aircraft engine based on stability estimation and prediction is characterized in that: the active compound control method comprises the following steps:
(1) pneumatic instability mechanism and active control method of gas compressor
(1.1) dynamic model of aerodynamic stability of gas compressor
On the basis of an MG3 model, the accuracy of the model is improved by considering the dynamic process of a compressor rotor and the influence of rotating stall high-order harmonics, and a new compressor variable-speed over-stall transient model is deduced;
(1.2) method for analyzing instability mechanism of gas compressor and actively controlling instability mechanism of gas compressor
The method comprises the steps of analyzing the occurrence of rotating stall and surge by adopting a bifurcation theory, deeply knowing the mechanism of the occurrence of rotating stall and surge from the viewpoint of system dynamics, providing theoretical guidance for the active stability control of the compressor, and designing an active control method for the pneumatic instability of the compressor according to a conclusion obtained by bifurcation analysis on a stability model of the compressor so as to design a corresponding control algorithm;
(1.3) gas compressor stability output feedback active control based on state estimator
The pressure ratio is controlled by adopting a state estimator, the state estimator estimates the flow coefficient of a pressure system according to an input pressure value, and then an active controller is designed, wherein the active controller consists of the state estimator and a state feedback controller, the state estimator and the state feedback controller form an output feedback controller, and the state feedback controller calculates according to the pressure coefficient and the flow coefficient to obtain a control instruction value;
(2) stability margin estimation and active stability control method for aircraft engine
(2.1) real-time model of aircraft engine surge
The method comprises the steps that an aero-engine surge real-time model is a precondition for developing an aero-engine active stability control simulation test based on a stability margin closed loop, and is established by considering the volumetric dynamics effect of an engine cavity, the stall area characteristic of a gas compressor, the flameout characteristic of a combustion chamber and the inlet distortion of an engine on the basis of an existing aero-engine component level model;
(2.2) Surge margin estimation Algorithm and simulation
Firstly, calculating the correlation for measuring the repeatability of the pressure pulsation signal according to the pressure pulsation signal near the blade obtained by a pressure sensor, and obtaining the times of the correlation value crossing a threshold value according to the off-line analysis of experimental data; secondly, establishing an engine stability margin estimation model according to the inherent characteristic relation between the threshold crossing times and the surge margin value, and accurately estimating the real stability margin of the engine through an interpolation method according to the engine surge margin estimation model;
(2.3) active stability control method for aircraft engine
After the surge margin of the engine is obtained through a surge margin estimation algorithm, namely an active stability control law based on surge margin estimation is designed to form a surge margin closed-loop control loop, wherein the control method mainly comprises a surge margin estimation module and an active stability controller module; wherein, the active stability control law is intended to adopt a robust H based on quadratic performance index2/H∞Method design, improvement of control systemRobustness;
(3) method for predicting instability of aircraft engine and controlling active anti-surge
(3.1) simulation model of instability foreboding signal
The method comprises the steps of introducing engine instability prediction into full-digital simulation, hardware-in-the-loop simulation and semi-physical simulation experiments of an engine control system, researching an active anti-surge control method based on the instability prediction under the condition of not carrying out real engine experiments, constructing instability foreboding signals, establishing a simulation model of the instability foreboding signals, carrying out simulation construction on the engine instability foreboding signals by adopting a model based on MG3 and a chaotic time sequence according to the characteristics of modal wave type instability foreboding disturbance, and considering the interaction between the instability foreboding signals and pressure pulsation signals generated by the circumferential rotation of a compressor rotor blade;
(3.2) Engine instability prediction Algorithm
Detecting generation of a destabilization precursor before engine destabilization, designing an engine destabilization prediction algorithm by adopting a time-frequency analysis based method for modal wave type destabilization precursors according to research results of engine destabilization precursor phenomena, respectively designing algorithms for signals at different sensor positions, adopting lower sampling frequency for sensors far away from a rotor blade of a compressor, directly carrying out frequency analysis to extract the strength of the engine destabilization precursor signals, modulating low-frequency precursor disturbance signals in frequency deviation and amplitude of high-frequency signals for the sensors above the rotor blade of the compressor, detecting low-frequency components from the amplitude of the high-frequency signals by adopting envelope detection, and carrying out spectrum analysis to obtain the strength of the destabilization precursor signals;
(3.3) active anti-surge control method
When the engine active stability controller fails, accurate and timely prediction can be carried out based on the instability prediction algorithm, active anti-surge control is implemented based on the prediction result, stable work of the engine can be fundamentally ensured, and the method specifically comprises the following operations:
(3.31) collecting an engine pressure signal, the pressure signal being sensitive to rotating stall and surge;
(3.32) identifying an engine instability foreboding signal by using an instability foreboding prediction algorithm, and sending an identification result to an active anti-surge controller, wherein the active anti-surge controller adopts a traditional proportional-integral controller;
(3.33) the active anti-surge controller calculates a corresponding execution mechanism control instruction according to the recognition result and the control rule, and the execution mechanism moves to enable the working point of the engine to be far away from a surge boundary according to the control instruction;
(4) composite control method for active stability of aircraft engine
A multi-loop active stability composite control method is designed from three different levels of stability expansion, residual stability margin utilization and active anti-surge based on a compressor part, and is used for inhibiting the pneumatic instability of an engine.
2. The active compound control method for aerodynamic stability of an aircraft engine based on stability estimation and prediction according to claim 1, characterized in that: in the practical application of the above (2.2), the surge margin estimation model needs to receive the pressure, flow and vibration signals collected by the sensor as input, while in the simulation, the engine model cannot simulate the signals with a certain stability margin, so as to develop the simulation experiment of the surge margin closed loop, and simulate the relationship between the correlation degree "threshold crossing event" and the engine surge margin; adopting a random sequence with the same distribution of the occurrence frequency of the threshold crossing events and the threshold value relation, and carrying out mapping simulation on the exponential relation of the correlation degree threshold crossing events and the surge margin by using a sliding threshold value; inputting the surge margin obtained by the calculation of the engine surge model into a threshold value calculation module to obtain the threshold value size of the real surge margin, generating a random number sequence by a random number generator according to a preset frequency, obtaining a threshold value crossing event sequence according to the threshold value, counting the threshold value crossing events to obtain the frequency of the crossing events, and obtaining the real surge margin through a simulation relation.
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| CN112594062B (en) * | 2020-11-13 | 2022-05-17 | 南京航空航天大学 | Simulation method for surge detection and surge elimination control verification |
| CN112696374B (en) * | 2020-11-16 | 2022-03-22 | 南京航空航天大学 | Air pressure simulation system of aircraft engine surge signal and control method thereof |
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| CN112560340B (en) * | 2020-12-09 | 2022-02-01 | 南京航空航天大学 | Method for estimating surge margin of aircraft engine and control method |
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| CN113279997B (en) * | 2021-06-04 | 2022-04-12 | 大连理工大学 | Aero-engine surge active control system based on fuzzy switching of controller |
| WO2022252206A1 (en) * | 2021-06-04 | 2022-12-08 | 大连理工大学 | Aero-engine surge active control system based on fuzzy switching of controllers |
| CN117252109B (en) * | 2023-11-14 | 2024-01-26 | 太仓点石航空动力有限公司 | Aeroengine stability analysis method and system based on data processing |
| CN117648827B (en) * | 2024-01-29 | 2024-04-16 | 中国航发四川燃气涡轮研究院 | Method for evaluating precision of performance simulation program of air compressor based on test database |
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