CN109339954A - A kind of Active Control Method based on aero-engine compressor component aerodynamic unstability - Google Patents
A kind of Active Control Method based on aero-engine compressor component aerodynamic unstability Download PDFInfo
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- CN109339954A CN109339954A CN201811169753.XA CN201811169753A CN109339954A CN 109339954 A CN109339954 A CN 109339954A CN 201811169753 A CN201811169753 A CN 201811169753A CN 109339954 A CN109339954 A CN 109339954A
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- compressor
- active
- stability
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- active control
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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
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
- F05D2270/101—Compressor surge or stall
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses the Active Control Method based on aero-engine compressor component aerodynamic unstability, the control method includes: (1) pneumatic stability of gas compressor dynamic model；(2) compressor instability Analysis on Mechanism and active control strategies；(3) the Compressor Stability output feedback active control based on state estimator.The present invention passes through the influence for considering compressor rotor dynamic process and rotating stall high-order harmonic wave, to improve compressor model precision；The mechanism of compressor aerodynamic unstability is disclosed by bifurcation theory；Using the conclusion of bifurcation theory, rotating stall and surge active controller are designed, inhibits the generation of unstable phenomenon, expands compressor stable operation range, meets actual operation requirements.
Description
Technical field
The present invention relates to the Active Control Methods based on aero-engine compressor component aerodynamic unstability, belong to aviation hair
Motivation stability control technical field.
Background technique
Current aero-engine is faced with high pressure ratio, high efficiency, high stability and high anti-distortion ability integration optimizing
Challenge, the contradiction between engine performance and stability are more and more prominent.For China in the high-performance enginer of development or even
For the engine of the following higher thrust ratio, stability problem will become more prominent, be that aero-engine of new generation is developed into
The critical issue and technology " bottleneck " lost.The difficult point of aero-engine aerodynamic stability control is the uncertain of stability boundaris
Property.Such as: inlet distortion, engine components performance degradation, manufacture and rigging error etc. factor can all lead to engine stabilizer
The movement on boundary, aerodynamic stability control method include passive control methods and Active Control Method.Current aero-engine
Aerodynamic stability is controlled using passive control methods, and control strategy is built upon on the basis of control instability line, in conjunction with
Augmentation control system and unstability restore control system to solve the problems, such as the unstable operation of engine in short-term.
It has been sent out by the passive control strategy of core of control instability line, in short-term augmentation control system and unstability recovery system
It opens up more mature, is widely used in the power device of third generation fighter plane, well ensure engine and fly
The safety of machine.However, stability margin, the in short-term open loop of augmentation control system and unstability recovery control that control instability line is conservative
The subsequent property of system is mainly reflected in the following aspects so that traditional control instability strategy has many fatal defects:
(1) presence of control instability line is unable to get the performance of engine to fully play, must not under identical performance requirement
The higher engine of non preference energy, this weight that will lead to engine are significantly increased, and thrust ratio substantially reduces；(2) unstability control
Line processed reduces the working range of engine, so that remaining surge margin is unable to get effective use, to reduce engine
Operability and aircraft mobility；(3) augmentation control system is opened loop control in short-term, it is meant that regardless of whether engine is true
Face unstability danger, pilot all can force start, this conservative control measure undoubtedly will also decrease the property of engine
Energy；(4) when unstability restores control system starting, engine has been in aerodynamic unstability state, if into " irrecoverability loses
Speed ", unstability restores control system and will be unable to play a role, and flame-out in flight restarting of having to, even if can successfully exit
Instability status, of short duration unstability also by the aging of acceleration motor, shorten the service life of engine.
Summary of the invention
The present invention is exactly in view of the deficienciess of the prior art, provide a kind of pneumatic based on aero-engine compressor component
The Active Control Method of unstability, by considering the influence of compressor rotor dynamic process and rotating stall high-order harmonic wave, to improve
Compressor model precision；The mechanism of compressor aerodynamic unstability is disclosed by bifurcation theory；Utilize the conclusion of bifurcation theory, design rotation
Turn stall and surge active controller, inhibit the generation of unstable phenomenon, expand compressor stable operation range, meets actual use
It is required that.
To solve the above problems, the technical solution used in the present invention is as follows:
A kind of Active Control Method based on aero-engine compressor component aerodynamic unstability, the control method include:
(1) pneumatic stability of gas compressor dynamic model
On the basis of MG3 model, the influence of compressor rotor dynamic process and rotating stall high-order harmonic wave is considered to mention
The precision of high model derives a new compressor variable speed fault speed transient model；
(2) compressor instability Analysis on Mechanism and active control strategies
Using the generation of bifurcation theory analysis rotating stall and surge, from the angle of system dynamics in depth derotation
The mechanism that stall and surge occur provides theoretical direction for the control of compressor active stability, according to Compressor Stability mould
The conclusion that the Bifurcation of type obtains can be designed compressor aerodynamic unstability active control strategies, and then design corresponding control
Algorithm；
(3) the Compressor Stability output feedback active control based on state estimator
Adoption status estimator controls pressure ratio, and state estimator estimates the stream of pressure system according to the pressure value of input
Coefficient of discharge, then active controller design is carried out, active controller is made of state estimator and state feedback controller, the two group
At an output feedback controller, control instruction value is calculated according to pressure coefficient and discharge coefficient in state feedback controller.
Compared with prior art, implementation result of the invention is as follows by the present invention:
(1) engine pressure ratio and stability margin can be increased, in compressor pressure ratio, the higher regional work of efficiency；Identical
Under pressure ratio, compressor series can be reduced, increases the thrust ratio of engine.
(2) engine can be made, in the lesser high-performance point work of surge margin, to improve adding for engine in accelerator
Fast performance enhances the mobility of aircraft.
(3) engine enter it is unstable before just implement effectively control, caused by reducing because of surge or stall to engine
Destruction, extend engine life, reduce maintenance cost.
Detailed description of the invention
Fig. 1 is the rotating stall and surge output feedback active control conceptual scheme of the present invention based on state estimator.
Specific embodiment
Illustrate the contents of the present invention below in conjunction with specific embodiments.
Rotating stall and surge output feedback active control to be of the present invention based on state estimator as shown in Figure 1:
Conceptual scheme.
Current aero-engine aerodynamic stability is controlled using passive control methods, and control strategy is built upon
On the basis of control instability line, control system is restored to solve the unstable of engine with unstability in conjunction with augmentation control system in short-term
Work problem.However, stability margin, the in short-term open loop of augmentation control system and unstability recovery control that control instability line is conservative
The subsequent property of system, so that traditional control instability strategy has many fatal defects.
The present invention will consider that compressor rotor dynamic process and rotating stall are humorous on the basis of conventional MG3 compressor model
Wave action establishes the pneumatic stability of gas compressor model for meeting active controller design accuracy, by bifurcation theory to stability
Model is analyzed, and the mechanism of compressor aerodynamic unstability is disclosed；Estimate to be not easy to measure in engineering by design point estimator
Quantity of state expands compressor part using nonlinear object Design of Feedback Controller pneumatic stability of gas compressor active controller
Aerodynamic stability.
Based on the Active Control Method of aero-engine compressor component aerodynamic unstability, the control method includes: (1) pressure
Mechanism of qi aerodynamic stability dynamic model
Rotating stall and surge phenomenon in compressibility are the key that carry out active control and theoretical basis, Moor with
Greitzer combines respective research achievement, is deduced famous MG model；MG model indicates by three partial differential equation,
Use Galerkin process and select a cubic curve as compressor performance characteristic curve, has obtained being indicated by ordinary differential system
Classical MG3 model.The present invention will consider compressor rotor dynamic process and rotating stall on the basis of classical MG3 model
The influence of high-order harmonic wave improves the precision of model, derives a new compressor variable speed fault speed transient model, MG
Model compression system block diagram is as shown in Figure 1.
(2) compressor instability Analysis on Mechanism and active control strategies
Study the mechanism of compressibility rotating stall and surge generation, prevention and active control to rotating stall and surge
It is of great significance；Testing, equipment difference higher by cost and risk due to compressibility causes test result to differ greatly
Factor restricts, and theory analysis has obtained sizable attention, and discloses the essence of numerous compressibility unstable phenomenons；Compression system
The buckling form of system provides the foundation for theory analysis；The buckling form of compressibility is Nonlinear state space model, is passed through
Forked tunnel can successfully capture the non-linear nature of compressibility.Proposed adoption bifurcation theory of the present invention analysis rotating stall and
The generation of surge in depth understands the mechanism of rotating stall and surge generation from the angle of system dynamics, is compressor active
Stability control provides theoretical direction, according to the conclusion that the Bifurcation to Compressor Stability model obtains, can be designed pressure
Mechanism of qi aerodynamic unstability active control strategies, and then design corresponding control algolithm.
(3) the Compressor Stability output feedback active control based on state estimator
The Algorithm of Active Control for being currently directed to compressor is needed mostly using flow or stall amplitude as inputting parameter,
However there was only pressure ratio in compressor is to be easier the amount of measurement, so using pressure ratio as the output feedback ontrol ability that can survey parameter
With prior practical significance.Therefore, proposed adoption state estimator of the present invention solves this problem, state estimator according to
The pressure value of input estimates the discharge coefficient of pressure system, then carries out active controller design.The control strategy of proposed adoption is such as
Shown in Fig. 1: controller is made of state estimator and state feedback controller, and the two forms an output feedback controller, shape
Control instruction value is calculated according to pressure coefficient and discharge coefficient in state feedback controller.
This programme is to expand this steady angle by compressor part to improve for aero-engine aerodynamic stability problem
Cngine aerodynamic stability designs a kind of Active Control Method expansion compressor steady operation model for compressor instability principle
It encloses.Specifically, by considering the influence of compressor rotor dynamic process and rotating stall high-order harmonic wave, to improve compressor model
Precision；The mechanism of compressor aerodynamic unstability is disclosed by bifurcation theory；Using the conclusion of bifurcation theory, rotating stall and asthma are designed
Shake active controller, inhibits the generation of unstable phenomenon, expands compressor stable operation range.
The foregoing is a detailed description of the present invention in conjunction with specific embodiments, and it cannot be said that the present invention is specifically real
It applies and is only limitted to these explanations.For those skilled in the art to which the present invention belongs, before not departing from present inventive concept
It puts, a number of simple deductions or replacements can also be made, all shall be regarded as belonging to the scope of protection of the invention.
Claims (1)
1. a kind of Active Control Method based on aero-engine compressor component aerodynamic unstability, it is characterised in that: the control
Method includes:
(1) pneumatic stability of gas compressor dynamic model
On the basis of MG3 model, the influence of compressor rotor dynamic process and rotating stall high-order harmonic wave is considered to improve mould
The precision of type derives a new compressor variable speed fault speed transient model；
(2) compressor instability Analysis on Mechanism and active control strategies
Using the generation of bifurcation theory analysis rotating stall and surge, rotating stall is in depth understood from the angle of system dynamics
The mechanism occurred with surge provides theoretical direction for the control of compressor active stability, according to Compressor Stability model
The conclusion that Bifurcation obtains can be designed compressor aerodynamic unstability active control strategies, and then design corresponding control algolithm；
(3) the Compressor Stability output feedback active control based on state estimator
Adoption status estimator controls pressure ratio, and state estimator estimates the flow system of pressure system according to the pressure value of input
Number, then active controller design is carried out, active controller is made of state estimator and state feedback controller, the two composition one
Control instruction value is calculated according to pressure coefficient and discharge coefficient in a output feedback controller, state feedback controller.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811169753.XA CN109339954A (en) | 2018-10-08 | 2018-10-08 | A kind of Active Control Method based on aero-engine compressor component aerodynamic unstability |
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| CN201811169753.XA CN109339954A (en) | 2018-10-08 | 2018-10-08 | A kind of Active Control Method based on aero-engine compressor component aerodynamic unstability |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112594062A (en) * | 2020-11-13 | 2021-04-02 | 南京航空航天大学 | Simulation method for surge detection and surge elimination control verification |
| CN113279997A (en) * | 2021-06-04 | 2021-08-20 | 大连理工大学 | Aero-engine surge active control system based on fuzzy switching of controller |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103198193A (en) * | 2013-04-12 | 2013-07-10 | 北京大学 | Method and system for air compressor rotating stall predication based on first-order modal amplitude slope |
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2018
- 2018-10-08 CN CN201811169753.XA patent/CN109339954A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103198193A (en) * | 2013-04-12 | 2013-07-10 | 北京大学 | Method and system for air compressor rotating stall predication based on first-order modal amplitude slope |
Non-Patent Citations (1)
| Title |
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| 黄伟: "航空发动机高稳定性控制及其在加速控制中的应用", 《中国博士学位论文全文数据库工程科技Ⅱ辑》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112594062A (en) * | 2020-11-13 | 2021-04-02 | 南京航空航天大学 | Simulation method for surge detection and surge elimination control verification |
| CN113279997A (en) * | 2021-06-04 | 2021-08-20 | 大连理工大学 | Aero-engine surge active control system based on fuzzy switching of controller |
| 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 |
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Application publication date: 20190215 |