CN110905603B - Vibration reduction system and method for reducing overall vibration of aircraft engine - Google Patents
Vibration reduction system and method for reducing overall vibration of aircraft engine Download PDFInfo
- Publication number
- CN110905603B CN110905603B CN201911149277.XA CN201911149277A CN110905603B CN 110905603 B CN110905603 B CN 110905603B CN 201911149277 A CN201911149277 A CN 201911149277A CN 110905603 B CN110905603 B CN 110905603B
- Authority
- CN
- China
- Prior art keywords
- vibration
- engine
- controller
- rotating speed
- electronic controller
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/10—Anti- vibration means
-
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
-
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention relates to the technical field of mechanical vibration control, in particular to a vibration reduction system and a vibration reduction method for reducing the whole machine vibration of an aircraft engine; the system comprises a rotating speed sensor, a rotating speed signal acquisition unit, a vibration sensor, a vibration signal acquisition unit, a vibration controller, an excitation processing unit and a vibration excitation device; the engine electronic controller sends the vibration numerical value and the azimuth angle of the current time and the next time obtained by analysis to the vibration controller; the vibration controller carries out vibration analysis and logic judgment according to the signals collected by the vibration signal collecting unit and the signals sent by the electronic controller to obtain control signals required by the vibration exciting device, and the control signals are processed by the exciting processing unit to control the vibration exciting device. The invention effectively reduces the whole machine vibration of the engine through intelligent adjustment.
Description
Technical Field
The invention relates to the technical field of mechanical vibration control, in particular to a vibration reduction system and a vibration reduction method for reducing the whole machine vibration of an aircraft engine.
Background
The aircraft engine belongs to a large-scale rotating machine with high temperature and high rotating speed, and a rotor of the engine can generate large unbalanced force during rotation due to the processing error of parts and the inherent frequency influence of the rotor, and the unbalanced force causes the vibration of the whole aircraft engine. The great vibration can influence the service life of the engine and the flight safety of the airplane, and the whole machine vibration value of the engine is an important parameter for monitoring whether the engine is in a normal state or not.
The traditional method for reducing the vibration level of the engine can improve the processing precision of engine parts and reduce the residual unbalance of the dynamic balance of the rotor, but the unbalance can not be completely eliminated all the time, and the rotor of the engine can generate unbalanced force all the time and generate the vibration of the whole machine. Mounting a vibration reduction device on the rotor of the engine is another solution to reduce the magnitude of engine vibrations.
Disclosure of Invention
The purpose of the invention is as follows: in order to solve the technical problems in the background art, the invention aims to provide a vibration reduction system and a vibration reduction method for reducing the overall vibration of an aircraft engine.
The technical scheme is as follows: a vibration reduction system for reducing the whole machine vibration of an aircraft engine comprises a rotating speed sensor, a rotating speed signal acquisition unit, a vibration sensor, a vibration signal acquisition unit, a vibration controller, an excitation processing unit and a vibration excitation device;
The engine electronic controller collects the rotating speed signal sent by the rotating speed signal acquisition unit, stores the rotating speed signal and compares the rotating speed signal with a rotating speed-vibration relation value stored by the electronic controller to obtain a vibration value and an azimuth angle of the engine at the current rotating speed, and predicts the rotating speed and the vibration value at the next time according to the operating state of the throttle platform; the vibration controller performs vibration analysis according to the signals acquired by the vibration signal acquisition unit, analyzes the vibration value and the azimuth angle, and sends a vibration instruction in the opposite direction to the excitation signal processing unit; the vibration excitation processing unit receives the instruction of the vibration controller and sends the instruction to the vibration excitation device to perform vibration adjustment.
The charge signal is converted into an electric signal through a charge amplifier or a data acquisition internal module.
The engine electronic controller at least has a rotating speed-vibration relational data base, and is used for data statistics of normal test run states of engines of the same type.
The vibration sensor can be a speed sensor or an acceleration sensor, and preferably, a piezoelectric acceleration sensor is adopted.
The vibration signal acquisition unit records a voltage signal and completes engineering unit conversion.
The vibration controller is an independent control element for processing vibration signals, and has the functions of collecting, storing and processing the vibration signals, sending vibration excitation instructions and carrying out two-way communication with an electronic controller of the engine.
The vibration controller is used as an independent control unit, can perform vibration analysis according to the signals collected by the vibration signal collecting unit, analyzes the vibration value and the azimuth angle, and sends a vibration instruction in the opposite direction to the excitation signal processing unit. The vibration controller can also carry out two-way communication with the electronic controller, and the vibration controller sends the vibration signal of gathering and the excitation signal that sends to the electronic controller, supplies engine data record and complete machine control regulation. The vibration controller receives the vibration value and the azimuth angle of the engine at the current time and the next time in a database from the electronic controller, and performs logic comparison with the vibration signal acquired by the vibration controller, trusts and sends a reverse vibration instruction of the next time in the database of the electronic controller to the excitation signal processing unit when the consistency of the vibration data reaches a set threshold value; and when the consistency of the vibration data does not reach the set threshold value, neglecting the vibration data of the electronic controller, and launching a reverse direction vibration instruction collected by the vibration sensor to the excitation signal processing unit.
Compared with the prior art, the invention has the following beneficial technical effects: the vibration of the whole engine can be reduced under the conditions of processing, assembly and self resonance of parts which cannot be avoided, and intelligent adjustment is carried out according to a rotating speed-vibration relational data base in an electronic controller.
Drawings
FIG. 1 is a schematic diagram of the system of the present invention;
figure 2 is a schematic view of the vibration exciting apparatus,
in the figure, 1-rotor, 2-force receiving component and 3-force applying component.
Detailed Description
In order to make the technical solution of the present invention more apparent, the present invention is further described in detail. The control system of the invention comprises a rotating speed sensor, a rotating speed signal acquisition unit, a vibration sensor, a vibration signal acquisition unit, a vibration controller, an excitation processing unit, a vibration excitation device and a rotor electronic controller.
The engine rotor has residual unbalance, so that unbalanced force is generated during rotation, and the unbalanced force brings vibration of the whole engine. The unbalance and the azimuth angle of the engine rotor in a stable rotating state are kept unchanged, the engine adopting the flexible rotor has critical rotating speed in a working rotating speed range, the vibration of the engine can generate a sudden increase phenomenon near the critical rotating speed, and the vibration direction of the engine also has a rule. The whole machine vibration level of the engine can be reduced by applying the reverse force which generates the vibration force on the rotor of the engine.
The rotating speed sensor, the rotating speed signal acquisition unit, the vibration sensor and the vibration signal acquisition unit are signal acquisition functional devices. The vibration signal processing unit is a functional device for converting electric signals in engineering units.
The vibration controller is used as an independent control unit, can independently control vibration, and can also be cooperatively controlled with the electronic controller.
When the vibration controller independently controls the vibration, vibration analysis is carried out according to signals collected by the vibration signal collecting unit, the vibration numerical value and the vibration azimuth angle are analyzed, and a vibration instruction in the opposite direction is sent to the excitation signal processing unit.
The vibration controller can also be in two-way communication with the electronic controller, and intelligent vibration control is carried out based on the rotating speed-vibration database. The vibration controller sends the collected vibration signal and the sent excitation signal to the electronic controller for data recording of the engine and control and adjustment of the whole engine. The vibration controller receives the vibration value and the azimuth angle of the engine at the current time and the next time in a database from the electronic controller, and performs logic comparison with the vibration signal acquired by the vibration controller, trusts and sends a reverse vibration instruction of the next time in the database of the electronic controller to the excitation signal processing unit when the consistency of the vibration data reaches a set threshold value; and when the consistency of the vibration data does not reach the set threshold value, neglecting the vibration data of the electronic controller, and launching a reverse direction vibration instruction collected by the vibration sensor to the excitation signal processing unit. Whether the vibration controller adopts bidirectional communication with the electronic controller for intelligent control depends on an operator instruction and comparison and judgment of multiple consistency comparison results of the current engine and data in the rotating speed-vibration relational data base, and if the multiple consistency comparison does not reach a set threshold value, independent control is used as a main scheme.
The vibration exciting device is composed of a force bearing component 2 and a force application component 3, the force application component provides force in four directions at intervals of 90 degrees, vector superposition of the force can be carried out according to the force in any two adjacent directions, force in any direction and magnitude in a plane is further generated, and the force application component in the four directions arranged in the directions at intervals of 90 degrees can improve the working reliability of the force application component and provide force with larger numerical value. The force bearing component 2 is arranged on the engine rotor 1, and the force application component is arranged on the engine static component. The force application member of the vibration exciting device is powered by the motor and generates force by means of electric energy.
Claims (9)
1. The utility model provides a reduce system that shakes of aircraft engine complete machine vibration which characterized in that: the system comprises a rotating speed sensor, a rotating speed signal acquisition unit, a vibration sensor, a vibration signal acquisition unit, a vibration controller, an excitation processing unit and a vibration excitation device;
the engine electronic controller collects the rotating speed signal sent by the rotating speed signal acquisition unit, stores the rotating speed signal and compares the rotating speed signal with a rotating speed-vibration relation value stored by the electronic controller to obtain a vibration value and an azimuth angle of the engine at the current rotating speed, and predicts the rotating speed and the vibration value at the next time according to the operating state of the throttle platform; the electronic controller of the engine sends the vibration numerical value and the azimuth angle of the current time and the next time obtained by analysis to the vibration controller; the vibration controller carries out vibration analysis and logic judgment according to the signals collected by the vibration signal collecting unit and the signals sent by the electronic controller to obtain control signals required by the vibration exciting device and sends the control signals to the exciting signal processing unit, and the exciting signal processing unit converts the control signals into control instructions to control the vibration exciting device;
The vibration analysis and logic judgment specifically means that the vibration controller receives a vibration value and an azimuth angle of the engine at the current time and the next time in a database of an electronic controller of the engine, and performs logic comparison with a vibration signal acquired by the vibration controller, and trusts and sends a reverse vibration instruction of the next time in the database of the electronic controller to the excitation signal processing unit when the consistency of the vibration data reaches a set threshold value; and when the consistency of the vibration data does not reach the set threshold value, neglecting the vibration data of the electronic controller, and launching a reverse direction vibration instruction collected by the vibration sensor to the excitation signal processing unit.
2. The vibration reduction system for reducing the overall vibration of the aircraft engine according to claim 1, wherein: the vibration controller is in two-way communication with the electronic controller of the engine, can perform vibration analysis according to signals collected by the vibration signal collecting unit, analyzes the vibration value and the azimuth angle, and sends a vibration instruction in the opposite direction to the excitation signal processing unit, and the vibration controller sends the collected vibration signals and the sent excitation signals to the electronic controller for data recording and overall control and adjustment of the engine.
3. The vibration reduction system for reducing the overall vibration of the aircraft engine according to claim 2, wherein: the communication mode between the vibration controller and the engine electronic controller depends on the comparison and judgment of the operator instruction and the multiple consistency comparison results of the data in the current engine and rotating speed-vibration relational data base.
4. A vibration reducing system for reducing the overall vibration of an aircraft engine according to any one of claims 1 to 3, wherein: the vibration controller is an independent control element for processing vibration signals, and has the functions of collecting, storing and processing the vibration signals, sending vibration excitation instructions, and independently performing vibration reduction control when the communication between the vibration controller and the engine electronic controller is interrupted.
5. A vibration reducing system for reducing the overall vibration of an aircraft engine according to claim 1 or 3, wherein: the engine electronic controller at least has a rotating speed-vibration relational data base, and is used for data statistics of normal test run states of engines of the same type.
6. The vibration reduction system for reducing the overall vibration of the aircraft engine according to claim 1, wherein: the rotating speed signal acquisition unit, the vibration controller and the excitation processing unit are integrated in the electronic controller of the engine.
7. The vibration reduction system for reducing the overall vibration of the aircraft engine according to claim 1, wherein: the vibration exciting device is composed of a force bearing component and a force application component, wherein the force application component provides force in four directions at intervals of 90 degrees, vector superposition of the force is carried out according to the force in any two adjacent directions, force in any direction and magnitude in a plane is further generated, the force bearing component is installed on an engine rotor, and the force application component is installed on an engine static component.
8. The vibration reduction system for reducing the overall vibration of the aircraft engine according to claim 7, wherein: the force application part in the vibration exciting device applies force to the force bearing part in a non-contact mode.
9. The vibration reduction system for reducing the overall vibration of the aircraft engine according to claim 1, wherein: the vibration sensor adopts a piezoelectric acceleration sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911149277.XA CN110905603B (en) | 2019-11-21 | 2019-11-21 | Vibration reduction system and method for reducing overall vibration of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911149277.XA CN110905603B (en) | 2019-11-21 | 2019-11-21 | Vibration reduction system and method for reducing overall vibration of aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110905603A CN110905603A (en) | 2020-03-24 |
| CN110905603B true CN110905603B (en) | 2022-07-29 |
Family
ID=69818504
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911149277.XA Active CN110905603B (en) | 2019-11-21 | 2019-11-21 | Vibration reduction system and method for reducing overall vibration of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110905603B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102008022895A1 (en) * | 2008-05-08 | 2009-11-19 | Eurocopter Deutschland Gmbh | Control arrangement for controlling actuators arranged in rotor blade of aircraft i.e. helicopter, has control device connected with groups of actuators by interface connecting units, respectively |
| CN105173111A (en) * | 2015-05-22 | 2015-12-23 | 北京安达维尔测控技术有限公司 | Portable vibration monitoring and maintenance system for helicopter |
| US10393216B2 (en) * | 2013-12-13 | 2019-08-27 | Lord Corporation | Redundant active vibration and noise control systems and methods |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8090482B2 (en) * | 2007-10-25 | 2012-01-03 | Lord Corporation | Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations |
-
2019
- 2019-11-21 CN CN201911149277.XA patent/CN110905603B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102008022895A1 (en) * | 2008-05-08 | 2009-11-19 | Eurocopter Deutschland Gmbh | Control arrangement for controlling actuators arranged in rotor blade of aircraft i.e. helicopter, has control device connected with groups of actuators by interface connecting units, respectively |
| US10393216B2 (en) * | 2013-12-13 | 2019-08-27 | Lord Corporation | Redundant active vibration and noise control systems and methods |
| CN105173111A (en) * | 2015-05-22 | 2015-12-23 | 北京安达维尔测控技术有限公司 | Portable vibration monitoring and maintenance system for helicopter |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110905603A (en) | 2020-03-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10006441B2 (en) | Management system for operating a wind energy plant and method using the management system | |
| CN102169328B (en) | Active control test platform and method for vibration of near space aircraft model | |
| US20070115023A1 (en) | Variable-structure diagnostics approach achieving optimized low-frequency data sampling for ema motoring subsystem | |
| US20210277869A1 (en) | Method and system for controlling a wind turbine to reduce nacelle vibration | |
| CN103482061B (en) | The harmonic synchronous identification revised law of Structural Response for Helicopters adaptive control | |
| Pan et al. | A review on self-recovery regulation (SR) technique for unbalance vibration of high-end equipment | |
| CN110471434B (en) | Intelligent reaction flywheel for spacecraft attitude control and control method thereof | |
| CN102288912A (en) | Tension-torsion mechanical separation mechanism and electric power system testing platform capable of being used for unmanned plane and model airplane design | |
| US20210207584A1 (en) | Method and system for controlling a wind turbine to reduce nacelle vibration | |
| CN104895747A (en) | Multi-channel motor set vibration data collecting system based on STM | |
| CN113834563A (en) | Mechanical vibration state signal acquisition and analysis system | |
| CN102900609B (en) | Giant magnetostrictive flap wind turbine blade vibration reduction system and control method | |
| Norman et al. | Full-scale wind tunnel test of a UH-60 individual blade control system for performance improvement and vibration, loads, and noise control | |
| CN109323853B (en) | Fan blade fan vibration detection device and fault detection prediction method | |
| CN110905603B (en) | Vibration reduction system and method for reducing overall vibration of aircraft engine | |
| CN102520631A (en) | On-line automatic balancing controller of rotating machinery | |
| CN105865731B (en) | A kind of real-time detecting system and its control method of electric car resonance speed | |
| Mao et al. | Vibration control for active magnetic bearing rotor system of high-speed flywheel energy storage system in a wide range of speed | |
| CN109406114A (en) | A kind of aeroengine rotor blade working condition checkout gear and detection method | |
| CN112067330A (en) | Equipment fault diagnosis method and device based on storage and calculation integrated technology | |
| CN115508032B (en) | Double-degree-of-freedom fatigue loading excitation device, system and control method for fan blade | |
| CN111237136A (en) | Method and system for extracting state information of wind driven generator sensor | |
| CN204881845U (en) | Multichannel wind turbine generator system vibrates data acquisition system based on STM | |
| CN109213220A (en) | A kind of Three Degree Of Freedom micro-vibration Experiment system for active control based on piezoelectric pile | |
| CN213414261U (en) | Lithium battery hybrid power test system experimental research system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |