CN105571867B - A kind of aero-engine vibration control experiment platform - Google Patents
A kind of aero-engine vibration control experiment platform Download PDFInfo
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- CN105571867B CN105571867B CN201610040169.9A CN201610040169A CN105571867B CN 105571867 B CN105571867 B CN 105571867B CN 201610040169 A CN201610040169 A CN 201610040169A CN 105571867 B CN105571867 B CN 105571867B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/025—Measuring arrangements
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- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
A kind of aero-engine vibration control experiment platform, including experiment sewing platform base, aero-engine ontology, drive system, TT＆C system and safety device；First driving motor of the drive system imparts power to the low pressure rotor system of aero-engine ontology through first shaft coupling, accessory drive system of second driving motor through second shaft coupling and aero-engine ontology imparts power to the high pressure rotor system of aero-engine ontology, the motor output shaft, low pressure rotor system and high pressure rotor system are equipped with capacitive displacement transducer, 2 grades of casings corresponding to 5 spring bearings of aero-engine, 3 grades of casings, 6 grades of casings, combustion box and high-pressure turbine casing are equipped with three-way vibration acceleration transducer, the various factors coupling that the experiment porch can be used for test analysis aero-engine shake machine problem；It is widely used in aero-engine dual rotors system vibration characteristics and vibration control strategy study.
Description
Technical field
The present invention relates to engine test device, more particularly to a kind of aero-engine experiment porch.
Background technology
Power plant of the aero-engine as aircraft is the key that weigh national power research and development, a manufacture level,
It is the important symbol of big country's strength, relation technological researching has high politics, economy and military value.In recent years to starting
Machine performance requirement is continuously improved, and the load of engine component increases considerably, and causes vibration problem very prominent, vibration control
As one of aero-engine important research project.
The research of aero-engine vibration control technology needs the support of corresponding experiment porch, the existing general face of experiment porch
It is locally built to aero-engine, is suitable for the research one by one of single factors.After it have passed through accumulation for many years, urgent need can be comprehensive
Reflect that the experiment porch of the various inducements of vibration noise is used for the correlative study of Noise and Vibration Control, is especially carried forward vigorously in country
Under the new situation, more units set foot in aviation field to civil-military inosculation, are badly in need of the support of such experiment porch.It is currently used for aeroplane engine
Machine vibration control research experiment porch aero-engine is reduced to various forms of rotor-support-foundation systems, for it is various single or this
Aero-engine dynamic response characteristic is studied under a little minority factors, overweight to promoting the development of High Performance Aeroengine technology to rise
Act on, have accumulated a large amount of outstanding achievements, but have been unable to meet it is further, with aero-engine actual motion it is more identical and
, various factors coupling vibratory response characteristic Research Requirements.A kind of aero-engine vibration control experiment platform of present disclosure
For the renovation and utilization of true aero-engine, it can be used for various factors coupling vibratory response characteristic and studied with control.
Invention content
For the above situation, the purpose of the present invention, which is that, overcomes shortcoming and defect of the existing technology, provides one
Kind aero-engine vibration control experiment platform, the experiment porch can reflect aero-engine high-low pressure under maneuvering flight conditions
The vibration truth of dual rotors system；And overall structure is consistent with the real structure of aero-engine, only to engine
Part-structure be transformed, improvement cost is relatively low, and transformation difficulty is not high, is easy to popularize.
A kind of aero-engine vibration control experiment platform, which includes experiment sewing platform base, and is fixed on reality
Test aero-engine ontology, drive system, TT＆C system and the safety device on sewing platform base；The first of the drive system
Driving motor imparts power to the low pressure rotor system of aero-engine ontology through first shaft coupling, and the of the drive system
Accessory drive system of two driving motors through second shaft coupling and aero-engine ontology imparts power to aero-engine sheet
The motor output shaft and aero-engine of the high pressure rotor system of body, first driving motor and/or the second driving motor
Low pressure rotor system and high pressure rotor system be equipped with capacitive displacement transducer, 5 spring bearings of aero-engine institute is right
2 grades of casings, 3 grades of casings, 6 grades of casings, combustion box and the high-pressure turbine casing answered are passed equipped with three-way vibration acceleration
Sensor.
The aero-engine ontology is the aero-engine for having removed after-burner and jet pipe part.
To realize structure optimization, further step：The supporting way of the aero-engine ontology of the experiment porch is logical
Four on casing hitch point suspensions are crossed to be mounted on experiment sewing platform base.
In order to facilitate the installation relation of the internal structure and each component of observation aero-engine, to the aero-engine
1 grade of casing, 4 grades of casings, combustion box, burning Interior Layout, combustion outer case, heat screen, the after-burner diffusion of ontology
Device outer wall carries out 1/8 cutting and forms observation window.
Then first driving motor of the drive system passes through the first shaft coupling by the radome fairing for compressor front end of dismantling
Device connects low pressure rotor system to drive low pressure rotor；Second driving motor of the drive system is by replacing aero-engine
Startup motor in middle accessory drive system drives high pressure rotor system.
The TT＆C system includes motor controlling cabinet, capacitive displacement transducer, three-way vibration acceleration transducer, data
Acquisition system, PC machine and connecting line.
It the start and stop of the first driving motor and/or the second driving motor in the drive system and turns round by TT＆C system
Motor controlling cabinet frequency control.
The aero-engine ontology and drive system of the experiment porch are set in safety device, the electricity of TT＆C system
Machine switch board is set to outside safety device.
The present invention compared with prior art caused by advantageous effect：
（Ⅰ）The present invention can be transformed obtained, each rotor portions on the prototype or volume production machine ontology of aero-engine
The size and installation site of part are consistent with actual conditions, are effectively prevented experimental result caused by due to form difference and are lost
Effect；
（Ⅱ）Overall structure of the present invention is scientific and reasonable, and transformation difficulty is little, and improvement cost is relatively low, and non-environmental-pollution is easy to
It popularizes；
（Ⅲ）Low pressure rotor system and high pressure rotor system of the present invention are available equipped with capacitive displacement transducer
Turn shaft run-out and axial runout to measure, three-way vibration acceleration sensing is equipped on the casing of each bearing corresponding position
Device is used for the vibration of measuring system, the case where being better understood by engine actual motion, convenient for more fully to engine
In critical component carry out vibration monitoring, provided for the multifactor lower vibration evolutionary process of aero-engine and Study on Vibration Control
Good experiment condition；
（Ⅳ）The present invention locally carries out cutting to engine, and the structure that each parts of engine are observed convenient for us is special
Point, the structural relation between each parts, birotor rotation function, the birotor slip function that displaying experiment porch has, with
And the working condition of each functional component.
The present invention is widely used in Analysis of Vibration Characteristic, vibration control and the status monitoring of aero-engine dual-rotor structure
Research.
The present invention is described in further detail with reference to the accompanying drawings and examples.
Description of the drawings
Fig. 1 is the experimental bench structural front view of the present invention；
Fig. 2 is the experimental bench structure top view of the present invention；
Fig. 3 is the experimental bench structure right view of the present invention；
Fig. 4 is aviation engine structure schematic diagram in the present invention；
Fig. 5 is aero-engine casing local cutting structural schematic diagram in the present invention；
Fig. 6 is the vertical view of support construction of the present invention；
Fig. 7 is the front view of inventive sensor installation；
Fig. 8 is the structure diagram of experimental bench of the present invention；
Fig. 9 is TT＆C system block diagram of the present invention.
In figure：1. aero-engine ontology；3. safety device；5. testing sewing platform base；6. first shaft coupling；7. second
Shaft coupling；8. capacitive displacement transducer；9. three-way vibration acceleration transducer；10. hitch point；11. low pressure rotor system；
12. high pressure rotor system；21. the first driving motor；22. the second driving motor；41. motor controlling cabinet.
Specific implementation mode
As shown in Figure 1, a kind of aero-engine vibration control experiment platform, the experiment porch by aero-engine ontology 1,
Drive system, safety device 3, TT＆C system and 5 five most of composition of experiment sewing platform base.
The drive system includes the first driving motor 21, first shaft coupling 6, the second driving motor 22 and second shaft coupling
7；The first driving motor 21 in the drive system imparts power to aero-engine ontology through the connection of first shaft coupling 6
1 low pressure rotor system 11, the second driving motor 22 of drive system is through in second shaft coupling 7 and aero-engine ontology 1
Accessory drive system imparts power to the high pressure rotor system 12 of aero-engine ontology 1；The drive system and aviation
Engine body 1, which is linked in sequence, to be fixed on experiment sewing platform base 5.As a kind of preferable experiment porch scheme, internal rotor is through
One shaft coupling is connected with the first driving motor, and outer rotor is connected through belt pulley, second shaft coupling with the second driving motor, substantially
Or, still there is larger difference, outer rotor is through belt pulley, second in the simulation to aero-engine key structure with practical structures
Shaft coupling is connected with the second driving motor, and it is poor that power transmits stability.A kind of aero-engine vibration control of present disclosure
The aero-engine ontology of experiment porch is the true aero-engine for having removed after-burner and jet pipe, is based on its reality
Structure is carried out vibration characteristics and is studied with control, and actual demand is complied fully with；Second driving motor of drive system is through the second shaft coupling
The accessory drive system of device and aero-engine ontology imparts power to high pressure rotor system, and more compact structure, stability are more
It is good.It can be transformed on the basis of retired aero-engine or prototype, it is both environmentally friendly, further save cost.
The TT＆C system include motor controlling cabinet 41, capacitive displacement transducer 8, three-way vibration acceleration transducer 9,
Data collecting system, PC machine and connecting line.Control system and display, capacitive displacement sensing are provided in motor controlling cabinet 41
Device 8 and three-way vibration acceleration transducer 9 belong to collecting part, and the signal output end of collecting part after filter filtering by connecting
The signal input part of connected control system, the signal input part of the signal output end connection display of control system, collecting part will
Signal is delivered to control system and is shown corresponding data over the display, or signal is exported after control system processing.
With reference to attached drawing, the aero-engine ontology 1 is true to be removed to after-burner and jet pipe part
Real critical aircraft engine parts.The structure of the aero-engine ontology 1 of the present invention includes mainly that low pressure rotor system 11 and high pressure turn
Subsystem 12, low pressure rotor system 11 are made of three-level low-pressure compressor, low pressure rotor and level-one low-pressure turbine, high pressure rotor system
System 12 is made of three-level high-pressure compressor, high pressure rotor and level-one high-pressure turbine, and low-pressure shaft forms double across hollow high-pressure shaft
Rotor-support-foundation system.Preferably, the low pressure rotor and high pressure rotor of aero-engine are equipped with capacitive displacement transducer 8.It is entire double
Rotor-support-foundation system is by 5 bearing supports, by front support bearing support at 2 grades of low-pressure compressors, is installed at 2 grades of high-pressure compressors
There is intershaft bearing support, there are two roller bearing supports for installation after three-level high-pressure compressor, are propped up after high-pressure turbine front end has
Bearing is supportted, there is stick roller bearing support between high-pressure turbine and low-pressure turbine；With reference to Fig. 4, there are machines at different levels in two-spool outside
Casket support, mainly have 1 grade of casing I, IV, 6 grade of casing V of 2-3 grades of II, 4 grade of casing, III, 5 grade of casing casings, combustion box VI,
High-pressure turbine casing VII, low-pressure turbine casing VIII, after-burner diffuser casing Ⅸ, after-burner casing Ⅹ and jet pipe
Casing Ⅺ.
The design feature of each parts of engine, the equipment relationship between each parts, exhibition are observed for the ease of us
Show that experiment porch has birotor rotation function, the working condition of birotor slip function and each functional component, such as Fig. 5 institutes
Show, to 1 grade of casing, I, 4 grade of casing III of aero-engine ontology 1, combustion box VI, burning Interior Layout, combustion outer case,
Heat screen, after-burner diffuser outer wall carry out 1/8 cutting；After-burner and jet pipe part to aero-engine into
Row is removed, and improved aero-engine is mounted on by four hitch points 10 suspension on 1 casing of aero-engine ontology
It tests on sewing platform base 5.Engine starts by starter, and the power resources of starter need to pass by attachment in starting motor
Dynamic system is transmitted, and is that attachment provides power by accessory drive system, starter, surpasses engine accessory power rating after starter starts
More clutch is closely related with the working condition of accessory drive system.On gas-turbine unit, there are many attachmentes to need
By engine gas turbine drive, the function of accessory drive system be exactly the shaft power of turbine is passed into each attachment, and
Meet requirement of each attachment to rotating speed, steering and power.Accessory drive system generally comprises accessory drive casing and accessory drive
Mechanism.Accessory drive gearbox is mounted directly on the engine, accessory drive gear in accessory drive gearbox, it include Cylinder Gear train and
Various forms of clutches, the attachment placement of twin spool gas turbine engine use the principle of Concentrate bid, greatly
Most attachmentes are installed concentratedly on special attachment casing, are driven by high pressure rotor.
The low pressure rotor of aero-engine is driven with the first driving motor 21, passes through the whole of compressor front end of dismantling
Then stream cover connects low pressure rotor system 11 and the first driving motor 21 to drive turning for low pressure rotor by first shaft coupling 6
Dynamic, the working speed of low pressure rotor is 300r/min；High pressure rotor rotation is driven by the second driving motor 22, with the second driving
Motor 22 replaces the startup motor in aero-engine in accessory drive system to drive high pressure rotor system 12, high pressure rotor
Working speed is 1500r/min；The rotating speed of two driving motors and start and stop are controlled by frequency converter.
The safety device 3 for security protection is housed in the outside of aero-engine, avoids rotary part because of accident
It flies off and injures testing crew, be used for the safety of the safety and testing equipment of guarantee test personnel.It is provided on safety device 3
Detection device and locking device, the detection device are used to detect the operating condition of safety device 3, the signal of the detection device
Output end connects the signal input part of control system, and the signal output end of control system connects the signal input part of locking device,
All buttons of the locking device on emergent stopping or locking hardware-software.Once safety device 3 is unreliable ready,
Experiment stops immediately, and locks all control knobs of hardware-software, while " safety device is not for display over the display
Thread " prompts, until safety device 3 is reliable ready.In addition, the unlatching to safety device 3 and master by control system
Axis carries out control, and only when rotating speed safety value of the speed of mainshaft less than setting, safety device 3 could be opened.
Collecting part mainly monitors stage body and Test condition in real time, such as Working Status Monitoring, Test Data Collecting
Deng by display real-time display, and exchanging data with control section, it is ensured that the safety of experiment.It is main in data acquisition
The sensor wanted has a three-way vibration acceleration transducer 9 and capacitive displacement transducer 8, the main installation site of sensor be
First driving motor, 21 output shaft, aeroplane engine inboard rotor connecting shaft and outer rotor connecting shaft are sensed equipped with capacitive displacement
Device 8, for measuring axial runout and the circular runout of shaft；2-3 grade casings corresponding to 5 spring bearings of aero-engine
II, 6 grades of casings V, combustion box VI and high-pressure turbine casing VII are equipped with three-way vibration acceleration transducer 9, for surveying
Measure its vibration；Tolerance can be arranged by the collected data of each sensor of each Sensor monitoring in working condition, once beyond holding
Difference, system starts buzzer and sends out alarm automatically, and corresponding display is made on software.
By being acquired to experimental data, analyzing processing, can be very good understand engine actual motion the case where, just
In more fully analyzing the problems such as vibration of critical component and complete machine in engine, for vibration evolution mechanism, vibration
Control and status monitoring provide good experiment condition.
Operation principle：The power of first driving motor 21 output drives turning for low pressure rotor system 11 through first shaft coupling 6
Dynamic, the rotation of low pressure rotor system 11 drives the rotation of low-pressure compressor and low-pressure turbine.Second driving motor 22 is through the second shaft coupling
Two pairs of spiral bevel gears in device 7 and casing driven accessary drive the rotation of high pressure rotor system 12, to drive high pressure pressure
The rotation of mechanism of qi and high-pressure turbine.
Embodiment 1, aircraft engine high pressure rotor vibration Characteristics：
Start the second driving motor 22, the power of the second driving motor 22 output is sent out through output shaft, 7 aviation of second shaft coupling
Nearby transmission system passes to high pressure rotor to motivation, to drive the rotation of high pressure rotor system 12, simulation aero-engine high
Press the operation of rotor；By the condenser type position on 22 output shaft of the second driving motor and aero-engine outer rotor connecting shaft
Displacement sensor 8, for measuring axial runout and the circular runout of shaft, by being mounted on II, 6 grade of 2-3 grades of casings of aero-engine
Three-dimensional acceleration transducer on casing V, combustion box VI and high-pressure turbine casing VII acquires vibration acceleration signal,
Connection Sensor output passes through to data collecting system after the signal of acquisition is converted to digital signal by data collecting system
Cable transfers data to computer data acquiring software, is analyzed by the signal to acquisition, so that it may be turned with analyzing high pressure
The vibration characteristics and research vibration control strategy of son.
Embodiment 2, aero-engine low-pressure compressor rotor vibration characteristics research：
Start the first driving motor 21, the power of the first driving motor 21 output is passed to through output shaft, first shaft coupling 6
Low pressure rotor system 11, to drive low pressure rotor system 11 to rotate, simulation aero-engine low pressure rotor operation, low pressure rotor
Working speed be 300r/min；By on 21 output shaft of the first driving motor and aeroplane engine inboard rotor connecting shaft
Capacitive displacement transducer 8, for measuring axial runout and the circular runout of shaft；By being mounted on 5 supports of aero-engine
Three-dimensional on 2-3 grades casing II, 6 grade of casing V, combustion box VI and high-pressure turbine casing VII corresponding to bearing accelerates
Sensor is spent, vibration acceleration signal, connection Sensor output to data collecting system are acquired, data collecting system will acquire
Signal be converted to digital signal after, computer data acquiring software is transferred data to by cable, passes through the letter to acquisition
It number is analyzed, so that it may to analyze the vibration characteristics and research vibration control strategy of low pressure rotor.
Embodiment 3, aero-engine complete machine oscillation characteristic research：
Start the first, second motor simultaneously, two motors, which synchronize, to be rotated forward, and the operation of aero-engine dual rotors system is simulated；
The rotating speed of low pressure rotor is 0 ~ 300r/min, and the rotating speed of high pressure rotor is 0 ~ 1500r/min, by being mounted on the first driving motor 21
Capacitive displacement transducer 8 in output shaft, aeroplane engine inboard rotor connecting shaft and outer rotor connecting shaft, for measuring shaft
Axial runout and circular runout；By II, 6 grade of casing of 2-3 grades casing corresponding to 5 spring bearings of aero-engine
V, the three-dimensional acceleration transducer on combustion box VI and high-pressure turbine casing VII acquires vibration acceleration signal；Connection
Sensor output passes through cable to data collecting system after the signal of acquisition is converted to digital signal by data collecting system
Computer data acquiring software is transferred data to, is analyzed by the signal to acquisition, so that it may to analyze aero-engine
The vibration characteristics and research vibration control strategy of complete machine.
The model analysis of embodiment 4, aero-engine key components and parts：
The key components and parts of aero-engine are tested using mould measurement system, in the portion of modal test to be carried out
Three-dimensional acceleration transducer is installed on part, acquires vibration acceleration signal, system is acquired with connection Sensor output to data
System carries out data acquisition and included analysis mould by mould measurement module (MTC Hammer) in application mould measurement system
Block (Modal analysis) carries out processing analyzing processing to data can obtain the intrinsic of aero-engine key components and parts
Frequency and the vibration shape.
Embodiment 5, aero-engine Modal Analysis：
Modal test is carried out to the complete machine of aero-engine using mould measurement software, by being mounted on aero-engine 5
The three-dimensional on 2-3 grades casing II, 6 grade of casing V, combustion box VI and high-pressure turbine casing VII corresponding to spring bearing
Acceleration transducer, acquires vibration acceleration signal, and connection Sensor output to data collecting system is surveyed by application mode
Mould measurement module (MTC Hammer) carries out data acquisition in examination and included analysis module (Modal analysis) is right
Data carry out the eigenfrequncies and vibration models that processing analyzing processing can obtain the complete machine of aero-engine.
Claims (8)
1. a kind of aero-engine vibration control experiment platform, it is characterised in that：The experiment porch includes experiment sewing platform base（5）,
And it is fixed on experiment sewing platform base（5）On aero-engine ontology（1）, drive system, TT＆C system and safety device
（3）；First driving motor of the drive system（21）Through first shaft coupling（6）Impart power to aero-engine ontology
（1）Low pressure rotor system（11）, the second driving motor of the drive system（22）Through second shaft coupling（7）And aeroplane engine
Machine ontology（1）Accessory drive system impart power to aero-engine ontology（1）High pressure rotor system（12）, described
One driving motor（21）And/or second driving motor（22）Motor output shaft and aero-engine low pressure rotor system
（11）With high pressure rotor system（12）It is equipped with capacitive displacement transducer（8）, corresponding to 5 spring bearings of aero-engine
2 grades of casings, 3 grades of casings, 6 grades of casings, combustion box and high-pressure turbine casing are equipped with three-way vibration acceleration transducer
（9）, in aero-engine ontology（1）Outside equipped with locking device be used for security protection safety device（3）.
2. according to a kind of aero-engine vibration control experiment platform described in claim 1, it is characterised in that：The aeroplane engine
Machine ontology（1）To have removed the aero-engine of after-burner and jet pipe part.
3. a kind of aero-engine vibration control experiment platform according to claim 1, it is characterised in that：The experiment porch
Aero-engine ontology（1）Supporting way be by four hitch points on casing（10）Suspension is mounted on experiment sewing platform base
（5）On.
4. a kind of aero-engine vibration control experiment platform according to claim 1, it is characterised in that：To the boat
Empty engine body（1）1 grade of casing, 4 grades of casings, combustion box, burning Interior Layout, combustion outer case, heat screen, reinforcing
Combustor diffuser outer wall carries out 1/8 cutting and forms observation window.
5. a kind of aero-engine vibration control experiment platform according to claim 1, it is characterised in that：The driving system
First driving motor of system（21）By the radome fairing for compressor front end of dismantling, then pass through first shaft coupling（6）Connect low pressure
Rotor-support-foundation system（11）To drive low pressure rotor；Second driving motor of the drive system（22）By replacing in aero-engine
Startup motor in accessory drive system drives high pressure rotor system（12）.
6. a kind of aero-engine vibration control experiment platform according to claim 1, it is characterised in that：The observing and controlling system
System includes motor controlling cabinet（41）, capacitive displacement transducer（8）, three-way vibration acceleration transducer（9）, data acquisition system
System, PC machine and connecting line.
7. a kind of aero-engine vibration control experiment platform according to claim 6, it is characterised in that：The driving
The first driving motor in system（21）And/or second driving motor（22）Start and stop and turn round by TT＆C system motor control
Cabinet（41）Frequency control.
8. a kind of aero-engine vibration control experiment platform according to claim 6, it is characterised in that：The experiment porch
Aero-engine ontology（1）It is set to safety device with drive system（3）It is interior, the motor controlling cabinet of TT＆C system（41）
It is set to safety device（3）Outside.
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