CN205538223U - Multifactor coupling vibration control comprehensive experiment platform of aeroengine - Google Patents
Multifactor coupling vibration control comprehensive experiment platform of aeroengine Download PDFInfo
- Publication number
- CN205538223U CN205538223U CN201620059118.6U CN201620059118U CN205538223U CN 205538223 U CN205538223 U CN 205538223U CN 201620059118 U CN201620059118 U CN 201620059118U CN 205538223 U CN205538223 U CN 205538223U
- Authority
- CN
- China
- Prior art keywords
- aero
- engine
- pressure rotor
- vibration control
- motor
- 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.)
- Expired - Fee Related
Links
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model provides a multifactor coupling vibration control comprehensive experiment platform of aeroengine, includes laboratory bench base, aeroengine body, actuating system, observing and controlling system and safety device, a driving motor of actuating system gives the low pressure rotor system of aeroengine body through first shaft coupling with the power transmission, the 2nd driving motor through the annex transmission system of second shaft coupling and aeroengine body with the high -pressure rotor system of power transmission for the aeroengine body, be equipped with capacitive displacement transducer on motor output shaft, low pressure rotor system and the high -pressure rotor system, be equipped with three -dimensional vibrational acceleration sensor on aeroengine 5 2 grades of quick -witted caskets that support bearing corresponded, 3 grades of quick -witted caskets, 6 grades of quick -witted caskets, combustion box and high pressure turbine caskets, should test multifactor coupling that the platform can be used for the testing analysis aeroengine quick -witted problem of shaking, extensively be applicable to two rotor system vibration characteristics of aeroengine and the research of vibration control tactics.
Description
Technical field
This utility model relates to engine test device, particularly to a kind of aero-engine experiment porch.
Background technology
Aero-engine, as the power set of aircraft, is to weigh the research and development of national power, a key for manufacture level, is the important symbol of big country's strength, and its relation technological researching has high politics, economy and military value.Requiring to improve constantly to engine performance in recent years, the load of engine component increases considerably, and causes vibration problem the most prominent, and vibration control becomes one of aero-engine important research project.
The research of aero-engine vibration control technology needs the support of corresponding experiment porch, existing experiment porch to generally face aero-engine local structure, it is adaptable to the research one by one of single factors.After have passed through accumulation for many years, urgent need can reflect the experiment porch correlational study for Noise and Vibration Control of the various inducement of vibration noise comprehensively, especially carrying forward vigorously civil-military inosculation under the new situation in country, more units set foot in aviation field, are badly in need of the support of this type of experiment porch.Aero-engine is reduced to the rotor-support-foundation system of multi-form by the experiment porch being currently used for aero-engine Study on Vibration Control, aero-engine dynamic response characteristic research under various single or these minority factors, development to advancing High Performance Aeroengine technology played important function, have accumulated a large amount of outstanding achievements, but can not meet further, more identical with aero-engine actual motion and, various factors coupling vibratory response characteristic research demand.The renovation and utilization that a kind of aero-engine various factors coupling vibration control comprehensive experiment table is true aero-engine that this utility model discloses, can be used for various factors coupling vibratory response characteristic and controls research.
Summary of the invention
For above-mentioned situation, the purpose of this utility model is that the shortcoming and defect overcoming prior art to exist, providing a kind of aero-engine various factors coupling vibration control comprehensive experiment table, this experiment porch can reflect aero-engine vibration truth of high-low pressure dual rotors system under maneuvering flight conditions；And overall structure is consistent with the real structure of aero-engine, simply transforming the part-structure of electromotor, improvement cost is relatively low, and transformation is not difficult, it is easy to penetration and promotion.
A kind of aero-engine various factors coupling vibration control comprehensive experiment table, this experiment porch includes laboratory table pedestal, and aero-engine body, drive system, TT&C system and the safety device being fixed on laboratory table pedestal；First driving motor of described drive system imparts power to the low pressure rotor system of aero-engine body through the first shaft coupling, second driving motor of described drive system imparts power to the high pressure rotor system of aero-engine body through the accessory drive system of the second shaft coupling and aero-engine body, described first drives motor and/or second to drive the motor output shaft of motor, and the low pressure rotor of aero-engine and high pressure rotor are provided 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 provided with three-way vibration acceleration transducer.
Described aero-engine body is to have removed after-burner and the aero-engine of jet pipe part.
For realizing structure optimization, further step: the supporting way of the aero-engine body of this experiment porch is to be hung by four hitch points on casing to be arranged on laboratory table pedestal.
Observe the internal structure of aero-engine and the installation relation of each parts for convenience, 1 grade of casing, 4 grades of casings, combustion box, combustor inner sleeve, combustion outer case, heat screen, after-burner diffuser outer walls of described aero-engine body are carried out 1/8 cutting and form observation window.
The first driving motor trousers by compressor front end of dismantling of described drive system, then connects low pressure rotor system by the first shaft coupling and drives low pressure rotor；Second driving motor of described drive system drives high pressure rotor system by the startup motor changed in aero-engine in accessory drive system.
Described TT&C system includes motor controlling cabinet, capacitive displacement transducer, three-way vibration acceleration transducer, data collecting system, PC and connecting line.
The first driving motor and/or second in described drive system drives the start and stop of motor and turns round by the motor controlling cabinet VFC of TT&C system.
The aero-engine body of this experiment porch and drive system are arranged in safety device, and the motor controlling cabinet of TT&C system is arranged at outside safety device.
This utility model produced beneficial effect compared to existing technology:
(I) this utility model can carry out transformation on the prototype of aero-engine or volume production machine body and prepares, and the size of each rotor part and installation site are all and practical situation holding is consistent, effectively prevent the experimental result inefficacy caused because of form difference；
(II) this utility model overall structure is scientific and reasonable, and transformation difficulty is little, and improvement cost is relatively low, non-environmental-pollution, it is easy to penetration and promotion；
(III) low pressure rotor system described in the utility model and high pressure rotor system are provided with capacitive displacement transducer and can be used to measure and turn shaft run-out and axial runout, the casing of each bearing correspondence position is provided with three-way vibration acceleration transducer for measuring the vibration of system, the situation of electromotor actual motion can be better understood by, it is easy to more fully the critical component in electromotor be carried out vibration monitoring, provides good experiment condition for the multifactor lower vibration evolutionary process of aero-engine and Study on Vibration Control；
(IV) this utility model carries out cutting to electromotor local, it is easy to us and observes the construction features of each parts of electromotor, structural relation between each parts, shows birotor spinfunction, birotor slip function that experiment porch possesses, and the working condition of each functional part.
This utility model is widely used in the Analysis of Vibration Characteristic of aero-engine dual-rotor structure, vibration control and status monitoring research.
The utility model is described in further detail with embodiment below in conjunction with the accompanying drawings.
Accompanying drawing explanation
Fig. 1 is laboratory table structural front view of the present utility model；
Fig. 2 is laboratory table structure top view of the present utility model；
Fig. 3 is laboratory table structure right view of the present utility model；
Fig. 4 is aviation engine structure schematic diagram in this utility model；
Fig. 5 is aero-engine casing biopsy cavity marker devices structural representation in this utility model；
Fig. 6 is the top view of this utility model supporting construction；
Fig. 7 is the front view that this utility model sensor is installed；
Fig. 8 is the structured flowchart of this utility model laboratory table；
Fig. 9 is this utility model TT&C system block diagram.
In figure: 1. aero-engine body；3. safety device；5. laboratory table pedestal；6. the first shaft coupling；7. the second shaft coupling；8. capacitive displacement transducer；9. three-way vibration acceleration sensing；10. hitch point；11. low pressure rotor systems；12. high pressure rotor systems；21. first drive motor；22. second drive motor；41. motor controlling cabinets.
Detailed description of the invention
As it is shown in figure 1, a kind of aero-engine various factors coupling vibration control comprehensive experiment table, this experiment porch is made up of with laboratory table pedestal 5 five major part aero-engine body 1, drive system, safety device 3, TT&C system.
Described drive system includes that first driving motor the 21, first shaft coupling 6, second drives motor 22 and the second shaft coupling 7；The first driving motor 21 in described drive system connects the low pressure rotor system 11 imparting power to aero-engine body 1 through the first shaft coupling 6, and the second driving motor 22 accessory drive system in the second shaft coupling 7 and aero-engine body 1 of drive system imparts power to the high pressure rotor system 12 of aero-engine body 1；Described drive system and aero-engine body 1 are linked in sequence and are fixed on laboratory table pedestal 5.As one preferable experiment porch scheme, internal rotor drives motor to be connected through the first shaft coupling and first, outer rotor drives motor to be connected through belt pulley, the second shaft coupling and second, substantially still, the simulation to aero-engine key structure, still larger difference is there is with practical structures, outer rotor drives motor to be connected through belt pulley, the second shaft coupling and second, power transmission poor stability.The aero-engine body of a kind of aero-engine various factors coupling vibration control comprehensive experiment table that this utility model discloses is the true aero-engine having removed after-burner and jet pipe, carry out vibration characteristics based on its practical structures and control research, complying fully with actual demand；Second driving motor of drive system imparts power to high pressure rotor system through the accessory drive system of the second shaft coupling and aero-engine body, and more compact structure, stability are more preferable.Can transform on the basis of retired aero-engine or prototype, both environmental protection, further save cost.
Described TT&C system includes motor controlling cabinet 41, capacitive displacement transducer 8, three-way vibration acceleration transducer 9, data collecting system, PC and connecting line.Motor controlling cabinet 41 is provided with control system and display, capacitive displacement transducer 8 and three-way vibration acceleration transducer 9 belong to collecting part, the signal output part of collecting part is by the signal input part of connection control system after filter filtering, the signal output part of control system connects the signal input part of display, signal is delivered to control system by collecting part, after control system processes, corresponding data is shown over the display, or signal is exported.
Referring to the drawings, described aero-engine body 1 is the true critical aircraft engine parts being removed after-burner and jet pipe part.The structure of aero-engine body 1 of the present utility model mainly includes low pressure rotor system 11 and high pressure rotor system 12, low pressure rotor system 11 is made up of three grades of low-pressure compressors, low pressure rotor and one-level low-pressure turbine, high pressure rotor system 12 is made up of three grades of high-pressure compressors, high pressure rotor and one-level high-pressure turbine, and low-pressure shaft forms dual rotors system through hollow high-pressure shaft.Whole dual rotors system is by 5 bearings, by front support bearings at 2 grades of low-pressure compressors, intershaft bearing is installed at 2 grades of high-pressure compressors support, two roller bearing supports are installed after three grades of high-pressure compressors, there is rear support bearing in high-pressure turbine front end, have stick roller bearing to support between high-pressure turbine and low-pressure turbine；With reference to Fig. 4, there is casing at different levels to support in two-spool outside, mainly have 1 grade of casing I, II, 4 grades of casings of 2-3 level casing, IV, 6 grades of casings V of III, 5 grades of 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 construction features of each parts of electromotor is observed for the ease of us, equipment relation between each parts, show that experiment porch possesses birotor spinfunction, birotor slip function, and the working condition of each functional part, as it is shown in figure 5, I, 4 grades of casings III of 1 grade of casing of aero-engine body 1, combustion box VI, combustor inner sleeve, combustion outer case, heat screen, after-burner diffuser outer wall are carried out 1/8 cutting；After-burner and jet pipe part to aero-engine are removed, and improved aero-engine is arranged on laboratory table pedestal 5 by four hitch points 10 suspensions on aero-engine body 1 casing.Electromotor relies on starter to start, the power resources of starter are in starting motor, need to be transmitted by accessory drive system, after starter starts, thering is provided power by accessory drive system for adnexa, starter, engine accessory power rating, freewheel clutch are all closely related with the working condition of accessory drive system.On gas-turbine unit, have many adnexaes need by electromotor gas turbine drive, the function of accessory drive system is exactly that the shaft power of turbine passes to each adnexa, and meet each adnexa to rotating speed, turn to and the requirement of power.Accessory drive system generally comprises accessory drive casing and accessory drive gear.Accessory drive gearbox is mounted directly on the engine, accessory drive gear is in accessory drive gearbox, it includes Cylinder Gear train and various forms of clutch, the adnexa of twin spool gas turbine electromotor disposes the principle using Concentrate bid, most of adnexaes are installed concentratedly on special attachment casing, high pressure rotor drive.
Drive motor 21 that the low pressure rotor of aero-engine is driven with first, trousers by compressor front end of dismantling, then connecting low pressure rotor system 11 and first by the first shaft coupling 6 drives motor 21 to drive the rotation of low pressure rotor, and the working speed of low pressure rotor is 300r/min；Driving motor 22 to drive high pressure rotor to rotate by second, drive high pressure rotor system 12 with the second startup motor driving motor 22 to change in aero-engine in accessory drive system, the working speed of high pressure rotor is 1500r/min；Rotating speed and the start and stop of two driving motors are controlled by converter.
In the outside of aero-engine equipped with the safety device 3 for security protection, it is to avoid rotary part injures testing crew, for safety and the safety of testing equipment of guarantee test personnel because of unexpected flying off.Detection device and locking device it is provided with on safety device 3, this detection device is for detecting the ruuning situation of safety device 3, the signal input part of the signal output part connection control system of this detection device, the signal output part of control system connects the signal input part of locking device, the locking device all buttons on emergent stopping or locking hardware-software.Once safety device 3 is the most ready, and test stops immediately, and locks all control knobs of hardware-software, the most over the display display " safety device is the most ready " prompting, until safety device 3 is the most ready.It addition, the unlatching of safety device 3 is carried out control with main shaft, only when the speed of mainshaft is less than the rotating speed safety value set, and safety device 3 just can be opened by control system.
Stage body and Test condition are mainly monitored by collecting part in real time, such as Working Status Monitoring, Test Data Collecting etc., are shown in real time by display, and exchange data with controlling part, it is ensured that the safety of test.Sensor main in data acquisition has three-way vibration acceleration transducer 9 and capacitive displacement transducer 8, the main installation site of sensor is to drive first to be provided with capacitive displacement transducer 8 in motor 21 output shaft, aeroplane engine inboard rotor connecting shaft and outer rotor connecting shaft, is used for measuring axial runout and the circular runout of rotating shaft；II, 6 grades of casings V of 2-3 level casing corresponding to 5 spring bearings of aero-engine, combustion box VI and high-pressure turbine casing VII are provided with three-way vibration acceleration transducer 9, are used for measuring its vibration；Duty by each sensor acquisition of each Sensor monitoring to data tolerance all can be set, once beyond tolerance, system automatically starts buzzer and sends alarm, and makes corresponding display on software.
By experimental data being acquired, analyzing and processing, the situation of electromotor actual motion can well be understood, it is easy to the problems such as more fully vibration to the critical component in electromotor and complete machine be analyzed, provides good experiment condition for vibration evolution mechanism, vibration control and status monitoring.
Operation principle: first drives the power of motor 21 output to drive the rotation of low pressure rotor system 11 through the first shaft coupling 6, and low pressure rotor system 11 rotates and drives low-pressure compressor and the rotation of low-pressure turbine.Second drives the motor 22 two pairs of spiral bevel gears in the second shaft coupling 7 and casing driven accessary to drive the rotation of high pressure rotor system 12, thus drives the rotation of high-pressure compressor and high-pressure turbine.
Embodiment 1, aircraft engine high pressure rotor vibration Characteristics:
Starting the second driving motor 22, second drives power drive system near output shaft, the second shaft coupling 7 aero-engine of motor 22 output to pass to high pressure rotor, thus drives the rotation of high pressure rotor system 12, the operation of simulation aircraft engine high pressure rotor；By the capacitive displacement transducer 8 being arranged in the second driving motor 22 output shaft and aero-engine outer rotor connecting shaft, it is used for measuring axial runout and the circular runout of rotating shaft, by being arranged on aero-engine 2-3 level casing II, 6 grades of casings V, three-dimensional acceleration transducer on combustion box VI and high-pressure turbine casing VII, gather vibration acceleration signal, connect Sensor output to data collecting system, after the signal of collection is converted to digital signal by data collecting system, computer data acquiring software is transferred data to by netting twine, by the signal gathered is analyzed, just can analyze vibration characteristics and the research vibration control strategy of high pressure rotor.
Embodiment 2, aero-engine low-pressure compressor rotor vibration characteristics research:
Start the first driving motor 21, first drives the power of motor 21 output to pass to low pressure rotor system 11 through output shaft, the first shaft coupling 6, thus driving low pressure rotor system 11 to rotate, simulation aero-engine low pressure rotor runs, and the working speed of low pressure rotor is 300r/min；By the capacitive displacement transducer 8 being arranged in the first driving motor 21 output shaft and aeroplane engine inboard rotor connecting shaft, it is used for measuring axial runout and the circular runout of rotating shaft；By the three-dimensional acceleration transducer on II, 6 grades of casings V of the 2-3 level casing being arranged on corresponding to 5 spring bearings of aero-engine, combustion box VI and high-pressure turbine casing VII, gather vibration acceleration signal, connect Sensor output to data collecting system, after the signal of collection is converted to digital signal by data collecting system, computer data acquiring software is transferred data to by netting twine, by the signal gathered is analyzed, it is possible to analyze vibration characteristics and the research vibration control strategy of low pressure rotor.
Embodiment 3, aero-engine complete machine oscillation characteristic research:
Starting first, second motor, two motor in synchrony rotate forward simultaneously, the operation of simulation aero-engine dual rotors system；The rotating speed of low pressure rotor is 0 ~ 300r/min, the rotating speed of high pressure rotor is 0 ~ 1500r/min, by the capacitive displacement transducer 8 being arranged in the first driving motor 21 output shaft, aeroplane engine inboard rotor connecting shaft and outer rotor connecting shaft, it is used for measuring axial runout and the circular runout of rotating shaft；By the three-dimensional acceleration transducer on II, 6 grades of casings V of the 2-3 level casing being arranged on corresponding to 5 spring bearings of aero-engine, combustion box VI and high-pressure turbine casing VII, gather vibration acceleration signal；Connect Sensor output to data collecting system, after the signal of collection is converted to digital signal by data collecting system, computer data acquiring software is transferred data to by netting twine, by the signal gathered is analyzed, it is possible to analyze vibration characteristics and the research vibration control strategy of aero-engine complete machine.
Embodiment 4, the model analysis of aero-engine key components and parts:
The key components and parts of aero-engine is tested by application mould measurement system, the parts of modal test to be carried out are installed three-dimensional acceleration transducer, gather vibration acceleration signal, use and connect Sensor output to data collecting system, carry out data acquisition and the analysis module (Modal analysis) that carries by mould measurement module (MTC Hammer) in application mould measurement system and data are carried out Treatment Analysis process and just can draw the eigenfrequncies and vibration models of aero-engine key components and parts.
Embodiment 5, aero-engine Modal Analysis:
Application mould measurement software carries out modal test to the complete machine of aero-engine, by the three-dimensional acceleration transducer on II, 6 grades of casings V of the 2-3 level casing being arranged on corresponding to 5 spring bearings of aero-engine, combustion box VI and high-pressure turbine casing VII, gather vibration acceleration signal, connection Sensor output is to data collecting system, by mould measurement module (MTC in application mould measurement
Hammer) carry out data acquisition and the analysis module (Modal analysis) that carries carries out Treatment Analysis and processes the eigenfrequncies and vibration models of the complete machine that just can draw aero-engine data.
Claims (8)
1. an aero-engine various factors coupling vibration control comprehensive experiment table, it is characterized in that: this experiment porch includes laboratory table pedestal (5), and aero-engine body (1), drive system, TT&C system and the safety device (3) being fixed on laboratory table pedestal (5)；First driving motor (21) of described drive system imparts power to the low pressure rotor system (11) of aero-engine body (1) through the first shaft coupling (6), second driving motor (22) of described drive system imparts power to the high pressure rotor system (12) of aero-engine body (1) through the accessory drive system of the second shaft coupling (7) and aero-engine body (1), described first drives motor (21) and/or second to drive the motor output shaft of motor (22), and the low pressure rotor of aero-engine and high pressure rotor are provided with capacitive displacement transducer (8), 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 provided with three-way vibration acceleration transducer (9).
2. according to a kind of aero-engine various factors coupling vibration control comprehensive experiment table described in claim 1, it is characterised in that: described aero-engine body (1) is for have removed after-burner and the aero-engine of jet pipe part.
A kind of aero-engine various factors coupling vibration control comprehensive experiment table the most according to claim 1, it is characterised in that: the supporting way of the aero-engine body (1) of this experiment porch is to be hung by four hitch points (10) on casing to be arranged on laboratory table pedestal (5).
A kind of aero-engine various factors coupling vibration control comprehensive experiment table the most according to claim 1, it is characterised in that: 1 grade of casing, 4 grades of casings, combustion box, combustor inner sleeve, combustion outer case, heat screen, after-burner diffuser outer walls of described aero-engine body (1) are carried out 1/8 cutting and form observation window.
A kind of aero-engine various factors coupling vibration control comprehensive experiment table the most according to claim 1, it is characterized in that: the first driving motor (21) of the described drive system trousers by compressor front end of dismantling, then connect low pressure rotor system (11) by the first shaft coupling (6) and drive low pressure rotor；Second driving motor (22) of described drive system drives high pressure rotor system (12) by the startup motor changed in aero-engine in accessory drive system.
A kind of aero-engine various factors coupling vibration control comprehensive experiment table the most according to claim 1, it is characterised in that: described TT&C system includes motor controlling cabinet (41), capacitive displacement transducer (8), three-way vibration acceleration transducer (9), data collecting system, PC and connecting line.
A kind of aero-engine various factors coupling vibration control comprehensive experiment table the most according to claim 6, it is characterised in that: the first driving motor (21) and/or second in described drive system drives the start and stop of motor (22) and turns round by motor controlling cabinet (41) VFC of TT&C system.
A kind of aero-engine various factors coupling vibration control comprehensive experiment table the most according to claim 6, it is characterized in that: the aero-engine body (1) of this experiment porch and drive system are arranged in safety device (3), and the motor controlling cabinet (41) of TT&C system is arranged at safety device (3) outward.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620059118.6U CN205538223U (en) | 2016-01-21 | 2016-01-21 | Multifactor coupling vibration control comprehensive experiment platform of aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620059118.6U CN205538223U (en) | 2016-01-21 | 2016-01-21 | Multifactor coupling vibration control comprehensive experiment platform of aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205538223U true CN205538223U (en) | 2016-08-31 |
Family
ID=56766082
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620059118.6U Expired - Fee Related CN205538223U (en) | 2016-01-21 | 2016-01-21 | Multifactor coupling vibration control comprehensive experiment platform of aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205538223U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105571867A (en) * | 2016-01-21 | 2016-05-11 | 苏州东菱振动试验仪器有限公司 | Vibration control experiment platform for aero-engine |
| CN106601115A (en) * | 2017-01-21 | 2017-04-26 | 长安大学 | Aero-engine detachable disk-drum-type rotor experiment table |
| CN109854378A (en) * | 2019-04-08 | 2019-06-07 | 沈阳建筑大学 | A kind of turbofan with mode tuning ability |
-
2016
- 2016-01-21 CN CN201620059118.6U patent/CN205538223U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105571867A (en) * | 2016-01-21 | 2016-05-11 | 苏州东菱振动试验仪器有限公司 | Vibration control experiment platform for aero-engine |
| CN105571867B (en) * | 2016-01-21 | 2018-10-02 | 苏州东菱振动试验仪器有限公司 | A kind of aero-engine vibration control experiment platform |
| CN106601115A (en) * | 2017-01-21 | 2017-04-26 | 长安大学 | Aero-engine detachable disk-drum-type rotor experiment table |
| CN106601115B (en) * | 2017-01-21 | 2019-06-21 | 长安大学 | A kind of aero-engine removable disk drum type rotor experimental bench |
| CN109854378A (en) * | 2019-04-08 | 2019-06-07 | 沈阳建筑大学 | A kind of turbofan with mode tuning ability |
| CN109854378B (en) * | 2019-04-08 | 2023-10-24 | 沈阳建筑大学 | Turbofan engine with mode adjustment capability |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105571867B (en) | A kind of aero-engine vibration control experiment platform | |
| CN205538223U (en) | Multifactor coupling vibration control comprehensive experiment platform of aeroengine | |
| EP3034812B1 (en) | Torque sensor monitoring for gas turbine engine | |
| CN204705483U (en) | A kind of aeromotor birotor Research on Dynamic Characteristic experiment porch | |
| CN102840882B (en) | State monitoring and fault diagnosis system of gas turbine generating unit and use method of state monitoring and fault diagnosis system | |
| CN112629840B (en) | Double-rotor-support-casing tester for aero-engine and testing method thereof | |
| CN204831793U (en) | Whirlpool shaft generator dynamic characteristic studies experimental apparatus | |
| JP2002152862A (en) | Data collection unit for remote supervisory system, and remote supervisory method | |
| CN106053091B (en) | A kind of piggyback pod comprehensive test device and test method based on virtual scene | |
| CN109459242B (en) | High-speed self-rotating test bed measurement and control system of solid rocket engine | |
| CN110457861A (en) | A kind of airborne turboshaft engine dynamical system visible diagnosis platform and construction method | |
| CN110686856A (en) | Vibration monitoring, early warning and safety protection system for wind tunnel test bed of helicopter 2 m-diameter rotor | |
| CN203130170U (en) | Low-pressure rotor autorotation tool used for borescope inspection of engine of civil aircraft | |
| CN108507670A (en) | A kind of vibrations method for diagnosing faults for paint finishing | |
| CN202403791U (en) | Portable gear drive noise testing system | |
| CN115371992A (en) | System and method for monitoring component failure in a gear train based system | |
| CN101368870B (en) | Preparation method of amplitude frequency spectrum used for mechanical rotor single cross section shaft vibration analysis | |
| CN106248382A (en) | Starter testing stand | |
| CN116337657A (en) | Online monitoring device for cracks of wheel disc low-cycle fatigue test | |
| EP2009451A2 (en) | Synchronous signal generator for trim balancing of jet engine | |
| CN214446024U (en) | Turbine puller for dismounting turbine rotating assembly of starter | |
| Huang | Vibration Testing of a Certain Turbojet Engine Using the Power Spectrum Analysis. | |
| CN104236798B (en) | The one side diagram balance method of the pure test mass nyquist diagram of rotating machinery start and stop car | |
| CN204832984U (en) | Multidimension sine vibration controlling means | |
| CN115560540B (en) | Integrated intelligent turbine cooler and control method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160831 Termination date: 20190121 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |