CN105571867A - Vibration control experiment platform for aero-engine - Google Patents
Vibration control experiment platform for aero-engine Download PDFInfo
- Publication number
- CN105571867A CN105571867A CN201610040169.9A CN201610040169A CN105571867A CN 105571867 A CN105571867 A CN 105571867A CN 201610040169 A CN201610040169 A CN 201610040169A CN 105571867 A CN105571867 A CN 105571867A
- Authority
- CN
- China
- Prior art keywords
- aeromotor
- pressure rotor
- vibration control
- experiment platform
- aero
- 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.)
- Granted
Links
Classifications
-
- 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
-
- 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
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
A vibration control experiment platform for an aero-engine comprises the components of an experiment platform base, an aero-engine body, a driving system, a testing control system and a security protecting device. A first driving motor of the driving system transmits a power to a low-pressure rotor system of the aero-engine body. A second driving motor transmits the power to a high-pressure rotor system of the aero-engine body through a second coupling and an accessory transmission system of the aero-engine body. A motor output shaft, the low-pressure rotor system and the high-pressure rotor system are provided with capacitive displacement sensors. A second-stage case, a third-stage case, a six-stage case, a combustion chamber case and a high-pressure turbo case which correspond with five supporting bearings of the aero-engine are provided with three-dimensional vibration acceleration sensors. The vibration control experiment platform can be used testing and analyzing a multi-factor coupled vibration problem of the aero-engine. The vibration control experiment platform can be widely used for researching vibration characteristic and vibration control strategy of an aero-engine double-rotor system.
Description
Technical field
The present invention relates to engine test device, particularly a kind of aeromotor experiment porch.
Background technology
Aeromotor is as the propulsion system of aircraft, and be the key of the national power research and development of measurement one, manufacture level, be the important symbol of big country's strength, its relation technological researching has high politics, economy and military value.Require to improve constantly to engine performance in recent years, the load of engine component increases considerably, and causes vibration problem very outstanding, and vibration control becomes one of aeromotor important research project.
The research of aeromotor vibration control technology needs the support of corresponding experiment porch, and the general Aviation engine local of existing experiment porch builds, and is applicable to the research one by one of single factors.After have passed through accumulation for many years, urgent need can reflect the correlative study of experiment porch for Noise and Vibration Control of the various inducement of vibration noise comprehensively, especially carry forward vigorously civil-military inosculation under the new situation in country, Geng Duo unit sets foot in aviation field, is badly in need of the support of this type of experiment porch.Aeromotor is reduced to multi-form rotor-support-foundation system by the existing experiment porch for aeromotor Study on Vibration Control, for aeromotor dynamic response characteristic research under various single or these minority factors, vital role was played to advancing the development of High Performance Aeroengine technology, have accumulated a large amount of outstanding achievements, but can not meet further, with aeromotor actual motion more identical and, various factors coupling vibratory response characteristic research demand.A kind of aeromotor vibration control experiment platform that the present invention discloses is the renovation and utilization of true aeromotor, can be used for various factors coupling vibratory response characteristic and controls to study.
Summary of the invention
For above-mentioned situation, object of the present invention is just the shortcoming and defect overcoming prior art existence, provide a kind of aeromotor vibration control experiment platform, this experiment porch can reflect the vibration truth of aeromotor high-low pressure dual rotors system under maneuvering flight conditions; And one-piece construction is consistent with the real structure of aeromotor, just transform the part-structure of engine, improvement cost is lower, and transformation is not difficult, and is easy to penetration and promotion.
A kind of aeromotor vibration control experiment platform, this experiment porch comprises experiment table pedestal, and is fixed on aeromotor body, drive system, TT&C system and the safety device on experiment table pedestal, first drive motor of described drive system through the first shaft coupling by power transmission to the low pressure rotor system of aeromotor body, second drive motor of described drive system through the accessory drive system of the second shaft coupling and aeromotor body by power transmission to the high pressure rotor system of aeromotor body, the motor output shaft of described first drive motor and/or the second drive motor, and the low pressure rotor system of aeromotor and high pressure rotor system are provided with capacitive displacement transducer, 2 grades of casings corresponding to aeromotor 5 spring bearings, 3 grades of casings, 6 grades of casings, combustion box and high-pressure turbine casing are provided with three-way vibration acceleration transducer.
Described aeromotor body is the aeromotor of having removed after-burner and jet pipe part.
For realizing structure optimization, further step: the supporting way of the aeromotor body of this experiment porch is hung by the hitch point of four on casing to be arranged on experiment table pedestal.
Conveniently observe the inner structure of aeromotor and the installation relation of each parts, 1 grade of casing of described aeromotor body, 4 grades of casings, combustion box, firing chamber inner sleeve, combustion outer case, thermoscreen, after-burner diffuser outer walls are carried out to 1/8 cutting and form observation window.
First drive motor of described drive system, by the radome fairing of pneumatic plant front end of dismantling, then connects low pressure rotor system by the first shaft coupling and drives low pressure rotor; Second drive motor of described drive system drives high pressure rotor system by the starter motor changed in aeromotor in accessory drive system.
Described TT&C system comprises motor controlling cabinet, capacitive displacement transducer, three-way vibration acceleration transducer, data acquisition system (DAS), PC and connecting line.
The first drive motor in described drive system and/or the start and stop of the second drive motor and turn round by the motor controlling cabinet variable frequency control of TT&C system.
The aeromotor 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.
The beneficial effect that the present invention is produced compared to existing technology:
(I) the present invention can carry out on the prototype of aeromotor or volume production machine body transformation obtain, the size of each rotor part and installation site are all consistent with actual conditions, effectively prevent cause because of form difference experimental result inefficacy;
(II) one-piece construction of the present invention is scientific and reasonable, and transformation difficulty is little, and improvement cost is lower, non-environmental-pollution, is easy to penetration and promotion;
(III) low pressure rotor system of the present invention and high pressure rotor system are provided with capacitive displacement transducer and can be used to measurement and turn shaft run-out and axial runout, the casing of each bearing correspondence position is provided with three-way vibration acceleration transducer and is used for the vibration of measuring system, better can understand the situation of engine actual motion, be convenient to more fully carry out vibration monitoring to the critical component in engine, for the multifactor lower vibration evolutionary process of aeromotor and Study on Vibration Control provide good experiment condition;
(IV) the present invention carries out cutting to engine local, be convenient to the design feature that we observe each parts of engine, structural relation between each parts, shows birotor spinfunction, birotor slip function that experiment porch possesses and the working condition of each functional part.
The present invention is widely used in the Analysis of Vibration Characteristic of aeromotor dual-rotor structure, vibration control and status monitoring research.
Below in conjunction with drawings and Examples, the present invention is described in further detail.
Accompanying drawing explanation
Fig. 1 is experiment table structural front view of the present invention;
Fig. 2 is experiment table structure vertical view of the present invention;
Fig. 3 is experiment table 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 biopsy cavity marker devices structural representation in the present invention;
Fig. 6 is the vertical view of supporting construction of the present invention;
Fig. 7 is the front view that sensor of the present invention is installed;
Fig. 8 is the structured flowchart of experiment table of the present invention;
Fig. 9 is TT&C system block diagram of the present invention.
In figure: 1. aeromotor body; 3. safety device; 5. experiment 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.
Embodiment
As shown in Figure 1, a kind of aeromotor vibration control experiment platform, this experiment porch is made up of aeromotor body 1, drive system, safety device 3, TT&C system and experiment table pedestal 5 five major part.
Described drive system comprises the first drive motor 21, first shaft coupling 6, second drive motor 22 and the second shaft coupling 7; The first drive motor 21 in described drive system connects by power transmission to the low pressure rotor system 11 of aeromotor body 1 through the first shaft coupling 6, the second drive motor 22 of drive system accessory drive system in the second shaft coupling 7 and aeromotor body 1 by power transmission to the high pressure rotor system 12 of aeromotor body 1; Described drive system and aeromotor body 1 are linked in sequence and are fixed on experiment table pedestal 5.As the good experiment porch scheme of one, internal rotor is connected with the first drive motor through the first shaft coupling, outer rotor is connected with the second drive motor through belt pulley, the second shaft coupling, simulation in essence still to aeromotor key structure, still larger difference is there is with practical structures, outer rotor is connected with the second drive motor through belt pulley, the second shaft coupling, power transmission poor stability.The aeromotor body of a kind of aeromotor vibration control experiment platform that the present invention discloses is the true aeromotor of having removed after-burner and jet pipe, carries out vibration characteristics and controls to study, complete realistic demand based on its practical structures; Second drive motor of drive system through the accessory drive system of the second shaft coupling and aeromotor body by power transmission to high pressure rotor system, more compact structure, stability are better.Can transform on the basis of retired aero-engine or prototype, both environmental protection, further save cost again.
Described TT&C system comprises motor controlling cabinet 41, capacitive displacement transducer 8, three-way vibration acceleration transducer 9, data acquisition system (DAS), PC and connecting line.Control system and display is provided with in motor controlling cabinet 41, 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 process, by corresponding data display over the display, or signal is exported.
With reference to accompanying drawing, described aeromotor body 1 is the true critical aircraft engine parts of removing after-burner and jet pipe part.The structure of aeromotor body 1 of the present invention mainly comprises 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.Preferably, the low pressure rotor of aeromotor and high pressure rotor are provided with capacitive displacement transducer 8.Whole dual rotors system is by 5 bearings, at 2 grades of low-pressure compressor places by front support bearings, intershaft bearing is installed at 2 grades of high-pressure compressor places 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, between high-pressure turbine and low-pressure turbine, have stick roller bearing to support; With reference to Fig. 4, there is casing at different levels to support in two-spool outside, mainly contain 1 grade of casing I, 2-3 level casing II, 4 grades of casings III, 5 grades of casings IV, 6 grades of casings V, 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 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 shown in Figure 5,1/8 cutting is carried out to 1 grade of casing, I, 4 grades of casings III of aeromotor body 1, combustion box VI, firing chamber inner sleeve, combustion outer case, thermoscreen, after-burner diffuser outer wall; The after-burner of aeromotor and jet pipe part are removed, improved aeromotor is hung by four hitch points 10 on aeromotor body 1 casing and is arranged on experiment table pedestal 5.Engine relies on starter to start, the power resources of starter are in actuating motor, need to be transmitted by accessory drive system, after starter starts, by accessory drive system for annex provides power, starter, engine accessory power rating, overrunning clutch are all closely related with the working condition of accessory drive system.On gas-turbine unit, have many annexes to need to be driven by the gas turbine of engine, the function of accessory drive system is exactly that the shaft power of turbine is passed to each annex, and meet each annex 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 directly installed on engine, accessory drive gear is in accessory drive gearbox, it comprises Cylinder Gear train and various forms of clutch coupling, the principle adopting Concentrate bid settled by the annex of twin spool gas turbine engine, most of annex is installed concentratedly on special attachment casing, is driven by high pressure rotor.
Drive with the low pressure rotor of the first drive motor 21 pairs of aeromotors, by the radome fairing of pneumatic plant front end of dismantling, then connect by the first shaft coupling 6 rotation that low pressure rotor system 11 and the first drive motor 21 drive low pressure rotor, the working speed of low pressure rotor is 300r/min; Drive high pressure rotor to rotate by the second drive motor 22, drive high pressure rotor system 12 with the second drive motor 22 starter motor changed in aeromotor in accessory drive system, the working speed of high pressure rotor is 1500r/min; The rotating speed of two drive motor and start and stop are controlled by frequency converter.
Safety device 3 for security protection is housed in the outside of aeromotor, avoids rotary part to injure testing crew because of unexpected flying off, be used for the safety of warranty test personnel and the safety of testing equipment.Safety device 3 is provided with pick-up unit and locking device, this pick-up unit is for detecting the ruuning situation of safety device 3, the signal input part of the signal output part connection control system of this pick-up unit, the signal output part of control system connects the signal input part of locking device, all buttons of locking device on emergent stopping or locking hardware-software.Once safety device 3 is reliably not ready, test stops immediately, and locks all control knobs of hardware-software, shows " safety device is not ready " prompting over the display, until safety device 3 is reliably ready simultaneously.In addition, to be carried out control by control system to the unlatching of safety device 3 and main shaft, only have when the speed of mainshaft is lower than the rotating speed safety value of setting, safety device 3 just can be opened.
Collecting part is mainly monitored in real time to stage body and Test condition, as Working Status Monitoring, Test Data Collecting etc., is shown in real time by display, and exchanges data with control section, guarantees the security tested.Sensor main in data acquisition has three-way vibration acceleration transducer 9 and capacitive displacement transducer 8, the main installation site of sensor is provided with capacitive displacement transducer 8 on the first drive motor 21 output shaft, aeroplane engine inboard rotor coupling shaft and outer rotor coupling shaft, is used for measuring axial runout and the diameter run-out of rotating shaft; 2-3 level casing corresponding to aeromotor 5 spring bearings II, 6 grades of casings V, combustion box VI and high-pressure turbine casings VII are provided with three-way vibration acceleration transducer 9, are used for measuring its vibration; The data that duty is collected by each sensor of each Sensor monitoring all can arrange tolerance, once exceed tolerance, system automatically starts hummer and gives the alarm, and on software, make corresponding display.
By gathering experimental data, analyzing and processing, the situation of engine actual motion can well be understood, be convenient to more fully analyze, for vibration evolution mechanism, vibration control and status monitoring provide good experiment condition problems such as the vibrations of the critical component in engine and complete machine.
Principle of work: the power that the first drive motor 21 exports is through the rotation of the first shaft coupling 6 energize low-pressure rotor-support-foundation system 11, and low pressure rotor system 11 rotates the rotation driving low-pressure compressor and low-pressure turbine.The two pair spiral bevel gears of the second drive motor 22 in the second shaft coupling 7 and casing driven accessary carry out the rotation of energizes high-pressure rotor-support-foundation system 12, thus the rotation of energizes high-pressure pneumatic plant and high-pressure turbine.
Embodiment 1, aircraft engine high pressure rotor vibration Characteristics:
Start the second drive motor 22, power kinematic train near output shaft, the second shaft coupling 7 aeromotor that second drive motor 22 exports passes to high pressure rotor, thus drive the rotation of high pressure rotor system 12, the operation of simulation aircraft engine high pressure rotor, by the capacitive displacement transducer 8 be arranged on the second drive motor 22 output shaft and aeromotor outer rotor coupling shaft, be used for measuring the axial runout of rotating shaft and diameter run-out, by being arranged on aeromotor 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, connecting sensor output line is to data acquisition system (DAS), after the signal of collection is converted to digital signal by data acquisition system (DAS), computer data acquiring software is transferred data to by netting twine, by analyzing the signal gathered, just can analyze vibration characteristics and the research vibration control strategy of high pressure rotor.
Embodiment 2, the research of aeromotor low-pressure compressor rotor vibration characteristics:
Start the first drive motor 21, the power that first drive motor 21 exports passes to low pressure rotor system 11 through output shaft, the first shaft coupling 6, thus driving low pressure rotor system 11 to rotate, simulation aeromotor low pressure rotor runs, and the working speed of low pressure rotor is 300r/min; By the capacitive displacement transducer 8 be arranged on the first drive motor 21 output shaft and aeroplane engine inboard rotor coupling shaft, be used for measuring the axial runout of rotating shaft and diameter run-out; By the three-dimensional acceleration transducer on the 2-3 level casing be arranged on corresponding to aeromotor 5 spring bearings II, 6 grades of casings V, combustion box VI and high-pressure turbine casings VII, gather vibration acceleration signal, connecting sensor output line is to data acquisition system (DAS), after the signal of collection is converted to digital signal by data acquisition system (DAS), computer data acquiring software is transferred data to by netting twine, by analyzing the signal gathered, vibration characteristics and the research vibration control strategy of low pressure rotor just can be analyzed.
Embodiment 3, aeromotor complete machine oscillation characteristic research:
Start first, second motor, two motor in synchrony rotate forward simultaneously, the operation of simulation aeromotor 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 be arranged on the first drive motor 21 output shaft, aeroplane engine inboard rotor coupling shaft and outer rotor coupling shaft, be used for measuring the axial runout of rotating shaft and diameter run-out; By the three-dimensional acceleration transducer on the 2-3 level casing be arranged on corresponding to aeromotor 5 spring bearings II, 6 grades of casings V, combustion box VI and high-pressure turbine casings VII, gather vibration acceleration signal; Connecting sensor output line is to data acquisition system (DAS), after the signal of collection is converted to digital signal by data acquisition system (DAS), computer data acquiring software is transferred data to by netting twine, by analyzing the signal gathered, vibration characteristics and the research vibration control strategy of aeromotor complete machine just can be analyzed.
The model analysis of embodiment 4, aeromotor key components and parts:
The key components and parts of application mould measurement system to aeromotor is tested, the parts that will carry out modal test install three-dimensional acceleration transducer, gather vibration acceleration signal, use connecting sensor output line to data acquisition system (DAS), carry out data acquisition by mould measurement module (MTCHammer) in application mould measurement system and the analysis module (Modalanalysis) that carries carries out to data the eigenfrequncies and vibration models that Treatment Analysis process just can draw aeromotor key components and parts.
Embodiment 5, aeromotor Modal Analysis:
Application mould measurement software carries out modal test to the complete machine of aeromotor, by the 2-3 level casing II be arranged on corresponding to aeromotor 5 spring bearings, 6 grades of casings V, three-dimensional acceleration transducer on combustion box VI and high-pressure turbine casing VII, gather vibration acceleration signal, connecting sensor output line is to data acquisition system (DAS), data acquisition is carried out and the analysis module (Modalanalysis) that carries carries out to data the eigenfrequncies and vibration models that Treatment Analysis process just can draw the complete machine of aeromotor by mould measurement module (MTCHammer) in application mould measurement.
Claims (8)
1. an aeromotor vibration control experiment platform, it is characterized in that: this experiment porch comprises experiment table pedestal (5), and be fixed on aeromotor body (1), drive system, TT&C system and the safety device (3) on experiment table pedestal (5), first drive motor (21) of described drive system through the first shaft coupling (6) by power transmission to the low pressure rotor system (11) of aeromotor body (1), second drive motor (22) of described drive system through the accessory drive system of the second shaft coupling (7) and aeromotor body (1) by power transmission to the high pressure rotor system (12) of aeromotor body (1), the motor output shaft of described first drive motor (21) and/or the second drive motor (22), and the low pressure rotor system (11) of aeromotor and high pressure rotor system (12) are provided with capacitive displacement transducer (8), 2 grades of casings corresponding to aeromotor 5 spring bearings, 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 aeromotor vibration control experiment platform according to claim 1, it is characterized in that: described aeromotor body (1) is for having removed the aeromotor of after-burner and jet pipe part.
3. a kind of aeromotor vibration control experiment platform according to claim 1, is characterized in that: the supporting way of the aeromotor body (1) of this experiment porch is hung by the hitch point of four on casing (10) to be arranged on experiment table pedestal (5).
4. a kind of aeromotor vibration control experiment platform according to claim 1, is characterized in that: 1 grade of casing of described aeromotor body (1), 4 grades of casings, combustion box, firing chamber inner sleeve, combustion outer case, thermoscreen, after-burner diffuser outer walls are carried out to 1/8 cutting and form observation window.
5. a kind of aeromotor vibration control experiment platform according to claim 1, it is characterized in that: first drive motor (21) of described drive system, by the radome fairing of pneumatic plant front end of dismantling, then connects low pressure rotor system (11) by the first shaft coupling (6) and drives low pressure rotor; Second drive motor (22) of described drive system drives high pressure rotor system (12) by the starter motor changed in aeromotor in accessory drive system.
6. a kind of aeromotor vibration control experiment platform according to claim 1, is characterized in that: described TT&C system comprises motor controlling cabinet (41), capacitive displacement transducer (8), three-way vibration acceleration transducer (9), data acquisition system (DAS), PC and connecting line.
7. a kind of aeromotor vibration control experiment platform according to claim 6, is characterized in that: the first drive motor (21) in described drive system and/or the start and stop of the second drive motor (22) and turn round by the motor controlling cabinet of TT&C system (41) variable frequency control.
8. a kind of aeromotor vibration control experiment platform according to claim 6, it is characterized in that: the aeromotor body (1) of this experiment porch and drive system are arranged in safety device (3), 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 |
|---|---|---|---|
| CN201610040169.9A CN105571867B (en) | 2016-01-21 | 2016-01-21 | A kind of aero-engine vibration control experiment platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610040169.9A CN105571867B (en) | 2016-01-21 | 2016-01-21 | A kind of aero-engine vibration control experiment platform |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105571867A true CN105571867A (en) | 2016-05-11 |
| CN105571867B CN105571867B (en) | 2018-10-02 |
Family
ID=55882253
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610040169.9A Expired - Fee Related CN105571867B (en) | 2016-01-21 | 2016-01-21 | A kind of aero-engine vibration control experiment platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105571867B (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106404412A (en) * | 2016-09-28 | 2017-02-15 | 中国航空工业集团公司北京航空精密机械研究所 | Device for measuring the eccentric position of the aero-engine bearing holder |
| CN107727340A (en) * | 2017-08-18 | 2018-02-23 | 上海机电工程研究所 | The elastic vibration mode testing method of rotary missile |
| CN109406152A (en) * | 2018-12-13 | 2019-03-01 | 中国科学院工程热物理研究所 | A kind of aero-engine is to turning birotor kinetic characteristics experiment porch |
| CN111005768A (en) * | 2019-11-21 | 2020-04-14 | 中国航发沈阳黎明航空发动机有限责任公司 | Electromagnetic counterweight device for rotor of aircraft engine |
| CN112629840A (en) * | 2020-11-20 | 2021-04-09 | 韩清凯 | Aircraft engine double-rotor-support-casing tester and testing method thereof |
| CN113109054A (en) * | 2021-05-06 | 2021-07-13 | 中国航发湖南动力机械研究所 | Complete machine dynamics dual-rotor test bed for turboshaft engine |
| CN113899539A (en) * | 2021-09-30 | 2022-01-07 | 清华大学 | Dual-rotor bearing cartridge receiver experiment system |
| CN114136564A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Vibration testing system and method for rotor bearing pedestal of aircraft engine |
| CN115076246A (en) * | 2022-06-28 | 2022-09-20 | 陕西航空电气有限责任公司 | Shaft coupler capable of isolating axial vibration |
| CN115184004A (en) * | 2022-09-08 | 2022-10-14 | 北京宇航推进科技有限公司 | Aviation birotor test bench |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2248110A (en) * | 1990-09-19 | 1992-03-25 | Rolls Royce Plc | Vibration analysis system for a multi-shaft turbine |
| US20040249520A1 (en) * | 2003-05-30 | 2004-12-09 | Maine Scott T. | Vibration engine monitoring neural network object monitoring |
| CN201724799U (en) * | 2010-07-16 | 2011-01-26 | 东北大学 | Vibration tester for inner-outer rotor systems |
| CN103308313A (en) * | 2013-05-15 | 2013-09-18 | 天津大学 | Base-movable aeroengine dual-rotor system model experiment platform |
| CN103471854A (en) * | 2013-09-26 | 2013-12-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Aero-engine body vibration characteristic analysis method |
| CN103528824A (en) * | 2013-10-31 | 2014-01-22 | 华中科技大学 | Elastic foundation based internal and external dual-rotor fault simulation experiment table |
| CN204705483U (en) * | 2015-06-05 | 2015-10-14 | 湖南科技大学 | A kind of aeromotor birotor Research on Dynamic Characteristic experiment porch |
| CN204831793U (en) * | 2015-06-05 | 2015-12-02 | 湖南科技大学 | Whirlpool shaft generator dynamic characteristic studies experimental apparatus |
| CN205538223U (en) * | 2016-01-21 | 2016-08-31 | 苏州东菱振动试验仪器有限公司 | Multifactor coupling vibration control comprehensive experiment platform of aeroengine |
-
2016
- 2016-01-21 CN CN201610040169.9A patent/CN105571867B/en not_active Expired - Fee Related
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2248110A (en) * | 1990-09-19 | 1992-03-25 | Rolls Royce Plc | Vibration analysis system for a multi-shaft turbine |
| US20040249520A1 (en) * | 2003-05-30 | 2004-12-09 | Maine Scott T. | Vibration engine monitoring neural network object monitoring |
| CN201724799U (en) * | 2010-07-16 | 2011-01-26 | 东北大学 | Vibration tester for inner-outer rotor systems |
| CN103308313A (en) * | 2013-05-15 | 2013-09-18 | 天津大学 | Base-movable aeroengine dual-rotor system model experiment platform |
| CN103471854A (en) * | 2013-09-26 | 2013-12-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Aero-engine body vibration characteristic analysis method |
| CN103528824A (en) * | 2013-10-31 | 2014-01-22 | 华中科技大学 | Elastic foundation based internal and external dual-rotor fault simulation experiment table |
| CN204705483U (en) * | 2015-06-05 | 2015-10-14 | 湖南科技大学 | A kind of aeromotor birotor Research on Dynamic Characteristic experiment porch |
| CN204831793U (en) * | 2015-06-05 | 2015-12-02 | 湖南科技大学 | Whirlpool shaft generator dynamic characteristic studies experimental apparatus |
| CN205538223U (en) * | 2016-01-21 | 2016-08-31 | 苏州东菱振动试验仪器有限公司 | Multifactor coupling vibration control comprehensive experiment platform of aeroengine |
Non-Patent Citations (3)
| Title |
|---|
| 刘永泉等: "航空发动机整机振动控制技术分析", 《航空发动机》 * |
| 艾延廷等: "航空发动机整机振动分析与控制", 《沈阳航空航天大学学报》 * |
| 陈予恕等: "航空发动机整机动力学研究进展与展望", 《航空学报》 * |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106404412A (en) * | 2016-09-28 | 2017-02-15 | 中国航空工业集团公司北京航空精密机械研究所 | Device for measuring the eccentric position of the aero-engine bearing holder |
| CN106404412B (en) * | 2016-09-28 | 2019-04-30 | 中国航空工业集团公司北京航空精密机械研究所 | It is a kind of for measuring the device of Aero-engine Bearing seat center displacement |
| CN107727340B (en) * | 2017-08-18 | 2019-09-17 | 上海机电工程研究所 | The elastic vibration mode testing method of rotary missile |
| CN107727340A (en) * | 2017-08-18 | 2018-02-23 | 上海机电工程研究所 | The elastic vibration mode testing method of rotary missile |
| CN109406152B (en) * | 2018-12-13 | 2021-01-12 | 中国科学院工程热物理研究所 | Aeroengine counter-rotating dual-rotor dynamic characteristic experiment platform |
| CN109406152A (en) * | 2018-12-13 | 2019-03-01 | 中国科学院工程热物理研究所 | A kind of aero-engine is to turning birotor kinetic characteristics experiment porch |
| CN111005768A (en) * | 2019-11-21 | 2020-04-14 | 中国航发沈阳黎明航空发动机有限责任公司 | Electromagnetic counterweight device for rotor of aircraft engine |
| CN112629840A (en) * | 2020-11-20 | 2021-04-09 | 韩清凯 | Aircraft engine double-rotor-support-casing tester and testing method thereof |
| CN112629840B (en) * | 2020-11-20 | 2023-11-17 | 韩清凯 | Double-rotor-support-casing tester for aero-engine and testing method thereof |
| CN113109054A (en) * | 2021-05-06 | 2021-07-13 | 中国航发湖南动力机械研究所 | Complete machine dynamics dual-rotor test bed for turboshaft engine |
| CN113899539A (en) * | 2021-09-30 | 2022-01-07 | 清华大学 | Dual-rotor bearing cartridge receiver experiment system |
| CN113899539B (en) * | 2021-09-30 | 2023-01-20 | 清华大学 | Dual-rotor bearing cartridge receiver experiment system |
| CN114136564A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Vibration testing system and method for rotor bearing pedestal of aircraft engine |
| CN115076246A (en) * | 2022-06-28 | 2022-09-20 | 陕西航空电气有限责任公司 | Shaft coupler capable of isolating axial vibration |
| CN115184004A (en) * | 2022-09-08 | 2022-10-14 | 北京宇航推进科技有限公司 | Aviation birotor test bench |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105571867B (en) | 2018-10-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105571867A (en) | Vibration control experiment platform for aero-engine | |
| EP3034812B1 (en) | Torque sensor monitoring for gas turbine engine | |
| CN205538223U (en) | Multifactor coupling vibration control comprehensive experiment platform of aeroengine | |
| CN102459821B (en) | Device and method for detecting a fault in a low-pressure fuel pump of a turbojet and turbojet including one such device | |
| CN204705483U (en) | A kind of aeromotor birotor Research on Dynamic Characteristic experiment porch | |
| CN204831793U (en) | Whirlpool shaft generator dynamic characteristic studies experimental apparatus | |
| JP2002152862A (en) | Data collection unit for remote supervisory system, and remote supervisory method | |
| EP3473805B1 (en) | Gas turbine engine drive system health monitoring system and method | |
| CN102735326A (en) | Real-time on-line monitoring apparatus of blade vibration of flue gas turbine | |
| CN104329222A (en) | On-line state monitoring and fault diagnosis method integrated into master control system for wind turbines | |
| Rezaei et al. | Development of a turbojet engine gearbox test rig for prognostics and health management | |
| CN107792391B (en) | Helicopter torsional vibration excitation test method based on FADEC control system | |
| CN115371992A (en) | System and method for monitoring component failure in a gear train based system | |
| CN108507670A (en) | A kind of vibrations method for diagnosing faults for paint finishing | |
| CN203130170U (en) | Low-pressure rotor autorotation tool used for borescope inspection of engine of civil aircraft | |
| CN203965033U (en) | A kind of boom-type roadheader spindle vibration monitoring running state device | |
| CN109281805A (en) | A kind of measuring multiple parameters intelligent inspection system | |
| EP2009451A2 (en) | Synchronous signal generator for trim balancing of jet engine | |
| CN102589675A (en) | Method for measuring mechanical resonance frequency by using servo driver | |
| CN104236798B (en) | The one side diagram balance method of the pure test mass nyquist diagram of rotating machinery start and stop car | |
| EP2971651B1 (en) | Methods for operating a gas turbine engine | |
| Huang | Vibration Testing of a Certain Turbojet Engine Using the Power Spectrum Analysis. | |
| Sree et al. | Tone and Broadband Noise Separation from Acoustic Data of a Scale-Model Contra-Rotating Open Rotor | |
| CN204638338U (en) | Cement industry roll squeezer condition monitoring system | |
| CN108104947A (en) | The real-time watch device of marine low speed diesel engine torsional vibration damper operating status |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20181002 Termination date: 20200121 |