CN104061994A - Elastic supporting device vibration strain monitoring method - Google Patents
Elastic supporting device vibration strain monitoring method Download PDFInfo
- Publication number
- CN104061994A CN104061994A CN201410282663.7A CN201410282663A CN104061994A CN 104061994 A CN104061994 A CN 104061994A CN 201410282663 A CN201410282663 A CN 201410282663A CN 104061994 A CN104061994 A CN 104061994A
- Authority
- CN
- China
- Prior art keywords
- vibration
- vibration strain
- rotor
- monitoring method
- foil gauge
- 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.)
- Pending
Links
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses an elastic supporting device vibration strain monitoring method. A supporting body of an elastic supporting device comprises a bearing pedestal and a plurality of elastic cage strips which are distributed in the circumferential direction of the bearing pedestal, wherein one end of each elastic cage strip outwards extends in the radial direction of the supporting body to form an installation edge, and a gap is formed between the circumferential outer wall of the bearing pedestal and a machine box and filled with lubricating oil so as to form an extruded oil film damper. The method includes the steps that a strain gauge is attached to at least one elastic cage strip and connected to a vibration strain measuring instrument outside the machine box through a lead, and the vibration strain value of the strain gauge is detected through the vibration strain measuring instrument; whether the detected vibration strain value is larger than the preset vibration strain alarm threshold value or not is judged, and an alarm signal is generated if yes. By detecting the vibration strain value of the strain gauge, the vibration strain of the elastic supporting device is accurately detected, it is ensured that a journal of the bearing pedestal works within an extruded oil film linear area, an alarm is given once the vibration strain value exceeds the threshold value, and safe running performance of a rotor is improved.
Description
Technical field
The present invention relates to vibrate strain monitoring field, especially, relate to for status monitoring and the vibration fault of middle-size and small-size aviation turboshaft engine high speed rotor operation and know method for distinguishing.
Background technology
For a long time, in Aero-engine Development, be all to rely on casing, accelerometer to be installed or velograph obtains the vibration information that rotor is delivered to casing in the running.Specific practice is near the vertical and horizontal level sensor installation seat of mounting edge, rear fulcrum forward at engine, then is contained on sensor holder with M5 bolt degree of will speed up meter or velograph, the vibration monitoring of realization to engine.
The vibration monitoring of prior art to big-and-middle-sized, non-yielding prop and the aeroengine rotor of rotating speed below 18000r/min, these signals are perhaps enough.But to vibration monitoring middle-size and small-size, that rotor cage type elastic support device adds squeeze film damper sinking support and the aviation turboshaft engine rotor of rotating speed more than 3000r/min, it is not enough that these signals just seem, vibration monitoring when especially engine rotor exists vibration fault operation.The damping effect that adds squeeze film damper due to rotor cage type elastic support device is large, and casing vibration signal can not reflect the vibration information of high speed rotor-supporting system completely, has also mixed on the contrary casing local vibration information.Especially the vertical and horizontal level sensor installation seat by near mounting edge rear fulcrum at engine, from engine rotor rear fulcrum too away from, centre is across which floor Thin-Wall Outer Casing.Therefore, does is this point rotor oscillation? or Thin-Wall Outer Casing vibration? or mount pad vibration? sometimes be all difficult to distinguish.Therefore, casing vibration signal of the prior art can not reflect the vibration information of high speed rotor-supporting system completely, has also mixed on the contrary casing local vibration information, needs the monitoring method of a kind of vibration information that can precise monitoring rotor-supporting system of exploitation badly.
Summary of the invention
The object of the invention is to provide a kind of elastic bearing device vibration strain monitoring method, to solve existing casing vibration information, cannot accurately reflect that the vibration strain of elastic bearing device and the squeeze film damper of elastic bearing device can not be operated in the technical matters of oil film linear zone reliably.
For achieving the above object, the technical solution used in the present invention is as follows:
A kind of elastic bearing device vibration strain monitoring method, the supporting body of elastic bearing device comprises bearing seat and along many elasticity cage bars of the circumferential distribution of bearing seat, the end of many elasticity cage bars is along the formation mounting edge that extends radially outwardly of supporting body, between the outer circumferential walls of bearing seat and casing, form space, and in space, be full of lubricating oil to form squeeze film damper; This monitoring method comprises:
Bonding foil gauge at least one elasticity cage bar, foil gauge is connected to through lead-in wire the vibration strain gauge of being located at outside casing, detects the vibration strain value of foil gauge through vibration strain gauge;
Judgement detects the vibration strain value obtaining and whether is greater than default vibration strain alarm threshold value, if be greater than, generates alerting signal.
Further, vibration strain alarm threshold value pre-establishes according to the structural parameters of elastic bearing device, and the computing formula of the vibration strain value of foil gauge is as follows:
ε＝(k·3h·y)/l
2
In above formula, the vibration strain value that ε is foil gauge, k is calibration factor, and h is the thickness of the elasticity cage bar that foil gauge is corresponding, and 1 is the length of the elasticity cage bar that foil gauge is corresponding, the design amplitude amount that y is bearing seat, wherein, the span of k is 0.8～1.2; Vibration strain alarm threshold value is the vibration strain value of the foil gauge that obtains after each structural parameters of substitution.
Further, the step of setting calibration factor k is as follows:
The mounting edge of elasticity cage bar corresponding to foil gauge is fixed, and the bearing seat of excitation elastic bearing device circumferentially rocks around its axle center;
Detect the vibration strain value of foil gauge and the amplitude amount of bearing seat;
According to the computing formula of the vibration strain value of foil gauge, obtain calibration factor k.
Further, the span of design amplitude amount y is: y≤0.4c, wherein, the radial play that c is squeeze film.
Further, foil gauge is bonded in the root of close mounting edge on elasticity cage bar.
Further, monitoring method also comprises:
The vibration strain value that adopts dynamic signal analyzer to detect vibration strain gauge carries out real-time analysis and shows spectrogram corresponding to vibration strain value, to judge the fault of rotor operation.
Further, elastic bearing device is two, lays respectively at front bearing place and the rear bearing place of the rotor of aviation turboshaft engine, and monitoring method also comprises:
Adopt dynamic signal analyzer to receive the vibration strain value of front bearing place detection in real time with the first Chart of axes track of generation front bearing place axle journal;
Dynamic signal analyzer receives the vibration strain value of rear bearing place detection in real time to generate the second Chart of axes track of rear bearing place axle journal;
Dynamic signal analyzer generates dual signal Chart of axes track according to the first Chart of axes track and the second Chart of axes track matching, to judge the fault of rotor operation.
Further, the operation troubles of rotor comprises: rotor unbalance, rotor misalignment, rotor bearing gap be connected with bearing seat loosening, rotor and stator part touch rub, at least one in squeeze film whirling motion, internal rotor hydrops, rolling main bearing fault and gear vibration fault.
The present invention has following beneficial effect:
Elastic bearing device vibration strain monitoring method of the present invention, by bonding foil gauge on elasticity cage bar, detect the vibration strain value of foil gauge accurately to detect the vibration strain of elastic bearing device, avoided casing vibration signal to be disturbed the detection causing inaccurate, and vibration strain gauge can show the vibration strain value of resilient bearing device in real time, and man-machine interface is friendly; Further, by vibration strain value that detection is obtained and default vibration strain alarm threshold value comparison, to guarantee that the axle journal of bearing seat is operated in the squeeze film range of linearity, overflow and report to the police, thereby improve the safe running performance of rotor.
Except object described above, feature and advantage, the present invention also has other object, feature and advantage.Below with reference to figure, the present invention is further detailed explanation.
Accompanying drawing explanation
The accompanying drawing that forms the application's a part is used to provide a further understanding of the present invention, and schematic description and description of the present invention is used for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the steps flow chart schematic diagram of preferred embodiment of the present invention elastic bearing device vibration strain monitoring method;
Fig. 2 is the structural representation of preferred embodiment of the present invention elastic bearing device;
Fig. 3 is that Fig. 2 is along the diagrammatic cross-section of A-A.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are elaborated, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
The preferred embodiments of the present invention provide a kind of elastic bearing device vibration strain monitoring method, with reference to Fig. 2 and Fig. 3, in the embodiment of the present invention, the supporting body of elastic bearing device 1 comprises bearing seat 11 and along many elasticity cage bars 13 of the circumferential distribution of bearing seat 11, the end of many elasticity cage bars 13 forms mounting edge 15 along extending radially outwardly of supporting body, between the outer circumferential walls of bearing seat and casing 4, form space, and in space, be full of lubricating oil to form squeeze film damper 5; In the present embodiment, the oil film outer shroud of squeeze film damper 5 designs on casing 4, and in oil film, ring is the external cylindrical surface of bearing seat, and the radial play in oil film between ring and oil film outer shroud is pressed concentric design, and along circumferentially impartial.In the present embodiment, bearing seat 11 connects rotors 7 through ball bearing 6, the vibration strain of elastic bearing device 1 after testing, and the Vibration Condition so that rotor 7 is run up is monitored, and with reference to Fig. 1, the present embodiment monitoring method comprises:
Step 101, bonding foil gauge at least one elasticity cage bar, foil gauge is connected to through lead-in wire the vibration strain gauge of being located at outside casing, detects the vibration strain value of foil gauge through vibration strain gauge;
Step 102, judgement detects the vibration strain value obtaining and whether is greater than default vibration strain alarm threshold value, if be greater than, generates alerting signal.
With reference to Fig. 3, in the present embodiment, on a plurality of elasticity cage bars 13, be bonded with foil gauge 2, foil gauge 23 is connected to the vibration strain gauge of being located at outside casing through going between, the vibration strain value that detects in real time foil gauge 2 by vibration strain gauge, obtains the vibration strain of elastic bearing device.The present embodiment vibration strain gauge carries out the vibration strain value obtaining after analog to digital conversion, carries out numeral and shows, to facilitate user to obtain in real time the vibration state information of rotor by display interface.In the present embodiment, because rotor 7 and elastic bearing device 1 are all in hot environment, the lead-in wire that the vibratory output of foil gauge 2 is passed to vibration strain gauge is divided into two sections, comprise the resistance to 250 ℃ of first above lead-in wires that are connected with foil gauge 2, the first lead-in wire leads to outside casing through resistance to more than 800 ℃ second.
Preferably, in order to improve the vibration sensitivity of the elastic bearing device 1 of foil gauge 2 detections, foil gauge 2 is bonded in the root of close mounting edge 15 on elasticity cage bar 13.In the present embodiment, foil gauge 2 is bonded in the horizontal direction of elasticity cage bar 13 and vertical direction the root near mounting edge 15.
The present embodiment, by vibration strain gauge being detected to the vibration strain value obtaining, compare with vibration strain alarm threshold value, to judge whether the axle journal of elastic bearing device is operated in the linear zone of squeeze film, because squeeze film damper 5 is mainly used in reducing the vibration of rotor itself and passes through the vibration of elastic bearing device 1 unofficial biography, therefore whether axle journal is operated in squeeze film linear zone, be related to the reliable and stable operation of rotor 7.The present embodiment, by reporting to the police to the amplitude of axle journal is excessive, has improved the security performance of rotor 7 operations.
In the present embodiment, vibration strain alarm threshold value pre-establishes according to the structural parameters of elastic bearing device 1, and the computing formula of the vibration strain value of foil gauge 2 is as follows:
ε＝(k·3h·y)/l
2
In above formula, ε is the vibration strain value of foil gauge, k is calibration factor, and h is the thickness of the elasticity cage bar that foil gauge is corresponding, and 1 is the length of the elasticity cage bar that foil gauge is corresponding, y is the design amplitude amount of bearing seat, be bearing seat around the design flow that rocks radius in its axle center, when bearing seat around its axle center to rock radius excessive, cause axle journal not to be operated in squeeze film linear zone, wherein, the span of k is 0.8～1.2; Vibration strain alarm threshold value is the vibration strain value of the foil gauge that obtains after each structural parameters of substitution.In the present embodiment, the calibration factor k=1.05 of elasticity cage bar, h=2.8mm, 1=28.5mm, y=0.032mm, according to formula, can vibrate strain alarming value is ε=348 μ ε.Vibration strain gauge often adopts 1mV/ μ ε output, and now exporting peak value is the alternating voltage signal of 348mV.If zoom into 2 times, adopt 2mV/ μ ε output, exporting at that time peak value is the alternating voltage signal of 696mV.
In the present embodiment, the step of setting calibration factor k is as follows:
The mounting edge of elasticity cage bar corresponding to foil gauge is fixed, and the bearing seat of excitation elastic bearing device circumferentially rocks around its axle center, in the present embodiment, adopts vibrator vibrating shaft bearing to rock around axle center;
Detect the vibration strain value of foil gauge and the amplitude amount of bearing seat;
According to the computing formula of the vibration strain value of foil gauge, obtain calibration factor k, by the vibration strain value, amplitude amount, h, 1 substitution ε=(the k3hy)/l that detect
2, can obtain calibration factor k.
In the present embodiment, the span of design amplitude amount y is: y≤0.4c, wherein, the radial play that c is squeeze film.
Preferably, also the running status of rotor and vibration fault are monitored, in the present embodiment, the vibration strain value that adopts dynamic signal analyzer to detect vibration strain gauge carries out real-time analysis and shows spectrogram corresponding to vibration strain value, to judge the fault of rotor operation.The working temperature of Small Aeroengine is high, rotor speed is high, fault mainly occurs in rotor-bearing system, and its modal vibration fault at least comprises: rotor unbalance, rotor misalignment, rotor bearing gap be connected with bearing seat loosening, rotor and stator part touch rub, squeeze film whirling motion, internal rotor hydrops, rolling main bearing fault, gear vibration fault etc.The present embodiment adopts the process of spectrogram monitoring fault as follows:
Rotor unbalance causes: within the scope of working speed, vibration amplitude increases with rotating speed and increases, and with rotating speed, reduces and reduces; Those skilled in the art are significantly higher than its frequency division by the fundamental frequency peak value on rumble spectrum figure and frequency multiplication peak value is judged rotor unbalance fault.
Rotor misalignment causes: rotor axial vibration increases and is greater than 0.5 times of radial vibration value; Those skilled in the art by rumble spectrum figure, occur rotating speed two frequencys multiplication even frequency tripling spectrum peak to judge rotor misalignment fault.
Rotor bearing gap is connected loosening causing with bearing seat: vibration mostly occur radially and vibration phase is unchanged, during rotating speed increase and decrease, uprushing appears in vibration amplitude, anticlimax phenomenon; Those skilled in the art still have the appearance such as frequency division and frequency multiplication to judge this fault except rotating speed fundamental frequency by the spectral peak in rumble spectrum.
Rotor and stator part touch to rub and cause: vibratory response there will be rotating speed fundamental frequency 1/2,1/3 ..., the vibration component such as 1/n, 2/n, 3/n; Vibration in time and touch and rub contact area size and change, is touched vibratory response amplitude while rubbing to increase severely, and be there will be rotor natural frequencies spectrum peak; Those skilled in the art judge this fault by there is rotor natural frequencies spectrum peak.
Squeeze film whirling motion causes: (0.40～0.49) times rotating speed fundamental vibration, those skilled in the art judge this fault by there is (0.40～0.49) times rotating speed fundamental vibration.
Internal rotor hydrops causes: 0.5 times of rotating speed fundamental vibration, there will be rotor natural frequencies spectrum peak after unstability.Those skilled in the art judge this fault by there is rotor natural frequencies spectrum peak.
Rolling main bearing fault causes: on bearing seat, vibration frequency is abundanter, as the rolling body of known certain bearing is counted z=15, rolling body diameter d=6mm, bearing pitch diameter D=56mm, contact angle α=30 °, rotating shaft gyro frequency f
0=750Hz, its bearing inner ring runway localized delamination causes 8.2f
0vibration, the 6.8f that outer race runway localized delamination causes
0vibration, bearing roller localized delamination causes 4.6f
0vibration.Those skilled in the art's analysis spectrum figure can judge this fault.
Gear vibration fault causes: during gear operation, because engagement is with greater impact, in vibration frequency-region signal, except speed-frequency, meshing frequency, also have centered by meshing frequency, take the symmetrical side frequency that axle rotating speed fundamental frequency or frequency multiplication be sideband; The gear of local anomaly, except meshing frequency, also has axle rotating speed fundamental frequency or its two frequency multiplication and frequency tripling composition in its frequency spectrum; The gear of tooth surface abrasion, contains meshing frequency and two frequencys multiplication and frequency tripling composition in its frequency spectrum; Along with the variation of kinematic error and the variation of gear rigidity, in spectrogram, presenting symmetrical sideband increases severely, the interval of sideband is relevant with source of trouble frequency, and the amplitude of sideband is relevant with fault degree (E), and those skilled in the art can judge this fault by analysis spectrum figure.
Preferably, the present embodiment monitoring method is for the vibration monitoring of the rotor of aviation turboshaft engine, and elastic bearing device is two, lays respectively at front bearing place and the rear bearing place of the rotor of aviation turboshaft engine, and this monitoring method also comprises:
Adopt dynamic signal analyzer to receive the vibration strain value of front bearing place detection in real time with the first Chart of axes track of generation front bearing place axle journal;
Dynamic signal analyzer receives the vibration strain value of rear bearing place detection in real time to generate the second Chart of axes track of rear bearing place axle journal;
Dynamic signal analyzer generates dual signal Chart of axes track according to the first Chart of axes track and the second Chart of axes track matching, to judge the fault of rotor operation.
The process that employing dual signal Chart of axes track carries out fault verification is as follows:
Rotor unbalance causes: within the scope of working speed, vibration amplitude increases with rotating speed and increases, and with rotating speed, reduces and reduces; Chart of axes track is oval.
Rotor misalignment causes: rotor axial vibration increases and is greater than 0.5 times of radial vibration value; Chart of axes track is variation triangle.
Rotor bearing gap is connected loosening causing with bearing seat: vibration mostly occur radially and vibration phase unchanged; During rotating speed increase and decrease, uprushing appears in vibration amplitude, anticlimax phenomenon; Chart of axes track is trilobal.
Rotor and stator part touch to rub and cause: vibratory response there will be rotating speed fundamental frequency 1/2,1/3 ..., the vibration component such as 1/n, 2/n, 3/n; Vibration in time and touch and rub contact area size and change, touches vibratory response amplitude while rubbing to increase severely, and Chart of axes track is more random figure.
In the present embodiment, preferably, monitoring method adopts dynamic signal analyzer to generate spectrogram to vibration strain value, and matching generation dual signal Chart of axes track, to strengthen the monitoring to the running status of rotor and vibration fault.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (8)
1. an elastic bearing device vibrates strain monitoring method, it is characterized in that, the supporting body of described elastic bearing device comprises bearing seat and along many elasticity cage bars of the circumferential distribution of described bearing seat, the end of described many elasticity cage bars is along the formation mounting edge that extends radially outwardly of described supporting body, between the outer circumferential walls of described bearing seat and casing, form space, and in described space, be full of lubricating oil to form squeeze film damper; This monitoring method comprises:
Bonding foil gauge on elasticity cage bar described at least one, described foil gauge is connected to through lead-in wire the vibration strain gauge of being located at outside described casing, detects the vibration strain value of described foil gauge through described vibration strain gauge;
Judgement detects the described vibration strain value obtaining and whether is greater than default vibration strain alarm threshold value, if be greater than, generates alerting signal.
2. elastic bearing device vibration strain monitoring method according to claim 1, is characterized in that,
Described vibration strain alarm threshold value pre-establishes according to the structural parameters of described elastic bearing device, and the computing formula of the vibration strain value of described foil gauge is as follows:
ε＝(k·3h·y)/l
2
In above formula, the vibration strain value that ε is described foil gauge, k is calibration factor, h is the thickness of the elasticity cage bar that described foil gauge is corresponding, and 1 is the length of the elasticity cage bar that described foil gauge is corresponding, the design amplitude amount that y is described bearing seat, wherein, the span of k is 0.8～1.2; Described vibration strain alarm threshold value is the vibration strain value of the described foil gauge that obtains after each structural parameters of substitution.
3. elastic bearing device vibration strain monitoring method according to claim 2, is characterized in that,
The step of setting described calibration factor k is as follows:
The mounting edge of described elasticity cage bar corresponding to described foil gauge is fixed, encouraged the bearing seat of described elastic bearing device circumferentially to rock around its axle center;
Detect the amplitude amount of vibration strain value and the described bearing seat of described foil gauge;
According to the computing formula of the vibration strain value of described foil gauge, obtain described calibration factor k.
4. elastic bearing device vibration strain monitoring method according to claim 3, is characterized in that,
The span of described design amplitude amount y is: y≤0.4c, wherein, the radial play that c is squeeze film.
5. elastic bearing device vibration strain monitoring method according to claim 4, is characterized in that,
Described foil gauge is bonded in the root of close described mounting edge on described elasticity cage bar.
6. elastic bearing device vibration strain monitoring method according to claim 5, is characterized in that, described monitoring method also comprises:
The vibration strain value that adopts dynamic signal analyzer to detect described vibration strain gauge carries out real-time analysis and shows spectrogram corresponding to described vibration strain value, to judge the fault of rotor operation.
7. elastic bearing device vibration strain monitoring method according to claim 6, is characterized in that,
Described elastic bearing device is two, lays respectively at front bearing place and the rear bearing place of the rotor of aviation turboshaft engine, and described monitoring method also comprises:
Adopt dynamic signal analyzer to receive the real-time described vibration strain value detecting in described front bearing place to generate the first Chart of axes track of described front bearing place axle journal;
Described dynamic signal analyzer receives the described vibration strain value of described rear bearing place detection in real time to generate the second Chart of axes track of described rear bearing place axle journal;
Described dynamic signal analyzer generates dual signal Chart of axes track according to described the first Chart of axes track and described the second Chart of axes track matching, to judge the fault of rotor operation.
8. elastic bearing device vibration strain monitoring method according to claim 7, is characterized in that,
The operation troubles of described rotor comprises: rotor unbalance, rotor misalignment, rotor bearing gap be connected with bearing seat loosening, rotor and stator part touch rub, at least one in squeeze film whirling motion, internal rotor hydrops, rolling main bearing fault and gear vibration fault.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410282663.7A CN104061994A (en) | 2014-06-23 | 2014-06-23 | Elastic supporting device vibration strain monitoring method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410282663.7A CN104061994A (en) | 2014-06-23 | 2014-06-23 | Elastic supporting device vibration strain monitoring method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104061994A true CN104061994A (en) | 2014-09-24 |
Family
ID=51549817
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410282663.7A Pending CN104061994A (en) | 2014-06-23 | 2014-06-23 | Elastic supporting device vibration strain monitoring method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104061994A (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105526304A (en) * | 2015-12-02 | 2016-04-27 | 西北工业大学 | Elastic support dry-friction damper with intelligent structure |
| CN105547534A (en) * | 2015-12-03 | 2016-05-04 | 中国航空动力机械研究所 | Elastic support capable of measuring axial load of rotor |
| CN105738057A (en) * | 2016-02-24 | 2016-07-06 | 中国航空动力机械研究所 | Mouse cage elastic supporting device vibration strain and amplitude calibration system and method |
| CN105889317A (en) * | 2016-04-22 | 2016-08-24 | 西北工业大学 | Supporting structure used for measuring parameter influence characteristics of extrusion oil film damper |
| CN106907355A (en) * | 2017-04-28 | 2017-06-30 | 中国航发湖南动力机械研究所 | A kind of elastic bearing squeeze film damper |
| CN108007692A (en) * | 2017-12-28 | 2018-05-08 | 湖南科技大学 | It is a kind of for turboshaft engine birotor experimental bench can dissection type supporting structure |
| CN110333060A (en) * | 2019-08-08 | 2019-10-15 | 中国船舶重工集团公司第七0三研究所 | A kind of oscillation of rotary machine rotor wireless measuring system based on piezoelectric self-power supplied |
| CN110657930A (en) * | 2018-06-29 | 2020-01-07 | 中国航发商用航空发动机有限责任公司 | Method and system for measuring vibration stress of part |
| CN110855085A (en) * | 2019-12-07 | 2020-02-28 | 湘潭华联电机有限公司 | High-speed motor with rotor fault detection device |
| CN111006830A (en) * | 2019-11-11 | 2020-04-14 | 东北大学 | Mouse cage type vibrating plate coupled particle bed experimental device and experimental method |
| CN111608749A (en) * | 2020-05-29 | 2020-09-01 | 中国航发湖南动力机械研究所 | Radial rigidity adjusting device and method for squirrel cage elastic support device and aero-engine |
| CN113188704A (en) * | 2021-04-30 | 2021-07-30 | 中国航发湖南动力机械研究所 | Method and device for testing axial force of squirrel-cage elastic support, electronic equipment and medium |
| CN113758697A (en) * | 2021-09-22 | 2021-12-07 | 哈尔滨工业大学 | Recognition method for dynamics coefficient of squeeze film damper |
| CN114856711A (en) * | 2022-05-12 | 2022-08-05 | 湖南科技大学 | Method and system for controlling vibration of rotor of turboshaft engine |
| CN115270896A (en) * | 2022-09-28 | 2022-11-01 | 西华大学 | Intelligent diagnosis method for identifying loosening fault of main bearing of aircraft engine |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102425639A (en) * | 2011-11-30 | 2012-04-25 | 中国航空动力机械研究所 | Elastic supporting structure |
| CN103698118A (en) * | 2013-12-14 | 2014-04-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Fatigue testing equipment for rotary micro radial displacement loading |
-
2014
- 2014-06-23 CN CN201410282663.7A patent/CN104061994A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102425639A (en) * | 2011-11-30 | 2012-04-25 | 中国航空动力机械研究所 | Elastic supporting structure |
| CN103698118A (en) * | 2013-12-14 | 2014-04-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Fatigue testing equipment for rotary micro radial displacement loading |
Non-Patent Citations (1)
| Title |
|---|
| 雷沬枝: "基于弹性支承动应力测量的转子系统故障诊断方法", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》, no. 72013, 15 July 2013 (2013-07-15) * |
Cited By (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105526304A (en) * | 2015-12-02 | 2016-04-27 | 西北工业大学 | Elastic support dry-friction damper with intelligent structure |
| CN105547534A (en) * | 2015-12-03 | 2016-05-04 | 中国航空动力机械研究所 | Elastic support capable of measuring axial load of rotor |
| CN105738057A (en) * | 2016-02-24 | 2016-07-06 | 中国航空动力机械研究所 | Mouse cage elastic supporting device vibration strain and amplitude calibration system and method |
| CN105738057B (en) * | 2016-02-24 | 2019-01-22 | 中国航空动力机械研究所 | Mouse cage elastic bearing device vibration strains and amplitude calibration system and method |
| CN105889317A (en) * | 2016-04-22 | 2016-08-24 | 西北工业大学 | Supporting structure used for measuring parameter influence characteristics of extrusion oil film damper |
| CN105889317B (en) * | 2016-04-22 | 2018-03-27 | 西北工业大学 | For determining the supporting structure of squeeze film damper parameter influencing characterisitic |
| CN106907355B (en) * | 2017-04-28 | 2019-03-05 | 中国航发湖南动力机械研究所 | A kind of elastic bearing squeeze film damper |
| CN106907355A (en) * | 2017-04-28 | 2017-06-30 | 中国航发湖南动力机械研究所 | A kind of elastic bearing squeeze film damper |
| CN108007692A (en) * | 2017-12-28 | 2018-05-08 | 湖南科技大学 | It is a kind of for turboshaft engine birotor experimental bench can dissection type supporting structure |
| CN108007692B (en) * | 2017-12-28 | 2023-11-10 | 湖南科技大学 | Split type supporting structure for double-rotor experiment table of turboshaft engine |
| CN110657930A (en) * | 2018-06-29 | 2020-01-07 | 中国航发商用航空发动机有限责任公司 | Method and system for measuring vibration stress of part |
| CN110333060A (en) * | 2019-08-08 | 2019-10-15 | 中国船舶重工集团公司第七0三研究所 | A kind of oscillation of rotary machine rotor wireless measuring system based on piezoelectric self-power supplied |
| CN110333060B (en) * | 2019-08-08 | 2024-05-24 | 中国船舶重工集团公司第七0三研究所 | Rotary machinery rotor vibration wireless measurement system based on piezoelectric self-energy supply |
| CN111006830A (en) * | 2019-11-11 | 2020-04-14 | 东北大学 | Mouse cage type vibrating plate coupled particle bed experimental device and experimental method |
| CN111006830B (en) * | 2019-11-11 | 2021-08-17 | 东北大学 | Mouse cage type vibrating plate coupled particle bed experimental device and experimental method |
| CN110855085A (en) * | 2019-12-07 | 2020-02-28 | 湘潭华联电机有限公司 | High-speed motor with rotor fault detection device |
| CN111608749B (en) * | 2020-05-29 | 2022-07-26 | 中国航发湖南动力机械研究所 | Radial rigidity adjusting device and method for squirrel-cage elastic support device and aero-engine |
| CN111608749A (en) * | 2020-05-29 | 2020-09-01 | 中国航发湖南动力机械研究所 | Radial rigidity adjusting device and method for squirrel cage elastic support device and aero-engine |
| CN113188704A (en) * | 2021-04-30 | 2021-07-30 | 中国航发湖南动力机械研究所 | Method and device for testing axial force of squirrel-cage elastic support, electronic equipment and medium |
| CN113188704B (en) * | 2021-04-30 | 2022-07-22 | 中国航发湖南动力机械研究所 | Method and device for testing axial force of squirrel-cage elastic support, electronic equipment and medium |
| CN113758697A (en) * | 2021-09-22 | 2021-12-07 | 哈尔滨工业大学 | Recognition method for dynamics coefficient of squeeze film damper |
| CN113758697B (en) * | 2021-09-22 | 2024-03-08 | 哈尔滨工业大学 | Identification method for dynamic coefficient of extrusion oil film damper |
| CN114856711A (en) * | 2022-05-12 | 2022-08-05 | 湖南科技大学 | Method and system for controlling vibration of rotor of turboshaft engine |
| CN114856711B (en) * | 2022-05-12 | 2023-09-15 | 湖南科技大学 | Method and system for controlling rotor vibration of turboshaft engine |
| CN115270896A (en) * | 2022-09-28 | 2022-11-01 | 西华大学 | Intelligent diagnosis method for identifying loosening fault of main bearing of aircraft engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104061994A (en) | Elastic supporting device vibration strain monitoring method | |
| RU2449252C2 (en) | Detection method of damage to support rolling bearing of engine | |
| US4955269A (en) | Turbine blade fatigue monitor | |
| Saruhan et al. | Vibration analysis of rolling element bearings defects | |
| CN103048132A (en) | Methods and systems for automatic rolling-element bearing fault detection | |
| US9574965B2 (en) | System and method of determining bearing health in a rotating machine | |
| US20120330578A1 (en) | Severity analysis apparatus and method for shafts of rotating machinery | |
| JP2824523B2 (en) | Method and apparatus for measuring fatigue of vibrating member | |
| CN106568565A (en) | Rotating machine vibration on-line monitoring device and rotating machine vibration on-line monitoring method | |
| JP2013096989A (en) | Systems and methods for use in monitoring operation of rotating component | |
| CN104111154B (en) | Vibration trend analysis method and vibration trend analysis system of wind generating set | |
| CN104154989B (en) | The vibration monitoring method of unstable state slewing and vibration monitor system | |
| CN105547462A (en) | Radial vibration measuring method of engine rotor | |
| CN105899928B (en) | Detection of fretting and/or scuffing with false indentation potential | |
| JP2015010525A (en) | Method and apparatus for monitoring turbine blade state | |
| CN207515897U (en) | A kind of coal mining machine electricity operation vibration monitoring equipment | |
| CN104330214A (en) | Simple field dynamic balancing method | |
| CN106092567A (en) | Rotating machinery fault Vibration Synchronization measuring method | |
| CN206374361U (en) | Printing machine accident warning device | |
| Wang et al. | Intelligent condition monitoring of rotating machinery through electrostatic sensing and signal analysis | |
| CN209214914U (en) | Rotating machinery bearing chamber vibrates examination value calibration facility | |
| RU2411466C1 (en) | Method of detecting resonance oscillations of turbo-machine rotor blades | |
| CN103867475A (en) | Method for detecting on-line running state of dual-rotor axial flow fan | |
| CN108571590A (en) | Mechanically-sealing apparatus | |
| US11906956B2 (en) | Monitoring device and monitoring method for detecting a diagnostic state |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20140924 |
|
| RJ01 | Rejection of invention patent application after publication |