CN114136564A - Vibration testing system and method for rotor bearing pedestal of aircraft engine - Google Patents
Vibration testing system and method for rotor bearing pedestal of aircraft engine Download PDFInfo
- Publication number
- CN114136564A CN114136564A CN202111222179.1A CN202111222179A CN114136564A CN 114136564 A CN114136564 A CN 114136564A CN 202111222179 A CN202111222179 A CN 202111222179A CN 114136564 A CN114136564 A CN 114136564A
- Authority
- CN
- China
- Prior art keywords
- vibration
- bearing
- casing
- bearing seat
- aircraft engine
- 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
Images
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
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/025—Measuring arrangements
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/04—Bearings
- G01M13/045—Acoustic or vibration analysis
Abstract
The invention discloses a vibration testing system and a vibration testing method for an aircraft engine rotor bearing seat. Firstly, a test system for obtaining the vibration transmission relation of a bearing case is built, and the test system simulates the installation boundary condition of the bearing case of the aircraft engine; and then arranging vibration sensors at the mounting edge of the casing and the position of the bearing seat, testing and acquiring the vibration transmission relation between the bearing casing bearing seat and the mounting position of the casing vibration sensor, and finally reversely deducing the vibration condition of the bearing seat through a vibration signal of the test casing vibration sensor during the whole machine test so as to achieve the purpose of monitoring the vibration intensity of the rotor.
Description
Technical Field
The invention belongs to the technical field of aero-engine part tests, and particularly relates to a vibration test system and a vibration test method for an aero-engine rotor bearing seat.
Background
Rotary machines such as aeroengines, steam turbines, compressors, fans, water pumps and the like are widely applied and play an important role in the fields of national defense, energy, electric power, traffic, chemical engineering and the like. The rotor system is an important component of a rotating machine, and the dynamic characteristics of the rotor system determine the working performance and the structural safety of the rotating machine. The bearing seat of the rotor of the aircraft engine is arranged on the bearing casing, and a plurality of fault factors can cause severe vibration of the bearing seat of the rotor of the aircraft engine.
Therefore, it is desirable to provide a monitoring system that can monitor rotor vibration.
Disclosure of Invention
In order to solve the above problems, to ensure the safe operation of the rotor and reduce the test risk, the detection of the rotor vibration is usually implemented by detecting the vibration condition at the rotor mounting seat.
The invention aims to provide a vibration testing system for a bearing seat of an aircraft engine rotor, which comprises:
the excitation subsystem is used for applying dynamic load to the bearing casing;
the boundary condition simulation subsystem is used for simulating the rigidity boundary condition of the bearing case;
and the vibration testing subsystem is used for testing the bearing casing vibration signal.
The vibration testing system of the bearing seat of the rotor of the aircraft engine provided by the invention is also characterized in that the excitation subsystem comprises:
the vibration exciter is used for providing a dynamic excitation signal;
and the connecting rod transmits the dynamic excitation signal provided by the vibration exciter to the bearing seat.
The vibration testing system of the bearing seat of the rotor of the aircraft engine is also characterized in that the casing boundary condition simulation subsystem comprises a simulation bearing casing mounting edge and a simulation bearing seat mounting edge, and the simulation bearing casing mounting edge is provided with a casing adapter section for connecting the casing mounting edge and a fixed base; the simulation bearing block mounting edge comprises a squirrel cage structure used for connecting the bearing block and the fixed base.
The vibration testing system of the bearing seat of the rotor of the aircraft engine is also characterized in that the rigidity of the switching section of the casing is the same as that of the mounting edge of the casing, and the rigidity of the squirrel cage structure is the same as that of the mounting edge of the bearing seat.
The vibration testing system for the bearing seat of the aircraft engine rotor is further characterized in that the vibration testing subsystem comprises a plurality of vibration sensors and a data acquisition system for acquiring signals of the vibration sensors.
The vibration testing system of the bearing seat of the aircraft engine rotor is also characterized in that the plurality of vibration sensors are respectively arranged on the bearing case bearing seat and the case, and the plurality of vibration sensors are uniformly arranged on the bearing case bearing seat and the case.
The vibration testing system of the bearing seat of the aircraft engine rotor is further characterized in that the vibration sensor comprises one of an acceleration sensor, a speed sensor and a displacement sensor.
The vibration testing system of the bearing seat of the rotor of the aircraft engine is further characterized in that the testing system can also be used for testing the rigidity response of a bearing case under different frequencies, and at the moment, the excitation subsystem further comprises a dynamic force sensor which is connected with a vibration exciter and used for acquiring the dynamic force of the vibration exciter.
Another object of the present invention is to provide a vibration testing method for an aircraft engine rotor bearing block as defined in any one of the above, the method comprising the steps of:
s1: constructing a vibration testing system of an aeroengine rotor bearing seat in a component testing environment;
s2: arranging vibration sensors on the bearing case bearing seat and the case;
s3: utilizing a vibration exciter to carry out dynamic excitation on a bearing case bearing seat, and respectively acquiring signals of the bearing case bearing seat and vibration sensors arranged on a case under the condition of different dynamic excitation parameters;
s4: processing data acquired by different sensors in S3 to obtain a vibration transfer relation;
s5: during the whole machine test, the vibration data of the casing is collected, and the vibration condition of the bearing casing bearing seat is obtained according to the vibration transmission relation.
The vibration testing method of the bearing seat of the rotor of the aircraft engine, provided by the invention, is further characterized in that in S3, the vibration exciter dynamically excites the bearing box bearing seat in the direction of arranging the vibration sensor, and the excitation frequency of the dynamic excitation is 20Hz-2000 Hz.
The vibration testing method of the bearing seat of the rotor of the aircraft engine provided by the invention is also characterized in that the data processing method in the S4 is as follows:
if the input of the test is vibration data a at the bearing seat0(omega) and the output is vibration data a on the casing1(omega) to obtain the vibration transfer function between the excitation point and the response point of the bearing case
Wherein a in the transfer function0、a1Is the response corresponding to the excitation frequency omega in each measurement point.
Compared with the prior art, the invention has the following beneficial effects
According to the vibration testing system for the rotor bearing seat of the aircraft engine, provided by the invention, the vibration transmission relation between the bearing case bearing seat and the mounting position of the case vibration sensor is obtained by simulating the mounting boundary condition of the bearing case of the aircraft engine, and then the vibration condition of the bearing seat is obtained by reversely deducing the vibration signal of the test case vibration sensor during the whole machine test, so that the purpose of monitoring the vibration intensity of the rotor is achieved.
Description of the drawings:
in order to more clearly illustrate the technical solution of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a vibration testing system of an aircraft engine rotor bearing seat according to an embodiment of the invention.
Detailed Description
In order to make the technical means, the creation features, the achievement purposes and the effects of the invention easy to understand, the following embodiments are specifically described in the test system provided by the invention with reference to the attached drawings.
In the description of the embodiments of the present invention, it should be understood that the terms "central", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only used for convenience in describing and simplifying the description of the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified. The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
The embodiment of the invention provides a vibration testing system of an aircraft engine rotor bearing seat, which comprises:
the excitation subsystem is used for applying dynamic load to the bearing casing;
the boundary condition simulation subsystem is used for simulating the rigidity boundary condition of the bearing case;
and the vibration testing subsystem is used for testing the bearing casing vibration signal.
In some embodiments, the excitation subsystem comprises: the vibration exciter 8 is used for providing a dynamic excitation signal; and the connecting rod 4 is used for transmitting the dynamic excitation signal provided by the vibration exciter 8 to the bearing seat. The vibration exciter 8 is used for dynamically exciting the bearing seat 7 to simulate the scraping of the bearing seat when the rotor rotates.
In some embodiments, the casing boundary condition simulation subsystem comprises a simulated bearing casing mounting edge 5 and a simulated bearing seat mounting edge 2, wherein the simulated bearing casing mounting edge 5 is provided with a casing adapter section for connecting the casing mounting edge and a fixed base; the simulation bearing block mounting edge 2 comprises a squirrel cage structure for connecting the bearing block 7 and the fixed base. The rigidity of the casing switching section is the same as that of the casing mounting edge, so that the casing mounting edge of the bearing casing has the same connection rigidity in the whole machine test; the rigidity of the squirrel cage structure is the same as that of the bearing seat mounting edge, so that the bearing seat mounting edge has the same connection rigidity during the whole machine test during the part test.
In some embodiments, the vibration testing subsystem includes a plurality of vibration sensors and a data acquisition system for acquiring vibration sensor signals. The vibration sensor signal includes vibration acceleration information, vibration velocity information, and vibration displacement information.
In some embodiments, the plurality of vibration sensors are respectively arranged on the bearing casing bearing seat and the casing, and the plurality of vibration sensors are uniformly arranged on the bearing casing bearing seat and the casing.
In some embodiments, 4 vibration sensors are respectively arranged on the bearing seat and the casing of the force bearing casing, the 0-degree direction vibration sensor 9 is respectively arranged in the direction with the included angle of 0 degrees with the horizontal plane, the 90-degree direction vibration sensor 6 is arranged in the direction with the included angle of 90 degrees with the horizontal plane, the 180-degree direction vibration sensor 3 is arranged in the direction with the included angle of 180 degrees with the horizontal plane, and the 270-degree direction vibration sensor 1 is arranged in the direction with the included angle of 270 degrees with the horizontal plane, in the using process, the vibration exciter 8 is respectively used for exciting the four directions of the bearing seat, and vibration signals on all positions are collected simultaneously. The vibration output of the vibration exciter 8 is controlled by vibration displacement, rapid sinusoidal scanning within the range of 20Hz to 2000Hz is carried out by respectively adopting different vibration excitation intensities, and corresponding data are recorded.
In some embodiments, the vibration sensor comprises one of an acceleration sensor, a velocity sensor, and a displacement sensor.
In some embodiments, the test system may also be used to test the stiffness response of the force-bearing case at different frequencies, and in this case, the excitation subsystem further includes a dynamic force sensor 10 connected to the vibration exciter and configured to obtain the dynamic force of the vibration exciter. The rigidity response test method of the bearing case under different frequencies is that the dynamic force at the bearing seat of the bearing case is divided by the displacement response of the load action point. The vibration exciter is used for exciting the bearing seat, a bearing case rigidity response test is carried out, dynamic force at the bearing seat is obtained through the dynamic force sensor 10, a displacement sensor is additionally arranged at the bearing seat of the case, and displacement at the bearing seat can be obtained through the displacement sensor at the outer ring of the bearing seat or obtained through acceleration quadratic integral conversion measured by the acceleration sensor.
In some embodiments, a method for vibration testing of an aircraft engine rotor bearing housing is provided, the method comprising the steps of:
s1: constructing a vibration testing system of an aeroengine rotor bearing seat in a component testing environment;
s2: arranging vibration sensors on the bearing case bearing seat and the case;
s3: utilizing a vibration exciter to carry out dynamic excitation on a bearing case bearing seat, and respectively acquiring signals of the bearing case bearing seat and vibration sensors arranged on a case under the condition of different dynamic excitation parameters;
s4: processing data acquired by different sensors in S3 to obtain a vibration transfer relation;
s5: during the whole machine test, the vibration data of the casing is collected, the vibration condition of the bearing casing bearing seat is obtained according to the vibration transmission relation, namely the vibration transmission relation between the bearing casing bearing seat and the casing mounting edge obtained during the part test, and the vibration magnitude at the bearing seat is directly reversely pushed by combining the vibration value of the casing mounting edge monitored during the whole machine test, so that the monitoring of the rotor vibration during the whole machine test is realized.
In some embodiments, in S3, the vibration exciter dynamically excites the bearing casing bearing seat in the direction in which the vibration sensor is disposed, and the excitation frequency of the dynamic excitation is 20Hz to 2000 Hz.
In some embodiments, the data processing method in S4 is as follows:
if the input of the test is vibration data a _0 (omega) at a bearing seat and the output is vibration data a _1 (omega) on the casing, the vibration transfer function H (omega) between the excitation point and the response point of the bearing casing is (a _1 (omega))/(a _0 (omega)),
wherein a _0 and a _1 in the transfer function are responses to the excitation frequency ω at each station.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are also included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (11)
1. A vibration testing system for an aircraft engine rotor bearing housing, the system comprising:
the excitation subsystem is used for applying dynamic load to the bearing casing;
the boundary condition simulation subsystem is used for simulating the rigidity boundary condition of the bearing case;
and the vibration testing subsystem is used for testing the bearing casing vibration signal.
2. The vibration testing system of an aircraft engine rotor bearing mount of claim 1, wherein the excitation subsystem comprises:
the vibration exciter is used for providing a dynamic excitation signal;
and the connecting rod transmits the dynamic excitation signal provided by the vibration exciter to the bearing seat.
3. The vibration testing system of the bearing seat of the aircraft engine rotor according to claim 1, wherein the casing boundary condition simulation subsystem comprises a simulated bearing casing mounting edge and a simulated bearing seat mounting edge, and the simulated bearing casing mounting edge is provided with a casing adapter section for connecting the casing mounting edge and the fixed base; the simulation bearing block mounting edge comprises a squirrel cage structure used for connecting the bearing block and the fixed base.
4. The vibration testing system of an aircraft engine rotor bearing housing of claim 3, wherein the stiffness of the cartridge receiver transition section is the same as the stiffness of the cartridge receiver mounting edge, and the stiffness of the squirrel cage structure is the same as the stiffness of the bearing housing mounting edge.
5. A vibration testing system for an aircraft engine rotor bearing housing according to claim 1, wherein the vibration testing subsystem comprises a plurality of vibration sensors and a data acquisition system for acquiring vibration sensor signals.
6. The vibration testing system of an aircraft engine rotor bearing mount of claim 5, wherein the plurality of vibration sensors are disposed on the force-bearing case bearing mount and the case, respectively, and the plurality of vibration sensors are uniformly disposed on the force-bearing case bearing mount and the case.
7. A vibration testing system for an aircraft engine rotor bearing housing according to claim 6, wherein the vibration sensor comprises one of an acceleration sensor, a velocity sensor and a displacement sensor.
8. A vibration testing system for an aircraft engine rotor bearing block according to any one of claims 1 to 7, wherein the testing system is further adapted to test the stiffness response of the force-bearing casing at different frequencies, and wherein the excitation subsystem further comprises a dynamic force sensor connected to the exciter for obtaining the dynamic force of the exciter.
9. A method of vibration testing of an aircraft engine rotor bearing housing according to any of claims 1 to 7, characterised in that the method comprises the steps of:
s1: constructing a vibration testing system of an aeroengine rotor bearing seat in a component testing environment;
s2: arranging vibration sensors on the bearing case bearing seat and the case;
s3: utilizing a vibration exciter to carry out dynamic excitation on a bearing case bearing seat, and respectively acquiring signals of the bearing case bearing seat and vibration sensors arranged on a case under the condition of different dynamic excitation parameters;
s4: processing data acquired by different sensors in S3 to obtain a vibration transfer relation;
s5: during the whole machine test, the vibration data of the casing is collected, and the vibration condition of the bearing casing bearing seat is obtained according to the vibration transmission relation.
10. The vibration testing method of the bearing seat of the aero-engine rotor according to claim 9, wherein in S3, the vibration exciter dynamically excites the bearing-box bearing seat in a direction in which the vibration sensor is arranged, and the excitation frequency of the dynamic excitation is 20Hz to 2000 Hz.
11. The vibration testing method for the bearing seat of the aircraft engine rotor as claimed in claim 9, wherein the data processing method in S4 is as follows:
if the input of the test is vibration data a at the bearing seat0(omega) and the output is vibration data a on the casing1(omega) to obtain the vibration transfer function between the excitation point and the response point of the bearing case
Wherein a in the transfer function0、a1Is the response corresponding to the excitation frequency omega in each measurement point.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111222179.1A CN114136564A (en) | 2021-10-20 | 2021-10-20 | Vibration testing system and method for rotor bearing pedestal of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111222179.1A CN114136564A (en) | 2021-10-20 | 2021-10-20 | Vibration testing system and method for rotor bearing pedestal of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114136564A true CN114136564A (en) | 2022-03-04 |
Family
ID=80395227
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111222179.1A Pending CN114136564A (en) | 2021-10-20 | 2021-10-20 | Vibration testing system and method for rotor bearing pedestal of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114136564A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114323656A (en) * | 2021-12-31 | 2022-04-12 | 哈尔滨工业大学 | Mechatronic rotary excitation device capable of generating high-low frequency excitation force simultaneously |
Citations (10)
| 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 |
| CN205958238U (en) * | 2016-06-28 | 2017-02-15 | 中航商用航空发动机有限责任公司 | Stiffness detection system of radially moving of aeroengine support case |
| 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 |
| CN109141893A (en) * | 2018-09-29 | 2019-01-04 | 天津大学 | Pneumatic birotor-casing multi-function test stand |
| 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 |
| CN109684711A (en) * | 2018-12-20 | 2019-04-26 | 中国人民解放军海军航空大学 | A kind of turboshaft engine is pneumatically connected more rotor coupled vibration analysis methods |
| CN111141518A (en) * | 2019-12-16 | 2020-05-12 | 西安交通大学 | Model-based asymmetric rotor bearing system unbalance identification method |
| US20200232867A1 (en) * | 2017-10-16 | 2020-07-23 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Vibration detection device, and unbalance detection device including the vibration detection device |
| CN112182939A (en) * | 2020-10-16 | 2021-01-05 | 中国航发四川燃气涡轮研究院 | Dynamic strength evaluation method for engine bearing frame |
| CN112629840A (en) * | 2020-11-20 | 2021-04-09 | 韩清凯 | Aircraft engine double-rotor-support-casing tester and testing method thereof |
-
2021
- 2021-10-20 CN CN202111222179.1A patent/CN114136564A/en active Pending
Patent Citations (10)
| 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 |
| CN205958238U (en) * | 2016-06-28 | 2017-02-15 | 中航商用航空发动机有限责任公司 | Stiffness detection system of radially moving of aeroengine support case |
| 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 |
| US20200232867A1 (en) * | 2017-10-16 | 2020-07-23 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Vibration detection device, and unbalance detection device including the vibration detection device |
| CN109141893A (en) * | 2018-09-29 | 2019-01-04 | 天津大学 | Pneumatic birotor-casing multi-function test stand |
| 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 |
| CN109684711A (en) * | 2018-12-20 | 2019-04-26 | 中国人民解放军海军航空大学 | A kind of turboshaft engine is pneumatically connected more rotor coupled vibration analysis methods |
| CN111141518A (en) * | 2019-12-16 | 2020-05-12 | 西安交通大学 | Model-based asymmetric rotor bearing system unbalance identification method |
| CN112182939A (en) * | 2020-10-16 | 2021-01-05 | 中国航发四川燃气涡轮研究院 | Dynamic strength evaluation method for engine bearing frame |
| CN112629840A (en) * | 2020-11-20 | 2021-04-09 | 韩清凯 | Aircraft engine double-rotor-support-casing tester and testing method thereof |
Non-Patent Citations (2)
| Title |
|---|
| 刘美茹 等: "无转速同步条件下转子叶片非接触振动测试方法研究" * |
| 欧阳运芳,明阳: "航空发动机双转子系统碰摩故障振动特性研究" * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114323656A (en) * | 2021-12-31 | 2022-04-12 | 哈尔滨工业大学 | Mechatronic rotary excitation device capable of generating high-low frequency excitation force simultaneously |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11860066B2 (en) | Dynamic strain field measuring method and system for rotor blade based on blade tip timing | |
| EP2518456A1 (en) | Method for monitoring demagnetization | |
| Koene et al. | Internet of things based monitoring of large rotor vibration with a microelectromechanical systems accelerometer | |
| CN108593229B (en) | Integral impeller blade vibration measurement device and measurement method | |
| CN111504587A (en) | Vertical hydraulic generator guide bearing support vibration characteristic evaluation system and method | |
| CN105067106B (en) | A kind of intershaft bearing vibration signals collecting method | |
| Gradzki et al. | Method of shaft crack detection based on squared gain of vibration amplitude | |
| Yunusa-Kaltungo et al. | Use of composite higher order spectra for faults diagnosis of rotating machines with different foundation flexibilities | |
| Pedotti et al. | Fault diagnostics in rotary machines through spectral vibration analysis using low-cost MEMS devices | |
| CN114136564A (en) | Vibration testing system and method for rotor bearing pedestal of aircraft engine | |
| CN102721462A (en) | Method for quickly computing Bode plot and Nyquist plot of rotary mechanical vehicle starting and parking processes | |
| KR20180024334A (en) | Diagnostic method for rotating machinery using rotor-bearing-foundation model | |
| CN113218551B (en) | Torque testing device, gearbox efficiency testing system and gearbox efficiency testing method | |
| Hassan et al. | Condition monitoring of helicopter drive shafts using quadratic-nonlinearity metric based on cross-bispectrum | |
| CN103712746B (en) | The acquiring method of Hysteresis phase lag in a kind of dynamic balance test of rotor | |
| Zurita et al. | Intelligent sensor based on acoustic emission analysis applied to gear fault diagnosis | |
| Laggan | Vibration monitoring | |
| Chen et al. | Identification of linearized dynamic characteristics of rolling element bearings | |
| Pedotti et al. | Instrument based on MEMS accelerometer for vibration and unbalance analysis in rotating machines | |
| KR101406778B1 (en) | Method for monitoring machinery health based on fictitious frequency response function and system using the same | |
| RU169944U1 (en) | Gearbox vibration control device | |
| CN207976250U (en) | A kind of horizontal crankshaft dynamic balancing measurement mechanism | |
| Bowler | Grid induced torsional vibrations in turbine-generators—Instrumentation, monitoring, and protection | |
| EP4092398A1 (en) | Arrangement, method, and computer program for estimating radial loading of rotating shaft on antifriction bearing | |
| Al-Hadad et al. | Rotating and non-rotating sensors for improving condition monitoring of wind turbines |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |