WO2018232809A1 - 基于激光测振仪的航空发动机整体叶盘旋转振动试验台及应用 - Google Patents
基于激光测振仪的航空发动机整体叶盘旋转振动试验台及应用 Download PDFInfo
- Publication number
- WO2018232809A1 WO2018232809A1 PCT/CN2017/093779 CN2017093779W WO2018232809A1 WO 2018232809 A1 WO2018232809 A1 WO 2018232809A1 CN 2017093779 W CN2017093779 W CN 2017093779W WO 2018232809 A1 WO2018232809 A1 WO 2018232809A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- blade
- measuring device
- vibration
- laser
- vibration measuring
- 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.)
- Ceased
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
- G01M15/00—Testing of engines
- G01M15/04—Testing internal-combustion engines
- G01M15/12—Testing internal-combustion engines by monitoring vibrations
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H9/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by using radiation-sensitive means, e.g. optical means
Definitions
- the invention belongs to the field of laser vibration measurement technology, and particularly relates to an aeroengine overall leaf disk rotation vibration test bench and application thereof based on a laser vibration meter.
- the conventional acceleration sensor has many advantages such as low cost and convenient testing, it is not suitable for testing the vibration of a rotating structure such as an integral leaf disc because of its need to be attached to the surface of the object to be tested, and at the same time, due to the additional mass and stiffness of the acceleration sensor. It also affects the accuracy of the overall leaf disk vibration test.
- people have been studying the vibration measurement methods of the whole leaf disc, including the collection loop transmission strain, radio remote control strain, capacitive coupling transmission strain, eddy current displacement sensor measurement, and blade tip clearance measurement, etc., but the above measurement Methods Due to various difficulties and limitations, any method can not effectively measure the actual working mode of all rotating blades and disc structures. Therefore, it is necessary to continue to study the new vibration testing technology of the overall blade of the aeroengine, and consider it comprehensively. Test efficiency, test accuracy and other aspects.
- laser vibrometer As an important instrument in photoelectric vibration measurement, laser vibrometer has changed the additional interference caused by traditional sensor contact measurement, and the non-contact vibration measurement method can obtain real-time vibration information of the measured object more accurately.
- the application of laser vibrometers in the aerospace field is also becoming more and more extensive.
- the invention provides an aeroengine overall leaf disc rotating vibration test bench based on a laser vibrometer, which can measure the blade and the disk surface in different forms of the same asynchronous differential speed in synchronization with the whole leaf disc to be tested. Vibration vibration test bench.
- Aeroengine overall blade rotation vibration test bench based on laser vibrometer, including base, motor, laser vibration measurement
- the instrument the main shaft, the casing, the leaf disk vibration measuring device, the blade vibration measuring device, the synchronous asynchronous differential device, the tip timing sensor, the timer and the control system, wherein the base is provided with a support platform 1 and a support base.
- the support base 2 and the support base 2 the laser vibrometer is mounted on the support table, the motor is mounted on the support table 2; the leaf disc vibration measuring device is provided with a rotating shaft, the whole leaf disc to be tested and the same An asynchronous differential device is mounted on the main shaft, and the leaf disc vibration measuring device is mounted with the same asynchronous differential device through the housing, and the rotating shaft and the main shaft are respectively mounted on the support base through the bearing and the bearing housing
- the motor is coupled to the main shaft via a coupling, and the blade vibration measuring device and the tip timing sensor are mounted on the housing, and the control system is used to control the operation of the test rig.
- the invention relates to an aeroengine monolithic rotational vibration test bench based on a laser vibrometer, wherein the leaf disc vibration measuring device comprises a linear actuator, a mirror and a reflecting device, and the linear actuator is a pen electric push a rod, a tip of the pen-type electric push rod is provided with a micro-motor, the mirror is fixedly disposed on the micro-motor, the mirror is at an angle of 45° with the axis of the pen-type electric push rod, the linear
- the actuator is fixedly disposed on the end of the main shaft;
- the reflecting device is a table body, one end of the reflecting device is a conical inner surface with a taper of 45°, and the inner surface of the cone is provided with a silver alloy reflective film.
- the other end of the reflecting device is provided with the rotating shaft.
- the laser vibrometer-based aeroengine integral blade disc rotational vibration test rig wherein the synchronous synchronizing differential device comprises a center wheel, a planet carrier, a planet gear, a planetary axle and an electromagnetic brake, the center wheel and the
- the planet carrier is fixedly mounted with the main shaft, the planetary gear is fixedly coupled with the planetary axle, the planetary axle penetrates into the planet carrier, and the end of the planetary axle is mounted with the electromagnetic brake;
- the center wheel meshes with the planet gears.
- the aero engine overall blade disc vibration vibration test bench based on a laser vibrometer wherein the housing comprises a shell ring, a through cover, a through cover, a partition plate and an inner ring gear, and the inner ring gear is disposed on the One end of the shell ring, the partition plate is disposed inside the shell ring, and the through cover and the through cover are respectively mounted on two sides of the shell ring by bolts; the inner ring gear meshes with the planet gear; The through cover is fixedly coupled to the reflecting device.
- the aircraft vibration measuring device for aero-engine integral blade disc based on a laser vibrometer comprising a probe, a servo motor, a longitudinal lead screw, a longitudinal lead screw nut, a longitudinal screw fixed seat, and a longitudinal direction Screw support base, connector, servo motor 2, transverse screw, transverse screw nut, transverse screw mount, transverse screw support, slider and guide rail, the two ends of the longitudinal lead screw are respectively connected with longitudinal lead screw a socket and a longitudinal screw support, the longitudinal screw nut is set on the longitudinal screw, the servo motor is mounted on the longitudinal screw holder for driving the longitudinal screw; the two ends of the transverse screw are respectively connected to the transverse screw holder And a transverse screw support, the transverse screw mount is fixedly connected with the longitudinal screw nut through the connector, the transverse screw nut is set on the transverse screw, and the probe is mounted on the transverse screw nut, a horizontal screw support is fixedly coupled to the slider, the slider is fitted with the rail, and a
- the above-mentioned laser vibration meter-based aeroengine overall leaf disc rotation vibration test bench preferably has a micro motor 2 for position adjustment of the lens of the probe for reflection
- the laser is perpendicular to the plane of the measured point.
- the laser vibrometer-based aeroengine integral leaf disc rotary vibration test rig preferably has three balance frames, and the balance frame is similar in quality and shape to the blade vibration measuring device.
- the balance frame is disposed on the casing at three positions spaced apart from the blade vibration measuring device by 90 degrees, and is used to eliminate the influence of dynamic imbalance during the rotation.
- the above-mentioned aero-engine integral blade disk rotation vibration test bench based on a laser vibrometer wherein the reflection device and the shaft of the rotating shaft are provided with axial through holes, and the reflecting device is provided with a radial hole and a horizontal a hole, the through cover is provided with a radial hole 2, the longitudinal screw support seat is provided with a transverse hole 2, the transverse screw fixing seat and the connector are provided with a transverse hole 3, the transverse screw
- the nut is provided with an optical aperture, and the axial through hole, the radial hole one, the transverse hole one, the radial hole two, the transverse hole two, the horizontal hole three and the light entrance hole are sequentially connected to form a laser path, and the laser path is
- the 90° turning point features a 45° mirror.
- the aero engine overall blade rotation vibration test bench based on the laser vibrometer wherein the control system is respectively connected to the laser vibrometer, the blade timing sensor, the timer, the linear actuator, the micro motor, and the electromagnetic Brake, servo motor 1, servo motor 2, micro motor 2 and motor.
- Step 1 The control system issues a command, the electromagnetic brake locks the planetary axle, and the central wheel, the carrier, the planetary gear and the planetary axle are locked together; the motor starts to rotate the spindle, the spindle drives the blade vibration measuring device, and the blade vibration measuring device Synchronous rotation with the asynchronous differential device, the tip timing sensor and the integral blade disk to be tested;
- Step 2 The laser vibrometer emits a laser light, passes through the axial through hole to the mirror of the leaf disc vibration measuring device, and reflects the silver alloy on the inner surface of the cone of the reflecting device with a taper of 45° through 45° reflection. On the reflective film, it is hit by 45° reflection on the surface of the whole leaf disc to be tested;
- Step 3 The push rod of the linear actuator is gradually fed forward, and at the same time, the micro motor on the push rod drives the mirror to rotate, and the laser is circled from the outer diameter to the center on the whole leaf disc surface to be tested. Point measurement to achieve vibration measurement;
- Step 4 the push rod of the linear actuator continues to feed into the axial through hole and stops at the radial hole;
- Step 5 simultaneously adjusting the rotation angle of the push rod and the micro motor of the linear actuator until the laser is injected into the radial hole 1 and hitting the probe of the blade vibration measuring device via the laser path;
- Step 6 The timer starts to count, and the servo motor 1 and the servo motor 2 are started at the same time, so that the probe is measured point by point along the radial and axial directions of the current blade to realize vibration measurement;
- Step 7 After the time T is measured, the current blade is measured, and the blade vibration detecting device is returned to the outer position of the whole leaf disc to be tested;
- Step 8 The timer applies a pulse to the electromagnetic brake to release the electromagnetic brake, the planetary axle is in a released state, the planetary gear rotates under the driving of the central wheel, and the planetary gear drives the inner ring gear to rotate, the shell and the blade tip
- the timing sensor generates a differential with the overall leaf disc to be tested
- Step 9 When the tip sensor detects the tip of the next blade, it applies a pulse to the electromagnetic brake and the timer; the electromagnetic brake locks the planetary axle; the timer starts to count, and the next blade is measured;
- Step 10 Cycle through steps 6 to 9 until all target blades on the integral blade disc to be tested are measured.
- the tip timing of the blade tip timing sensor is used, and the angle between the adjacent blades of the whole blade to be measured is ⁇ , and the tip timing sensor is measured.
- the head is fixed on the plane of the casing in the radial direction of the integral blade disc to be measured, such that the angle between the axis and the axis of the probe of the blade vibration measuring device is ⁇ /2, thus the tip sensor at the tip.
- the blade tip timing sensor applies a pulse signal to the electromagnetic brake to brake the blade when the blade passes the tip timing sensor.
- the timer the preparation work before the vibration measurement includes the measurement time of the measurement time used for the vibration measurement of each blade in the static state of the whole leaf disc to be tested, and the vibration time used by the i-th blade is t i , Timer time
- the function is to start timing after the blade tip timing sensor sends a braking command, and after the time T, the electromagnetic brake is pulsed to release the electromagnetic brake, thereby converting the blade vibration detecting device from the synchronous vibration detecting state to the asynchronous transition state.
- the same asynchronous differential device according to the present invention realizes the same asynchronous conversion function in the case of synchronization with the integral blade disk to be tested, and provides a possibility for continuous vibration measurement by blade, and the blade vibration measuring device
- the horizontal and vertical displacement function realizes the integral coverage of the various points on the surface of the blade and the adjustable torsion probe makes it possible to measure the surface of the twisted blade point by point.
- the leaf disk vibration measuring device realizes the uniform velocity-by-point vibration measurement function of the disk surface under the rotating state. .
- FIG. 1 is a front view of an aeroengine overall blade rotation vibration test bench based on a laser vibrometer
- FIG. 2 is a top view of an aeroengine overall blade rotation vibration test bench based on a laser vibrometer
- Figure 3 is a structural diagram of the same asynchronous differential device
- Figure 4 is a right side view of Figure 3;
- Figure 5 is a structural view of the blade vibration measuring device
- Figure 6 is a structural view of a leaf disc vibration measuring device
- Figure 7 is a schematic diagram of a laser path
- Figure 8 is an enlarged view of a portion B in Figure 7;
- Figure 9 is an enlarged view of a portion C in Figure 7;
- Figure 10 is the tip timing sensor
- the aeroengine overall blade rotation vibration test bench based on the laser vibrometer includes a base 1, a motor 16, a laser vibrometer 3, a spindle 12, a housing 10, a leaf disk vibration measuring device, a blade vibration measuring device 8, a synchronous asynchronous differential device, a tip timing sensor 43, a timer and a control system, wherein the base 1 is provided with a support base 2, a support base 20, a support base 18 and a support base 2 17.
- the laser vibrometer 3 is mounted on a support table 2, and the motor 16 is mounted on a support table 17; the leaf disc vibration measuring device is provided with a rotating shaft 4, and the whole leaf disc 9 to be tested and the same An asynchronous differential device is mounted on the spindle 12, and the blade disk vibration measuring device is mounted with the same asynchronous differential device through the housing 10, and the rotating shaft 4 and the spindle 12 are respectively mounted through bearings and bearing housings.
- the motor 16 is coupled to the main shaft 12 via a coupling 15, and the blade vibration measuring device 8 and the tip timing sensor 43 are mounted on the housing 10.
- the control system is used to control the operation of the test rig;
- the leaf disc vibration measuring device comprises a linear actuator 6, a mirror and a reflecting device 5,
- the linear actuator 6 is a pen type electric push rod, and a tip of the pen type electric push rod is provided with a micro motor.
- the mirror is fixedly disposed on the micro motor, the mirror is at an angle of 45° with the axis of the pen type electric push rod, and the linear actuator 6 is fixedly disposed on the end of the main shaft 12;
- the reflection device 5 is a table body, one end of the reflection device 5 is a conical inner surface with a taper of 45°, the inner surface of the cone is provided with a silver alloy reflection film 36, and the other end of the reflection device 5 is provided with the Rotary shaft 4;
- the synchronous asynchronous differential device comprises a center wheel 14, a planet carrier 22, eight planet wheels 13, a planetary axle 21 and an electromagnetic brake 11, the central wheel 14 and the planet carrier 22 being fixedly mounted with the main shaft 12 Together, the planetary gear 13 is fixedly coupled to the planetary axle 21, the planetary axle 21 penetrates into the planet carrier 22, and the end of the planetary axle 21 is mounted with the electromagnetic brake 11; The wheel 14 meshes with the planet gear 13;
- the housing 10 includes a housing ring, a through cover 7, a through cover, a partition and an inner ring gear, the inner ring gear is disposed at one end of the housing ring, and the partition plate is disposed inside the housing ring
- the through cover 7 and the through cover are respectively mounted on both sides of the bezel by bolts; the inner ring gear is meshed with the planetary gear 13; the through cover 7 is fixedly coupled with the reflecting device 5 ;
- the blade vibration measuring device 8 includes a probe 35, a servo motor 28, a longitudinal screw mount 27, a longitudinal lead screw 26, a longitudinal lead nut 25, a longitudinal lead screw support 23, a connector 29, and a servo motor 2 , transverse screw mount 30, a transverse screw 24, a transverse screw nut 31, a transverse screw support 34, a slider 32 and a guide rail 33.
- the two ends of the longitudinal screw 26 are respectively connected to the longitudinal screw holder 27 and the longitudinal screw support 23, and the longitudinal threads
- the lever nut 25 is set on the longitudinal lead screw 26, and the servo motor 28 is mounted on the longitudinal lead screw mount 27 for driving the longitudinal lead screw 26;
- the two ends of the transverse lead screw 24 are respectively connected to the transverse lead screw mount 30 and the transverse thread
- the bar support base 34, the transverse screw mount 30 is fixedly coupled to the longitudinal screw nut 25 via the connector 29, and the transverse screw nut 31 is fitted over the transverse screw 24, and the probe 35 is mounted on the transverse wire
- the transverse screw support 34 is fixedly coupled to the slider 32, the slider 32 is fitted together with the guide rail 33, and the servo motor 2 is mounted in the connector 29 for Driving a transverse screw 24;
- a longitudinal lead screw mount 27 and a longitudinal lead screw support 23 are fixedly mounted on the through cover 7, the guide rail 33 is fixedly mounted on the partition;
- the probe 35 is provided with a miniature a
- the reflection device 5 and the shaft center of the rotating shaft 4 are provided with an axial through hole 37.
- the reflecting device 5 is provided with a radial hole 38 and a horizontal hole 39, and the through cover 7 is provided with a radial hole.
- the longitudinal screw support base 23 is provided with a transverse hole 216, and the transverse screw fixing base 30 and the connector 29 are provided with a transverse hole 38, and the transverse screw nut 31 is provided with light.
- the hole, the axial through hole 37, the radial hole 38, the transverse hole 39, the radial hole 40, the transverse hole 41, the transverse hole 32 and the light entrance hole are sequentially connected to form a laser passage, in the laser a 45° mirror is placed at the 90° turn;
- the control system is respectively connected to the laser vibrometer 3, the blade timing sensor 43, the timer, the linear actuator 6, the micro motor 1, the electromagnetic brake 11, the servo motor 28, the servo motor 2, the micro motor 2 and The motor 16 is controlled.
- Step 1 The control system issues an instruction, and the electromagnetic brake 11 locks the planetary axle 21 to lock the center wheel 14, the carrier 22, the planetary gear 13 and the planetary axle 21 into one body; the motor 16 starts to rotate the spindle 12, and the spindle 12 drives the blade.
- the disk vibration measuring device, the blade vibration measuring device 8, the synchronous asynchronous differential device, the tip timing sensor 43 and the integral blade disk 9 to be tested are synchronously rotated;
- Step 2 The laser vibrometer 3 emits laser light, passes through the axial through hole 37 to the mirror of the leaf disc vibration measuring device, and is deflected by 45° on the inner surface of the cone of the reflecting device 5 with a taper of 45°.
- the silver alloy reflective film 36 is again deflected by 45° on the disk surface of the whole leaf disc 9 to be tested;
- Step 3 The push rod of the linear actuator 6 is fed forward gradually, and at the same time, the micro motor on the push rod drives the mirror to rotate, and the laser passes from the outer diameter to the center on the disk surface of the whole leaf disc 9 to be tested.
- the circle is measured point by point to achieve vibration measurement;
- Step 4 the push rod of the linear actuator 6 continues to feed into the axial through hole 37 and stops at the radial hole 38;
- Step 5 simultaneously adjust the rotation angle of the push rod and the micro motor of the linear actuator 6 until the laser light enters the radial hole 38, and hits the probe 35 of the blade vibration measuring device 8 via the laser path. on;
- Step 6 The timer starts counting, and at the same time, the servo motor 28 and the servo motor 2 are started, so that the probe 35 is measured point by point along the radial direction and the axial direction of the current blade to realize vibration measurement;
- Step 7 After the lapse of the time T, the current blade is measured, and the blade vibration measuring device 8 is returned to the outer position of the whole leaf disc 9 to be tested;
- Step 8 The timer applies a pulse to the electromagnetic brake 11, so that the electromagnetic brake 11 is in the released state, the planetary axle 21 is in the released state, the planetary gear 13 rotates under the driving of the central wheel 14, and the planetary gear 13 drives the inner ring gear to rotate.
- the housing 10 and the tip timing sensor 43 generate a differential with the integral leaf disc 9 to be tested;
- Step 9 When the tip timing sensor 43 detects the tip of the next blade, the electromagnetic brake 11 and the timer are pulsed; the electromagnetic brake 11 locks the planetary axle 21; the timer starts counting, and the next blade is measured;
- Step 10 Cycle through steps 6 to 9 until all target blades on the integral blade disc 9 to be tested are measured.
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Testing Of Engines (AREA)
Abstract
一种基于激光测振仪的航空发动机整体叶盘旋转振动试验台，包括底座（1）、电动机（16）、激光测振仪（3）、主轴（12）、壳体（10）、叶盘测振装置、叶片测振装置（8）、同异步差速装置、叶尖定时传感器（43）、计时器和控制系统，底座（1）上依次设有支撑台一（2）、支撑座一（20）、支撑座二（18）和支撑台二（17），激光测振仪（3）安装在支撑台一（2）上，电动机（16）安装在支撑台二（17）上；叶盘测振装置设有转轴（4），待测的整体叶盘（9）和同异步差速装置安装在主轴（12）上，叶盘测振装置通过壳体（10）与同异步差速装置安装在一起，转轴（4）及主轴（12）通过轴承和轴承座分别安装在支撑座一（20）和支撑座二（18）上，电动机（16）通过联轴器（15）与主轴（12）连接，叶片测振装置（8）和叶尖定时传感器（43）安装在壳体（10）上，控制系统用于控制试验台的运行。
Description
本发明属于激光测振技术领域，具体涉及一种基于激光测振仪的航空发动机整体叶盘旋转振动试验台及应用。
为了提高航空发动机的推重比，众多航空发动机企业竞相研发整体叶盘技术。整体叶盘是将叶片和轮盘通过先进的工艺做成一体，省去常规叶盘连接的榫头和榫槽，使结构大大简化，在航空发动机风扇、压气机、涡轮上采用整体叶盘结构可有效提高航空发动机的推重比。然而，整体叶盘结构具有模态密集的特点，在航空发动机运转时，由于气流激励，很容易使整体叶盘发生共振。此外，整体叶盘的盘体更薄，盘叶刚度相差不多，因而这种共振模式多为盘片耦合振动，其危害性更大。为此，有必要建立针对航空发动机整体叶盘的旋转振动试验台，也便可以深入研究其复杂的振动特点与行为特征。
传统加速度传感器虽然具有成本低、测试方便等许多优势，但由于其需要粘贴到被测对象的表面，因而不适合测试整体叶盘等旋转结构的振动，同时由于加速度传感器的附加质量和刚度的影响，也会影响整体叶盘振动测试的精度。另外，长期以来，虽然人们一直研究整体叶盘的振动测量方法，包括集流环传输应变、无线电遥控应变、电容耦合传输应变、电涡流位移传感器测量，以及叶片顶尖间隙测量等方式，但上述测量方法由于各种困难和局限性，任何一种方法都无法有效测量所有旋转叶片及盘体结构的实际工作振型，因而，有必要继续研究航空发动机整体叶盘的新型振动测试技术，并综合考虑测试效率、测试精度等方面的影响。
激光测振仪作为光电振动测量中的一种重要仪器，改变了传统传感器接触式测量所带来的附加干扰问题，且非接触式振动测量方式可更加准确地获得被测物体的实时振动信息，目前，激光测振仪在航空航天领域的应用也越来越广泛。
发明内容
本发明提供一种基于激光测振仪的航空发动机整体叶盘旋转振动试验台，可以在与待测的整体叶盘同步旋转的情况下，以不同形式的同异步差速测量叶片与盘面各点振动的振动试验台。
本发明的技术方案如下：
基于激光测振仪的航空发动机整体叶盘旋转振动试验台，包括底座、电动机、激光测振
仪、主轴、壳体、叶盘测振装置、叶片测振装置、同异步差速装置、叶尖定时传感器、计时器和控制系统，所述底座上依次设有支撑台一、支撑座一、支撑座二和支撑台二，所述激光测振仪安装在支撑台一上，所述电动机安装在支撑台二上；所述叶盘测振装置设有转轴，待测的整体叶盘和同异步差速装置安装在所述主轴上，所述叶盘测振装置通过所述壳体与同异步差速装置安装在一起，所述转轴及主轴通过轴承和轴承座分别安装在支撑座一和支撑座二上，所述电动机通过联轴器与所述主轴连接，所述叶片测振装置和叶尖定时传感器安装在所述壳体上，所述控制系统用于控制试验台的运行。
所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其中所述叶盘测振装置包括线性作动器、反射镜和反射装置，所述线性作动器为笔式电动推杆，笔式电动推杆的端头设置微型马达一，所述反射镜固定设置在所述微型马达一上，所述反射镜与笔式电动推杆的轴线成45°夹角，所述线性作动器固定设置在所述主轴的端头上；所述反射装置为台体，所述反射装置的一端为锥度45°的圆锥内表面，所述圆锥内表面设有银合金反射膜，所述反射装置的另一端设有所述转轴。
所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其中所述同异步差速装置包括中心轮、行星架、行星轮、行星轮轴和电磁制动器，所述中心轮和所述行星架与所述主轴固定安装在一起，所述行星轮与所述行星轮轴固定连接在一起，所述行星轮轴穿入所述行星架中，所述行星轮轴的端头安装所述电磁制动器；所述中心轮与所述行星轮啮合。
所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其中所述壳体包括壳圈、透盖、通盖、隔板和内齿圈，所述内齿圈设置在所述壳圈的一端，所述隔板设置在所述壳圈的内部，所述透盖和通盖通过螺栓分别安装在所述壳圈的两侧；所述内齿圈与所述行星轮啮合；所述透盖与所述反射装置固定连接在一起。
所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其中所述叶片测振装置包括测头、伺服电机一、纵向丝杠、纵向丝杠螺母、纵向丝杠固定座、纵向丝杠支撑座、连接器、伺服电机二、横向丝杠、横向丝杠螺母、横向丝杠固定座、横向丝杠支撑座、滑块和导轨，纵向丝杠的两端分别连接纵向丝杠固定座和纵向丝杠支撑座，纵向丝杠螺母套装在纵向丝杠上，伺服电机一安装在纵向丝杠固定座上用于驱动纵向丝杠；横向丝杠的两端分别连接横向丝杠固定座和横向丝杠支撑座，横向丝杠固定座通过所述连接器与纵向丝杠螺母固定连接在一起，横向丝杠螺母套装在横向丝杠上，所述测头安装在横向丝杠螺母上，横向丝杠支撑座与所述滑块固定连接在一起，所述滑块与所述导轨配合安装在一起，伺服电机二安装在所述连接器中用于驱动横向丝杠；纵向丝杠固定座和纵向丝杠支撑座固定安装在所述透盖
上，所述导轨固定安装在所述隔板上。
所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其优选方案为，所述测头设有微型马达二，用于对所述测头的镜片进行位置调整，使其反射的激光与被测点法平面垂直。
所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其优选方案为，还包括三个平衡架，所述平衡架与所述叶片测振装置质量和形态相类似，所述平衡架设置在所述壳体上与所述叶片测振装置呈90度相隔、对称的三个位置，用以消除旋转过程中的动不平衡影响。
所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其中所述反射装置和所述转轴的轴心设有轴向通孔，所述反射装置设有径向孔一和横孔一，所述透盖设有径向孔二，所述纵向丝杠支撑座设有横孔二，所述横向丝杠固定座和所述连接器设有横孔三，所述横向丝杠螺母设有进光孔，所述轴向通孔、径向孔一、横孔一、径向孔二、横孔二、横孔三和进光孔依次连通形成激光通路，在所述激光通路90°转折的地方设有45°反光镜。
所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其中所述控制系统分别连接所述激光测振仪、叶片定时传感器、计时器、线性作动器、微型马达一、电磁制动器、伺服电机一、伺服电机二、微型马达二和电动机。
上述基于激光测振仪的航空发动机整体叶盘旋转振动试验台的应用，包括如下步骤：
步骤1：控制系统发出指令，电磁制动器锁紧行星轮轴，使中心轮、行星架、行星轮和行星轮轴锁紧为一体；电动机启动使主轴旋转，主轴带动叶盘测振装置、叶片测振装置、同异步差速装置、叶尖定时传感器和待测的整体叶盘做同步旋转；
步骤2：激光测振仪发出激光，通过所述轴向通孔打到叶盘测振装置的反射镜上，经45°反射打在所述反射装置的锥度45°的圆锥内表面的银合金反射膜上，又经45°反射打在待测的整体叶盘盘面上；
步骤3：线性作动器的推杆向前逐步进给，同时推杆上的微型马达一带动所述反射镜旋转，激光在待测的整体叶盘盘面上由外径至中心一圈圈逐点进行测量实现测振；
步骤4：线性作动器的推杆继续进给进入所述轴向通孔内部，并于所述径向孔一处停止；
步骤5：同时调节线性作动器的推杆及微型马达一旋转角度，直至激光射进径向孔一中，并经所述激光通路打在所述叶片测振装置的测头上；
步骤6：计时器开始计时，同时启动伺服电机一和伺服电机二，使测头沿着当前叶片的径向与轴向方向逐点进行测量实现测振；
步骤7：经过计时时间T后，当前叶片测振完毕，所述叶片测振装置回位至待测的整体叶盘外侧位置；
步骤8：计时器对电磁制动器施加脉冲，使电磁制动器处于释放状态，行星轮轴处于释放状态，行星轮在中心轮带动下旋转，行星轮带动所述内齿圈旋转，所述壳体及叶尖定时传感器与待测的整体叶盘产生差速；
步骤9：叶尖定时传感器探测到下一个叶片的叶尖时对电磁制动器与计时器施加脉冲；电磁制动器锁紧行星轮轴；计时器开始计时，对下一个叶片进行测量；
步骤10：循环进行步骤6至步骤9，直至待测的整体叶盘上的所有目标叶片测振完毕为止。
所述叶尖定时传感器，针对于本发明而言，只取叶尖定时传感器的叶尖定时作用，设待测的整体叶盘相邻叶片之间的夹角为θ，将叶尖定时传感器测头固定于待测的整体叶盘径向方向的壳体法平面上，使其轴线与所述叶片测振装置的测头轴线的夹角为θ/2，如此一来，在叶尖定时传感器测头依靠同异步差速装置向下一个叶片的测量位置过渡时，每当有叶片经过叶尖定时传感器时，叶尖定时传感器则对电磁制动器施加一个脉冲信号使其制动，恢复叶片测振装置与待测的整体叶盘的同步状态，并且保证了叶片测振装置测头位于两相邻叶片的中间位置，即测振位置。
所述计时器，测振之前的准备工作就包括在待测的整体叶盘静止状态下，对每个叶片测振所用的测量时间的统计，设第i个叶片所用测振时间为ti，则计时器计时时间
其作用为在叶尖定时传感器发出制动命令之后开始计时，计时时间T后对电磁制动器给与脉冲，使电磁制动器释放，从而使叶片测振装置从同步测振状态向异步过渡状态转换。
本发明的有益效果为：本发明涉及的同异步差速装置实现了与待测的整体叶盘同步的情况下同异步转换功能，为逐个叶片的连续测振提供了可能，叶片测振装置的横纵向位移功能，实现了叶片表面各点的整体覆盖加之可调节的扭转测头使扭曲叶片表面逐点测振成为可能；叶盘测振装置实现了旋转状态下盘面的匀速逐点测振功能。
图1为基于激光测振仪的航空发动机整体叶盘旋转振动试验台主视图；
图2为基于激光测振仪的航空发动机整体叶盘旋转振动试验台俯视图；
图3为同异步差速装置结构图；
图4为图3的右视图；
图5为叶片测振装置结构图；
图6为叶盘测振装置结构图；
图7为激光通路示意图；
图8为图7中B处放大图；
图9为图7中C处放大图；
图10为叶尖定时传感器
如图1-10所示，基于激光测振仪的航空发动机整体叶盘旋转振动试验台，包括底座1、电动机16、激光测振仪3、主轴12、壳体10、叶盘测振装置、叶片测振装置8、同异步差速装置、叶尖定时传感器43、计时器和控制系统，所述底座1上依次设有支撑台一2、支撑座一20、支撑座二18和支撑台二17，所述激光测振仪3安装在支撑台一2上，所述电动机16安装在支撑台二17上；所述叶盘测振装置设有转轴4，待测的整体叶盘9和同异步差速装置安装在所述主轴12上，所述叶盘测振装置通过所述壳体10与同异步差速装置安装在一起，所述转轴4及主轴12通过轴承和轴承座分别安装在支撑座一20和支撑座二18上，所述电动机16通过联轴器15与所述主轴12连接，所述叶片测振装置8和叶尖定时传感器43安装在所述壳体10上，所述控制系统用于控制试验台的运行；
其中所述叶盘测振装置包括线性作动器6、反射镜和反射装置5，所述线性作动器6为笔式电动推杆，笔式电动推杆的端头设置微型马达一，所述反射镜固定设置在所述微型马达一上，所述反射镜与笔式电动推杆的轴线成45°夹角，所述线性作动器6固定设置在所述主轴12的端头上；所述反射装置5为台体，所述反射装置5的一端为锥度45°的圆锥内表面，所述圆锥内表面设有银合金反射膜36，所述反射装置5的另一端设有所述转轴4；
其中所述同异步差速装置包括中心轮14、行星架22、八个行星轮13、行星轮轴21和电磁制动器11，所述中心轮14和所述行星架22与所述主轴12固定安装在一起，所述行星轮13与所述行星轮轴21固定连接在一起，所述行星轮轴21穿入所述行星架22中，所述行星轮轴21的端头安装所述电磁制动器11；所述中心轮14与所述行星轮13啮合；
其中所述壳体10包括壳圈、透盖7、通盖、隔板和内齿圈，所述内齿圈设置在所述壳圈的一端，所述隔板设置在所述壳圈的内部，所述透盖7和通盖通过螺栓分别安装在所述壳圈的两侧；所述内齿圈与所述行星轮13啮合；所述透盖7与所述反射装置5固定连接在一起；
其中所述叶片测振装置8包括测头35、伺服电机一28、纵向丝杠固定座27、纵向丝杠26、纵向丝杠螺母25、纵向丝杠支撑座23、连接器29、伺服电机二、横向丝杠固定座30、
横向丝杠24、横向丝杠螺母31、横向丝杠支撑座34、滑块32和导轨33，纵向丝杠26的两端分别连接纵向丝杠固定座27和纵向丝杠支撑座23，纵向丝杠螺母25套装在纵向丝杠26上，伺服电机一28安装在纵向丝杠固定座27上用于驱动纵向丝杠26；横向丝杠24的两端分别连接横向丝杠固定座30和横向丝杠支撑座34，横向丝杠固定座30通过所述连接器29与纵向丝杠螺母25固定连接在一起，横向丝杠螺母31套装在横向丝杠24上，所述测头35安装在横向丝杠螺母31上，横向丝杠支撑座34与所述滑块32固定连接在一起，所述滑块32与所述导轨33配合安装在一起，伺服电机二安装在所述连接器29中用于驱动横向丝杠24；纵向丝杠固定座27和纵向丝杠支撑座23固定安装在所述透盖7上，所述导轨33固定安装在所述隔板上；所述测头35设有微型马达二，用于对所述测头35的镜片进行位置调整，使其反射的激光与被测点法平面垂直；还包括三个平衡架19，所述平衡架19与所述叶片测振装置8质量和形态相类似，所述平衡架19设置在所述壳体10上与所述叶片测振装置8呈90度相隔、对称的三个位置，用以消除旋转过程中的动不平衡影响；
其中所述反射装置5和所述转轴4的轴心设有轴向通孔37，所述反射装置5设有径向孔一38和横孔一39，所述透盖7设有径向孔二40，所述纵向丝杠支撑座23设有横孔二41，所述横向丝杠固定座30和所述连接器29设有横孔三42，所述横向丝杠螺母31设有进光孔，所述轴向通孔37、径向孔一38、横孔一39、径向孔二40、横孔二41、横孔三42和进光孔依次连通形成激光通路，在所述激光通路90°转折的地方设有45°反光镜；
其中所述控制系统分别连接所述激光测振仪3、叶片定时传感器43、计时器、线性作动器6、微型马达一、电磁制动器11、伺服电机一28、伺服电机二、微型马达二和电动机16，实施控制。
上述基于激光测振仪的航空发动机整体叶盘旋转振动试验台的应用，包括如下步骤：
步骤1：控制系统发出指令，电磁制动器11锁紧行星轮轴21，使中心轮14、行星架22、行星轮13和行星轮轴21锁紧为一体；电动机16启动使主轴12旋转，主轴12带动叶盘测振装置、叶片测振装置8、同异步差速装置、叶尖定时传感器43和待测的整体叶盘9做同步旋转；
步骤2：激光测振仪3发出激光，通过所述轴向通孔37打到叶盘测振装置的反射镜上，经45°反射打在所述反射装置5的锥度45°的圆锥内表面的银合金反射膜36上，又经45°反射打在待测的整体叶盘9盘面上；
步骤3：线性作动器6的推杆向前逐步进给，同时推杆上的微型马达一带动所述反射镜旋转，激光在待测的整体叶盘9盘面上由外径至中心一圈圈逐点进行测量实现测振；
步骤4：线性作动器6的推杆继续进给进入所述轴向通孔37内部，并于所述径向孔一38处停止；
步骤5：同时调节线性作动器6的推杆及微型马达一旋转角度，直至激光射进径向孔一38中，并经所述激光通路打在所述叶片测振装置8的测头35上；
步骤6：计时器开始计时，同时启动伺服电机一28和伺服电机二，使测头35沿着当前叶片的径向与轴向方向逐点进行测量实现测振；
步骤7：经过计时时间T后，当前叶片测振完毕，所述叶片测振装置8回位至待测的整体叶盘9外侧位置；
步骤8：计时器对电磁制动器11施加脉冲，使电磁制动器11处于释放状态，行星轮轴21处于释放状态，行星轮13在中心轮14带动下旋转，行星轮13带动所述内齿圈旋转，所述壳体10及叶尖定时传感器43与待测的整体叶盘9产生差速；
步骤9：叶尖定时传感器43探测到下一个叶片的叶尖时对电磁制动器11与计时器施加脉冲；电磁制动器11锁紧行星轮轴21；计时器开始计时，对下一个叶片进行测量；
步骤10：循环进行步骤6至步骤9，直至待测的整体叶盘9上的所有目标叶片测振完毕为止。
Claims (10)
- 基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其特征在于，包括底座、电动机、激光测振仪、主轴、壳体、叶盘测振装置、叶片测振装置、同异步差速装置、叶尖定时传感器、计时器和控制系统，所述底座上依次设有支撑台一、支撑座一、支撑座二和支撑台二，所述激光测振仪安装在支撑台一上，所述电动机安装在支撑台二上；所述叶盘测振装置设有转轴，待测的整体叶盘和同异步差速装置安装在所述主轴上，所述叶盘测振装置通过所述壳体与同异步差速装置安装在一起，所述转轴及主轴通过轴承和轴承座分别安装在支撑座一和支撑座二上，所述电动机通过联轴器与所述主轴连接，所述叶片测振装置和叶尖定时传感器安装在所述壳体上，所述控制系统用于控制试验台的运行。
- 根据权利要求1所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其特征在于，所述叶盘测振装置包括线性作动器、反射镜和反射装置，所述线性作动器为笔式电动推杆，笔式电动推杆的端头设置微型马达一，所述反射镜固定设置在所述微型马达一上，所述反射镜与笔式电动推杆的轴线成45°夹角，所述线性作动器固定设置在所述主轴的端头上；所述反射装置为台体，所述反射装置的一端为锥度45°的圆锥内表面，所述圆锥内表面设有银合金反射膜，所述反射装置的另一端设有所述转轴。
- 根据权利要求2所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其特征在于，所述同异步差速装置包括中心轮、行星架、行星轮、行星轮轴和电磁制动器，所述中心轮和所述行星架与所述主轴固定安装在一起，所述行星轮与所述行星轮轴固定连接在一起，所述行星轮轴穿入所述行星架中，所述行星轮轴的端头安装所述电磁制动器；所述中心轮与所述行星轮啮合。
- 根据权利要求3所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其特征在于，所述壳体包括壳圈、透盖、通盖、隔板和内齿圈，所述内齿圈设置在所述壳圈的一端，所述隔板设置在所述壳圈的内部，所述透盖和通盖通过螺栓分别安装在所述壳圈的两侧；所述内齿圈与所述行星轮啮合；所述透盖与所述反射装置固定连接在一起。
- 根据权利要求4所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其特征在于，所述叶片测振装置包括测头、伺服电机一、纵向丝杠、纵向丝杠螺母、纵向丝杠固定座、纵向丝杠支撑座、连接器、伺服电机二、横向丝杠、横向丝杠螺母、横向丝杠固定座、横向丝杠支撑座、滑块和导轨，纵向丝杠的两端分别连接纵向丝杠固定座和纵向丝杠支撑座，纵向丝杠螺母套装在纵向丝杠上，伺服电机一安装在纵向丝杠固定座上用于驱动纵向丝杠；横向丝杠的两端分别连接横向丝杠固定座和横向丝杠支撑座，横向丝杠固定座通过所 述连接器与纵向丝杠螺母固定连接在一起，横向丝杠螺母套装在横向丝杠上，所述测头安装在横向丝杠螺母上，横向丝杠支撑座与所述滑块固定连接在一起，所述滑块与所述导轨配合安装在一起，伺服电机二安装在所述连接器中用于驱动横向丝杠；纵向丝杠固定座和纵向丝杠支撑座固定安装在所述透盖上，所述导轨固定安装在所述隔板上。
- 根据权利要求5所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其特征在于，所述测头设有微型马达二，用于对所述测头的镜片进行位置调整，使其反射的激光与被测点法平面垂直。
- 根据权利要求5所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其特征在于，还包括三个平衡架，所述平衡架与所述叶片测振装置质量和形态相类似，所述平衡架设置在所述壳体上与所述叶片测振装置呈90度相隔、对称的三个位置，用以消除旋转过程中的动不平衡影响。
- 根据权利要求6所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其特征在于，所述反射装置和所述转轴的轴心设有轴向通孔，所述反射装置设有径向孔一和横孔一，所述透盖设有径向孔二，所述纵向丝杠支撑座设有横孔二，所述横向丝杠固定座和所述连接器设有横孔三，所述横向丝杠螺母设有进光孔，所述轴向通孔、径向孔一、横孔一、径向孔二、横孔二、横孔三和进光孔依次连通形成激光通路，在所述激光通路90°转折的地方设有45°反光镜。
- 根据权利要求6所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台，其特征在于，所述控制系统分别连接所述激光测振仪、叶片定时传感器、计时器、线性作动器、微型马达一、电磁制动器、伺服电机一、伺服电机二、微型马达二和电动机。
- 一种如权利要求1-9之一所述的基于激光测振仪的航空发动机整体叶盘旋转振动试验台的应用，其特征在于，包括如下步骤：步骤1：控制系统发出指令，电磁制动器锁紧行星轮轴，使中心轮、行星架、行星轮和行星轮轴锁紧为一体；电动机启动使主轴旋转，主轴带动叶盘测振装置、叶片测振装置、同异步差速装置、叶尖定时传感器和待测的整体叶盘做同步旋转；步骤2：激光测振仪发出激光，通过所述轴向通孔打到叶盘测振装置的反射镜上，经45°反射打在所述反射装置的锥度45°的圆锥内表面的银合金反射膜上，又经45°反射打在待测的整体叶盘盘面上；步骤3：线性作动器的推杆向前逐步进给，同时推杆上的微型马达一带动所述反射镜旋转，激光在待测的整体叶盘盘面上由外径至中心一圈圈逐点进行测量实现测振；步骤4：线性作动器的推杆继续进给进入所述轴向通孔内部，并于所述径向孔一处停止；步骤5：同时调节线性作动器的推杆及微型马达一旋转角度，直至激光射进径向孔一中，并经所述激光通路打在所述叶片测振装置的测头上；步骤6：计时器开始计时，同时启动伺服电机一和伺服电机二，使测头沿着当前叶片的径向与轴向方向逐点进行测量实现测振；步骤7：经过计时时间T后，当前叶片测振完毕，所述叶片测振装置回位至待测的整体叶盘外侧位置；步骤8：计时器对电磁制动器施加脉冲，使电磁制动器处于释放状态，行星轮轴处于释放状态，行星轮在中心轮带动下旋转，行星轮带动所述内齿圈旋转，所述壳体及叶尖定时传感器与待测的整体叶盘产生差速；步骤9：叶尖定时传感器探测到下一个叶片的叶尖时对电磁制动器与计时器施加脉冲；电磁制动器锁紧行星轮轴；计时器开始计时，对下一个叶片进行测量；步骤10：循环进行步骤6至步骤9，直至待测的整体叶盘上的所有目标叶片测振完毕为止。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2019565531A JP6849251B2 (ja) | 2017-06-24 | 2017-07-21 | レーザー振動計に基づく航空機エンジンブリスクの回転振動試験ベンチ及びその活用 |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710489440.1 | 2017-06-24 | ||
| CN201710489440.1A CN107132049B (zh) | 2017-06-24 | 2017-06-24 | 基于激光测振仪的航空发动机整体叶盘旋转振动试验台及应用 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2018232809A1 true WO2018232809A1 (zh) | 2018-12-27 |
Family
ID=59736438
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/CN2017/093779 Ceased WO2018232809A1 (zh) | 2017-06-24 | 2017-07-21 | 基于激光测振仪的航空发动机整体叶盘旋转振动试验台及应用 |
Country Status (3)
| Country | Link |
|---|---|
| JP (1) | JP6849251B2 (zh) |
| CN (1) | CN107132049B (zh) |
| WO (1) | WO2018232809A1 (zh) |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110700901A (zh) * | 2019-11-19 | 2020-01-17 | 中国特种设备检测研究院 | 一种用于叶轮机械故障模拟及监测的实验装置 |
| CN110940274A (zh) * | 2019-12-17 | 2020-03-31 | 山西迪迈沃科光电工业有限公司 | 回转体内腔尺寸全自动检测线 |
| CN111426758A (zh) * | 2020-02-20 | 2020-07-17 | 中国铁道科学研究院集团有限公司 | 探轮标定试验台 |
| CN112222617A (zh) * | 2020-09-16 | 2021-01-15 | 华南师范大学 | 一种自动化的激光焊接装置及焊接方法 |
| CN113820005A (zh) * | 2021-09-22 | 2021-12-21 | 国网上海市电力公司 | 一种电力设备支撑桩体便携式振动检测装置及操作方法 |
| CN114061408A (zh) * | 2021-11-11 | 2022-02-18 | 哈尔滨工业大学 | 一种用于叶尖间隙试验的间隙控制试验机构 |
| CN114112195A (zh) * | 2021-12-02 | 2022-03-01 | 郑州世纪精信机械制造有限公司 | 贯流风叶注塑件动平衡检测装置及检测方法 |
| CN114166336A (zh) * | 2021-12-02 | 2022-03-11 | 成都市鸿侠科技有限责任公司 | 一种智能化飞机发电机叶片频率测量工装及其加工工艺 |
| CN114577120A (zh) * | 2022-04-19 | 2022-06-03 | 安正计量检测有限公司 | 一种计量仪器设备的质量检测装置 |
| CN114739501A (zh) * | 2022-03-19 | 2022-07-12 | 中国民用航空飞行学院 | 用于飞机发动机涡轮叶片的检测装置 |
| WO2022218449A1 (en) * | 2021-04-13 | 2022-10-20 | České vysoké učení technické v Praze | A device for measuring vibrations of a moving object |
| CN115469112A (zh) * | 2022-08-19 | 2022-12-13 | 北京精密机电控制设备研究所 | 一种行星滚柱丝杠接触点位置相对运动速度测量装置 |
| CN115824080A (zh) * | 2022-11-23 | 2023-03-21 | 北京航空航天大学 | 一种用于旋转曲面径向形变测量的传感器标定装置及方法 |
| CN116046311A (zh) * | 2023-01-09 | 2023-05-02 | 南昌大学 | 一种飞机发动机叶片固有频率自动化测量装置及其测量方法 |
| CN116625478A (zh) * | 2023-07-21 | 2023-08-22 | 同日智能科技(徐州)有限公司 | 一种减速电机振动测试设备 |
| CN116659788A (zh) * | 2023-07-27 | 2023-08-29 | 沂源县华阳能源设备有限公司 | 一种汽轮机叶轮振动性能测试装置 |
| CN117504157A (zh) * | 2024-01-05 | 2024-02-06 | 深圳市吉斯迪科技有限公司 | 半导体激光器治疗光路调节机构 |
| CN118443142A (zh) * | 2024-07-05 | 2024-08-06 | 华能平凉发电有限责任公司 | 一种汽轮机叶片的振动检测装置 |
| CN118534151A (zh) * | 2024-07-22 | 2024-08-23 | 四川川航航空发动机维修工程有限责任公司 | 一种模拟飞机发动机转速传感器的工作环境的性能检测装置及检测方法 |
| CN119373544A (zh) * | 2024-12-31 | 2025-01-28 | 招金矿业股份有限公司夏甸金矿 | 一种便于调节的采矿用通风装置 |
| EP4517280A1 (en) * | 2023-09-01 | 2025-03-05 | RTX Corporation | System and method for accurately positioning optical tip-timing probe |
| CN120176573A (zh) * | 2025-05-22 | 2025-06-20 | 西安爱德华测量设备股份有限公司 | 双激光叶片边缘测量装置 |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107132049B (zh) * | 2017-06-24 | 2019-03-22 | 东北大学 | 基于激光测振仪的航空发动机整体叶盘旋转振动试验台及应用 |
| CN107727346B (zh) * | 2017-10-10 | 2019-06-18 | 东北大学 | 螺栓松动下纤维增强复合盘鼓薄壁构件旋转振动试验台 |
| CN107966259A (zh) * | 2017-10-30 | 2018-04-27 | 东北大学 | 纤维增强复合薄壁构件的冲击与热复合试验装置 |
| CN109084882B (zh) * | 2018-09-30 | 2023-09-26 | 华南理工大学 | 旋转圆盘振动检测控制装置及方法 |
| CN111239432B (zh) * | 2020-02-10 | 2021-05-28 | 西安交通大学 | 基于叶端定时的叶片到达时间测量方法及其采集系统 |
| KR102273610B1 (ko) * | 2020-04-07 | 2021-07-06 | 한국전력공사 | 회전체 진동 신호 처리 보드, 회전체 진동 신호 감시 시스템, 및 회전체 진동 감시 방법 |
| KR102273609B1 (ko) * | 2020-04-07 | 2021-07-06 | 한국전력공사 | 회전체진동 감시 시스템 및 회전체진동 감시 방법 |
| CN113468788B (zh) * | 2021-07-20 | 2022-08-16 | 中国科学院工程热物理研究所 | 一种发动机整体叶盘变形协调设计方法 |
| CN113551920A (zh) * | 2021-07-26 | 2021-10-26 | 上海航数智能科技有限公司 | 一种综合监测型航空发动机输出功率稳定度检测仪 |
| CN113959556B (zh) * | 2021-09-22 | 2022-06-28 | 上海交通大学 | 旋转叶片叶尖定时传感器动态标定装置 |
| JP7747053B2 (ja) * | 2021-09-28 | 2025-10-01 | 株式会社Ihi | ブリスクの振動検出装置 |
| CN115901755B (zh) * | 2022-11-11 | 2024-11-12 | 哈尔滨工业大学 | 一种用于送粉式增材制造粉末分布状态测量装置 |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103364069A (zh) * | 2012-04-05 | 2013-10-23 | 中国航空工业集团公司沈阳发动机设计研究所 | 一种基于无转速定位的非接触式旋转叶片振动测试方法 |
| CN103528776A (zh) * | 2013-09-27 | 2014-01-22 | 东北大学 | 一种高阶旋转叶片动力学相似测试实验台及测试方法 |
| US20140268100A1 (en) * | 2013-03-15 | 2014-09-18 | United Technologies Corporation | Multiple Laser Time of Arrival Probe |
| CN205300906U (zh) * | 2015-12-07 | 2016-06-08 | 广东电网有限责任公司电力科学研究院 | 一种将叶片振动信号和轴振信号融合的旋转实验装置 |
| CN206019842U (zh) * | 2016-09-13 | 2017-03-15 | 中国航空动力机械研究所 | 叶片振动模拟装置及具有其的测试系统 |
| CN107132049A (zh) * | 2017-06-24 | 2017-09-05 | 东北大学 | 基于激光测振仪的航空发动机整体叶盘旋转振动试验台及应用 |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1010478A1 (ru) * | 1981-05-29 | 1983-04-07 | Московский авиационный технологический институт им.К.Э.Циолковского | Устройство дл балансировки роторов |
| JPS62150133A (ja) * | 1985-12-25 | 1987-07-04 | Hitachi Ltd | 翼の回転試験装置 |
| JPH0727601A (ja) * | 1993-07-12 | 1995-01-31 | Mitsubishi Heavy Ind Ltd | 非接触振動計測方法および装置 |
| JP5353517B2 (ja) * | 2009-07-17 | 2013-11-27 | 株式会社Ｉｈｉ | タービン翼の振動計測装置 |
| WO2013181598A1 (en) * | 2012-05-31 | 2013-12-05 | The Regents Of The University Of Michigan | Laser-based edge detection |
| US8925387B2 (en) * | 2012-12-19 | 2015-01-06 | United Technologies Corporation | Traversing time of arrival probe |
| CN105258887B (zh) * | 2015-10-22 | 2017-11-14 | 西安热工研究院有限公司 | 一种利用磁力激振的叶片动态频率测试装置 |
| CN105424160B (zh) * | 2015-11-20 | 2019-03-08 | 天津大学 | 实现叶片同步振动参数辨识的方法 |
-
2017
- 2017-06-24 CN CN201710489440.1A patent/CN107132049B/zh active Active
- 2017-07-21 WO PCT/CN2017/093779 patent/WO2018232809A1/zh not_active Ceased
- 2017-07-21 JP JP2019565531A patent/JP6849251B2/ja not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103364069A (zh) * | 2012-04-05 | 2013-10-23 | 中国航空工业集团公司沈阳发动机设计研究所 | 一种基于无转速定位的非接触式旋转叶片振动测试方法 |
| US20140268100A1 (en) * | 2013-03-15 | 2014-09-18 | United Technologies Corporation | Multiple Laser Time of Arrival Probe |
| CN103528776A (zh) * | 2013-09-27 | 2014-01-22 | 东北大学 | 一种高阶旋转叶片动力学相似测试实验台及测试方法 |
| CN205300906U (zh) * | 2015-12-07 | 2016-06-08 | 广东电网有限责任公司电力科学研究院 | 一种将叶片振动信号和轴振信号融合的旋转实验装置 |
| CN206019842U (zh) * | 2016-09-13 | 2017-03-15 | 中国航空动力机械研究所 | 叶片振动模拟装置及具有其的测试系统 |
| CN107132049A (zh) * | 2017-06-24 | 2017-09-05 | 东北大学 | 基于激光测振仪的航空发动机整体叶盘旋转振动试验台及应用 |
Cited By (29)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110700901A (zh) * | 2019-11-19 | 2020-01-17 | 中国特种设备检测研究院 | 一种用于叶轮机械故障模拟及监测的实验装置 |
| CN110940274A (zh) * | 2019-12-17 | 2020-03-31 | 山西迪迈沃科光电工业有限公司 | 回转体内腔尺寸全自动检测线 |
| CN111426758A (zh) * | 2020-02-20 | 2020-07-17 | 中国铁道科学研究院集团有限公司 | 探轮标定试验台 |
| CN112222617A (zh) * | 2020-09-16 | 2021-01-15 | 华南师范大学 | 一种自动化的激光焊接装置及焊接方法 |
| WO2022218449A1 (en) * | 2021-04-13 | 2022-10-20 | České vysoké učení technické v Praze | A device for measuring vibrations of a moving object |
| CN113820005A (zh) * | 2021-09-22 | 2021-12-21 | 国网上海市电力公司 | 一种电力设备支撑桩体便携式振动检测装置及操作方法 |
| CN113820005B (zh) * | 2021-09-22 | 2024-03-26 | 国网上海市电力公司 | 一种电力设备支撑桩体便携式振动检测装置及操作方法 |
| CN114061408A (zh) * | 2021-11-11 | 2022-02-18 | 哈尔滨工业大学 | 一种用于叶尖间隙试验的间隙控制试验机构 |
| CN114112195A (zh) * | 2021-12-02 | 2022-03-01 | 郑州世纪精信机械制造有限公司 | 贯流风叶注塑件动平衡检测装置及检测方法 |
| CN114166336A (zh) * | 2021-12-02 | 2022-03-11 | 成都市鸿侠科技有限责任公司 | 一种智能化飞机发电机叶片频率测量工装及其加工工艺 |
| CN114166336B (zh) * | 2021-12-02 | 2024-04-05 | 成都市鸿侠科技有限责任公司 | 一种智能化飞机发电机叶片频率测量工装及其加工工艺 |
| CN114112195B (zh) * | 2021-12-02 | 2023-09-01 | 郑州世纪精信机械制造有限公司 | 贯流风叶注塑件动平衡检测装置及检测方法 |
| CN114739501B (zh) * | 2022-03-19 | 2023-07-28 | 中国民用航空飞行学院 | 用于飞机发动机涡轮叶片的检测装置 |
| CN114739501A (zh) * | 2022-03-19 | 2022-07-12 | 中国民用航空飞行学院 | 用于飞机发动机涡轮叶片的检测装置 |
| CN114577120A (zh) * | 2022-04-19 | 2022-06-03 | 安正计量检测有限公司 | 一种计量仪器设备的质量检测装置 |
| CN115469112A (zh) * | 2022-08-19 | 2022-12-13 | 北京精密机电控制设备研究所 | 一种行星滚柱丝杠接触点位置相对运动速度测量装置 |
| CN115824080A (zh) * | 2022-11-23 | 2023-03-21 | 北京航空航天大学 | 一种用于旋转曲面径向形变测量的传感器标定装置及方法 |
| CN116046311A (zh) * | 2023-01-09 | 2023-05-02 | 南昌大学 | 一种飞机发动机叶片固有频率自动化测量装置及其测量方法 |
| CN116625478A (zh) * | 2023-07-21 | 2023-08-22 | 同日智能科技(徐州)有限公司 | 一种减速电机振动测试设备 |
| CN116625478B (zh) * | 2023-07-21 | 2023-11-07 | 同日智能科技(徐州)有限公司 | 一种减速电机振动测试设备 |
| CN116659788A (zh) * | 2023-07-27 | 2023-08-29 | 沂源县华阳能源设备有限公司 | 一种汽轮机叶轮振动性能测试装置 |
| CN116659788B (zh) * | 2023-07-27 | 2023-10-13 | 沂源县华阳能源设备有限公司 | 一种汽轮机叶轮振动性能测试装置 |
| EP4517280A1 (en) * | 2023-09-01 | 2025-03-05 | RTX Corporation | System and method for accurately positioning optical tip-timing probe |
| CN117504157B (zh) * | 2024-01-05 | 2024-03-26 | 深圳市吉斯迪科技有限公司 | 半导体激光器治疗光路调节机构 |
| CN117504157A (zh) * | 2024-01-05 | 2024-02-06 | 深圳市吉斯迪科技有限公司 | 半导体激光器治疗光路调节机构 |
| CN118443142A (zh) * | 2024-07-05 | 2024-08-06 | 华能平凉发电有限责任公司 | 一种汽轮机叶片的振动检测装置 |
| CN118534151A (zh) * | 2024-07-22 | 2024-08-23 | 四川川航航空发动机维修工程有限责任公司 | 一种模拟飞机发动机转速传感器的工作环境的性能检测装置及检测方法 |
| CN119373544A (zh) * | 2024-12-31 | 2025-01-28 | 招金矿业股份有限公司夏甸金矿 | 一种便于调节的采矿用通风装置 |
| CN120176573A (zh) * | 2025-05-22 | 2025-06-20 | 西安爱德华测量设备股份有限公司 | 双激光叶片边缘测量装置 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107132049A (zh) | 2017-09-05 |
| JP2020525755A (ja) | 2020-08-27 |
| JP6849251B2 (ja) | 2021-03-24 |
| CN107132049B (zh) | 2019-03-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2018232809A1 (zh) | 基于激光测振仪的航空发动机整体叶盘旋转振动试验台及应用 | |
| CN114440790B (zh) | 同时检测薄壁回转体内外壁面形与厚度分布的方法与装置 | |
| CN107727346B (zh) | 螺栓松动下纤维增强复合盘鼓薄壁构件旋转振动试验台 | |
| CN101947746B (zh) | 一种基于激光干涉的球杆测量装置及其测量方法 | |
| CN108519103B (zh) | 利用自准直仪的稳定平台多姿态精度同步评定装置及方法 | |
| CN103604608B (zh) | 轻型运动飞机螺旋桨拉力试验台 | |
| CN110873647B (zh) | 微型发动机滚转俯仰姿态试验台 | |
| CN102062581A (zh) | 基于角锥棱镜轴系径向跳动的测量装置 | |
| CN105423876A (zh) | 基于公差调控的大型高速回转装备装配测量方法及装置 | |
| CN114739626A (zh) | 一种基于快速响应压敏漆的旋转叶栅测压试验方法 | |
| CN108918065A (zh) | 一种鼓筒-轮盘螺栓连接结构的实验装置及测试方法 | |
| CN108760118A (zh) | 一种测量惯性平台台体质量不平衡力矩的装置及方法 | |
| CN104792280B (zh) | 位移式轴承接触角测量方法 | |
| CN110501114A (zh) | 三维力传感器动态特性校准装置及方法 | |
| CN103335833B (zh) | 在线测量超精密静压主轴动态性能的装置及采用该装置测量静压主轴动态性能的方法 | |
| CN103776365A (zh) | 基于径向与轴向基准的航空发动机多轴转子装配方法与装置 | |
| CN107340111B (zh) | 用于复合材料圆柱壳行波振动测试的旋转振动试验台 | |
| Warren et al. | Optical non-contacting vibration measurement of rotating turbine blades II | |
| D'Emilia et al. | Calibration test bench for three-axis accelerometers An accurate and low-cost proposal | |
| CN209258418U (zh) | 无人机旋翼单向动平衡测试系统 | |
| CN103335783B (zh) | 一种超精密直驱式静压主轴动平衡方法 | |
| CN109030861A (zh) | 一种用于流体力学试验中粒子图像测速仪测量旋转部件的同步装置及方法 | |
| CN103791821A (zh) | 基于径向误差与轴向倾斜的航空发动机转子装配方法与装置 | |
| CN118533059A (zh) | 一种双轴模式下的内外轴轴心轨迹测量方法及系统 | |
| CN208443367U (zh) | 一种齿轮齿侧间隙可调的实验装置 |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 17915154 Country of ref document: EP Kind code of ref document: A1 |
|
| ENP | Entry into the national phase |
Ref document number: 2019565531 Country of ref document: JP Kind code of ref document: A |
|
| NENP | Non-entry into the national phase |
Ref country code: DE |
|
| 122 | Ep: pct application non-entry in european phase |
Ref document number: 17915154 Country of ref document: EP Kind code of ref document: A1 |
|
| 122 | Ep: pct application non-entry in european phase |
Ref document number: 17915154 Country of ref document: EP Kind code of ref document: A1 |