CN108507482A - A kind of device and method for the quiet dynamic blade tip radius of gyration measuring turbine rotor - Google Patents
A kind of device and method for the quiet dynamic blade tip radius of gyration measuring turbine rotor Download PDFInfo
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- CN108507482A CN108507482A CN201810224153.2A CN201810224153A CN108507482A CN 108507482 A CN108507482 A CN 108507482A CN 201810224153 A CN201810224153 A CN 201810224153A CN 108507482 A CN108507482 A CN 108507482A
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- China
- Prior art keywords
- light curtain
- turbine rotor
- blade
- distance measuring
- blade tip
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/08—Measuring arrangements characterised by the use of optical techniques for measuring diameters
Abstract
The present invention is a kind of device and method for the quiet dynamic blade tip radius of gyration measuring turbine rotor, the static state and dynamic rotation radius that can be used for obtaining the blade tip position of aero-engine and the turbine rotor blade in gas turbine, to which turning in aero-engine and gas turbine assembling process, the tip clearance between quiet component provides a measuring technique and supports to obtain.Tested turbine rotor is mounted on the idler wheel of fore-stock and after-poppet by the device, and is locked by locking rack, and the output axis connection of Hooks coupling universal coupling and spindle box is then passed through.For each blade being tested on turbine rotor wheel rim, the present invention measures the radius of gyration at its blade tip position using contactless light curtain distance measuring sensor, when rotating speed is relatively low, the elongation of blade can be ignored, and measured result is the static blade tip radius of gyration at this time；When rotating speed is higher, the elongation of blade is larger, and measured result is the dynamic blade tip radius of gyration at this time.
Description
Technical field
The present invention is a kind of device and method for the quiet dynamic blade tip radius of gyration measuring turbine rotor, belongs to measuring technique
Field.
Background technology
In aero-engine and gas turbine, turbine rotor is one of key structure part therein, is mainly used for fire
It burns the high temperature of room outflow, most of potential energy of high-pressure gas and thermal energy and is converted into mechanical work, to drive fan, compressor and spiral
The attachmentes such as paddle work.It is, in general, that " turbine rotor " is the general name of turbine rotation component, mainly by working-blade, the turbine disk and
The compositions such as turbine wheel shaft.In aero-engine and the course of work of gas turbine, turbine rotor is always all in revolution at a high speed shape
State, rotating speed would generally reach 15000 revs/min or more.Under so high rotary regimes, the work on turbine disk wheel rim
Blade will produce prodigious centrifugal force, and resulting centrifugal load is that blade being afforded during the work time is most important
Load.Under the action of this centrifugal load, tensile stress caused by blade interior is in higher level, to make blade exist
Stretcher strain is generated in the radial direction, causes the elongation of blade to a certain extent.
The elongation of blade can cause the radial clearance between the blade tip position of turbine rotor and casing inner wall to reduce, and too small
Tip clearance can then cause blade tip and rub with touching for casing inner wall, can even cause leaf destruction and casing to damage when serious, it is right
The safe handling of aero-engine and gas turbine generates great threat.Therefore, in China's advanced aero engine and combustion gas wheel
In the design process of machine, the quiet dynamic blade tip radius of gyration of turbine rotor has become a technical parameter being particularly concerned,
Geometry and critical size design to the turbine disk, working-blade etc. all have great influence.Meanwhile it to realize and aviation is sent out
The measurement and control of tip clearance during motivation and gas turbine operation, one of important means are exactly to obtain turbine rotor to exist
The dynamic blade tip radius of gyration of each blade under revolution at a high speed state.
With the continuous promotion of China's aero-engine performance, the efficiency potential for further excavating aero-engine is needed,
This just needs to keep the radial clearance between turbine rotor blade tip and casing inner wall as small as possible, is made with reducing working media leakage
At loss in efficiency.Therefore, it is necessary to the blade tip radius of gyration to turbine rotor to accurately control, and especially turbine rotor is in height
The dynamic blade tip radius of gyration under speed operating, there is an urgent need to develop novel, efficient automatic measurement equipment.Currently, at me
The aero-engine of state and the development of gas turbine and production unit ask the measurement of the blade tip radius of gyration of turbine rotor
Topic, typically only by the light instruments approximate measure static radius such as large-scale vernier caliper, and for turbine rotor revolution at a high speed
Dynamic Radius under state then there is no effective measurement means.
In recent years, with the rapid development of the related disciplines such as optics, electronics and sensing technology, many photoelectric sensors and
Measurement method is introduced in aviation field, is successfully solved many conventional measurement techniques and is difficult to or insurmountable asks
Topic.Optical measurement sensors have many advantages, such as non-contact, fast response time, high certainty of measurement and convenient for miniaturization, thus especially
Crucial geometry suitable for aero-engine and gas turbine assembling process and dimension information test problems.The present invention exactly exists
It is proposed that there is prodigious innovation meaning under such background and in conjunction with the active demand of aero-engine and gas turbine industry
Justice and practical value, have a extensive future.
Invention content
The present invention is exactly to design and provide a kind of to measure the quiet dynamic of turbine rotor for above-mentioned prior art situation
The device and method of the state blade tip radius of gyration, the purpose is to obtain the static state and dynamic rotation at the blade tip position of turbine rotor blade
Radius, to for obtain in aero-engine and gas turbine assembling process turn, the tip clearance between quiet component provide one
Item measuring technique support.
The purpose of the present invention is achieved through the following technical solutions：
Technical scheme of the present invention provides a kind of device for the quiet dynamic blade tip radius of gyration measuring turbine rotor, the dress
The static state and dynamic rotation radius at the blade tip position for obtaining the turbine rotor blade in aero-engine and gas turbine are set,
To for obtain in aero-engine and gas turbine assembling process turn, the tip clearance between quiet component one measurement is provided
Technical support, it is characterised in that：The device includes pedestal (1), fore-stock (2), after-poppet (3), spindle box (4), universal joint shaft
Device (6), tested turbine rotor (7), light curtain distance measuring sensor (8) and sensor mobile station (9).Wherein, the bottom of pedestal (1) is logical
It crosses foundation bolt to be fixed on solid ground or ground, preceding branch is installed and fixed successively in the table top upper edge Y-direction of pedestal (1)
Frame (2), after-poppet (3), spindle box (4).The distance between fore-stock (2) and after-poppet (3) on tested turbine rotor (7)
Axial distance between preceding axle journal (22) and rear shaft neck (23) is identical.Motor, the output shaft of motor are installed inside spindle box (4)
(5) it is connect with the rear portion of tested turbine rotor (7) by Hooks coupling universal coupling (6), turbine rotor (7) rotation is tested to drive；
It is additionally provided with angular encoder inside spindle box (4), to record the circumferential angular position of output shaft (5), and marks and is tested turbine
The serial number of each blade (20) on rotor (7) keeps each blade (20) corresponding with the circumferential angular position of output shaft (5).
Fore-stock (2) is identical with the structure of after-poppet (3), the support for providing tested turbine rotor (7) and revolution item
Part.Fore-stock (2) and after-poppet (3) include bracket base (10), axis pin (11), locking rack (12), retaining mechanism (13) and rolling
It takes turns (14).Bracket base (10) is mounted on the table top of pedestal (1), and the top of bracket base (10) is provided with 2 idler wheels
(14), to be supported on the preceding axle journal (22) of tested turbine rotor (7) or the two bottom sides of rear shaft neck (23) from below.Locking rack
(12) one end is linked together by being mounted on the axis pin (11) of bracket base (10) side with bracket base (10), locking rack
(12) it can be rotated around axis pin (11), to realize the opening and closing of locking rack (12)；The other end of locking rack (12) is equipped with
Retaining mechanism (13), for being locked with the other side of bracket base (10) after closure.It is equipped in the middle part of locking rack (12)
One idler wheel (14), for the preceding axle journal (22) of tested turbine rotor (7) pressed from above or the top of rear shaft neck (23).When
After locking rack (12) and bracket base (10) are closed and lock, 3 idler wheels (14) on bracket base (10) and locking rack (12)
It can realize the clamping and positioning to the preceding axle journal (22) or rear shaft neck (23) that are tested turbine rotor (7).
Fore-stock (2) has prodigious rigidity with after-poppet (3), and rigid support and folder are provided for tested turbine rotor (7)
Tightly, to ensure that tested turbine rotor (7) will not be sent out under revolution at a high speed state because the centrifugal load suffered by itself is unbalanced
Raw vibration, makes axis of rotation generate beat and influence measurement accuracy.Idler wheel (14) on fore-stock (2) and after-poppet (3) can be with
Using rolling bearing.
When measurement, tested turbine rotor (7) is placed on fore-stock (2) and after-poppet (3), preceding axle journal (22) is placed
On 2 idler wheels (14) on the bracket base (10) of fore-stock (2), and its rear shaft neck (23) is placed on the branch of after-poppet (3)
On 2 idler wheels (14) on frame pedestal (10), bearing height and the mutual alignment of fore-stock (2) and after-poppet (3) are adjusted separately
Relationship keeps the axis of rotation of tested turbine rotor (7) placed thereon parallel with Y-direction, by fore-stock (2) after the completion of adjustment
Merga pass retaining mechanism (13) is closed with the locking rack (12) on after-poppet (3) to be locked.
Tested turbine rotor (7) is connect by Hooks coupling universal coupling (6) with the output shaft (5) of spindle box (4).By universal joint shaft
One end of device (6) is bolted on the end face of output shaft (5) of spindle box (4), the other end be bolted on by
It surveys on the rear end face of the shaft (21) of turbine rotor (7), to enable the rotation of the output shaft (5) of spindle box (4) to be transmitted to
On tested turbine rotor (7), and the circumferential angular position of tested turbine rotor (7) passes through the week of the output shaft (5) of spindle box (4)
It is obtained to angular position, for marking the position for the blade (20) being tested on turbine rotor (7).
Side close to fore-stock (2) on pedestal (1) is equipped with sensor mobile station (9), light curtain distance measuring sensor (8)
Crossbeam (18) along Z-direction be mounted on sensor mobile station (9) on, make parallel optical screen (17) court of light curtain distance measuring sensor (8)
Blade (20) on tested turbine rotor (7).Sensor mobile station (9) can generate two maintenance and operations with Y-direction in X direction
It is dynamic, to adjust the mutual alignment relation between light curtain distance measuring sensor (8) and tested turbine rotor (7), to make tested turbine
The leaf tip potential energy of the blade (20) of rotor (7) enough enters in the measured zone of light curtain distance measuring sensor (8).Sensor moves
It is equipped with grating scale in the X-direction and Y-direction of platform (9), to ensure robust motion and the positioning of light curtain distance measuring sensor (8)
Precision.Light curtain distance measuring sensor (8) is adjusted relative to tested turbine rotor by the movement of sensor mobile station (9) in X direction
(7) radial position makes the blade (20) on tested turbine rotor (7) being capable of shield portions parallel optical screen in turning course
(17)；And light curtain distance measuring sensor (8) is adjusted along the movement of Y-direction by sensor mobile station (9) and is turned relative to tested turbine
The axial position of sub (7), to realize the static state and dynamic rotation radius at the tip position of the turbine rotor blade on different cross section
It measures.
Light curtain distance measuring sensor (8) progress data acquisition synchronous with the angular encoder that spindle box (4) is internal, so that light curtain
The output result of distance measuring sensor (8) can be corresponding with the serial number of tested blade (20).
Speed change gear is installed in spindle box (4), so that output shaft (5) exports different rotating speeds.
The structure of light curtain distance measuring sensor (8) includes light curtain transmitter (15), light curtain receiver (16) and crossbeam (18).Light
Curtain transmitter (15) and light curtain receiver (16) are separately mounted to both ends and the position face of crossbeam (18), light curtain transmitter
(15) it is L that the light source in sends out a beam width to light curtain receiver (16)0Parallel optical screen (17), and by light curtain receiver (16)
In optical sensitive device receive.
Light curtain distance measuring sensor (8) is contactless distance measuring sensor, and the measurement of distance is realized based on principle is blocked,
The region that measured zone is occupied by parallel optical screen (17), measurement range are 0~L0, L0For the overall width of parallel optical screen (17).When
When testee is not entered in measured zone, parallel optical screen (17) is not blocked, to all be received by light curtain receiver (16),
The output of light curtain distance measuring sensor (8) at this time is 0；And when testee does not enter in measured zone, if testee will be put down
Row light curtain (17) has blocked the part that width is l, to prevent this part parallel optical screen from being received by light curtain receiver (16), and
The width only not blocked by testee, which is the part of Δ, to be received by light curtain receiver (16), the sensing of light curtain ranging at this time
The output of device (8) is Δ.Therefore, the distance l of testee movement is
L=L0-Δ
Technical scheme of the present invention additionally provides a kind of quiet dynamic blade tip radius of gyration using above-mentioned measurement turbine rotor
Device carry out turbine rotor the quiet dynamic blade tip radius of gyration measure method, it is characterised in that：The step of this method, is as follows：
Step 1: before measurement starts, will be mounted on device by the normal disc measured and calibrated, and make standard round
The circumferential edges of disk enter in the measured zone of light curtain distance measuring sensor (8), at this time by the radius value of normal disc and light curtain
The output valve of distance measuring sensor (8) is subtracted each other, you can calibrate the top edge of the parallel optical screen (17) of light curtain distance measuring sensor (8) with
The distance between axis of rotation of normal disc L；
Step 2: removing normal disc, tested turbine rotor (7) is mounted on device, at this time light curtain distance measuring sensor
(8) the distance between the top edge of parallel optical screen (17) and the axis of rotation of tested turbine rotor (7) L are complete via step 1
At calibration；
Step 3: the output shaft (5) of control spindle box (4), which drives, is tested turbine rotor (7) with the speed less than 100 revs/min
Degree revolution, blade tip radius of gyration value of measured blade (20) is defined as the static leaf of tested turbine rotor (7) during this
The sharp radius of gyration.The output of synchronous acquisition light curtain distance measuring sensor (8) and the internal angular encoder of spindle box (4), when i-th
When blade (20) enters the measured zone of light curtain distance measuring sensor (8), reads its blade tip position and block parallel optical screen (17) most
The output Δ of light curtain distance measuring sensor (8) when bigi, then the radius of gyration R at the blade tip position of i-th blade (20)iFor
Ri=L+li=L+ (L0-Δi)
In above formula, liThe parallel optical screen of light curtain distance measuring sensor (8) is sheltered from for the blade tip position of i-th blade (20)
(17) width；ΔiFor the width for the parallel optical screen (17) not sheltered from by blade tip position, as light curtain distance measuring sensor (8)
Output；L0For the overall width of parallel optical screen (17), L0=li+Δi；
Step 4: the output shaft (5) of control spindle box (4) is driven with the rotating speed higher than 500 revs/min is tested turbine rotor
(7) it turns round, blade tip radius of gyration value of measured blade (20) is defined as the dynamic leaf of tested turbine rotor (7) during this
The sharp radius of gyration.The output of synchronous acquisition light curtain distance measuring sensor (8) and the internal angular encoder of spindle box (4), when i-th
When blade (20) enters the measured zone of light curtain distance measuring sensor (8), reads its blade tip position and block parallel optical screen (17) most
The output Δ of light curtain distance measuring sensor (8) when bigi, then the radius of gyration R at the blade tip position of i-th blade (20)iFor
Ri=L+li=L+ (L0-Δi)
In above formula, liThe parallel optical screen of light curtain distance measuring sensor (8) is sheltered from for the blade tip position of i-th blade (20)
(17) width；ΔiFor the width for the parallel optical screen (17) not sheltered from by blade tip position, as light curtain distance measuring sensor (8)
Output；L0For the overall width of parallel optical screen (17), L0=li+Δi。
The advantages of the present invention program, is as follows：
The blade tip position of turbine rotor blade is obtained present invention employs contactless light curtain distance measuring sensor measurement
Static state and dynamic rotation radius, and the survey of the quiet dynamic blade tip radius of gyration on turbine rotor different cross section may be implemented
Amount.The compact-sized of the present invention, strong applicability, easy to use, high degree of automation, can realize the quiet dynamic leaf of turbine rotor
The magnitude tracing of the sharp radius of gyration, and it is suitable for a plurality of types of turbine rotors, to provide a kind of measurement aeroplane engine
The method and apparatus of the quiet dynamic blade tip radius of gyration of turbine rotor in machine and gas turbine.
Description of the drawings
Fig. 1 is the overall structure diagram of the present invention；
Fig. 2 is the structural schematic diagram of the fore-stock of the present invention, after-poppet；
Fig. 3 is the structural schematic diagram of the light curtain distance measuring sensor of the present invention；
Fig. 4 is the measuring principle schematic diagram of the light curtain distance measuring sensor of the present invention；
Fig. 5 is the structural schematic diagram of tested turbine rotor；
Fig. 6 is the measuring principle schematic diagram of the present invention.
Specific implementation mode
Shown in attached drawing 1~6, this kind measures the device of the quiet dynamic blade tip radius of gyration of turbine rotor, including pedestal
(1), fore-stock (2), after-poppet (3), spindle box (4), Hooks coupling universal coupling (6), tested turbine rotor (7), light curtain ranging sensing
Device (8) and sensor mobile station (9).Wherein, the bottom of pedestal (1) is fixed on solid ground or ground by foundation bolt
On, fore-stock (2), after-poppet (3) and spindle box (4) are installed and fixed successively in the table top upper edge Y-direction of pedestal (1).Preceding branch
Axis between the distance between frame (2) and after-poppet (3) and the preceding axle journal (22) on tested turbine rotor (7) and rear shaft neck (23)
To apart from identical.Motor is installed inside spindle box (4), the output shaft (5) of motor passes through Hooks coupling universal coupling (6) and tested turbine
The rear portion of rotor (7) connects, and turbine rotor (7) rotation is tested to drive；It is additionally provided with angular coding inside spindle box (4)
Device to record the circumferential angular position of output shaft (5), and marks the serial number for each blade (20) being tested on turbine rotor (7),
Keep each blade (20) corresponding with the circumferential angular position of output shaft (5).
Fore-stock (2) is identical with the structure of after-poppet (3), fore-stock (2) and after-poppet (3) include bracket base (10),
Axis pin (11), locking rack (12), retaining mechanism (13) and idler wheel (14).Bracket base (10) is mounted on the table top of pedestal (1),
The top of bracket base (10) is provided with 2 idler wheels (14), to be supported on the preceding axle journal of tested turbine rotor (7) from below
(22) or the two bottom sides of rear shaft neck (23).One end of locking rack (12) is by being mounted on the axis pin of bracket base (10) side
(11) it links together with bracket base (10), locking rack (12) can be rotated around axis pin (11), to realize locking rack (12)
Opening and closing；The other end of locking rack (12) is equipped with retaining mechanism (13), for after closure with bracket base (10)
It locks the other side.At the middle part of locking rack (12), there are one idler wheels (14) for installation, for tested turbine rotor pressed from above
(7) top of preceding axle journal (22) or rear shaft neck (23).After locking rack (12) and bracket base (10) are closed and are locked, holder
3 idler wheels (14) on pedestal (10) and locking rack (12) can realize to be tested turbine rotor (7) preceding axle journal (22) or after
The clamping and positioning of axle journal (23).
Side close to fore-stock (2) on pedestal (1) is equipped with sensor mobile station (9), light curtain distance measuring sensor (8)
Crossbeam (18) along Z-direction be mounted on sensor mobile station (9) on.Sensor mobile station (9) can generate in X direction with the side Y
To two dimensional motion, to adjust the mutual alignment relation between light curtain distance measuring sensor (8) and tested turbine rotor (7), to
The leaf tip potential energy of the blade (20) of tested turbine rotor (7) is set enough to enter in the measured zone of light curtain distance measuring sensor (8).
It is equipped with grating scale in the X-direction and Y-direction of sensor mobile station (9).Light curtain distance measuring sensor (8) is interior with spindle box (4)
The angular encoder in portion, which synchronizes, carries out data acquisition, so that the output result of light curtain distance measuring sensor (8) can be with tested blade
(20) serial number is corresponding.
Speed change gear is installed in spindle box (4), so that output shaft (5) exports different rotating speeds.
Light curtain distance measuring sensor (8) includes light curtain transmitter (15), light curtain receiver (16) and crossbeam (18).Light curtain emits
Device (15) and light curtain receiver (16) are separately mounted to both ends and the position face of crossbeam (18), in light curtain transmitter (15)
It is L that light source sends out a beam width to light curtain receiver (16)0Parallel optical screen (17), and by the optics in light curtain receiver (16)
Sensitive Apparatus receives.
The quiet dynamic leaf of turbine rotor is carried out using the device of the quiet dynamic blade tip radius of gyration of above-mentioned measurement turbine rotor
The method that the sharp radius of gyration measures, it is characterised in that：The step of this method, is as follows：
Step 1: before measurement starts, will be mounted on device by the normal disc measured and calibrated, and make standard round
The circumferential edges of disk enter in the measured zone of light curtain distance measuring sensor (8), at this time by the radius value of normal disc and light curtain
The output valve of distance measuring sensor (8) is subtracted each other, you can calibrate the top edge of the parallel optical screen (17) of light curtain distance measuring sensor (8) with
The distance between axis of rotation of normal disc L；
Step 2: removing normal disc, tested turbine rotor (7) is mounted on device, at this time light curtain distance measuring sensor
(8) the distance between the top edge of parallel optical screen (17) and the axis of rotation of tested turbine rotor (7) L are complete via step 1
At calibration；
Step 3: the output shaft (5) of control spindle box (4), which drives, is tested turbine rotor (7) with the speed less than 100 revs/min
Degree revolution, blade tip radius of gyration value of measured blade (20) is defined as the static leaf of tested turbine rotor (7) during this
The sharp radius of gyration.The output of synchronous acquisition light curtain distance measuring sensor (8) and the internal angular encoder of spindle box (4), when i-th
When blade (20) enters the measured zone of light curtain distance measuring sensor (8), reads its blade tip position and block parallel optical screen (17) most
The output Δ of light curtain distance measuring sensor (8) when bigi, then the radius of gyration R at the blade tip position of i-th blade (20)iFor
Ri=L+li=L+ (L0-Δi)
In above formula, liThe parallel optical screen of light curtain distance measuring sensor (8) is sheltered from for the blade tip position of i-th blade (20)
(17) width；ΔiFor the width for the parallel optical screen (17) not sheltered from by blade tip position, as light curtain distance measuring sensor (8)
Output；L0For the overall width of parallel optical screen (17), L0=li+Δi；
Step 4: the output shaft (5) of control spindle box (4) is driven with the rotating speed higher than 500 revs/min is tested turbine rotor
(7) it turns round, blade tip radius of gyration value of measured blade (20) is defined as the dynamic leaf of tested turbine rotor (7) during this
The sharp radius of gyration.The output of synchronous acquisition light curtain distance measuring sensor (8) and the internal angular encoder of spindle box (4), when i-th
When blade (20) enters the measured zone of light curtain distance measuring sensor (8), reads its blade tip position and block parallel optical screen (17) most
The output Δ of light curtain distance measuring sensor (8) when bigi, then the radius of gyration R at the blade tip position of i-th blade (20)iFor
Ri=L+li=L+ (L0-Δi)
In above formula, liThe parallel optical screen of light curtain distance measuring sensor (8) is sheltered from for the blade tip position of i-th blade (20)
(17) width；ΔiFor the width for the parallel optical screen (17) not sheltered from by blade tip position, as light curtain distance measuring sensor (8)
Output；L0For the overall width of parallel optical screen (17), L0=li+Δi。
Claims (4)
1. a kind of device for the quiet dynamic blade tip radius of gyration measuring turbine rotor, it is characterised in that：The device includes pedestal
(1), fore-stock (2), after-poppet (3), spindle box (4), Hooks coupling universal coupling (6), tested turbine rotor (7), light curtain ranging sensing
Device (8) and sensor mobile station (9).Wherein, the bottom of pedestal (1) is fixed on solid ground or ground by foundation bolt
On, fore-stock (2), after-poppet (3) and spindle box (4) are installed and fixed successively in the table top upper edge Y-direction of pedestal (1).Preceding branch
Axis between the distance between frame (2) and after-poppet (3) and the preceding axle journal (22) on tested turbine rotor (7) and rear shaft neck (23)
To apart from identical.Motor is installed inside spindle box (4), the output shaft (5) of motor passes through Hooks coupling universal coupling (6) and tested turbine
The rear portion of rotor (7) connects, and turbine rotor (7) rotation is tested to drive；It is additionally provided with angular coding inside spindle box (4)
Device to record the circumferential angular position of output shaft (5), and marks the serial number for each blade (20) being tested on turbine rotor (7),
Keep each blade (20) corresponding with the circumferential angular position of output shaft (5).
Fore-stock (2) is identical with the structure of after-poppet (3), and fore-stock (2) and after-poppet (3) include bracket base (10), axis pin
(11), locking rack (12), retaining mechanism (13) and idler wheel (14).Bracket base (10) is mounted on the table top of pedestal (1), is being propped up
The top of frame pedestal (10) is provided with 2 idler wheels (14), be supported on from below tested turbine rotor (7) preceding axle journal (22) or
The two bottom sides of rear shaft neck (23).One end of locking rack (12) is by being mounted on the axis pin (11) of bracket base (10) side and propping up
Frame pedestal (10) links together, and locking rack (12) can be rotated around axis pin (11), and open and close are played with realize locking rack (12)
It closes；The other end of locking rack (12) is equipped with retaining mechanism (13), for another side chain with bracket base (10) after closure
Tightly.At the middle part of locking rack (12), there are one idler wheels (14) for installation, for the front axle of tested turbine rotor (7) pressed from above
The top of neck (22) or rear shaft neck (23).After locking rack (12) and bracket base (10) are closed and are locked, bracket base (10)
The preceding axle journal (22) or rear shaft neck (23) to being tested turbine rotor (7) can be realized with 3 idler wheels (14) on locking rack (12)
Clamping and positioning.
Side close to fore-stock (2) on pedestal (1) is equipped with sensor mobile station (9), the cross of light curtain distance measuring sensor (8)
Beam (18) is mounted on along Z-direction in sensor mobile station (9).Sensor mobile station (9) can generate in X direction with Y-direction
Two dimensional motion, to adjust the mutual alignment relation between light curtain distance measuring sensor (8) and tested turbine rotor (7), to make by
The leaf tip potential energy for surveying the blade (20) of turbine rotor (7) enough enters in the measured zone of light curtain distance measuring sensor (8).Sensing
It is equipped with grating scale in the X-direction and Y-direction of device mobile station (9).Light curtain distance measuring sensor (8) and spindle box (4) inside
Angular encoder, which synchronizes, carries out data acquisition, so that the output result of light curtain distance measuring sensor (8) can be with tested blade (20)
Serial number it is corresponding.
2. a kind of device of quiet dynamic blade tip radius of gyration measuring turbine rotor according to claim 1, feature exist
In：Speed change gear is installed in spindle box (4), so that output shaft (5) exports different rotating speeds.
3. a kind of device of quiet dynamic blade tip radius of gyration measuring turbine rotor according to claim 1, feature exist
In：Light curtain distance measuring sensor (8) includes light curtain transmitter (15), light curtain receiver (16) and crossbeam (18).Light curtain transmitter
(15) and light curtain receiver (16) is separately mounted to both ends and the position face of crossbeam (18), the light in light curtain transmitter (15)
It is L that source sends out a beam width to light curtain receiver (16)0Parallel optical screen (17), and it is quick by the optics in light curtain receiver (16)
Inductor component receives.
4. using a kind of device progress turbine turn for the quiet dynamic blade tip radius of gyration measuring turbine rotor described in claim 1
The method that the quiet dynamic blade tip radius of gyration of son measures, it is characterised in that：The step of this method, is as follows：
Step 1: before measurement starts, will be mounted on device by the normal disc measured and calibrated, and make normal disc
Circumferential edges enter in the measured zone of light curtain distance measuring sensor (8), at this time by the radius value of normal disc and light curtain ranging
The output valve of sensor (8) is subtracted each other, you can calibrates top edge and the standard of the parallel optical screen (17) of light curtain distance measuring sensor (8)
The distance between axis of rotation of disk L；
Step 2: remove normal disc, tested turbine rotor (7) is mounted on device, at this time light curtain distance measuring sensor (8)
The distance between the top edge of parallel optical screen (17) and the axis of rotation of tested turbine rotor (7) L complete to mark via step 1
It is fixed；
Step 3: the output shaft (5) of control spindle box (4), which drives, is tested turbine rotor (7) with the speed less than 100 revs/min time
Turn, blade tip radius of gyration value of measured blade (20) is defined as the static blade tip time of tested turbine rotor (7) during this
Turn radius.The output of synchronous acquisition light curtain distance measuring sensor (8) and the internal angular encoder of spindle box (4), works as i-th blade
(20) when entering the measured zone of light curtain distance measuring sensor (8), read its blade tip position block parallel optical screen (17) maximum when
Light curtain distance measuring sensor (8) output Δi, then the radius of gyration R at the blade tip position of i-th blade (20)iFor
Ri=L+li=L+ (L0-Δi)
In above formula, liThe parallel optical screen (17) of light curtain distance measuring sensor (8) is sheltered from for the blade tip position of i-th blade (20)
Width；ΔiFor the width for the parallel optical screen (17) not sheltered from by blade tip position, as light curtain distance measuring sensor (8) is defeated
Go out；L0For the overall width of parallel optical screen (17), L0=li+Δi；
Step 4: the output shaft (5) of control spindle box (4) is driven with the rotating speed higher than 500 revs/min is tested turbine rotor (7) time
Turn, blade tip radius of gyration value of measured blade (20) is defined as the dynamic blade tip time of tested turbine rotor (7) during this
Turn radius.The output of synchronous acquisition light curtain distance measuring sensor (8) and the internal angular encoder of spindle box (4), works as i-th blade
(20) when entering the measured zone of light curtain distance measuring sensor (8), read its blade tip position block parallel optical screen (17) maximum when
Light curtain distance measuring sensor (8) output Δi, then the radius of gyration R at the blade tip position of i-th blade (20)iFor Ri=L+li=
L+(L0-Δi)
In above formula, liThe parallel optical screen (17) of light curtain distance measuring sensor (8) is sheltered from for the blade tip position of i-th blade (20)
Width；ΔiFor the width for the parallel optical screen (17) not sheltered from by blade tip position, as light curtain distance measuring sensor (8) is defeated
Go out；L0For the overall width of parallel optical screen (17), L0=li+Δi。
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| CN111638048A (en) * | 2020-05-28 | 2020-09-08 | 扬州大学 | Simulation device for rubbing fault caused by thermal bending of multistage bladed disk rotor |
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| CN115741075A (en) * | 2022-12-13 | 2023-03-07 | 烟台市奥威制冷设备有限公司 | Twin-screw compressor rotor pairing tool |
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| CN115284130A (en) * | 2022-07-04 | 2022-11-04 | 青岛中科国晟动力科技有限公司 | Rotor blade tip grinding method |
| CN115741075A (en) * | 2022-12-13 | 2023-03-07 | 烟台市奥威制冷设备有限公司 | Twin-screw compressor rotor pairing tool |
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Application publication date: 20180907 |