CN106611553A - Loading device for sudden unbalance of aeroengine experimental instrument - Google Patents
Loading device for sudden unbalance of aeroengine experimental instrument Download PDFInfo
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- CN106611553A CN106611553A CN201710126304.6A CN201710126304A CN106611553A CN 106611553 A CN106611553 A CN 106611553A CN 201710126304 A CN201710126304 A CN 201710126304A CN 106611553 A CN106611553 A CN 106611553A
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- clamping
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- blade
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- backing plate
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B25/00—Models for purposes not provided for in G09B23/00, e.g. full-sized devices for demonstration purposes
- G09B25/02—Models for purposes not provided for in G09B23/00, e.g. full-sized devices for demonstration purposes of industrial processes; of machinery
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- Business, Economics & Management (AREA)
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- Theoretical Computer Science (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a loading device for the sudden unbalance of an aeroengine experimental instrument. One end of each of two clamping arms of an elastic clamping tool is a connection plate which is fixedly connected with a fan disc of the aeroengine experimental instrument, and the other ends of the two clamping arms are clamping ends. The end faces of the clamping ends are inclined surfaces matched with the clamping surface of a simulation vane. A backing plate is fixed on the surface of the fan disc of the aeroengine experimental instrument, and one side surface of one backing plate is enabled to be attached to an end face of the root end of the vane. One end of the cover plate is fixed on the upper surface of the backing plate, and the other end covers the surface of the root of the simulation vane after rotating fit. The device simulates a dovetail mortise groove of a real vane. During flying-off, the device achieves the flying-off through a centrifugal force, and there is no additional force, no external impact force and no additional kinetic energy, thereby causing no impact on the flying posture and flying track of a broken vane. Therefore, the simulation condition is closer to the real condition, and the amount of flying-off unbalance and a balance speed can be accurately controlled. Moreover, the device is simple in structure, is low in cost, and is high in feasibility.
Description
Technical field
The present invention relates to aero-engine field, particularly big Bypass Ratio Turbofan Engine fan blade sudden unbalance reality
The research tested.
Background technology
Since manned active flight technology is realized first from the mankind, aircraft industry technology achieves significant progress.Aviation
Electromotor plays vital effect in the evolution of aeronautical technology as " heart " of aircraft.In civilian big duct
Than, in aero-engine, electromotor once suffers foreign object (such as flying bird, stone ice cube, broken tyre block, metal parts and instrument
Deng) clash into and fan blade occurs come off (Fan Blade Off), there is non-inclusive event, it will just having a strong impact on electromotor
Often work, fatal threat is caused to the flight safety of aircraft, loss difficult to the appraisal is caused to personnel and property.For example, it is broken
Sector-meeting breaks the part of fan with air-flow flows backward, makes engine cut-off；Fragment is clipped between blade tip and casing and is turned
Subband rotation, can cause engine fire by friction；Fan propeller can produce very big out-of-balance force, cause engine luggine
Increase；If the blade for fractureing punches casing, structure and system of aircraft etc. can be also broken.
Blade is flown off and later vibration to carry out numerous studies be very necessary, and uneven charger then grinds
Study carefully the prerequisite that blade flies off.In SCI periodicals " Theoretical and experimental investigation on
the sudden unbalance and rub-impact in rotor system caused by blade off”
In (Mechanical Systems and Signal Processing 76-77 (2016) 111-135), uneven loading dress
Put is to beat disconnected simulation blade to construct amount of unbalance with adjustable spring.The uneven charger structure is more complicated, and
It is repeatable bad.
In EI periodicals " flex rotor-squeeze film damper system sudden unbalance response experimentation " (aviation power
Journal, 1989,4 (1)：68～69.) in, using the simulation blade for tangentially striking off method need manufacture a thin neck, compare in processing
It is more complicated and repeatable bad, it is relatively costly；In periodical " Transient Vibration of High Speed
Lightweight Rotor Due to Sudden Imbalance”(Transactions of the Japan Society
Of Mechanical Engineers Series C, 1990, Vol.56 (522), pp.275-283) used in pin it is fixed
Position, but collision impact is had, and simulation effect is bad, it is impossible to accurate simulation blade amount of unbalance.It is therefore, a kind of with low cost,
Favorable repeatability and can accurate simulation blade fly off rotating speed and the uneven charger of amount of unbalance is significant.
The content of the invention
Poor to overcome the shortcomings of complex structure present in prior art, repeatability, the present invention proposes a kind of aviation
The charger of engine test device sudden unbalance.
The present invention includes cover plate, backing plate and spring chuck, wherein：The spring chuck includes two clamping limbs, each to clamp
One end of arm is the connecting plate being connected with aero-engine tester fan disk, and the other end is bare terminal end；The bare terminal end
End face is the inclined-plane coordinated with simulation blade clamping face.The backing plate is fixed on the card of the aero-engine tester fan disk
On, and make a side surface of the backing plate fit with the end face of the root end.One end of the cover plate is fixed on the upper of the backing plate
Surface, and make the top on simulation blade root surface of another end cap of the cover plate after turning to match somebody with somebody.
Two clamping arm configurations in the spring chuck are identical, in opposite direction.The inclined-plane of the bare terminal end end face is along folder
The length direction of gripping arm extends, and defines wedge angle in the bare terminal end.
The middle part bending of two clamping limbs in the spring chuck, the angle of bending is meeting the installation of the spring chuck
.Side surface of the bare terminal end of the clamping limb after complete perpendicular to the simulation blade.
The spring chuck is in the position of the aero-engine tester fan disk card with matched simulation leaf
The blade tip of piece is concordant with the edge of the fan disk or is slightly advisable beyond the edge of fan disk.
The groove of " V " shape, the interior table of the groove both sides are machined with respectively in the both side surface simulated at blade root
Face defines described clamping face.
The present invention has with low cost a, favorable repeatability, it is easy to implement and can accurately simulate blade fly off rotating speed
And the features such as amount of unbalance.Leaf abscission, fracture experiment and the survey of big Bypass Ratio Turbofan Engine are particularly for aero-engine
Examination is there is provided guardian technique so that substantial amounts of with low cost and repeatable strong sudden unbalance experiment is possibly realized, from
And be that research fan blade comes off there is provided more experimental verifications, thinking and method are provided for simulation experiment, be electromotor
Fusing after sudden unbalance provides model basis with load shedding, it may be said that be the prerequisite of sudden unbalance experiment expansion.
The uneven charger of present invention design includes several parts such as spring chuck, simulation blade, cover plate, backing plate.Bullet
Property fixture, cover plate be bolted on disk, simulate blade and be fixed on and be made up of spring chuck, radial direction cover plate, axial cover plate
In tongue-and-groove.Here fixture, cover plate and simulation blade are processed with steel.
When rotating speed is relatively low, centrifugal force is less, and elastic fixture can then limit blade makes which not fly out；When reaching
During design speed, simulation blade centrifugal force is larger, and fixture can not provide enough centripetal forces, and simulation blade overcomes centripetal force, from
Depart from device.The device is by changing the simulation quality of blade, center of gravity place radius, tenon width, tenon drift angle (or tenon
Semiapex angle) etc. parameter reach default unbalanced load and unbalanced load loading rotating speed.
Compared with prior art, the beneficial effect of present invention acquirement is：
1. simulate blade in uneven charger to intercouple with tongue-and-groove before flying out with spring chuck, from largely
On simulate the dove-tail form tongue-and-groove of real blade.When flying off, flown off with the effect of centrifugal force, without additional force, moved without extraneous
Power is impacted, and will not introduce extra kinetic energy, so as to not interfere with the flight attitude and flight path of broken blade, with truth
It is closer to；
2. verify through many experiments, the experiment worked it out flies off rotating ratio with theory and relatively coincide, as shown in fig. 7, dissipating
Point represents experiment rotating speed, solid line representation theory rotating speed, up and down 5% limits of error of the dotted line for theoretical rotational speed.Can be clearly seen that
Experiment flies off rotating speed and flies off rotating speed phase ratio error within 5% with theory, and data stabilization.It is demonstrated experimentally that the mould applied
Intend the rotor unbalance charger that flies off of blade and there is preferably repeatable and reliability, and the amount of unbalance for flying off and
Balancing speed accurately can be controlled；
3. simple structure, with low cost, and exploitativeness is strong.
Description of the drawings
Fig. 1 is the cooperation schematic diagram of the present invention and model rotor tester fan disk.
Fig. 2 is the structural representation of the present invention.
Fig. 3 is the A-A direction views of Fig. 2.
Fig. 4 is the cooperation schematic diagram for removing cover plate.
Fig. 5 is the stress diagram that blade is simulated in the slow-speed of revolution.
Fig. 6 is the stress diagram that blade is simulated in high rotating speed.
Fig. 7 is that the experimental verification of the present invention flies off rotating speed and theory flies off rotating speed comparison diagram.In figure：
1. spring chuck；2. fan disk；3. counterweight；4. blade is simulated；5. cover plate；6. backing plate；7. rotating speed is tested；
8. theoretical rotational speed；9. 5% limits of error up and down of theoretical rotational speed.
Specific embodiment
The present embodiment is a kind of uneven charger, including spring chuck 1, simulation blade 4, cover plate 5 and backing plate 6.This
Embodiment is applied on the model rotor tester of Northwestern Polytechnical University, for providing amount of unbalance.
The uneven charger includes cover plate 5, backing plate 6 and spring chuck 1, wherein：The spring chuck includes two
Individual clamping limb, one end of each clamping limb are connecting plate, and the other end is bare terminal end；The end face of the bare terminal end is and simulates blade
The inclined-plane that 4 clamping faces coordinate.The backing plate 6 is located at blade root one end of the simulation blade, and fits with the end face of the root end.Institute
The one end for stating cover plate 5 is fixed on the upper surface of the backing plate 6.
Two clamping arm configurations in the spring chuck 1 are identical, in opposite direction.Two clamping limbs are cross section for square
Shape it is shaft-like.There is screw on the connecting plate of the spring chuck one end.To enable the spring chuck to be easily fixed on simulation
The fan panel surface of tester, makes to bend in the middle part of shaft-like clamping limb, the angle of bending with meet the spring chuck installation i.e.
Can.Side surface of the bare terminal end of the clamping limb after bending perpendicular to the simulation blade.The end face of the bare terminal end is and simulation
The inclined-plane that the clamping face of vane side surface coordinates, the inclined-plane extend along the length direction of clamping limb, define point in the bare terminal end
Angle.
Both side surface difference to enable the simulation blade 4 and the present embodiment to coordinate, at the simulation blade root
The groove of " V " shape is machined with, the both sides inner surface of the groove defines described clamping face.
During use, the linkage section of the spring chuck 1 is fixed in the card of fan disk, by the simulation blade root
The " V " shape groove at place is coordinated with two bare terminal ends of the spring chuck, makes the wedge angle at described two gripping arm ends insert " V "
In shape groove, and the inclined-plane of each bare terminal end is made to fit with the clamping face of simulation blade respectively；The blade tip and the wind of the simulation blade
The edge of fanning tray is concordant or slightly exceeds the edge of fan disk.Backing plate 6 is fixed in the card of the fan disk, and makes the backing plate
A side surface with simulation blade root end face fit.One end of cover plate 5 is fixed on into the upper surface of the backing plate 6, and is made
Another end cap of the cover plate is in the simulation blade root surface.
When the fan disk high-speed rotation, the simulation blade under the influence of centrifugal force, can be along the fan disk
Radially fly off.And the simulation blade is controlled by cover plate 5 fly off direction, and the simulation blade is avoided in the fan disk slow-speed of revolution
Under axial direction come off.
Fig. 5 and Fig. 6 are that the present embodiment simulates leaf position view in different rotating speeds.The design for having reacted the present embodiment is former
Manage and fly off scheme.In fig. 5 it can be seen that in the slow-speed of revolution, centrifugal force F is less than clamping force Q, blade will not fall off.When turn
Speed gradually rises, and centrifugal force is increasing, and when reaching the high rotating speed shown in Fig. 6, the spacing on 1 top of spring chuck is gradually opened,
Blade will fly off.When rotating speed continues to rise, the top distance of spring chuck 1 is more than the bottom tenon width W for simulating blade 4.
Blade flies off, and spring chuck returns to original state under the return action of elastic force, will not damage, and can be upper once real
It is continuing with testing.
Fig. 7 is that the rotating speed that flies off of the experimental verification present invention flies off rotating speed comparison diagram with theory.The rotating speed 7 that many experiments are obtained
With it is theoretical fly off rotating speed 8 compared with, all within 5% limits of error 9 of theoretical rotational speed.
Spring chuck 1, cover plate 5 and backing plate 6 in the uneven charger of the present embodiment can be manufactured using steel.
Simulation blade then according to rotating speed is flown off, can fly off the difference of quality and use steel and aluminium.
The present embodiment has very big representative and verity, and cost in terms of simulation actual engine leaf abscission
It is cheap, it is simple to manufacture, good reliability, it is repeatable strong, it is to carry out the prerequisite in sudden unbalance experiment.For aviation is sent out
The experimentation of motivation is significant.
Claims (5)
1. a kind of charger of aero-engine tester sudden unbalance, it is characterised in that including cover plate, backing plate and elasticity
Fixture, wherein：The spring chuck includes two clamping limbs, and one end of each clamping limb is and aero-engine tester fan
The connecting plate that disk is connected, the other end is bare terminal end；The end face of the bare terminal end is the inclined-plane coordinated with simulation blade clamping face；Institute
State backing plate to be fixed in the card of the aero-engine tester fan disk, and make a side surface and the root end of the backing plate
End face laminating；One end of the cover plate is fixed on the upper surface of the backing plate, and makes another end cap of the cover plate after turning to match somebody with somebody
The top on simulation blade root surface.
2. the charger of aero-engine tester sudden unbalance as claimed in claim 1, it is characterised in that the elasticity
Two clamping arm configurations in fixture are identical, in opposite direction；Prolong along the length direction of clamping limb on the inclined-plane of the bare terminal end end face
Stretch, wedge angle is defined in the bare terminal end.
3. the as claimed in claim 1 charger of aero-engine tester sudden unbalance, it is characterised in that in the mould
Intend the groove that the both side surface at blade root is machined with " V " shape respectively, the inner surface of the groove both sides defines described folder
Hold face.
4. the charger of aero-engine tester sudden unbalance as claimed in claim 1, it is characterised in that the elasticity
Fixture is in the position of the aero-engine tester fan disk card with the blade tip and the fan of matched simulation blade
Edge of the edge of disk concordantly or slightly beyond fan disk is advisable.
5. the charger of aero-engine tester sudden unbalance as claimed in claim 2, it is characterised in that the elasticity
The middle part bending of two clamping limbs in fixture, the angle of bending is meeting the installation of the spring chuck；Folder after complete
Side surface of the bare terminal end of gripping arm perpendicular to the simulation blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710126304.6A CN106611553B (en) | 2017-03-06 | 2017-03-06 | The loading device of aero-engine tester sudden unbalance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710126304.6A CN106611553B (en) | 2017-03-06 | 2017-03-06 | The loading device of aero-engine tester sudden unbalance |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106611553A true CN106611553A (en) | 2017-05-03 |
| CN106611553B CN106611553B (en) | 2019-04-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710126304.6A Active CN106611553B (en) | 2017-03-06 | 2017-03-06 | The loading device of aero-engine tester sudden unbalance |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109580138A (en) * | 2018-12-05 | 2019-04-05 | 南京航空航天大学 | The loading device and test method of aeroengine rotor testing stand sudden unbalance |
| CN111947836A (en) * | 2020-08-17 | 2020-11-17 | 哈电发电设备国家工程研究中心有限公司 | Test device and method for simulating sudden unbalance fault of rotor system |
| CN111947835A (en) * | 2020-08-17 | 2020-11-17 | 哈电发电设备国家工程研究中心有限公司 | Sudden unbalance fault simulation device and method applying rotating machinery |
| CN113280979A (en) * | 2021-06-21 | 2021-08-20 | 中国民航大学 | Sudden-load unbalance applying device for simulating blade flying off |
| CN114373361A (en) * | 2022-01-11 | 2022-04-19 | 安胜（天津）飞行模拟系统有限公司 | Method for simulating bird strike and volcanic ash scenes on flight simulator |
| FR3132350A1 (en) * | 2022-02-02 | 2023-08-04 | Airbus Helicopters | rotor unbalance simulator and test bench equipped with this simulator |
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| CN105510044A (en) * | 2015-12-31 | 2016-04-20 | 苏州东菱科技有限公司 | High-speed rotor blade flying-off test device and test method |
| CN105547462A (en) * | 2015-12-16 | 2016-05-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Radial vibration measuring method of engine rotor |
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| JPS60116899A (en) * | 1983-11-28 | 1985-06-24 | Toshiba Corp | Runner |
| CN103534443A (en) * | 2011-05-17 | 2014-01-22 | 斯奈克玛 | Turbine engine impeller |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109580138A (en) * | 2018-12-05 | 2019-04-05 | 南京航空航天大学 | The loading device and test method of aeroengine rotor testing stand sudden unbalance |
| CN109580138B (en) * | 2018-12-05 | 2020-09-25 | 南京航空航天大学 | Loading device and testing method for sudden unbalance of aero-engine rotor test bed |
| CN111947836A (en) * | 2020-08-17 | 2020-11-17 | 哈电发电设备国家工程研究中心有限公司 | Test device and method for simulating sudden unbalance fault of rotor system |
| CN111947835A (en) * | 2020-08-17 | 2020-11-17 | 哈电发电设备国家工程研究中心有限公司 | Sudden unbalance fault simulation device and method applying rotating machinery |
| CN111947836B (en) * | 2020-08-17 | 2022-05-27 | 哈电发电设备国家工程研究中心有限公司 | Test device and method for simulating sudden unbalance fault of rotor system |
| CN113280979A (en) * | 2021-06-21 | 2021-08-20 | 中国民航大学 | Sudden-load unbalance applying device for simulating blade flying off |
| CN114373361A (en) * | 2022-01-11 | 2022-04-19 | 安胜（天津）飞行模拟系统有限公司 | Method for simulating bird strike and volcanic ash scenes on flight simulator |
| CN114373361B (en) * | 2022-01-11 | 2023-11-10 | 安胜（天津）飞行模拟系统有限公司 | Method for simulating bird strike and volcanic ash scene on flight simulator |
| FR3132350A1 (en) * | 2022-02-02 | 2023-08-04 | Airbus Helicopters | rotor unbalance simulator and test bench equipped with this simulator |
| EP4224133A1 (en) | 2022-02-02 | 2023-08-09 | Airbus Helicopters | Unbalance simulator of a rotor and test bench with this simulator |
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| CN106611553B (en) | 2019-04-19 |
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Inventor after: Wang Siji Inventor after: Liao Mingfu Inventor after: Hou Lizhen Inventor after: Wang Yanai Inventor after: Jia Runtian Inventor before: Wang Siji Inventor before: Liao Mingfu Inventor before: Hou Lizhen Inventor before: Wang Yankai Inventor before: Jia Runtian |