CN106611553B - The loading device of aero-engine tester sudden unbalance - Google Patents
The loading device of aero-engine tester sudden unbalance Download PDFInfo
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- CN106611553B CN106611553B CN201710126304.6A CN201710126304A CN106611553B CN 106611553 B CN106611553 B CN 106611553B CN 201710126304 A CN201710126304 A CN 201710126304A CN 106611553 B CN106611553 B CN 106611553B
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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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Abstract
A kind of loading device of aero-engine tester sudden unbalance, one end of two clamping limbs of spring chuck are the connecting plate being connected with aero-engine tester fan disk, and the other end is clamping end；Clamping end end face is the inclined-plane with simulation blade clamping face cooperation.Backing plate is fixed in the disk of the aero-engine tester fan disk, and is bonded a side surface of the backing plate with the end face of the root end.One end of cover board is fixed on the upper surface of the backing plate, the top on simulation blade root surface of another end cap after turning to match.Invention emulates the dove-tail form tongue-and-grooves of real blade.When flying off, it is flown off with the effect of centrifugal force, without additional force, without extraneous dynamic impact, additional kinetic energy will not be introduced, to will not influence the flight attitude and flight path of broken blade, is closer to truth, and the amount of unbalance and balancing speed flown off can accurately control, and have the characteristics that of simple structure and low cost, exploitativeness is strong.
Description
Technical field
The present invention relates to aero-engine field, especially big Bypass Ratio Turbofan Engine fan blade sudden unbalance is real
The research tested.
Background technique
Since the mankind realize manned active flight technology for the first time, aircraft industry technology achieves significant progress.Aviation
" heart " of the engine as aircraft, plays a crucial role in the development process of aeronautical technology.In civilian big duct
Than in aero-engine, once engine is by foreign object (such as flying bird, stone ice cube, broken tyre block, metal parts and tool
Deng) hit occur fan blade fall off (Fan Blade Off), there is non-inclusive event, it will seriously affecting engine just
Often work, fatal threat is caused to the flight safety of aircraft, causes loss difficult to the appraisal to personnel and property.For example, broken
The component of behind the fan is flowed backward and is broken in sector-meeting with air-flow, makes engine cut-off；Fragment, which is clipped between blade tip and casing, to be turned
Subband rotation, engine fire can be caused by friction；Fan propeller can generate very big out-of-balance force, cause engine luggine
It increases；If the blade to fracture punches casing, structure and system of aircraft etc. can be also broken.
Blade is flown off and later vibration progress numerous studies are very necessary, and uneven loading device is then ground
Study carefully the prerequisite that blade is flown off.In SCI periodical " 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), imbalance load dress
Set is to beat disconnected simulation blade with adjustable spring to construct amount of unbalance.The imbalance loading device structure is more complicated, and
Repeatability is bad.
In EI periodical " flex rotor-squeeze film damper system sudden unbalance response experimental study " (aviation power
1989,4 (1): journal in 68~69.), needs to manufacture a thin neck using the simulation blade for tangentially striking off method, compares in processing
It is more complex, and repeatable bad, higher cost；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) it is middle fixed using a pin
Position, but collision impact is had, simulation effect is bad, is unable to accurate simulation blade amount of unbalance.It is therefore, a kind of low in cost,
Favorable repeatability and can accurate simulation blade fly off revolving speed and the uneven loading device of amount of unbalance is of great significance.
Summary of the invention
For overcome the shortcomings of it is existing in the prior art structure is complicated, repeatability it is poor, the invention proposes a kind of aviations
The loading device of engine test device sudden unbalance.
The present invention includes cover board, backing plate and spring chuck, in which: 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 clamping end；The clamping end
End face is the inclined-plane with simulation blade clamping face cooperation.The backing plate is fixed on the disk of the aero-engine tester fan disk
On, and it is bonded a side surface of the backing plate with the end face of the root end.One end of the cover board 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 board after turning to match.
Two clamping arm configurations in the spring chuck are identical, contrary.The inclined-plane of the clamping end end face is along folder
The length direction of gripping arm extends, and forms wedge angle in the clamping end.
The middle parts of two clamping limbs in the spring chuck is bent, and the angle of bending is to meet the installation of the spring chuck
?.Side surface of the clamping end of clamping limb after complete perpendicular to the simulation blade.
The spring chuck is in the position of the aero-engine tester fan disk disk with matched simulation leaf
And the edge of the fan disk is concordant or slightly the edge beyond fan disk is advisable for the blade tip of piece.
Both side surface at the simulation blade root is machined with the groove of " V " shape, the interior table of the groove two sides respectively
Face forms the clamping face.
The present invention has low in cost a, favorable repeatability, easy to implement and can accurately simulate blade flies off revolving speed
And the features such as amount of unbalance.The leaf abscission, fracture experiment and survey of big Bypass Ratio Turbofan Engine are especially for aero-engine
Examination provides key technique, such that a large amount of low in cost and repeatable strong sudden unbalance is tested, from
And be that research fan blade falls off and provides more experimental verifications, idea and method is provided for simulated experiment, for engine
Fusing and load shedding after sudden unbalance provide model basis, it may be said that are the prerequisites of sudden unbalance experiment expansion.
The uneven loading device that the present invention designs includes several parts such as spring chuck, simulation blade, cover board, backing plate.Bullet
Property fixture, cover board be bolted on disk, simulation blade is fixed on to be made of spring chuck, radial cover board, axial cover board
In tongue-and-groove.Here fixture, cover board and simulation blade are process with steel.
When revolving speed is lower, centrifugal force is smaller, and elastic fixture then will limit blade, and so that it will not fly out；When reaching
When design speed, simulation blade centrifugal force is larger, and fixture cannot provide enough centripetal force, and simulation blade overcomes centripetal force, from
It is detached from device.The device passes through radius where changing the simulation quality of blade, center of gravity, tenon width, tenon apex angle (or tenon
Semiapex angle) etc. parameters reach default unbalanced load and unbalanced load load revolving speed.
Compared with prior art, the beneficial effect that the present invention obtains is:
1. simulating blade in uneven loading device and spring chuck being intercoupled before flying out with tongue-and-groove, from largely
On simulate the dove-tail form tongue-and-groove of real blade.It when flying off, is flown off with the effect of centrifugal force, no additional force, no extraneous moves
Power impact, will not introduce additional kinetic energy, to will not influence the flight attitude and flight path of broken blade, with truth
It is closer to；
2. verifying by many experiments, the experiment worked it out coincide compared with theory flies off revolving speed, as shown in fig. 7, dissipating
Point represents experiment revolving speed, solid line representation theory revolving speed, and dotted line is 5% limits of error up and down of theoretical rotational speed.It can be clearly seen that
Experiment flies off revolving speed, and error is within 5% compared with theory flies off revolving speed, and data stabilization.It is demonstrated experimentally that applied mould
The rotor unbalance loading device that quasi- blade is flown off has preferable repeatability and a reliability, and the amount of unbalance flown off and
Balancing speed can accurately control；
3. structure is simple, low in cost, exploitativeness is strong.
Detailed description of the invention
Fig. 1 is the cooperation schematic diagram of the present invention with model rotor tester fan disk.
Fig. 2 is structural schematic diagram of the invention.
Fig. 3 is the A-A direction view of Fig. 2.
Fig. 4 is the cooperation schematic diagram for removing cover board.
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 revolving speed.
Fig. 7 is that experimental verification of the invention flies off revolving speed and theory flies off revolving speed comparison diagram.In figure:
1. spring chuck；2. fan disk；3. counterweight；4. simulating blade；5. cover board；6. backing plate；7. testing revolving speed；
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 loading device, including spring chuck 1, simulation blade 4, cover board 5 and backing plate 6.This
Embodiment is applied on the model rotor tester of Northwestern Polytechnical University, for providing amount of unbalance.
The imbalance loading device includes cover board 5, backing plate 6 and spring chuck 1, in which: the spring chuck includes two
A clamping limb, one end of each clamping limb are connecting plate, and the other end is clamping end；The end face of the clamping end is and simulation blade
The inclined-plane of 4 clamping faces cooperation.The backing plate 6 is located at blade root one end of the simulation blade, and is bonded with the end face of the root end.Institute
The one end for stating cover board 5 is fixed on the upper surface of the backing plate 6.
Two clamping arm configurations in the spring chuck 1 are identical, contrary.Two clamping limbs are that cross section is square
Shape it is rod-shaped.There is screw hole 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 bending in the middle part of rod-shaped clamping limb, and the angle of bending is to meet the installation of the spring chuck i.e.
It can.Side surface of the clamping end of clamping limb after bending perpendicular to the simulation blade.The end face of the clamping end is and simulation
The inclined-plane of the clamping face cooperation of vane side surface, the inclined-plane extend along the length direction of clamping limb, form point in the clamping end
Angle.
Both side surface difference to enable the simulation blade 4 to cooperate with the present embodiment, at the simulation blade root
It is machined with the groove of " V " shape, the two sides inner surface of the groove forms the clamping face.
In use, the linkage section of the spring chuck 1 is fixed in the disk of fan disk, by the simulation blade root
The " V " shape slot at place and two clamping ends of the spring chuck cooperate, and the wedge angle at described two gripping arm ends is made to be inserted into " V "
In shape slot, and it is bonded the inclined-plane of each clamping end 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 disk of the fan disk, and makes the backing plate
A side surface with simulation blade root end face be bonded.One end of cover board 5 is fixed on to the upper surface of the backing plate 6, and is made
Another end cap of the cover board 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
Radial direction is flown off.And the simulation blade is controlled by cover board 5 and flies off direction, and avoids the simulation blade in the fan disk slow-speed of revolution
Under axial direction fall off.
Fig. 5 and Fig. 6 is 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 centrifugal force F is less than clamping force Q in the slow-speed of revolution, blade be will not fall off.When turn
Speed gradually rises, and centrifugal force is increasing, and when reaching high revolving speed shown in fig. 6, the spacing on 1 top of spring chuck is gradually opened,
Blade will be flown off.When revolving speed continues to rise, the top distance of spring chuck 1 is greater than the bottom end tenon width W of simulation blade 4.
Blade is flown off, and spring chuck returns to original state under the return action of elastic force, will not be damaged, and can be real next time
It is continued to use in testing.
Fig. 7 is that the experimental verification revolving speed that flies off of the invention flies off revolving speed comparison diagram with theory.The revolving speed 7 that many experiments obtain
It is flown off compared with revolving speed 8 with theoretical, all within 5% limits of error 9 of theoretical rotational speed.
Spring chuck 1, cover board 5 and backing plate 6 in the uneven loading device of the present embodiment can be manufactured using steel.
The difference that simulation blade according to revolving speed is flown off, can then fly off quality uses steel and aluminium.
The present embodiment has very big representativeness and authenticity, and cost in terms of simulating actual engine leaf abscission
It is cheap, it is simple to manufacture, good reliability, repeatability is strong, is the prerequisite carried out in sudden unbalance experiment.Aviation is sent out
The experimental study of motivation is of great significance.
Claims (2)
1. a kind of loading device of aero-engine tester sudden unbalance, which is characterized in that including cover board, backing plate and elasticity
Fixture, in which: the spring chuck includes two clamping limbs, and one end of each clamping limb is and aero-engine tester fan
The connected connecting plate of disk, the other end is clamping end；The end face of the clamping end is the inclined-plane with simulation blade clamping face cooperation；Institute
It states backing plate to be fixed in the disk of the aero-engine tester fan disk, and makes a side surface and the simulation leaf of the backing plate
The end face of the root end of piece is bonded；One end of the cover board is fixed on the upper surface of the backing plate, and makes another end cap of the cover board
The top on the simulation blade root surface after turning to match；
Two clamping arm configurations in the spring chuck are identical, contrary；The inclined-plane of the clamping end end face is along clamping limb
Length direction extend, form wedge angle in the clamping end；
Both side surface at the simulation blade root is machined with the groove of " V " shape, the inner surface shape of the groove two sides respectively
At the clamping face；
The middle part of two clamping limbs in the spring chuck is bent, and the angle of bending is to meet the installation of the spring chuck i.e.
It can；Side surface of the clamping end of clamping limb after bending perpendicular to the simulation blade.
2. the loading device of aero-engine tester sudden unbalance as described in claim 1, which is characterized in that the elasticity
Fixture is in the position of the aero-engine tester fan disk disk so that the blade tip and the wind of matched simulation blade
The edge of fanning tray is concordant, or slightly the edge beyond fan disk is advisable.
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 |
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| Publication Number | Publication Date |
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| CN106611553A CN106611553A (en) | 2017-05-03 |
| CN106611553B true CN106611553B (en) | 2019-04-19 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN111947835B (en) * | 2020-08-17 | 2022-06-07 | 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 |
| CN113280979B (en) * | 2021-06-21 | 2022-07-22 | 中国民航大学 | Sudden-load unbalance applying device for simulating blade flying off |
| 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 |
| FR3132350B1 (en) | 2022-02-02 | 2023-12-22 | Airbus Helicopters | rotor unbalance simulator and test bench equipped with this simulator |
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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 |
| CN203627331U (en) * | 2013-10-12 | 2014-06-04 | 上海马陆日用友捷汽车电气有限公司 | Fan blade balancing clamp |
| CN105449484A (en) * | 2014-08-28 | 2016-03-30 | 中航商用航空发动机有限责任公司 | Slip ring electrical feed-through device and engine |
| 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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2017
- 2017-03-06 CN CN201710126304.6A patent/CN106611553B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN203627331U (en) * | 2013-10-12 | 2014-06-04 | 上海马陆日用友捷汽车电气有限公司 | Fan blade balancing clamp |
| CN105449484A (en) * | 2014-08-28 | 2016-03-30 | 中航商用航空发动机有限责任公司 | Slip ring electrical feed-through device and engine |
| 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 |
| 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 |
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| CN106611553A (en) | 2017-05-03 |
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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 |
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