CN106441902A - Sub-scale simulated aero-engine rotation test device - Google Patents
Sub-scale simulated aero-engine rotation test device Download PDFInfo
- Publication number
- CN106441902A CN106441902A CN201610857702.0A CN201610857702A CN106441902A CN 106441902 A CN106441902 A CN 106441902A CN 201610857702 A CN201610857702 A CN 201610857702A CN 106441902 A CN106441902 A CN 106441902A
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- simulated
- bearing
- support plate
- aero
- rotating shaft
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- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
Abstract
The invention discloses a sub-scale simulated aero-engine rotation test device which comprises simulated casings, a simulated support plate, a simulated rotor shaft, a simulated blade disc, a simulated drum, a front fulcrum bearing, a middle fulcrum bearing, a rear fulcrum bearing and simulated front and rear mounting sections. The sub-scale simulated aero-engine rotation test device is driven by a motor to rotate through a set of breaking shaft protection devices. The simulated casings are connected via mounting side bolts. The simulated support plate is in welded connection with the simulated casings. The simulated blade disc is connected with a mounting plate and a shaft via bolts. The simulated drum is connected with the simulated support plate via bolts. The simulated front mounting section is connected with a rigid mounting base via bolts and a suspend rod. The simulated rear mounting section is connected with the rigid mounting base via bolts and a hinge. The various components of the sub-scale simulated aero-engine rotation test device can be disassembled and assembled to meet the needs of different tests.
Description
Technical field
The present invention relates to aero-engine shock dynamics and seaworthiness airworthiness compliance technical field.
Background technology
Aero-engine is operationally possible to meet with the shock of exotic such as flying bird, hail it is also possible to meet with rotor
Blade failure and occur blade fly accident therefore, because foreign object strike or blade fly to lose the steady operation shape destroying aero-engine
State, moment can produce great sudden unbalance load, in design and use aero-engine it is necessary to consider that such impact carries
The impact that lotus works to engine health.The foreign object ingestions adopting actual engine and blade fly mistake test and come more in the world at present
The safety when meeting with above-mentioned sudden applied load for the checking electromotor, costs dearly.Meet with impact load for exploring aero-engine
Structure safety analytical method during lotus is it is necessary to using test, the means such as analyze, verify, accordingly, it would be desirable to develop a kind of new test
Device, to solve the above problems, partly substitutes the overall test of actual engine.
Content of the invention
For the problems referred to above and Shortcomings, the invention provides test battery device, this device can be simulated aviation and be sent out
The primary load bearing of motivation rotor and main force transferring structure, carry out foreign object strike and fly to lose test with simulation blade, contribute to exploration aviation and send out
The structure safety analytical when meeting with foreign object strike or blade flies the sudden applied loads such as mistake for the motivation.
For achieving the above object, present invention Asia scale simulation aero-engine rotation test device can adopt following technical side
Case：
A kind of Asia scale simulation aero-engine rotation test device, including rotating shaft, the motor of drive shaft rotation, is located at
The simulation leaf dish of rotating shaft front end, the front fulcrum bearing being arranged in rotating shaft, the front simulation drum barrel being installed on front fulcrum bearing, peace
The central bearing point bearing being contained in rotating shaft, the support plate being installed on central bearing point bearing, oneself front edge of board extend and surround simulation leaf
The front housing of disk, the rear fulcrum bearing being arranged in rotating shaft, the rear simulation drum barrel being installed on rear fulcrum bearing, it is fixedly connected
Plate and the rear rear housing simulating drum barrel；Rear housing surrounds the rotating shaft of part；Described central bearing point bearing be located at front fulcrum bearing and after
Between fulcrum roller；The rear end of front housing is fixed on the front surface of support plate；Described front simulation drum barrel be provided with first sensor,
Support plate is provided with second sensor, front housing outer surface is provided with 3rd sensor, rear housing outer surface is provided with the 4th sensor.
Pass through in the present invention to arrange forward and backward casing, support plate, the rotating shaft of model rotor axle, simulation leaf dish, forward and backward drum barrel etc.
Crucial load and force transferring part, realize the structure of model rotor structural aeronautical electromotor, and all kinds of shock dynamics of convenient installation
Parameter sensors, to meet the demand of different tests test.Foreign object strike can be carried out and simulation blade flies to lose test, contribute to
Explore the structure safety analytical when meeting with foreign object strike or blade flies the sudden applied loads such as mistake for the aero-engine.
And the test method in the present invention can employ the following technical solutions：
When carrying out impact strength test, first, second, third, fourth sensor, all using foil gauge, obtains four positions
The deformation put and stressing conditions；
When carrying out vibration test, first, second, third, fourth sensor, all using acceleration of vibration meter, obtains machine
Casket, drum barrel and the vibration characteristics propping up Board position；
When bird is hit, ice hits test for development, second sensor uses foil gauge, and first, the three, the 4th sensors use
Accelerometer measures, and obtains the vibratory response under temporary impact load；
When carrying out blade loss test, third and fourth sensor uses foil gauge, and first, second sensor uses and adds
Velometer measures, and obtains at deformation and the strain, and drum barrel and support plate at casing due to shaking that unbalanced load leads to
Dynamic.
Above-mentioned test method, by the structure setting of sub- scale simulation aero-engine rotation test device, Neng Gou
Line sensor is flexibly entered according to different tests measurement data to be obtained at first, second, third, fourth sensor
Setting, can carry out different tests on same assay device, substantially increase the versatility of assay device.
Brief description
Fig. 1 is the structural representation that the present invention simulates aero-engine rotation test device.
Specific embodiment
Below in conjunction with the accompanying drawings, be further elucidated with the present invention it should be understood that these embodiments be merely to illustrate the present invention and without
In the scope limiting the controlled hail discharger of aero-engine environmental test of the present invention, after having read the present invention, this
The modification of the various equivalent form of values to the present invention for the skilled person all falls within the application claims limited range.
Refer to shown in Fig. 1, the present invention discloses a kind of Asia scale simulation aero-engine rotation test device, including rotating shaft
9th, the motor 13 of drive shaft 9 rotation, the simulation leaf dish 21 being located at rotating shaft 9 front end, the front fulcrum bearing being arranged in rotating shaft 9
20th, the front simulation drum barrel 19 being installed on front fulcrum bearing 20, the central bearing point bearing 17 being arranged in rotating shaft 9, be installed in
Put the support plate 18 on bearing 17, extend and surround the front housing 1 of simulation leaf dish 21 from support plate 18 front end, be arranged in rotating shaft 9
Rear fulcrum bearing 14, the rear simulation drum barrel 10 being installed on rear fulcrum bearing 14, be fixedly connected support plate 18 and afterwards simulate drum barrel
10 rear housing 16.Rear housing 16 surrounds the rotating shaft 9 of part.Described central bearing point bearing 17 is located at front fulcrum bearing 20 and rear fulcrum
Between bearing 14；The rear end of front housing 1 is fixed on the front surface of support plate and is collectively forming simulated engine by-pass air duct.Rear housing
16 are collectively forming simulated engine main duct with support plate 18 and rear simulation drum barrel 10.Pass through welding even between support plate and forward and backward casing
It is connected into overall load-bearing frame, aeroengine rotor primary load bearing framework can be simulated.Separately, in the present embodiment, forward and backward casing is
Thin cylinder band installs side and reinforcing rib structure.Simulation blade passes through bolt and mounting disc is connected with axle, can simulate aeroplane engine
The load producing during the rotation of machine fan；It is bolted between simulation drum barrel and simulation support plate, Aero-engine Bearing can be simulated
Force-transmitting state.And above-mentioned structure is integrally fixed on rigid support.Arrange in present embodiment in order to fixed supported slab 18 and rear mold
Intend the rigid support of drum barrel 10；Described support plate 18 installs section 6 before being provided with, front section 6 of installing is arranged on rigid support by suspension rod 5
On；After described, simulation drum barrel 10 installs section 8 after being provided with, and installs section 8 afterwards and is arranged on rigid support by hinge rod 7, front,
The connection installing section afterwards with rigid support can simulate the main load path that aero-engine installs section.
Described front simulation drum barrel 19 is provided with first sensor 2, support plate 18 is provided with second sensor 3, front housing 1 appearance
Face is provided with 3rd sensor 4, rear housing 16 outer surface is provided with the 4th sensor 15.Wherein, described rotating shaft 9 and motor 13 export
Axle is coaxially connected, and is connected by prestressing force groove protection device 12 between rotating shaft 9 and output shaft.Motor 13 is protected by prestressing force groove
Protection unit 12 drive shaft 9 rotates, and flies to lose test, prestressing force groove protection dress to complete the foreign object strike under rotation status or blade
Putting 12 when running well is shaft coupling, automatically twists off when overload exceedes design margin, disconnects power connector, and protection test fills
Put.
In addition, in present embodiment, the setting of three fulcrum rollers makes rotating shaft 9 be supported by tree-pointb earing system：Front fulcrum
Bearing 20 is thrust bearing, bears the axial force that sudden applied load is met in rotating shaft, central bearing point bearing 17 and rear fulcrum bearing 14 are ball
Bearing, bears the radial force that sudden applied load is met in rotating shaft 9, and supports whole rotating shaft.
During test, motor rotor driven rotates, and when leaf dish experience impact or simulation blade fly to lose, sudden applied load is by axle
Hold system, drum barrel, support plate, primary load bearing framework, rear fulcrum load-bearing frame spread out of, and are delivered to rigid support by front and back's safety joint
On, period items kinetic parameter has the sensor record being arranged on each feature locations for analysis.
In addition, providing following preferably test example in present embodiment to embody above-mentioned Asia scale simulation aeroplane engine
Machine rotation test device is capable of the test method of concrete application.
When carrying out impact strength test, first, second, third, fourth sensor, all using foil gauge, obtains four positions
The deformation put and stressing conditions；
When carrying out vibration test, first, second, third, fourth sensor, all using acceleration of vibration meter, obtains machine
Casket, drum barrel and the vibration characteristics propping up Board position；
When bird is hit, ice hits test for development, second sensor uses foil gauge, and first, the three, the 4th sensors use
Accelerometer measures, and obtains the vibratory response under temporary impact load；
When carrying out blade loss test, third and fourth sensor uses foil gauge, and first, second sensor uses and adds
Velometer measures, and obtains at deformation and the strain, and drum barrel and support plate at casing due to shaking that unbalanced load leads to
Dynamic.
In addition, the concrete methods of realizing of the present invention and approach are a lot, the above is only the preferred embodiment of the present invention.
It should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention, can also do
Go out some improvements and modifications, these improvements and modifications also should be regarded as protection scope of the present invention.Clearly not each in the present embodiment
The all available prior art of ingredient is realized.
Claims (5)
1. a kind of Asia scale simulation aero-engine rotation test device it is characterised in that：Rotate including rotating shaft, drive shaft
Motor, the simulation leaf dish being located at rotating shaft front end, the front fulcrum bearing being arranged in rotating shaft, the front mould being installed on front fulcrum bearing
Intend drum barrel, the central bearing point bearing being arranged in rotating shaft, the support plate being installed on central bearing point bearing, extend and wrap from a front edge of board
The front housing of leaf dish, the rear fulcrum bearing being arranged in rotating shaft, the rear simulation drum barrel being installed on rear fulcrum bearing, solid intended by boxing
Surely support plate and the rear rear housing simulating drum barrel are connected；Rear housing surrounds the rotating shaft of part；Described central bearing point bearing is located at front fulcrum
Between bearing and rear fulcrum bearing；The rear end of front housing is fixed on the front surface of support plate；Described front simulation drum barrel is provided with
One sensor, support plate are provided with second sensor, front housing outer surface is provided with 3rd sensor, rear housing outer surface is provided with
Four sensors.
2. according to claim 1 Asia scale simulation aero-engine rotation test device it is characterised in that：Described rotating shaft
Coaxially connected with motor output shaft, and be connected by prestressing force groove protection device between rotating shaft and output shaft.
3. according to claim 1 and 2 Asia scale simulation aero-engine rotation test device it is characterised in that：Front
Point bearing is thrust bearing, and central bearing point bearing is ball bearing, and rear fulcrum bearing is ball bearing.
4. according to claim 3 Asia scale simulation aero-engine rotation test device it is characterised in that：Also include using
With fixed supported slab and the rear rigid support simulating drum barrel；Described support plate installs section before being provided with, front section of installing is existed by hanger erection
On rigid support；After described, simulation drum barrel installs section after being provided with, and installs section afterwards and is arranged on rigid support by hinge rod.
5. as any one of Claims 1-4 sub- scale simulation aero-engine rotation test device test method, its
It is characterised by：
When carrying out impact strength test, first, second, third, fourth sensor all using foil gauge, obtains four positions
Deformation and stressing conditions；
When carrying out vibration test, first, second, third, fourth sensor, all using acceleration of vibration meter, obtains casing, drum
Cylinder and the vibration characteristics propping up Board position；
When bird is hit, ice hits test for development, second sensor uses foil gauge, and first, the three, the 4th sensors are using acceleration
Degree meter measures, and obtains the vibratory response under temporary impact load；
When carrying out blade loss test, third and fourth sensor uses foil gauge, and first, second sensor uses acceleration
Meter measures, and obtains the vibration leading at the deformation at casing and strain, and drum barrel and support plate due to unbalanced load.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610857702.0A CN106441902B (en) | 2016-09-27 | 2016-09-27 | A kind of sub- scale simulation aero-engine rotation test device and test method |
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|---|---|---|---|
| CN201610857702.0A CN106441902B (en) | 2016-09-27 | 2016-09-27 | A kind of sub- scale simulation aero-engine rotation test device and test method |
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| CN106441902A true CN106441902A (en) | 2017-02-22 |
| CN106441902B CN106441902B (en) | 2017-08-04 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107084844A (en) * | 2017-04-19 | 2017-08-22 | 西北工业大学 | A kind of test method of blade construction simulating piece |
| CN109540447A (en) * | 2018-11-12 | 2019-03-29 | 中国飞行试验研究院 | Aeroengine fan blades foreign object strike test platform |
| CN110793782A (en) * | 2019-09-19 | 2020-02-14 | 中国科学院力学研究所 | Small turbine shaft engine test and test device |
| CN112213062A (en) * | 2020-09-29 | 2021-01-12 | 南京航空航天大学 | Sudden-increase high-energy basic excitation test bed for laboratory and test method |
| CN113418938A (en) * | 2021-06-19 | 2021-09-21 | 西北工业大学 | Device and method for comparison test of radar absorbing material of aircraft engine fan support plate |
| CN113495002A (en) * | 2020-04-03 | 2021-10-12 | 中国航发商用航空发动机有限责任公司 | Rotary impact test device for non-full-ring fan blade of aero-engine |
| CN114166675A (en) * | 2021-12-02 | 2022-03-11 | 江苏心源航空科技有限公司 | Rotary erosion simulation casing |
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| CN101561351A (en) * | 2009-06-04 | 2009-10-21 | 中国航空工业集团公司西安飞机设计研究所 | Airplane engine dynamic simulation test bed |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107084844A (en) * | 2017-04-19 | 2017-08-22 | 西北工业大学 | A kind of test method of blade construction simulating piece |
| CN109540447A (en) * | 2018-11-12 | 2019-03-29 | 中国飞行试验研究院 | Aeroengine fan blades foreign object strike test platform |
| CN109540447B (en) * | 2018-11-12 | 2020-12-29 | 中国飞行试验研究院 | Foreign object impact test platform for fan blade of aero-engine |
| CN110793782A (en) * | 2019-09-19 | 2020-02-14 | 中国科学院力学研究所 | Small turbine shaft engine test and test device |
| CN110793782B (en) * | 2019-09-19 | 2020-10-27 | 中国科学院力学研究所 | Small turbine shaft engine test and test device |
| CN113495002A (en) * | 2020-04-03 | 2021-10-12 | 中国航发商用航空发动机有限责任公司 | Rotary impact test device for non-full-ring fan blade of aero-engine |
| CN112213062A (en) * | 2020-09-29 | 2021-01-12 | 南京航空航天大学 | Sudden-increase high-energy basic excitation test bed for laboratory and test method |
| CN112213062B (en) * | 2020-09-29 | 2022-07-26 | 南京航空航天大学 | Sudden-increase high-energy basic excitation test bed for laboratory and test method |
| CN113418938A (en) * | 2021-06-19 | 2021-09-21 | 西北工业大学 | Device and method for comparison test of radar absorbing material of aircraft engine fan support plate |
| CN114166675A (en) * | 2021-12-02 | 2022-03-11 | 江苏心源航空科技有限公司 | Rotary erosion simulation casing |
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| Publication number | Publication date |
|---|---|
| CN106441902B (en) | 2017-08-04 |
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