CN209264425U - Aero-turbine rotor blade bending stiffness experimental rig - Google Patents
Aero-turbine rotor blade bending stiffness experimental rig Download PDFInfo
- Publication number
- CN209264425U CN209264425U CN201822017812.3U CN201822017812U CN209264425U CN 209264425 U CN209264425 U CN 209264425U CN 201822017812 U CN201822017812 U CN 201822017812U CN 209264425 U CN209264425 U CN 209264425U
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- China
- Prior art keywords
- fixedly connected
- fixed
- rotor blade
- room
- clamping
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- Expired - Fee Related
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- 238000005452 bending Methods 0.000 title claims abstract description 18
- 239000007787 solid Substances 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000004886 process control Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
Abstract
The utility model discloses a kind of aero-turbine rotor blade bending stiffness experimental rigs, including clamping room, pedestal, first pillar, lower locating piece, second pillar, pressure apparatus, rotor blade, clamping device, controller and display screen, room is clamped to be fixedly connected on the first pillar, first pillar is fixedly connected on pedestal, lower locating piece is fixedly connected on pedestal, second pillar is fixedly connected on pedestal, pressure apparatus is fixedly connected on the second pillar, clamping device is fixed in the rectangular inner cavity for clamping room, clamping room includes rectangular inner cavity and sliding groove, clamping device includes fixed block, electric pushrod, fixed link, rotor plate, tooth, motor and gear, electric pushrod is fixed in fixed block, one end of fixed link is fixedly connected on fixed block by bearing, rotor plate is fixedly connected on fixed block, tooth fixation is set It sets on rotor plate, motor is fixedly connected on clamping interior, and gear is fixedly connected on the output end of motor.
Description
Technical field
The utility model relates to rotor blade tensioning technique field, specially a kind of aero-turbine rotor blade is curved
Stiffness experimental rig.
Background technique
In aerial motor spare part test, need to carry out rotor blade bending stiffness test, to verify blade resistance
The ability of bending deformation needs it to be fixed clamping, since the shape of blade itself is in the test of blade bending stiffness
Curved face type, and just need for the blade of different curvatures using different fixed clamping devices, this just brings to test operation
It is inconvenient.
Utility model content
The purpose of this utility model is to provide a kind of aero-turbine rotor blade bending stiffness experimental rig, with
Solve the problems mentioned above in the background art.
To achieve the above object, the utility model provides the following technical solutions: a kind of aero-turbine rotor blade
Bending stiffness experimental rig, including clamp room, pedestal, the first pillar, lower locating piece, the second pillar, pressure apparatus, rotor leaf
Piece, clamping device, controller and display screen, the clamping room are fixedly connected on first pillar, and first pillar is solid
On the base, the lower locating piece is fixedly connected on the base, and second pillar is fixedly connected on institute for fixed connection
It states on pedestal, the pressure apparatus is fixedly connected on second pillar, and the rotor blade passes through lower locating piece and clamping
Device is fixed, and the clamping device is fixed in the rectangular inner cavity for clamping room, and the controller is fixedly connected
On the base, the display screen is fixed on the controller.
The clamping room includes rectangular inner cavity and sliding groove, and the rectangular inner cavity is provided with the inside for clamping room, institute
Sliding groove is stated to be provided on the bottom surface for clamping room.
The clamping device includes fixed block, electric pushrod, fixed link, rotor plate, tooth, motor, gear and briquetting, described
Electric pushrod is fixedly connected in the fixed block, and one end of the fixed link is fixedly connected on the fixed block by bearing
On, the rotor plate is fixedly connected on the upper surface of the fixed block, and the tooth is fixed on the rotor plate, the electricity
Machine is fixedly connected on the clamping interior, and the gear is fixedly connected on the output end of the motor, and the briquetting is fixedly connected
In the output end of the electric pushrod.
Preferably, the rectangular inner cavity is connected with the sliding groove.
Preferably, the quantity of the clamping device is two sets, and is separately positioned on the left and right sides for clamping room.
Preferably, the other end of the fixed link is fixedly connected on the inner wall for clamping room.
Preferably, the gear is meshed with the tooth and connect.
Preferably, the pressure apparatus, the electric pushrod and the motor are electrically connected with the controller by program
It connects.
Compared with prior art, the utility model has the beneficial effects that aero-turbine rotor blade bending is rigid
Spend experimental rig:
Clamping device can be moved in rectangular inner cavity by sliding groove, and lower locating piece can be rotor blade
Lower surface provides a fulcrum so that it to be fixed, and fixed block can provide support for electric pushrod, and electric pushrod can band
Rotor blade is fixed in dynamic pressure block, and fixed link can be supported fixed block, can also fixed block be allow to rotate around it,
Motor can be rotated with moving gear, and gear can drive the tooth being engaged with and the rotor plate mutually fixed with tooth and fixed block to turn
Dynamic, controller can carry out process control to pressure apparatus, electric pushrod and motor, to carry out accurate operation, display screen
It can show the size for the power that pressure apparatus applies rotor blade.
Detailed description of the invention
Fig. 1 is utility model diagram；
Fig. 2 is the utility model fixed link and clamping room connection schematic diagram；
Fig. 3 is that the utility model clamps room schematic bottom view.
In figure: 1 clamps room, 101 rectangular inner cavities, 102 sliding grooves, 2 pedestals, 3 first pillars, 4 lower locating pieces, 5 second
Column, 6 pressure apparatus, 7 rotor blades, 8 clamping devices, 81 fixed blocks, 82 electric pushrods, 83 fixed links, 84 rotor plates, 85 teeth,
86 motors, 87 gears, 88 briquettings, 9 controllers, 10 display screens.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, fall within the protection scope of the utility model.
Fig. 1-3 is please referred to, the utility model provides a kind of technical solution: a kind of aero-turbine rotor blade bending
Stiffness test device, including clamp room 1, pedestal 2, the first pillar 3, lower locating piece 4, the second pillar 5, pressure apparatus 6, rotor leaf
Piece 7, clamping device 8, controller 9 and display screen 10 clamp room 1 and are fixedly connected on the first pillar 3, and the first pillar 3 is fixed to be connected
It connects on pedestal 2, the first pillar 3 can provide support to clamp the component of room 1 and its inside, and lower locating piece 4 is fixedly connected on
On pedestal 2, lower locating piece 4 can provide a fulcrum for the lower surface of rotor blade 7 it to be fixed, the second pillar 5
It is fixedly connected on pedestal 2, the second pillar 5 can provide support for pressure apparatus 6, and pressure apparatus 6 is fixedly connected on second
On column 5, pressure apparatus 6 can carry out bending stiffness test to rotor blade 7, be provided with guide rail, can be respectively to rotor leaf
The different position of piece 7 is tested, and is additionally provided with pressure sensor on pressure apparatus 6, can detecte to the application of rotor blade 7
The size of power, rotor blade 7 are fixed by lower locating piece 4 and clamping device 8, and clamping device 8, which is fixed at, clamps room 1
Rectangular inner cavity 101 in, controller 9 is fixedly connected on pedestal 2, controller 9 can to pressure apparatus 6, electric pushrod 82 with
And motor 86 carries out process control, to carry out accurate operation, display screen 10 is fixed on controller 9, and display screen 10 can
To show the size of power that pressure apparatus 6 applies rotor blade 7.
Clamping room 1 includes rectangular inner cavity 101 and sliding groove 102, and rectangular inner cavity 101 is provided with the inside for clamping room 1, sliding
Slot 102 is provided on the bottom surface for clamping room 1, and rectangular inner cavity 101 is connected with sliding groove 102.
Clamping device 8 includes fixed block 81, electric pushrod 82, fixed link 83, rotor plate 84, tooth 85, motor 86, gear 87
With briquetting 88, the quantity of clamping device 8 is two sets, and is separately positioned on the left and right sides of clamping room 1, and clamping device 8 can be
It in rectangular inner cavity 101, is moved by sliding groove 102, electric pushrod 82 is fixedly connected in fixed block 81, electric pushrod 82
Model ANT-26, electric pushrod 82 can drive briquetting 88 that rotor blade 7 is fixed, and one end of fixed link 83 is logical
It crosses bearing to be fixedly connected on fixed block 81, fixed link 83 can be supported fixed block 81, can also make fixed block 81 can be with
It rotates around it, fixed block 81 can provide support for electric pushrod 82, and the other end of fixed link 83, which is fixedly connected on, clamps room 1
On inner wall, rotor plate 84 is fixedly connected on the upper surface of fixed block 81, and tooth 85 is fixed on rotor plate 84, and motor 86 is fixed
It is connected to and clamps in room 1, the model MSME 5AZG1 of motor 86, motor 86 can be rotated with moving gear 87, and gear 87 is fixed
Be connected to the output end of motor 86, gear 87 is meshed with tooth 85 and connect, gear 87 can drive the tooth 85 being engaged with and
Fixed rotor plate 84 and fixed block 81 rotate with 85 phase of tooth, and briquetting 88 is fixedly connected on the output end of electric pushrod 82, briquetting
88 and lower locating piece 4 be the material with certain ductility, clamping device 8 can be made when being clamped in this way, briquetting
88 and lower locating piece 4 can be bonded with rotor blade 7 more accurate, promote the effect fixed to clamp, it is pressure apparatus 6, electronic
Push rod 82 and motor 86 and controller 9 are electrically connected by program.
Carry out rotor blade 7 bending stiffness test when need fixation first is clamped to rotor blade 7, will first need by
The rotor blade 7 of test is placed on lower locating piece 4, and a hand catches rotor blade 7 to prevent its shaking, then passes through controller
9, starting motor 86 is rotated with moving gear 87 and tooth 85, works as pressure according to the curvature of rotor blade 7 to adjust the position of briquetting 88
When block 88 can be fitted in completely on rotor blade 7, that is, indicate that the curvature of the angle of electric pushrod 82 at this time and rotor blade 7 is kissed
It closes, recycles electric pushrod 82 that briquetting 88 is driven to clamp rotor blade 7, restarting pressure device 6 is tested.
While there has been shown and described that the embodiments of the present invention, for the ordinary skill in the art,
It is understood that these embodiments can be carried out with a variety of variations in the case where not departing from the principles of the present invention and spirit, repaired
Change, replacement and variant, the scope of the utility model is defined by the appended claims and the equivalents thereof.
Claims (6)
1. a kind of aero-turbine rotor blade bending stiffness experimental rig, including clamp room (1), pedestal (2), first
Column (3), lower locating piece (4), the second pillar (5), pressure apparatus (6), rotor blade (7), clamping device (8), controller (9) and
Display screen (10), it is characterised in that: the clamping room (1) is fixedly connected on first pillar (3), first pillar
(3) it being fixedly connected on the pedestal (2), the lower locating piece (4) is fixedly connected on the pedestal (2), and described second
Column (5) is fixedly connected on the pedestal (2), and the pressure apparatus (6) is fixedly connected on second pillar (5), described
Rotor blade (7) is fixed by lower locating piece (4) and clamping device (8), and the clamping device (8) is fixed at described
In the rectangular inner cavity (101) for clamping room (1), the controller (9) is fixedly connected on the pedestal (2), the display screen
(10) it is fixed on the controller (9)；
The clamping room (1) includes rectangular inner cavity (101) and sliding groove (102), and the rectangular inner cavity (101) is provided with the folder
The inside of tight room (1), the sliding groove (102) are provided on the bottom surface for clamping room (1)；
The clamping device (8) include fixed block (81), electric pushrod (82), fixed link (83), rotor plate (84), tooth (85),
Motor (86), gear (87) and briquetting (88), the electric pushrod (82) is fixedly connected in the fixed block (81), described solid
One end of fixed pole (83) is fixedly connected on the fixed block (81) by bearing, and the rotor plate (84) is fixedly connected on described
The upper surface of fixed block (81), the tooth (85) are fixed on the rotor plate (84), and the motor (86) is fixedly connected
In the clamping room (1), the gear (87) is fixedly connected on the output end of the motor (86), and the briquetting (88) is fixed
It is connected to the output end of the electric pushrod (82).
2. aero-turbine rotor blade bending stiffness experimental rig according to claim 1, it is characterised in that: institute
Rectangular inner cavity (101) is stated to be connected with the sliding groove (102).
3. aero-turbine rotor blade bending stiffness experimental rig according to claim 1, it is characterised in that: institute
The quantity for stating clamping device (8) is two sets, and is separately positioned on the left and right sides for clamping room (1).
4. aero-turbine rotor blade bending stiffness experimental rig according to claim 1, it is characterised in that: institute
The other end for stating fixed link (83) is fixedly connected on the inner wall for clamping room (1).
5. aero-turbine rotor blade bending stiffness experimental rig according to claim 1, it is characterised in that: institute
It states gear (87) and is meshed with the tooth (85) and connect.
6. aero-turbine rotor blade bending stiffness experimental rig according to claim 1, it is characterised in that: institute
Pressure apparatus (6), the electric pushrod (82) and the motor (86) and the controller (9) are stated to be electrically connected by program.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822017812.3U CN209264425U (en) | 2018-11-28 | 2018-11-28 | Aero-turbine rotor blade bending stiffness experimental rig |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822017812.3U CN209264425U (en) | 2018-11-28 | 2018-11-28 | Aero-turbine rotor blade bending stiffness experimental rig |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209264425U true CN209264425U (en) | 2019-08-16 |
Family
ID=67565587
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822017812.3U Expired - Fee Related CN209264425U (en) | 2018-11-28 | 2018-11-28 | Aero-turbine rotor blade bending stiffness experimental rig |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209264425U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11231265B2 (en) * | 2019-02-21 | 2022-01-25 | Safran Aircraft Engines | System for measuring a bending deformation of a surface of a material |
-
2018
- 2018-11-28 CN CN201822017812.3U patent/CN209264425U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11231265B2 (en) * | 2019-02-21 | 2022-01-25 | Safran Aircraft Engines | System for measuring a bending deformation of a surface of a material |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190816 Termination date: 20211128 |
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| CF01 | Termination of patent right due to non-payment of annual fee |