CN220454826U - Aeroengine blade vibration testing device - Google Patents
Aeroengine blade vibration testing device Download PDFInfo
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- CN220454826U CN220454826U CN202323526983.6U CN202323526983U CN220454826U CN 220454826 U CN220454826 U CN 220454826U CN 202323526983 U CN202323526983 U CN 202323526983U CN 220454826 U CN220454826 U CN 220454826U
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- 238000012360 testing method Methods 0.000 title claims abstract description 69
- 230000035939 shock Effects 0.000 claims abstract description 26
- 238000013016 damping Methods 0.000 claims abstract description 18
- 230000007423 decrease Effects 0.000 claims 1
- 230000007774 longterm Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 3
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000010287 polarization Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model discloses an aero-engine blade vibration testing device, and relates to the technical field of aero-engines. Including the base platform, base platform top is provided with the shock attenuation platform, and the shock attenuation platform outside is fixed with spacing sleeve board, is provided with shock-absorbing structure between shock attenuation platform and the base platform, and the symmetry is fixed with the support on the shock attenuation platform and erects the platform, and the support erects the positive dorsal symmetry setting of platform, is provided with vibration test structure on the support and erects the bench for test operation to the blade. According to the vibration testing device, through the arrangement of the vibration testing structure and the vibration testing structure, the vibration testing structure is convenient for testing a plurality of blades at the same time, and the hinged plate, the springs and the damping rods in the vibration testing structure play a role in damping the vibration table together, so that the vibration table is not easy to vibrate when the vibration testing device is subjected to vibration testing operation, the whole testing device is subjected to vibration damping protection to a certain extent, the testing device is prevented from being damaged to a certain extent due to long-term testing operation, and the testing result is ensured.
Description
Technical Field
The utility model relates to the technical field of aero-engines, in particular to an aero-engine blade vibration testing device.
Background
The aeroengine is a highly complex and precise thermodynamic machine, the aeroengine blade is used as a core acting component of the aeroengine, the running state parameter of the aeroengine blade directly influences the running state, the working efficiency and the safety performance of the whole engine system, and vibration test operation is required when the blade is used.
The prior device and method for testing the vibration of the aero-engine blade (patent publication number: CN 115979555A) have the following defects: according to the testing device, the rotating blades are excited through the polarization module, so that the blades are easier to enter a resonance state, the amplitude of vibration of the blades is increased, and the testing effect of vibration of the blades is facilitated.
Disclosure of Invention
The utility model aims to provide an aero-engine blade vibration testing device which is used for solving the problems in the background technology.
In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides an aeroengine blade vibration testing arrangement, including the base platform, base platform top is provided with the shock attenuation platform, the shock attenuation platform outside is fixed with spacing sleeve board, be provided with shock-absorbing structure between shock attenuation platform and the base platform, the symmetry is fixed with the support vertical bench on the shock attenuation platform, the support vertical bench positive dorsal scale symmetry sets up, be provided with vibration test structure on the support vertical bench, a plurality of spacing horizontal poles are provided with to the vibration test structure for test operation to the blade including seting up the mounting groove on the base platform, the symmetry is provided with a plurality of spacing horizontal poles in the mounting groove, a plurality of spacing horizontal pole middle parts are fixed mutually, spacing horizontal pole both ends all are fixed with the fixed plate, fixed plate and mounting groove tank bottom are fixed mutually, all the slip cap is equipped with the sliding block on the spacing horizontal pole, correspond between sliding block and the shock attenuation platform and be provided with the hinge plate, be provided with the spring between sliding block and the corresponding fixed plate.
Preferably, the both ends of the hinged plate are fixedly inserted with rotating rods, both ends of the rotating rods are rotatably sleeved with limiting plates, the limiting plates at one end are fixed with the bottom surface of the damping table, and the limiting plates at the other end are fixed with the top surface of the sliding block.
Preferably, the spring is sleeved on the limiting cross rod, one end of the spring is connected with the fixed plate, the other end of the spring is connected with the sliding block, a damping rod is connected between the sliding block at the same side position and the fixed plate, and the limiting sleeve plate is sleeved on the base table in a sliding manner.
Preferably, the vibration test structure comprises a transverse rod arranged between supporting vertical tables, a sliding groove matched with the vertical sliding of the transverse rod is formed in the supporting vertical tables, a connecting rod is sleeved in the middle of the transverse rod in a rotating mode, a short rod is fixedly inserted into one end of the connecting rod, a rotating disc is sleeved on the short rod in a rotating mode, a shaft rod is fixed to one face of the rotating disc in a middle shaft mode, a mounting plate fixed to the damping table is sleeved on the shaft rod in a sleeved mode, the shaft rod rotates to penetrate through the mounting plate, and a rotating motor is connected to the outer end of the shaft rod.
Preferably, the transverse bar is symmetrically fixed with a U-shaped plate at equal intervals, the opening of the U-shaped plate faces to the outer side, a casing is arranged on the outer side of the U-shaped plate, and the casing is used for carrying out vibration test operation on the blade.
Preferably, a bottom clamping block is fixed on a bottom flat plate of the U-shaped plate, a top clamping block is arranged above the bottom clamping block, a vertical rod is fixed on the top surface of the top clamping block, the vertical rod penetrates through the U-shaped plate and the casing shell, a transverse plate is fixed on the top end of the vertical rod, and an electric telescopic rod is connected between the transverse plate and the casing shell and used for driving the top clamping block to descend to clamp the blades.
Compared with the prior art, the utility model has the beneficial effects that:
this aeroengine blade vibration testing arrangement, through shock-absorbing structure and vibration test structure's setting, vibration test structure is convenient for carry out test operation simultaneously to a plurality of blades, and articulated slab, spring and the damping lever in the shock-absorbing structure have played the cushioning effect together to the shock attenuation platform for the shock attenuation platform is difficult for taking place to vibrate when the device carries out vibration test operation, to a certain extent, carries out shock attenuation protection to testing arrangement wholly, avoids long-term test operation to lead to testing arrangement to take place certain damage, has guaranteed the test result.
Drawings
FIG. 1 is a schematic perspective view of the present utility model;
FIG. 2 is a front view of the present utility model;
FIG. 3 is a cross-sectional view of the present utility model;
fig. 4 is a schematic perspective view of a shock absorbing assembly, a base table and a retainer plate according to the present utility model.
In the figure: 1. a base table; 101. a mounting groove; 2. a shock absorbing platform; 201. a limiting sleeve plate; 202. a limiting cross bar; 203. a fixing plate; 204. a sliding block; 205. a spring; 206. a damping rod; 207. a hinged plate; 208. a rotating rod; 209. a limiting plate; 3. supporting a vertical table; 301. a transverse bar; 302. a U-shaped plate; 303. a casing; 304. a bottom clamping block; 305. a vertical rod; 306. a cross plate; 307. an electric telescopic rod; 4. a connecting rod; 401. rotating the disc; 402. a mounting plate; 403. a sliding groove.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
In the vibration test process of the aeroengine blade, a vibration test device is needed, the test device provided by the utility model is specially used for carrying out vibration test operation on a plurality of blades, the overall stability of the device is protected in the test operation process, the damage caused by the overall vibration of the device is avoided, the service life of the device is prolonged, and in the use process of the device, the device needs to carry out preparation work such as checking in advance, so that the normal operation of the device is ensured.
As shown in fig. 1 to 4, the present utility model provides a technical solution: the utility model provides an aeroengine blade vibration testing arrangement, including base platform 1, base platform 1 top is provided with shock attenuation platform 2, the shock attenuation platform 2 outside is fixed with spacing sleeve board 201, be provided with shock-absorbing structure between shock attenuation platform 2 and the base platform 1, the symmetry is fixed with support vertical platform 3 on the shock attenuation platform 2, the positive dorsal symmetry of support vertical platform 3 sets up, be provided with vibration test structure on the support vertical platform 3, be used for carrying out test operation to the blade, shock-absorbing structure is including seting up the mounting groove 101 on base platform 1, mounting groove 101 inner circumference symmetry is provided with a plurality of spacing horizontal poles 202, a plurality of spacing horizontal poles 202 middle parts are fixed mutually, spacing horizontal pole 202 both ends all are fixed with fixed plate 203, fixed plate 203 is fixed mutually with the mounting groove 101 tank bottom, all the slip cap is equipped with slider 204 on the spacing horizontal pole 202, correspond between slider 204 and the shock attenuation platform 2 and be provided with spring 205 between slider 204 and the corresponding fixed plate 203.
In the embodiment, the rotating rods 208 are fixedly inserted into two ends of the hinge plate 207, the limiting plates 209 are fixedly sleeved on two ends of the rotating rods 208, the limiting plates 209 at one end are fixed with the bottom surface of the shock absorption table 2, the limiting plates 209 at the other end are fixed with the top surface of the sliding block 204, the springs 205 are sleeved on the limiting cross rods 202, one ends of the springs 205 are connected with the fixing plates 203, the other ends of the springs 205 are connected with the sliding block 204, damping rods 206 are connected between the sliding block 204 and the fixing plates 203 at the same side positions, the limiting sleeve plates 201 are slidably sleeved on the base table 1, wherein the damping rods 206 adopt dampers in the prior art, the limiting cross rods 202 play a role of limiting and guiding, the stable sliding of the sliding blocks 204 is guaranteed, and the two ends of the hinge plate 207 rotate to a certain extent by taking the corresponding rotating rods 208 as shafts.
In the embodiment, vibration test structure includes setting up the horizontal bar 301 between supporting vertical platform 3, the sliding tray 403 with horizontal bar 301 vertical slip looks adaptation has been seted up on the supporting vertical platform 3, horizontal bar 301 middle part rotates the cover and is equipped with connecting rod 4, connecting rod 4 one end is fixed to be inserted and is equipped with the quarter butt, rotate the cover on the quarter butt and be equipped with the rotation disc 401, rotation disc 401 one side axis is fixed with the arbor, the cover is equipped with the mounting panel 402 that is fixed mutually with shock attenuation platform 2 on the arbor, the arbor rotates and runs through on mounting panel 402, the arbor outer end is connected with rotating motor, equidistant symmetry is fixed with U template 302 on the horizontal bar 301, U template 302 opening is towards outside position, install the receiver 303 in the U template 302 outside, receiver 303 is used for carrying out vibration test operation to the blade, wherein, receiver 303 adopts prior art, the quarter butt sets up at rotation disc 401 border position, when rotation disc 401 rotates, connecting rod 4 both ends carry out the rotation of corresponding angle respectively, drive horizontal bar 301 wholly and reciprocate in sliding tray 403.
In the embodiment, be fixed with bottom clamp splice 304 on the bottom flat board of U template 302, bottom clamp splice 304 top is provided with the top clamp splice, top clamp splice top surface is fixed with montant 305, montant 305 runs through U template 302 and receiver 303 shell, montant 305 top is fixed with diaphragm 306, be connected with electric telescopic handle 307 between diaphragm 306 and the receiver 303 shell, be used for driving top clamp splice and descend and clip the blade, through shock-absorbing structure and vibration test structure's setting, vibration test structure is convenient for carry out test operation simultaneously to a plurality of blades, hinge plate 207 in the shock-absorbing structure, spring 205 and damping rod 206 play the cushioning effect together to shock-absorbing platform 2, be difficult for taking place vibrations when the device carries out vibration test operation, to a certain extent, carry out shock-absorbing protection to testing arrangement wholly, avoid long-term test operation to lead to testing arrangement to take place certain damage, the test result has been guaranteed.
Working principle: when the device is used, a plurality of blades to be tested are fixed through the clamping of the bottom clamping blocks 304 and the top clamping blocks, the blades are positioned and installed, then the device is started, the rotating motor drives the rotating disc 401 to rotate, the connecting rod 4 drives the transverse rod 301 to integrally lift and reciprocate, vibration test operation can be performed, in the test operation process, the damping table 2 performs damping operation under the action of the hinge plates 207, the springs 205 and the damping rods 206, and the stability of the damping table 2 can be ensured.
Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made hereto without departing from the spirit and scope of the utility model as defined by the appended embodiments and equivalents thereof.
Claims (6)
1. The utility model provides an aeroengine blade vibration testing arrangement, includes base platform (1), its characterized in that: base platform (1) top is provided with shock attenuation platform (2), shock attenuation platform (2) outside is fixed with spacing sleeve board (201), be provided with shock-absorbing structure between shock attenuation platform (2) and base platform (1), the symmetry is fixed with on shock-absorbing platform (2) and supports upright platform (3), the positive dorsal symmetry of support upright platform (3) sets up, be provided with vibration test structure on supporting upright platform (3) for test operation to the blade, shock-absorbing structure is including seting up mounting groove (101) on base platform (1), mounting groove (101) inner circumference symmetry is provided with a plurality of spacing horizontal pole (202), a plurality of spacing horizontal pole (202) middle parts are fixed mutually, spacing horizontal pole (202) both ends all are fixed with fixed plate (203), fixed plate (203) are fixed mutually with the mounting groove (101) tank bottom, all the slip cap is equipped with slider (204) on spacing horizontal pole (202), be provided with hinge plate (207) between slider (204) and shock-absorbing platform (2) correspondingly, be provided with spring (205) between slider (204) and the corresponding fixed plate (203).
2. An aero-engine blade vibration testing device according to claim 1, wherein: the utility model discloses a damping device, including hinged plate (207), slider (204), slider, shock attenuation platform (2), hinged plate (207), pivoted bar (208) are all fixedly inserted at hinged plate (207) both ends, and pivoted bar (208) both ends all rotate the cover and are equipped with limiting plate (209), and limiting plate (209) and shock attenuation platform (2) bottom surface that are located one end are fixed mutually, and limiting plate (209) and slider (204) top surface that are located the other end are fixed mutually.
3. An aero-engine blade vibration testing device according to claim 1, wherein: the spring (205) is sleeved on the limiting cross rod (202), one end of the spring (205) is connected with the fixed plate (203), the other end of the spring is connected with the sliding block (204), a damping rod (206) is connected between the sliding block (204) and the fixed plate (203) at the same side, and the limiting sleeve plate (201) is sleeved on the base table (1) in a sliding mode.
4. An aero-engine blade vibration testing device according to claim 1, wherein: the vibration test structure comprises a transverse rod (301) arranged between supporting vertical tables (3), a sliding groove (403) matched with the vertical sliding of the transverse rod (301) is formed in the supporting vertical tables (3), a connecting rod (4) is rotatably sleeved in the middle of the transverse rod (301), a short rod is fixedly inserted into one end of the connecting rod (4), a rotating disc (401) is rotatably sleeved on the short rod, a shaft rod is fixedly arranged on one surface of the rotating disc (401) in a central shaft mode, a mounting plate (402) fixed with a damping table (2) is sleeved on the shaft rod in a sleeved mode, the shaft rod rotates to penetrate through the mounting plate (402), and a rotating motor is connected to the outer end of the shaft rod.
5. An aero-engine blade vibration testing device according to claim 4, wherein: the blade vibration testing device is characterized in that U-shaped plates (302) are symmetrically fixed on the transverse rods (301) at equal intervals, the openings of the U-shaped plates (302) face to the outer side, a casing (303) is arranged on the outer side of each U-shaped plate (302), and the casing (303) is used for carrying out vibration testing operation on the blade.
6. An aero-engine blade vibration testing device according to claim 5, wherein: bottom clamp splice (304) are fixed with on the bottom flat board of U template (302), and bottom clamp splice (304) top is provided with a clamp splice, and a clamp splice top surface is fixed with montant (305), and montant (305) run through U template (302) and receiver (303) shell, and montant (305) top is fixed with diaphragm (306), is connected with electric telescopic handle (307) between diaphragm (306) and the receiver (303) shell for drive a clamp splice decline and clip the blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323526983.6U CN220454826U (en) | 2023-12-25 | 2023-12-25 | Aeroengine blade vibration testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323526983.6U CN220454826U (en) | 2023-12-25 | 2023-12-25 | Aeroengine blade vibration testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220454826U true CN220454826U (en) | 2024-02-06 |
Family
ID=89734739
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323526983.6U Active CN220454826U (en) | 2023-12-25 | 2023-12-25 | Aeroengine blade vibration testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220454826U (en) |
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2023
- 2023-12-25 CN CN202323526983.6U patent/CN220454826U/en active Active
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