CN215065140U - Aviation dual-rotor comprehensive vibration test experiment table - Google Patents
Aviation dual-rotor comprehensive vibration test experiment table Download PDFInfo
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- CN215065140U CN215065140U CN202121060641.8U CN202121060641U CN215065140U CN 215065140 U CN215065140 U CN 215065140U CN 202121060641 U CN202121060641 U CN 202121060641U CN 215065140 U CN215065140 U CN 215065140U
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Abstract
The utility model discloses an aviation birotor comprehensive vibration test experiment table, which comprises a working platform, a high-pressure rotor, a low-pressure rotor, a high-pressure rotor driving mechanism and a low-pressure rotor driving mechanism, wherein a first supporting seat, a second supporting seat, a third supporting seat, a fourth supporting seat and a fifth supporting seat are sequentially arranged on the working platform at intervals; the low-pressure rotor penetrates through the support seats and is supported by the first support seat, the second support seat and the fifth support seat; one end of the high-pressure rotor is supported by a fourth supporting seat and connected with the hollow shaft, and an intermediate bearing is arranged between the other end of the high-pressure rotor and the low-pressure rotor; the hollow shaft is sleeved outside the low-pressure rotor and supported by a third supporting seat, and the hollow shaft is connected with the high-pressure rotor driving mechanism; and a plurality of weight discs are arranged on the high-pressure rotor and the low-pressure rotor. The utility model discloses rotor vibration characteristic experiment demand under multiple operating mode can be realized.
Description
Technical Field
The utility model relates to a relevant technical field of rotor vibration test specifically is an aviation birotor comprehensive vibration test laboratory bench.
Background
In the field of aviation, such as small unmanned aerial vehicles and the like, an engine with a double-rotor structure is a main engine structure form at present. The twin-rotor engine is mainly a structure in which a high-pressure rotor and a low-pressure rotor are coupled together through an intermediate bearing. The outer ring of the intermediate bearing is arranged on the high-pressure rotor to rotate positively, and the inner ring of the intermediate bearing is arranged on the low-pressure rotor to rotate negatively. In order to continuously optimize the engine technology, it is necessary to intensively study the vibration characteristics of the high-pressure rotor, the low-pressure rotor, and the like through experimental means. However, the related vibration test experiment table in the existing market is generally high in construction cost, single in test working condition and difficult to meet the vibration experiment requirements of the aviation dual-rotor system under various working conditions.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aviation birotor comprehensive vibration test experiment table, it has the laboratory bench and builds low cost, can realize the experiment demand of rotor vibration characteristic under the multiple operating mode.
The utility model discloses a realize above-mentioned purpose, realize through following technical scheme:
an aviation dual-rotor comprehensive vibration test experiment table comprises a working platform, a high-pressure rotor, a low-pressure rotor, a high-pressure rotor driving mechanism and a low-pressure rotor driving mechanism,
a first supporting seat, a second supporting seat, a third supporting seat, a fourth supporting seat and a fifth supporting seat are sequentially arranged on the working platform at intervals;
the low-pressure rotor penetrates through the support seats and is supported by the first support seat, the second support seat and the fifth support seat; one end of the low-pressure rotor is connected with the low-pressure rotor driving mechanism;
the high-pressure rotor is sleeved outside the low-pressure rotor, one end of the high-pressure rotor is supported by the fourth supporting seat and connected with the hollow shaft, and an intermediate bearing is arranged between the other end of the high-pressure rotor and the low-pressure rotor;
the hollow shaft is sleeved outside the low-pressure rotor and supported by a third supporting seat, and the hollow shaft is connected with the high-pressure rotor driving mechanism;
and a plurality of weight discs are arranged on the high-pressure rotor and the low-pressure rotor.
Further, low pressure rotor actuating mechanism includes low pressure rotor driving piece, and low pressure rotor driving piece sets up in the first supporting seat or the fifth supporting seat outside, and low pressure electronic driving piece passes through coupling joint low pressure rotor one end.
Further, the low pressure rotor driver is an electric motor or a gas turbine driver.
Furthermore, high pressure rotor actuating mechanism includes high pressure rotor driving piece, and high pressure rotor driving piece sets up in third supporting seat one side, and high pressure rotor driving piece passes through belt drive subassembly or bevel gear subassembly and connects the hollow shaft.
Further, the high pressure rotor driver is an electric motor or a gas turbine driver.
Furthermore, a squirrel cage elastic support is arranged between the third supporting seat and the fourth supporting seat.
Furthermore, the hollow shaft and the high-pressure rotor are connected through a coupling, and the coupling is arranged inside the squirrel-cage elastic support.
Furthermore, a damper is arranged on the fourth supporting seat, and a gap for forming an oil film through high-pressure oil pumping is formed between the damper and the squirrel cage elastic support.
Further, all set up the bearing in first supporting seat, second supporting seat, third supporting seat, fourth supporting seat and the fifth supporting seat and be used for supporting corresponding low pressure rotor or high-pressure rotor.
Further, work platform be T type groove platform, first supporting seat, second supporting seat, third supporting seat, fourth supporting seat and fifth supporting seat all through the mounting screw on work platform, and accessible T type groove carries out position control.
Contrast prior art, the beneficial effects of the utility model reside in that:
1. the utility model belongs to novel bearing structure's two rotors of aviation synthesize vibration test experiment table structure can satisfy the rotor vibration test under the circumstances such as different high-low pressure rotor rotational speeds, different drive methods, different support positions.
2. The utility model discloses in, overall structure overall arrangement is simple reasonable, and the change that the drive mode can be convenient can realize consequently the experiment of multiple drive modes such as bi-motor drive, two gas turbine drive, single motor drive.
3. The utility model discloses in, set up squirrel cage elastic support and squeeze film attenuator, vibration when can the effective absorption rotor pass through critical speed, consequently, the vibration characteristic test of rotor under this platform can realize higher rotational speed.
Drawings
Fig. 1 is a schematic diagram of the general structure of the present invention.
Fig. 2 is a schematic diagram of the overall structure of the present invention.
Fig. 3 is a schematic sectional structure diagram of the present invention.
Reference numerals shown in the drawings:
1. a working platform; 2. a first support base; 3. a second support seat; 4. a third support seat; 5. a fourth supporting seat; 6. a fifth supporting seat; 7. a low-pressure rotor; 8. a high pressure rotor; 9. a high pressure rotor drive; 10. a low pressure rotor drive; 11. a weight plate; 12. a hollow shaft; 13. a belt drive assembly; 14. the squirrel cage is elastically supported; 15. a damper; 16. and an intermediate bearing.
Detailed Description
The present invention will be further described with reference to the following specific examples. It should be understood that these examples are for illustrative purposes only and are not intended to limit the scope of the present invention. Furthermore, it should be understood that various changes or modifications of the present invention may be made by those skilled in the art after reading the teachings of the present invention, and these equivalents also fall within the scope defined in the present application.
As shown in fig. 1 to 3, the related structure of the test bench for testing the comprehensive vibration of the aviation dual-rotor is provided in this embodiment.
The vibration testing experiment table of the embodiment mainly comprises a working platform 1, a high-pressure rotor 8, a low-pressure rotor 7 and a corresponding driving and supporting structure. Wherein, a first supporting seat 2, a second supporting seat 3, a third supporting seat 4, a fourth supporting seat 5 and a fifth supporting seat 6 are sequentially arranged on the working platform 1 from left to right at intervals; the low-pressure rotor 7 passes through the first support seat 2, the second support seat 3, the third support seat 4, the fourth support seat 5 and the fifth support seat 6, and the low-pressure rotor 7 is supported by the first support seat 2, the second support seat 3 and the fifth support seat 6; all set up the bearing on the supporting seat that corresponds for support low pressure rotor 7, low pressure rotor actuating mechanism is connected to the one end of low pressure rotor 7, drives low pressure rotor 7's high-speed rotation through low pressure rotor actuating mechanism.
Preferably, the working platform 1 adopts a T-shaped groove platform, so that the position of each supporting seat can be conveniently adjusted.
The high-pressure rotor 8 is sleeved outside the low-pressure rotor 7, the high-pressure rotor 7 is positioned between the fourth supporting seat 5 and the fifth supporting seat 6, one end of the high-pressure rotor 8 is supported by the fourth supporting seat 5 and connected with a hollow shaft 12, and an intermediate bearing 16 is arranged between the other end of the high-pressure rotor 8 and the low-pressure rotor 7; the intermediate bearing 16 is a rolling rod bearing, the outer ring follows the high-pressure rotor 8, the inner ring follows the low-pressure rotor 7, the two rotors rotate in a forward direction and a reverse direction, and a gland (not shown in the figure) can be arranged behind the bearing. The rotation of high pressure rotor 8 is the power through hollow shaft 12 transmission, and hollow shaft 12 cover is located low pressure rotor 7 outside and is supported through third supporting seat 4, and high pressure rotor actuating mechanism is connected to hollow shaft 12, and high pressure rotor actuating mechanism rotates at a high speed through drive hollow shaft 12, and then drives high pressure rotor 8's high-speed rotation.
All install a plurality of counter weight dishes 11 on high pressure rotor 8 and low pressure rotor 7, the counter weight dish 11 position is adjustable, and the counter weight dish is used for imitating blade shape and weight on the one hand, and on the other hand can reduce the critical rotational speed of rotor, when avoiding higher high-speed rotation, has not reached first critical value yet.
Above-mentioned laboratory bench of this embodiment, when the experiment, 11 positions of adjustment counter weight disc to and behind the first supporting seat 2, second supporting seat 3, third supporting seat 4, fourth supporting seat 5 and the 6 positions of fifth supporting seat that correspond, can make low pressure rotor 7, high-pressure rotor 8 rotate at a high speed through starting low pressure rotor actuating mechanism, high-pressure rotor actuating mechanism, and then measure the vibration data of both under the multiple operating mode.
In this embodiment, the low pressure rotor driving mechanism includes low pressure rotor driving piece 9, and low pressure rotor driving piece 9 sets up in first supporting seat 2 or the outside of fifth supporting seat 6, and with low pressure rotor 7 coaxial setting, it passes through coupling joint low pressure rotor 7 one end, and low pressure rotor driving piece 9 can be motor or gas turbine driving machine, through electric drive or gas drive. The high-pressure rotor driving mechanism comprises a high-pressure rotor driving part 10, the high-pressure rotor driving part 10 is arranged on one side of the third supporting seat 4, the high-pressure rotor driving part 10 is connected to the hollow shaft 12 through a belt transmission assembly 13 or a bevel gear assembly, and the high-pressure rotor driving part 10 can be a motor or a gas turbine driving machine and is driven by electricity or gas. The above-mentioned drive structure overall arrangement of this embodiment can make things convenient for the change of driving piece, consequently, can realize the test of the rotor vibration condition under the different operating modes of electric drive or gas drive.
In order to ensure the stability of the experimental table during high-speed operation, in this embodiment, preferably, a squirrel cage elastic support 14 is arranged between the third support seat 4 and the fourth support seat 5, a coupler for connection between the hollow shaft 12 and the high-pressure rotor 8 is arranged inside the squirrel cage elastic support 14, meanwhile, a damper 15 is arranged on the fourth support seat 5, a gap for forming an oil film by high-pressure oil pumping is arranged between the damper 15 and the squirrel cage elastic support 14, so as to form an extrusion oil film damper structure, which can be used for damping, and is opened when the rotor passes through a critical rotation speed, so as to greatly reduce vibration, ensure that the system can pass through the critical rotation speed smoothly, and ensure the stable operation of the experimental table.
Claims (10)
1. An aviation dual-rotor comprehensive vibration test experiment table, which comprises a working platform, a high-pressure rotor, a low-pressure rotor, a high-pressure rotor driving mechanism and a low-pressure rotor driving mechanism, and is characterized in that,
a first supporting seat, a second supporting seat, a third supporting seat, a fourth supporting seat and a fifth supporting seat are sequentially arranged on the working platform at intervals;
the low-pressure rotor penetrates through the support seats and is supported by the first support seat, the second support seat and the fifth support seat; one end of the low-pressure rotor is connected with the low-pressure rotor driving mechanism;
the high-pressure rotor is sleeved outside the low-pressure rotor, one end of the high-pressure rotor is supported by the fourth supporting seat and connected with the hollow shaft, and an intermediate bearing is arranged between the other end of the high-pressure rotor and the low-pressure rotor;
the hollow shaft is arranged outside the low-pressure rotor and is supported by a third supporting seat, and the hollow shaft is connected with the high-pressure rotor driving mechanism;
and a plurality of weight discs are arranged on the high-pressure rotor and the low-pressure rotor.
2. The test bench of claim 1, wherein the low-pressure rotor driving mechanism comprises a low-pressure rotor driving member, the low-pressure rotor driving member is disposed outside the first supporting seat or the fifth supporting seat, and the low-pressure electronic driving member is coupled to one end of the low-pressure rotor through a coupling.
3. The aerial dual rotor comprehensive vibration testing bench of claim 2, wherein the low pressure rotor drive is an electric motor or a gas turbine drive.
4. The test bench for testing comprehensive vibration of aviation birotors as claimed in claim 1, wherein the high-pressure rotor driving mechanism comprises a high-pressure rotor driving member, the high-pressure rotor driving member is arranged on one side of the third supporting seat, and the high-pressure rotor driving member is connected with the hollow shaft through a belt transmission assembly or a bevel gear assembly.
5. The aerial dual rotor comprehensive vibration testing bench of claim 4, wherein the high pressure rotor driver is an electric motor or a gas turbine driver.
6. The test bench for testing comprehensive vibration of aviation birotors as claimed in claim 1, wherein a squirrel cage elastic support is arranged between the third support seat and the fourth support seat.
7. The test bench for testing comprehensive vibration of aviation birotors as claimed in claim 6, wherein the hollow shaft and the high-pressure rotor are connected through a coupling, and the coupling is arranged inside the squirrel cage elastic support.
8. The test bench for testing aviation dual-rotor comprehensive vibration as claimed in claim 6, wherein a damper is arranged on the fourth supporting seat, and a gap for forming an oil film by high-pressure oil pumping is arranged between the damper and the squirrel-cage elastic support.
9. The test bench for testing comprehensive vibration of aviation dual rotors as claimed in claim 1, wherein the first support seat, the second support seat, the third support seat, the fourth support seat and the fifth support seat are all provided with bearings for supporting corresponding low-pressure rotors or high-pressure rotors.
10. The test bench of claim 1, wherein the working platform is a T-shaped groove platform, and the first support seat, the second support seat, the third support seat, the fourth support seat and the fifth support seat are all mounted on the working platform by screws, and can be adjusted in position by the T-shaped groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121060641.8U CN215065140U (en) | 2021-05-18 | 2021-05-18 | Aviation dual-rotor comprehensive vibration test experiment table |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121060641.8U CN215065140U (en) | 2021-05-18 | 2021-05-18 | Aviation dual-rotor comprehensive vibration test experiment table |
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| CN215065140U true CN215065140U (en) | 2021-12-07 |
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| CN202121060641.8U Active CN215065140U (en) | 2021-05-18 | 2021-05-18 | Aviation dual-rotor comprehensive vibration test experiment table |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115235783A (en) * | 2022-09-22 | 2022-10-25 | 山东宇航推进航天科技有限公司 | Double-rotor coupling test device |
| CN117890093A (en) * | 2024-03-12 | 2024-04-16 | 太仓点石航空动力有限公司 | Vibration damping characteristic test equipment and test method for extrusion oil film damper |
-
2021
- 2021-05-18 CN CN202121060641.8U patent/CN215065140U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115235783A (en) * | 2022-09-22 | 2022-10-25 | 山东宇航推进航天科技有限公司 | Double-rotor coupling test device |
| CN115235783B (en) * | 2022-09-22 | 2023-08-22 | 山东宇航推进航天科技有限公司 | Birotor coupling test device |
| CN117890093A (en) * | 2024-03-12 | 2024-04-16 | 太仓点石航空动力有限公司 | Vibration damping characteristic test equipment and test method for extrusion oil film damper |
| CN117890093B (en) * | 2024-03-12 | 2024-05-10 | 太仓点石航空动力有限公司 | Vibration damping characteristic test equipment and test method for extrusion oil film damper |
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Effective date of registration: 20230117 Address after: Room A502, Building 19, Innovation and Entrepreneurship Plaza, Science and Technology Innovation City, High-tech Industrial Development Zone, Harbin, Heilongjiang Province, 150000 Patentee after: Harbin Qunshu Machinery Technology Co.,Ltd. Address before: Building 2, Longjiang community, 35 Xuefu Sandao street, Nangang District, Harbin City, Heilongjiang Province Patentee before: Huang Jie |