CN211927275U - Aviation dual-rotor comprehensive vibration characteristic test bed - Google Patents
Aviation dual-rotor comprehensive vibration characteristic test bed Download PDFInfo
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- CN211927275U CN211927275U CN202020998045.3U CN202020998045U CN211927275U CN 211927275 U CN211927275 U CN 211927275U CN 202020998045 U CN202020998045 U CN 202020998045U CN 211927275 U CN211927275 U CN 211927275U
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Abstract
The utility model provides an aviation dual-rotor comprehensive vibration characteristic test bed, which comprises a base, a low-pressure rotor, a high-pressure rotor, a low-pressure rotor drive and a high-pressure rotor drive; the low-pressure rotor is fixedly arranged on one side of the base and connected with one end of the low-pressure rotor, and the axis of the low-pressure rotor is overlapped with the axis of the low-pressure rotor; the high-pressure rotor is sleeved outside the low-pressure rotor, one end of the high-pressure rotor, close to the low-pressure rotor, is matched with the low-pressure rotor through a bearing, one end of the high-pressure rotor, far away from the low-pressure rotor, is supported through a bearing seat fixedly arranged on the base, and a bearing is arranged between the end of the high-pressure rotor and the bearing seat; the high-pressure rotor is fixedly installed on the base and connected with the high-pressure rotor in a driving mode, and the axis of the high-pressure rotor is perpendicular to the axis of the high-pressure rotor. The utility model discloses a to the birotor system of this test bench vibration capability test, can improve for aeroengine and provide powerful experimental data.
Description
Technical Field
The utility model relates to a rotor vibration test correlation technique field specifically is an aviation birotor comprehensive vibration characteristic test bench.
Background
The rotor system is the core structure of an aircraft engine, and the main rotor system of the aircraft engine is a double-rotor structure, namely a high-pressure rotor and a low-pressure rotor are connected together through a bearing. The research on the aviation dual-rotor system is always the work focus of some colleges and research institutions, so that the corresponding aviation dual-rotor system vibration characteristic test bed is produced.
Due to the professional limitation of the aviation dual-rotor system, the vibration test bed built by each existing large high-efficiency and scientific research unit is extremely complex and single in structure, is generally built for the local structure of an aero-engine, and is suitable for the vibration characteristic research of a single factor. Therefore, designing a test bed which is easy to build and can comprehensively research the vibration characteristics of the aviation dual-rotor system from multiple aspects is a technical problem which needs to be solved urgently by the technical personnel in the field.
SUMMERY OF THE UTILITY MODEL
For solving the not enough of prior art, the utility model discloses combine prior art, from practical application, provide an aviation birotor synthesis vibration characteristic test bench, this test bench has and easily builds, can guarantee high-pressure rotor and the high-speed pivoted characteristics of low pressure rotor relatively stable, carries out the vibration capability test through the birotor system to this test bench, can improve for aeroengine and provide strong experimental data.
The technical scheme of the utility model as follows:
an aviation dual-rotor comprehensive vibration characteristic test bed comprises a base, a low-pressure rotor, a high-pressure rotor, a low-pressure rotor driver and a high-pressure rotor driver;
the low-pressure rotor is fixedly arranged on one side of the base in a driving mode and is connected with one end of the low-pressure rotor, and the axis of the low-pressure rotor is overlapped with the axis of the low-pressure rotor;
the high-pressure rotor is sleeved outside the low-pressure rotor, one end of the high-pressure rotor, close to the low-pressure rotor, is matched with the low-pressure rotor through a bearing, one end of the high-pressure rotor, far away from the low-pressure rotor, is supported through a bearing seat fixedly installed on the base, and a bearing is arranged between the end of the high-pressure rotor and the bearing seat;
the high-pressure rotor is fixedly installed on the base and connected with the high-pressure rotor, and the axis of the high-pressure rotor is perpendicular to the axis of the high-pressure rotor.
Furthermore, one end of the high-pressure rotor, which is far away from the low-pressure rotor drive, is connected with the high-pressure rotor drive through a gear.
Furthermore, the high-pressure rotor drive comprises a drive shaft, the drive shaft is rotatably arranged in the bearing block, and the drive shaft is connected with the high-pressure rotor through a gear.
Furthermore, a driven bevel gear is fixedly mounted on the end face of one side, far away from the low-pressure rotor, of the high-pressure rotor, a driving bevel gear is fixedly mounted on the end face of the driving shaft, and the driving bevel gear is meshed with the driven bevel gear.
Furthermore, the low-voltage electric main shaft driven by the low-voltage rotor is connected with one end of the low-voltage rotor through a coupler, and the high-voltage electric main shaft driven by the high-voltage rotor is connected with the driving shaft through a coupler.
Further, the coupler is a nylon rope coupler.
Furthermore, both ends of the low-pressure rotor extend out of the high-pressure rotor, and bearing seats are arranged at both ends of the high-pressure rotor to realize supporting.
Furthermore, a bearing seat is arranged at one end, close to the low-pressure rotor drive, of the low-pressure rotor, and two bearing seats are arranged at one end, far away from the low-pressure rotor drive, of the low-pressure rotor.
Further, the low-pressure rotor and the high-pressure rotor are both provided with a counterweight plate.
Further, the high pressure rotor drive and the low pressure rotor drive are fixedly mounted on the base through fasteners.
The utility model has the advantages that:
1. the utility model discloses an aviation birotor test bench's structural design is compact reasonable, easily buildding of test bench, and the drive configuration who adopts of test bench arranges and the support mode of low pressure rotor and high-pressure rotor, can guarantee the high-speed rotation of the relatively stable between low pressure rotor and the high-pressure rotor, through the vibration condition test to under the high-speed operation of rotor, can provide strong data support for aeroengine's improvement.
2. The utility model discloses an among the bearing structure, easy dismounting between each bearing frame, simple structure is rationally distributed, and the arrangement of bearing frame and low pressure rotor adopt direct drive's mode, high pressure rotor to adopt gear drive's mode, can make low pressure rotor and high pressure rotor keep good stability when high-speed rotating, and the support mode of rotor easily supports the data test under the environment (can adopt two squirrel cage elastic supports, squeeze film support etc. if concrete support) to the difference.
Drawings
FIG. 1 is a schematic view of the structure of the present invention;
FIG. 2 is a schematic top view of the present invention;
fig. 3 is a side view of the structure of the present invention.
Reference numerals shown in the drawings:
1. a base; 2. driving a low-pressure rotor; 3. driving a high-pressure rotor; 4. a first bearing housing; 5. a second bearing housing; 6. a third bearing seat; 7. a fourth bearing seat; 8. a fifth bearing seat; 9. a first bearing; 10. a second bearing; 11. a third bearing; 12. a fourth bearing; 13. a fifth bearing; 14. a first low pressure rotor counterweight disc; 15. a high pressure rotor counterweight disc; 16. a second low pressure rotor counterweight disc; 17. a high pressure rotor; 18. a low-pressure rotor; 19. a driven bevel gear; 20. a first coupling; 21. a second coupling; 22. a drive shaft; 23. a drive bevel gear; 24. a high voltage drive mounting plate; 25. the high-voltage driving mounting plate is provided with a long groove; 26. a low voltage drive mounting plate; 27. the low voltage drives the long groove of the mounting plate.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments. 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, 2 and 3, the present invention provides a schematic diagram of a related structure of an aviation dual-rotor test bed.
The embodiment of the utility model provides an in, provide an aviation birotor comprehensive vibration characteristic test bench.
The test bench of this embodiment includes specifically: a low pressure rotor 18, a high pressure rotor 17, a low pressure rotor drive 2, a high pressure rotor drive 3; the high-voltage rotor drive 3 is arranged on the side surface adjacent to the low-voltage rotor drive 2, the axis of the high-voltage rotor drive 3 is vertical to the axis of the high-voltage rotor 17, the high-voltage rotor 17 and the low-voltage rotor 18 are in relative rotation, and the length of the low-voltage rotor 18 is greater than that of the high-voltage rotor 17, so that the two ends of the low-voltage rotor 18 in the high-voltage rotor 17 extend out of the high-voltage rotor 17;
in this embodiment, the high-pressure rotor 17 is sleeved outside the low-pressure rotor 18, one end of the high-pressure rotor 17 close to the low-pressure rotor drive 2 is matched with the low-pressure rotor 18 through the second bearing 10, one end of the high-pressure rotor 17 far away from the low-pressure rotor drive 2 is supported by the third bearing seat 6 fixedly mounted on the base 1, and the third bearing 11 is arranged between the end of the high-pressure rotor 17 and the third bearing seat 6. The driving mode arrangement and the rotor supporting mode in the embodiment can ensure the stable operation of the high-pressure rotor 17 and the low-pressure rotor 18 at a high speed, so as to better simulate a double-rotor system of an aircraft engine. Meanwhile, in the embodiment, the structural design is compact, and the test bed is easy to build.
In another embodiment of the present invention, there is also provided a specific supporting structure of the rotor.
As shown, the rotor is supported by five bearing blocks. The method comprises the following steps: a first bearing seat 4 for supporting the low-pressure rotor 18 is arranged at one end of the low-pressure rotor 18 close to the low-pressure rotor drive 2, a second bearing seat 5 for supporting the high-pressure rotor 17 is arranged at one end of the high-pressure rotor 17, a third bearing seat 6 for supporting the high-pressure rotor 17 is arranged at the other end of the high-pressure rotor 17, a fourth bearing seat 7 and a fifth bearing seat 8 for supporting the low-pressure rotor 18 are arranged at one end of the low-pressure rotor 18 far away from the low-pressure rotor drive 2, and the fifth bearing seat 8 is arranged at the end part of the low-pressure rotor 18; the high-pressure rotor drive 3 is arranged on the side of the third bearing block 6. In the above rotor supporting structure of this embodiment, the first bearing seat 4, the fourth bearing seat 7, and the fifth bearing seat 8 are used to separately support the low pressure rotor 18, the third bearing seat 6 is used to separately support the high pressure rotor 17, the second bearing seat 5 is used to simultaneously support the high pressure rotor 17 and the low pressure rotor 18, and the first bearing seat 4, the second bearing seat 5, the third bearing seat 6, the fourth bearing seat 7, and the fifth bearing seat 8 are respectively provided therein with the corresponding first bearing 9, the second bearing 10, the third bearing 11, the fourth bearing 12, and the fifth bearing 13. Through the support structure, the relative high-speed rotation of the low-pressure rotor 18 and the high-pressure rotor 17 can be ensured, and the test data can be tested by adopting double-squirrel-cage elastic support or squeeze film dampers at the positions of the first bearing seat 4, the second bearing seat 5, the third bearing seat 6, the fourth bearing seat 7 and the fifth bearing seat 8.
In this embodiment, specifically, the second bearing 10 in the second bearing housing 5 is disposed between the outer diameter of the low pressure rotor 18 and the inner diameter of the high pressure rotor 17, and the third bearing 11 in the third bearing housing 6 is sleeved on the outer diameter of the high pressure rotor 17. One end of the high-pressure rotor 17 and the low-pressure rotor 18 are supported together through the second bearing 10, and the other end of the high-pressure rotor is supported independently through the third bearing 11 fixed on the base 1, so that high-speed stable rotation can be realized.
In this embodiment, as shown in the figure, a first low-pressure rotor counterweight disk 14 is arranged between the first bearing seat 4 and the second bearing seat 5, a second low-pressure rotor counterweight disk 14 is arranged between the fourth bearing seat 7 and the fifth bearing seat 8, a high-pressure rotor counterweight disk 15 mounted on a high-pressure rotor 17 is arranged between the second bearing seat 5 and the third bearing seat 6, and the stable high-speed relative rotation of the low-pressure rotor 18 and the high-pressure rotor 17 is ensured through the arrangement of the counterweight disks.
In another embodiment of the present invention, there is also provided a driving structure of the rotor.
In this embodiment, the low-voltage rotor drive 2 includes a low-voltage electric spindle, the low-voltage rotor drive 2 is fixedly mounted on the base 1 and can adjust a position on the base 1 along an axial direction of the low-voltage electric spindle, and the low-voltage electric spindle of the low-voltage rotor drive 2 is connected to one end of the low-voltage rotor 18 through a first coupler 20;
high-voltage rotor drive 3 is including high-voltage electricity main shaft, high-voltage rotor drive fixed mounting in just can be in on the base 1 along its high-voltage electricity main shaft axis direction adjustment position, high-voltage electricity main shaft pass through second shaft coupling 21 and connect a drive shaft 22, and drive shaft 22 passes through gear connection high-voltage rotor 17.
In this embodiment, the low-pressure rotor drive 2 can be adjusted in position, the first coupling 20 is easy to disassemble and assemble, the high-pressure rotor drive 3 can be adjusted in position, the second coupling 21 is easy to disassemble and assemble, and the transition drive shaft 22 is arranged between the high-pressure rotor drive 3 and the high-pressure rotor 17 in a gear matching mode, so that the test bed is easy to realize and install, and the compactness of the structure of the test bed can be ensured.
In the present embodiment, as shown in the figure, the driving shaft 21 is rotatably disposed in the third bearing seat 6, and the driving shaft 21 and the high-pressure rotor 17 are connected by a bevel gear; the bevel gear comprises a driving bevel gear 23 and a driven bevel gear 19, the driving bevel gear 23 is installed at one end of the driving shaft 21, the driven bevel gear 19 is installed at one end of the high-pressure rotor 17, the driving bevel gear 23 is meshed with the driven bevel gear 19, reversing is achieved through the bevel gear, the high-pressure rotor drives 3 to drive the high-pressure rotor 17 to rotate at a high speed, and the purpose of gear driving is achieved.
In this embodiment, the driven bevel gear 19 is installed on the high-pressure rotor 17 at the end far away from the low-pressure rotor drive 2, and the first coupler 20 and the second coupler 21 both adopt nylon rope couplers, so as to ensure the convenience in disassembly and assembly and the stability in connection.
In the present embodiment, the low-pressure rotor drive 2 and the high-pressure rotor drive 3 are configured to be adjustable in position. Specifically, the base 1 is provided with a long strip-shaped track capable of being provided with a fastener; the low-pressure rotor drive 2 comprises a low-pressure drive mounting plate 26, and a long groove 27 of the low-pressure drive mounting plate is arranged on the low-pressure drive mounting plate 26;
the low-pressure rotor drive 2 can realize position adjustment and fixation through the matching of the low-pressure drive mounting plate long groove 27, a rail and a fastener; similarly, the high-voltage rotor drive 3 comprises a high-voltage drive mounting plate 24, and a long groove 25 of the high-voltage drive mounting plate is arranged on the high-voltage drive mounting plate 24; the high-pressure rotor drive 3 realizes position adjustment and fixation through the matching of the long groove 25 of the high-pressure drive mounting plate, a track and a fastener. This structure makes low pressure rotor drive 2, high pressure rotor drive 3 have position adjustment convenience, easy dismounting, the advantage of easy test bench integral erection.
Claims (10)
1. The test bed for the comprehensive vibration characteristics of the aviation dual-rotor is characterized by comprising a base, a low-pressure rotor, a high-pressure rotor, a low-pressure rotor driver and a high-pressure rotor driver;
the low-pressure rotor is fixedly arranged on one side of the base in a driving mode and is connected with one end of the low-pressure rotor, and the axis of the low-pressure rotor is overlapped with the axis of the low-pressure rotor;
the high-pressure rotor is sleeved outside the low-pressure rotor, one end of the high-pressure rotor, close to the low-pressure rotor, is matched with the low-pressure rotor through a bearing, one end of the high-pressure rotor, far away from the low-pressure rotor, is supported through a bearing seat fixedly installed on the base, and a bearing is arranged between the end of the high-pressure rotor and the bearing seat;
the high-pressure rotor is fixedly installed on the base and connected with the high-pressure rotor, and the axis of the high-pressure rotor is perpendicular to the axis of the high-pressure rotor.
2. The test bed for comprehensive vibration characteristics of aviation dual rotors as claimed in claim 1, wherein one end of the high-pressure rotor far away from the low-pressure rotor drive is connected with the high-pressure rotor drive through a gear.
3. The test bed for comprehensive vibration characteristics of aviation dual rotors as claimed in claim 2, wherein the high pressure rotor drive comprises a drive shaft, the drive shaft is rotatably mounted in a bearing seat, and the drive shaft is connected with the high pressure rotor through a gear.
4. The test bed for comprehensive vibration characteristics of aviation dual rotors as claimed in claim 3, wherein a driven bevel gear is fixedly mounted on the end surface of one side of the high-pressure rotor far away from the driving of the low-pressure rotor, a driving bevel gear is fixedly mounted on the end surface of the driving shaft, and the driving bevel gear is meshed with the driven bevel gear.
5. The test bed for comprehensive vibration characteristics of aviation dual-rotor according to claim 4, wherein the low-voltage electric spindle driven by the low-voltage rotor is connected with one end of the low-voltage rotor through a coupler, and the high-voltage electric spindle driven by the high-voltage rotor is connected with the driving shaft through a coupler.
6. The test bed for comprehensive vibration characteristics of the aviation dual-rotor structure as claimed in claim 5, wherein the coupler is a nylon rope coupler.
7. The test bed for comprehensive vibration characteristics of aviation dual-rotor according to claim 1, wherein two ends of the low-pressure rotor extend out of the high-pressure rotor, and bearing seats are arranged at two ends of the low-pressure rotor for realizing support.
8. The test bed for the comprehensive vibration characteristics of the aviation dual-rotor as claimed in claim 7, wherein one end of the low-pressure rotor, which is close to the low-pressure rotor drive, is provided with one bearing seat, and the end of the low-pressure rotor, which is far away from the low-pressure rotor drive, is provided with two bearing seats.
9. The test bed for comprehensive vibration characteristics of aviation dual rotors according to claim 1, wherein the low-pressure rotor and the high-pressure rotor are provided with weight plates.
10. The test bed for testing the comprehensive vibration characteristics of the aviation dual-rotor structure as claimed in claim 1, wherein the high-pressure rotor driver and the low-pressure rotor driver are fixedly mounted on the base through fasteners.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020998045.3U CN211927275U (en) | 2020-06-03 | 2020-06-03 | Aviation dual-rotor comprehensive vibration characteristic test bed |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020998045.3U CN211927275U (en) | 2020-06-03 | 2020-06-03 | Aviation dual-rotor comprehensive vibration characteristic test bed |
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| CN211927275U true CN211927275U (en) | 2020-11-13 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112629840A (en) * | 2020-11-20 | 2021-04-09 | 韩清凯 | Aircraft engine double-rotor-support-casing tester and testing method thereof |
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2020
- 2020-06-03 CN CN202020998045.3U patent/CN211927275U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112629840A (en) * | 2020-11-20 | 2021-04-09 | 韩清凯 | Aircraft engine double-rotor-support-casing tester and testing method thereof |
| CN112629840B (en) * | 2020-11-20 | 2023-11-17 | 韩清凯 | Double-rotor-support-casing tester for aero-engine and testing method thereof |
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