CN211908611U - Rotor driving structure of aviation dual-rotor test bed - Google Patents
Rotor driving structure of aviation dual-rotor test bed Download PDFInfo
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- CN211908611U CN211908611U CN202020998043.4U CN202020998043U CN211908611U CN 211908611 U CN211908611 U CN 211908611U CN 202020998043 U CN202020998043 U CN 202020998043U CN 211908611 U CN211908611 U CN 211908611U
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Abstract
The utility model provides a rotor driving structure of an aviation dual-rotor test bed, which comprises a base, a low-voltage rotor, a high-voltage rotor, a low-voltage rotor driver and a high-voltage rotor driver, wherein the low-voltage rotor driver comprises a low-voltage electric spindle, the low-voltage rotor driver is fixedly installed on the base and can adjust the position on the base along the axis direction of the low-voltage electric spindle, and the low-voltage electric spindle driven by the low-voltage rotor is connected with one end of the low-voltage rotor through a coupler; the high-voltage rotor drive comprises a high-voltage electric spindle, the high-voltage rotor drive is fixedly mounted on the base and can be adjusted in position along the axis direction of the high-voltage electric spindle on the base, the high-voltage electric spindle is connected with a drive shaft through a coupler, and the drive shaft is connected with the high-voltage rotor through a gear. The driving structure can realize the relatively high-speed operation driving of the high-pressure rotor and the low-pressure rotor, is reasonable and compact in layout and convenient to install, and is easy to build a test bed.
Description
Technical Field
The utility model relates to a rotor vibration test correlation technique field specifically is a rotor drive structure of aviation birotor 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. The structural design of the aviation dual-rotor test bed is complex, the layout of the driving structure and the connection relation between the driving structure and the rotor are decisive factors, and the stability of the rotor in operation can be influenced, so that the design of the rotor driving structure which is easy to arrange and build on the test bed and can ensure the stable operation of the dual rotors is a technical problem to be solved urgently by 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 the rotor drive structure of two rotor test benches of aviation, this drive structure can realize the relative high-speed operation drive of high-pressure rotor and low pressure rotor, and drive structural layout is reasonable, compact, simple to operate, easily buildding of test bench.
The technical scheme of the utility model as follows:
a rotor driving structure of an aviation dual-rotor test bed comprises a base, a low-pressure rotor, a high-pressure rotor, a low-pressure rotor driver and a high-pressure rotor driver, wherein the low-pressure rotor is arranged in the high-pressure rotor, two ends of the low-pressure rotor driver extend out of the high-pressure rotor,
the low-voltage rotor drive comprises a low-voltage electric main shaft, the low-voltage rotor drive is fixedly arranged on the base and can adjust the position on the base along the axial direction of the low-voltage electric main shaft, and 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;
the high-voltage rotor drive comprises a high-voltage electric spindle, the high-voltage rotor drive is fixedly mounted on the base and can be adjusted in position along the axis direction of the high-voltage electric spindle on the base, the high-voltage electric spindle is connected with a drive shaft through a coupler, and the drive shaft is connected with the high-voltage rotor through a gear.
Further, the axis of the high-voltage electric spindle is perpendicular to the axis of the low-voltage electric spindle.
Furthermore, a bearing seat is arranged on the base, the driving shaft is rotatably arranged in the bearing seat, and the driving shaft is connected with the high-pressure rotor through a bevel gear.
Further, the bevel gears comprise a driving bevel gear and a driven bevel gear, the driving bevel gear is installed at one end of the driving shaft, the driven bevel gear is installed at one end of the high-pressure rotor, and the driving bevel gear is meshed with the driven bevel gear.
Further, the driven bevel gear is arranged at one end, far away from the low-pressure rotor, of the high-pressure rotor.
Further, the bearing seat is simultaneously used for supporting one end of the high-pressure rotor.
Further, the high-voltage electric main shaft is connected with the driving shaft through a nylon rope coupler, and the low-voltage electric main shaft is connected with the low-voltage rotor through a nylon rope coupler.
Furthermore, the base is provided with a long-strip-shaped track capable of being provided with a fastener; and the low-pressure rotor drive and the high-pressure rotor drive are fixedly arranged at the adaptive positions of the strip-shaped tracks through fasteners.
Further, the low-voltage rotor drive comprises a low-voltage drive mounting plate, and a long groove of the low-voltage drive mounting plate is arranged on the low-voltage drive mounting plate;
the low pressure rotor drives the position adjustment through the cooperation of the low pressure drive mounting plate rectangular groove, the track and the fastener.
Further, the high-voltage rotor drive comprises a high-voltage drive mounting plate, and a long groove of the high-voltage drive mounting plate is arranged on the high-voltage drive mounting plate;
the high-pressure rotor drive realizes position adjustment through the matching of the long-strip groove of the high-pressure drive mounting plate, the track and the fastener.
The utility model has the advantages that:
1. the utility model discloses in, can drive the low pressure rotor through low pressure rotor drive and high pressure rotor drive, the relative high speed of high pressure rotor rotates, low pressure rotor drive and high pressure rotor drive adopt to arrange perpendicularly, the mode of coupling joint, can be after rotor system equipment is accomplished, the installation of actuating system carries out again, because actuating system can carry out position control as independent structure, consequently, can make putting up of test bench comparatively easy, high pressure rotor adopts the drive mode of gear simultaneously, can guarantee the high-speed stable rotation of rotor, and make test bench overall structure compact reasonable, and occupation space is little.
2. The utility model discloses in, overall structure overall arrangement easily realizes and assembles, and low pressure rotor drive and high-pressure rotor drive mounting means are convenient, also are convenient for adjust.
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 a rotor drive structure of aviation birotor test bench.
As shown, 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 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.
The embodiment of the utility model provides a, still provide the bearing structure of above-mentioned rotor.
The specific rotor is supported through five bearing blocks, and the five bearing blocks are respectively as follows: 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.
Claims (10)
1. A rotor driving structure of an aviation dual-rotor test bed comprises a base, a low-pressure rotor, a high-pressure rotor, a low-pressure rotor driver and a high-pressure rotor driver, wherein the low-pressure rotor is arranged in the high-pressure rotor, and two ends of the low-pressure rotor driver extend out of the high-pressure rotor,
the low-voltage rotor drive comprises a low-voltage electric main shaft, the low-voltage rotor drive is fixedly arranged on the base and can adjust the position on the base along the axial direction of the low-voltage electric main shaft, and 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;
the high-voltage rotor drive comprises a high-voltage electric spindle, the high-voltage rotor drive is fixedly mounted on the base and can be adjusted in position along the axis direction of the high-voltage electric spindle on the base, the high-voltage electric spindle is connected with a drive shaft through a coupler, and the drive shaft is connected with the high-voltage rotor through a gear.
2. The rotor driving structure of an aviation dual-rotor test bed as claimed in claim 1, wherein the axis of the high voltage electric spindle is perpendicular to the axis of the low voltage electric spindle.
3. The rotor driving structure of an aviation dual-rotor test bed as claimed in claim 1, wherein the base is provided with a bearing seat, the driving shaft is rotatably disposed in the bearing seat, and the driving shaft and the high-pressure rotor are connected through a bevel gear.
4. The rotor driving structure of an aviation dual-rotor test bed as claimed in claim 3, wherein the bevel gears comprise a driving bevel gear and a driven bevel gear, the driving bevel gear is mounted at one end of the driving shaft, the driven bevel gear is mounted at one end of the high-pressure rotor, and the driving bevel gear is engaged with the driven bevel gear.
5. The rotor driving structure of an aviation dual-rotor test bed as claimed in claim 4, wherein said driven bevel gear is installed at one end of said high-pressure rotor far from the driving of said low-pressure rotor.
6. The rotor driving structure of an aviation dual-rotor test bed as claimed in claim 3, wherein said bearing seat is used to support one end of said high-pressure rotor at the same time.
7. The rotor driving structure of the aviation dual-rotor test bed as claimed in claim 1, wherein the high voltage electric spindle and the driving shaft are connected through a nylon rope coupling, and the low voltage electric spindle and the low voltage rotor are connected through a nylon rope coupling.
8. The rotor driving structure of the aviation dual-rotor test bed as claimed in claim 1, wherein the base is provided with an elongated rail on which a fastener can be mounted; and the low-pressure rotor drive and the high-pressure rotor drive are fixedly arranged at the adaptive positions of the strip-shaped tracks through fasteners.
9. The rotor driving structure of an aviation dual-rotor test bed as claimed in claim 8, wherein the low pressure rotor driver comprises a low pressure driving mounting plate, and the low pressure driving mounting plate is provided with a low pressure driving mounting plate elongated slot;
the low pressure rotor drives the position adjustment through the cooperation of the low pressure drive mounting plate rectangular groove, the track and the fastener.
10. The rotor driving structure of an aviation dual-rotor test bed as claimed in claim 8, wherein the high-pressure rotor driver comprises a high-pressure driving mounting plate, and the high-pressure driving mounting plate is provided with a long groove;
the high-pressure rotor drive realizes position adjustment through the matching of the long-strip groove of the high-pressure drive mounting plate, the track and the fastener.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020998043.4U CN211908611U (en) | 2020-06-03 | 2020-06-03 | Rotor driving structure of aviation dual-rotor test bed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020998043.4U CN211908611U (en) | 2020-06-03 | 2020-06-03 | Rotor driving structure of aviation dual-rotor test bed |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211908611U true CN211908611U (en) | 2020-11-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020998043.4U Active CN211908611U (en) | 2020-06-03 | 2020-06-03 | Rotor driving structure of aviation dual-rotor test bed |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211908611U (en) |
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2020
- 2020-06-03 CN CN202020998043.4U patent/CN211908611U/en active Active
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