CN211927274U - Rotor supporting structure of aviation dual-rotor test bed - Google Patents
Rotor supporting structure of aviation dual-rotor test bed Download PDFInfo
- Publication number
- CN211927274U CN211927274U CN202020998044.9U CN202020998044U CN211927274U CN 211927274 U CN211927274 U CN 211927274U CN 202020998044 U CN202020998044 U CN 202020998044U CN 211927274 U CN211927274 U CN 211927274U
- Authority
- CN
- China
- Prior art keywords
- rotor
- pressure rotor
- low
- bearing seat
- pressure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model provides a rotor supporting structure of an aviation dual-rotor test bed, which comprises a low-pressure rotor, a high-pressure rotor, a low-pressure rotor drive and a high-pressure rotor drive, wherein the low-pressure rotor is arranged in the high-pressure rotor, and two ends of the low-pressure rotor extend out of the high-pressure rotor; a first bearing seat used for supporting the low-pressure rotor is arranged at one end, close to the low-pressure rotor drive, of the low-pressure rotor, a second bearing seat used for supporting the high-pressure rotor is arranged at one end of the high-pressure rotor, a third bearing seat used for supporting the high-pressure rotor is arranged at the other end of the high-pressure rotor, a fourth bearing seat and a fifth bearing seat used for supporting the low-pressure rotor are arranged at one end, far away from the low-pressure rotor drive, of the low-pressure rotor, and the fifth bearing seat is located at the end portion of the; the high-pressure rotor is arranged on one side of the third bearing seat in a driving mode. The utility model discloses a change rotor support mode and realize the research of rotor vibration characteristic, provide reliable test data for the research of two rotor system vibration characteristic of aviation.
Description
Technical Field
The utility model relates to a rotor vibration test correlation technique field specifically is a rotor bearing 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 supporting mode of the rotor in the aviation dual-rotor system has great influence on the vibration characteristic of the rotor, so that the design of the rotor supporting structure which is easy to build and can comprehensively research the vibration characteristic of the aviation dual-rotor system from multiple aspects is a technical problem which needs 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 a rotor bearing structure of two rotor test benches of aviation, realize the research of rotor vibration characteristic through changing rotor support mode, provide reliable test data for the research of two rotor system vibration characteristic of aviation.
The technical scheme of the utility model as follows:
a rotor supporting structure of an aviation dual-rotor test bed comprises 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 connected with one end of the low-pressure rotor in a driving mode, the high-pressure rotor is connected with the high-pressure rotor in a driving mode, the low-pressure rotor is arranged in the high-pressure rotor, and two ends of the low-pressure rotor extend out of the high-;
a first bearing seat used for supporting the low-pressure rotor is arranged at one end, close to the low-pressure rotor drive, of the low-pressure rotor, a second bearing seat used for supporting the high-pressure rotor is arranged at one end of the high-pressure rotor, a third bearing seat used for supporting the high-pressure rotor is arranged at the other end of the high-pressure rotor, a fourth bearing seat and a fifth bearing seat used for supporting the low-pressure rotor are arranged at one end, far away from the low-pressure rotor drive, of the low-pressure rotor, and the fifth bearing seat is located at the end portion of the;
the high-pressure rotor is arranged on one side of the third bearing seat in a driving mode.
Further, the bearing in the second bearing seat is arranged between the outer diameter of the low-pressure rotor and the inner diameter of the high-pressure rotor, and the bearing in the third bearing seat is sleeved on the outer diameter of the high-pressure rotor.
Further, the axis of the low-pressure rotor drive coincides with the low-pressure rotor, and the axis of the high-pressure rotor drive is perpendicular to the high-pressure rotor.
Furthermore, a driving shaft driven by the high-pressure rotor is rotatably arranged in the third bearing seat, and the driving shaft driven by the high-pressure rotor is connected with the high-pressure rotor through a bevel gear.
Further, be equipped with the low pressure rotor counter weight dish of installing on the low pressure rotor between first bearing frame and the second bearing frame and between fourth bearing frame and the fifth bearing frame, be equipped with the high pressure rotor counter weight dish of installing on the high pressure rotor between second bearing frame and the third bearing frame.
Furthermore, the first bearing seat, the second bearing seat, the third bearing seat, the fourth bearing seat and the fifth bearing seat are all fixed on the base.
The utility model has the advantages that:
1. the utility model discloses in, the support mode of five bearing frames is adopted to the rotor bearing structure of two rotor systems of aviation, in five bearing frames, a common support high pressure rotor and low pressure rotor that is used for, the low pressure rotor is supported alone to the other three, another one supports high pressure rotor alone, through this special bearing structure, when carrying out rotor vibration capability test, can replace the setting with each bearing frame between two squirrel cage elastic support and squeeze film damping support, through the test to rotor vibration performance, provide experimental data support for aeroengine's optimal design.
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 rotation to gather the vibration characteristic of rotor under high-speed.
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 bearing structure of aviation birotor test bench.
As shown, the rotor support mechanism includes 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 the rotor supporting structure of this embodiment, it is specific that the rotor is supported through five bearing seats, which are respectively: 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 (6)
1. A rotor supporting structure of an aviation dual-rotor test bed comprises a low-pressure rotor, a high-pressure rotor, a low-pressure rotor driver and a high-pressure rotor driver, wherein the low-pressure rotor driver is connected with one end of the low-pressure rotor, the high-pressure rotor driver is connected with the high-pressure rotor,
the low-pressure rotor is arranged in the high-pressure rotor, and two ends of the low-pressure rotor extend out of the high-pressure rotor;
a first bearing seat used for supporting the low-pressure rotor is arranged at one end, close to the low-pressure rotor drive, of the low-pressure rotor, a second bearing seat used for supporting the high-pressure rotor is arranged at one end of the high-pressure rotor, a third bearing seat used for supporting the high-pressure rotor is arranged at the other end of the high-pressure rotor, a fourth bearing seat and a fifth bearing seat used for supporting the low-pressure rotor are arranged at one end, far away from the low-pressure rotor drive, of the low-pressure rotor, and the fifth bearing seat is located at the end portion of the;
the high-pressure rotor is arranged on one side of the third bearing seat in a driving mode.
2. The rotor support structure of an aviation dual-rotor test bed as claimed in claim 1, wherein the bearing in the second bearing housing is disposed between the outer diameter of the low pressure rotor and the inner diameter of the high pressure rotor, and the bearing in the third bearing housing is disposed on the outer diameter of the high pressure rotor.
3. The rotor support structure of an aerial dual-rotor test rig according to claim 1, wherein the axis of the low pressure rotor drive is coincident with the low pressure rotor and the axis of the high pressure rotor drive is perpendicular to the high pressure rotor.
4. The rotor support structure of an aviation dual-rotor test bed as claimed in claim 3, wherein the high-pressure rotor-driven driving shaft is rotatably disposed in the third bearing seat, and the high-pressure rotor-driven driving shaft is connected with the high-pressure rotor through a bevel gear.
5. The rotor support structure of an aviation dual-rotor test bed as claimed in claim 1, wherein a low-pressure rotor counterweight disk mounted on a low-pressure rotor is disposed between the first bearing seat and the second bearing seat and between the fourth bearing seat and the fifth bearing seat, and a high-pressure rotor counterweight disk mounted on a high-pressure rotor is disposed between the second bearing seat and the third bearing seat.
6. The rotor support structure of an airborne dual-rotor test rig according to claim 1, wherein the first bearing block, the second bearing block, the third bearing block, the fourth bearing block and the fifth bearing block are all fixed on a base.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020998044.9U CN211927274U (en) | 2020-06-03 | 2020-06-03 | Rotor supporting structure of aviation dual-rotor test bed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020998044.9U CN211927274U (en) | 2020-06-03 | 2020-06-03 | Rotor supporting structure of aviation dual-rotor test bed |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211927274U true CN211927274U (en) | 2020-11-13 |
Family
ID=73320141
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020998044.9U Active CN211927274U (en) | 2020-06-03 | 2020-06-03 | Rotor supporting structure of aviation dual-rotor test bed |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211927274U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115184004A (en) * | 2022-09-08 | 2022-10-14 | 北京宇航推进科技有限公司 | Aviation birotor test bench |
| 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 |
-
2020
- 2020-06-03 CN CN202020998044.9U patent/CN211927274U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115184004A (en) * | 2022-09-08 | 2022-10-14 | 北京宇航推进科技有限公司 | Aviation birotor test bench |
| 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 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN211927274U (en) | Rotor supporting structure of aviation dual-rotor test bed | |
| CN209692544U (en) | Combination mechanism | |
| CN210469209U (en) | Multipoint parallel synchronous driving solar tracking system | |
| CN109018430A (en) | Rotor craft blade is performance test bed | |
| CN211927275U (en) | Aviation dual-rotor comprehensive vibration characteristic test bed | |
| CN110635661A (en) | Horizontal water-cooling double-cylinder type permanent magnet speed regulator | |
| CN215065140U (en) | Aviation dual-rotor comprehensive vibration test experiment table | |
| CN110661482A (en) | Solar photovoltaic power generation system based on big data | |
| CN211908611U (en) | Rotor driving structure of aviation dual-rotor test bed | |
| CN108945525B (en) | Small frame type control moment gyro driven by hollow ultrasonic motor | |
| CN110808657B (en) | Motor mounting structure with noise reduction function | |
| CN208885918U (en) | A kind of adjustable center distance gear assembly | |
| CN109268446B (en) | Tandem type three-dimensional vibration reduction single-machine equipment installation device and aircraft | |
| CN104253523A (en) | Combined permanent magnet eddy current speed governor | |
| CN212175539U (en) | Ventilation pressure-relief type sound absorption and insulation barrier for high-speed railway | |
| CN208010353U (en) | A kind of cutter head of shield machine mechanism that rimless combination type permanent-magnet linear synchronous motor directly drives | |
| JP2022517092A (en) | Improvement method for stator installation in wind turbine generators | |
| CN112816193A (en) | Variable load endurance testing device and testing method for electric control actuator | |
| CN112082788A (en) | Variable inertia follow-up large-load simulation test device of thrust vector servo mechanism | |
| CN108900066A (en) | Circular arc motor and Medical Devices | |
| CN110907110B (en) | Angle vibration table combining rigidity and flexible guiding | |
| CN219661287U (en) | Chair back position and posture adjusting driving structure | |
| CN218596782U (en) | Integration rail unit and rail equipment of polishing | |
| CN214793515U (en) | Mounting structure of internal temperature sensor for bus duct | |
| CN217950581U (en) | Dual-drive wind power generation device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |