CN219242434U - Piston type aeroengine crankshaft and screw device - Google Patents
Piston type aeroengine crankshaft and screw device Download PDFInfo
- Publication number
- CN219242434U CN219242434U CN202223355031.8U CN202223355031U CN219242434U CN 219242434 U CN219242434 U CN 219242434U CN 202223355031 U CN202223355031 U CN 202223355031U CN 219242434 U CN219242434 U CN 219242434U
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- crankshaft
- wall
- cylinder body
- screw
- speed sensor
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Abstract
The utility model discloses a piston type aeroengine crankshaft and a screw device, which comprises a fairing, a screw body and a cylinder body, wherein one end of the cylinder body is provided with a reduction gearbox, one side of the reduction gearbox is provided with a screw shaft through a bearing, one end of the cylinder body is provided with a crankshaft body penetrating through the reduction gearbox, one side of the crankshaft body is provided with the fairing, one side of the fairing, which is close to the cylinder body, is provided with a signal disc through a connecting plate, the top end of the cylinder body is provided with a first bracket, the inside of the first bracket is provided with a second magneto-electric rotating speed sensor, the outer wall of the crankshaft body is provided with a dual-mass flywheel, the outer wall of the dual-mass flywheel is provided with a first magneto-electric rotating speed sensor, and the outer wall of the crankshaft body is provided with a large bolt.
Description
Technical Field
The utility model relates to the technical field of engines, in particular to a crankshaft and a screw device of a piston aeroengine.
Background
The crankshaft is the most important component in an engine. The engine is used for bearing the force transmitted by the connecting rod, converting the force into torque, outputting the torque through the crankshaft and driving other accessories on the engine to work. The crankshaft is subjected to the combined action of centrifugal force of the rotating mass, periodically-changed gas inertia force and reciprocating inertia force, so that the crankshaft is subjected to bending torsion load. Therefore, the crankshaft is required to have enough strength and rigidity, and the journal surface needs to be wear-resistant, uniform in work and good in balance.
However, the existing piston aeroengine crankshafts and screws have the following problems during use: the existing crankshaft and propeller shaft testing method and tool have the problems of complex installation and operation, poor testing accuracy, low testing efficiency and the like. How to create a device which has simple structure, convenient installation and lower cost and can obtain real-time torsional vibration data of a crankshaft and a propeller shaft is a technical problem which needs to be solved urgently in the industry.
Disclosure of Invention
The utility model aims to provide a crankshaft and a screw device of a piston type aeroengine, which are used for solving the related problems in the background art.
In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides a piston aeroengine bent axle and screw means, includes radome fairing, screw body and torsion damper, the one end of cylinder body is provided with the reducing gear box, the bent axle body that runs through the reducing gear box is installed to cylinder body one end, and the radome fairing is installed to one side of crankshaft body, one side that the radome fairing is close to the cylinder body is provided with the signal disc through the connecting plate, first support is installed on the top of cylinder body, and the inside of first support is provided with second magneto-electric speed sensor, the outer wall of bent axle body is provided with dual mass flywheel, and dual mass flywheel's outer wall is provided with first magneto-electric speed sensor, big bolt is installed to the outer wall of bent axle body, the outer wall of bent axle body is through big bolt fixed mounting torsion damper, the timing shroud is installed to one side that the cylinder body is close to torsion damper, the bottom of timing shroud is provided with the oil pan, and one side of oil pan is through the bolt fastening second support, photoelectric encoder is installed through the mounting hole to the outer wall of second support.
The technical scheme provides a piston aeroengine bent axle and screw device, the outer wall of radome fairing is provided with the screw body that is connected with the screw axle.
According to the piston type aeroengine crankshaft and the screw device, a gap is kept between the second magneto-electric rotating speed sensor and the signal panel.
The technical scheme provides a piston aeroengine bent axle and screw means, the inside of big bolt is provided with the screw layer, and the internally mounted of screw groove has flat-head bolt.
According to the technical scheme, one end of the photoelectric encoder is contacted with the plain bolt.
Compared with the prior art, the utility model provides a piston aeroengine crankshaft and a screw device, which have the following beneficial effects:
1. according to the utility model, the first magnetoelectric rotating speed sensor is arranged on the cylinder body, and the dual-mass flywheel is rigidly connected with one end of the crankshaft body, so that the rotating speed of one end of the crankshaft body is measured, and the rotating speed of the signal panel is driven to rotate through the rotation of the propeller body, so that the second magnetoelectric rotating speed sensor measures the rotating speed of the propeller shaft at the propeller body, and the torsion angle of the propeller shaft can be obtained.
2. According to the utility model, when the engine is started to run, the dual-mass flywheel rotates, the first magneto-electric rotating speed sensor measures the rotating speed of the dual-mass flywheel, the rotating speed is approximately equal to the rotating speed of one end of the crankshaft body, and the torsion angle of one end of the crankshaft body is obtained through data processing.
Drawings
FIG. 1 is a front view of a cylinder and dual mass flywheel of the present utility model;
fig. 2 is a right side view of the torsional vibration damper and the photoelectric encoder of the present utility model.
In the figure: 1. a fairing; 2. a propeller body; 3. a signal panel; 4. a first magneto-electric speed sensor; 5. a first bracket; 6. a reduction gearbox; 7. a second magneto-electric rotation speed sensor; 8. a dual mass flywheel; 9. a cylinder; 10. a torsional damper; 11. a photoelectric encoder; 12. a timing cover; 13. a large bolt; 14. a second bracket; 15. an oil pan; 16. a crankshaft body.
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.
Embodiment 1, as shown in fig. 1-2, the present utility model provides a technical solution: the utility model provides a piston aeroengine bent axle and screw device, including radome fairing 1, screw body 2 and torsional damper 10, the one end of cylinder body 9 is provided with reducing gear box 6, the bent axle body 16 that runs through reducing gear box 6 is installed to cylinder body 9 one end, and radome fairing 1 is installed to one side of crank axle body 16, one side that radome fairing 1 is close to cylinder body 9 is provided with signal disc 3 through the connecting plate, first support 5 is installed on the top of cylinder body 9, and the inside of first support 5 is provided with second magneto-electric speed sensor 7, the outer wall of crank axle body 16 is provided with dual mass flywheel 8, and the outer wall of dual mass flywheel 8 is provided with first magneto-electric speed sensor 4, the outer wall welding of radome fairing 1 has screw body 2, and screw body 2 quantity is 3, keep the clearance between second magneto-electric speed sensor 7 and the signal disc 3, install on cylinder body 9 through first magneto-electric speed sensor 4, and dual mass 8 carries out rigid connection with crank axle body 16 one end, thereby measure the rotational speed of crank axle body 16 one end, and through screw body 2 rotation, drive screw body 2 rotation, make the second magneto-electric speed sensor 7 can measure screw shaft 7 department, thereby screw shaft 2 rotation speed sensor obtains.
Working principle: the method comprises the steps of firstly switching on an external motor, when an engine is started to run, rotating a dual-mass flywheel 8, measuring the rotating speed of the dual-mass flywheel 8 by a first magneto-electric rotating speed sensor 4, obtaining the rotating speed of one end of a crankshaft body 16 approximately equivalent to the rotating speed of the crankshaft body 16, obtaining the torsion angle of one end of the crankshaft body 16 through data processing, rotating a propeller body 2 to drive a signal panel 3 to rotate, measuring the rotating speed of a propeller shaft by a second magneto-electric rotating speed sensor 7, obtaining the torsion angle of the propeller shaft through data processing, and finally calculating the difference value between the torsion angle of the propeller shaft and the torsion angle of the dual-mass flywheel 8 under the same rotating speed to obtain the torsion vibration of the propeller shaft.
Finally, it should be noted that the above description is only for illustrating the technical solution of the present utility model, and not for limiting the scope of the present utility model, and that the simple modification and equivalent substitution of the technical solution of the present utility model can be made by those skilled in the art without departing from the spirit and scope of the technical solution of the present utility model.
Claims (5)
1. The utility model provides a piston aeroengine bent axle and screw means, includes radome fairing, screw body and cylinder body, its characterized in that: one end of the cylinder body is provided with a reduction gearbox, one side of the reduction gearbox is provided with a propeller shaft through a bearing, one end of the cylinder body is provided with a crankshaft body penetrating through the reduction gearbox, one side of the crankshaft body is provided with a fairing, one side of the fairing, which is close to the cylinder body, is provided with a signal panel through a connecting plate, the top end of the cylinder body is provided with a first bracket, the inside of the first bracket is provided with a second magneto-electric rotating speed sensor, the outer wall of the crankshaft body is provided with a dual-mass flywheel, and the outer wall of dual mass flywheel is provided with first magnetoelectric rotational speed sensor, big bolt is installed to the outer wall of bent axle body, the outer wall of bent axle body is through big bolt fixed mounting has torsional damper, the cylinder body is close to one side of torsional damper and installs the cover in right time, the bottom of cover in right time is provided with the oil pan, and one side of oil pan is through the bolt fastening second support, photoelectric encoder is installed through the mounting hole to the outer wall of second support.
2. A piston aeroengine crankshaft and screw device as claimed in claim 1, wherein: the outer wall of the fairing is provided with a propeller body connected with a propeller shaft.
3. A piston aeroengine crankshaft and screw device as claimed in claim 1, wherein: and a gap is kept between the second magneto-electric rotating speed sensor and the signal panel.
4. A piston aeroengine crankshaft and screw device as claimed in claim 1, wherein: the inside of big bolt is provided with the screw thread layer, and the internally mounted of screw thread groove has flat-head bolt.
5. A piston aeroengine crankshaft and screw device as claimed in claim 4, wherein: one end of the photoelectric encoder is contacted with the plain bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223355031.8U CN219242434U (en) | 2022-12-14 | 2022-12-14 | Piston type aeroengine crankshaft and screw device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223355031.8U CN219242434U (en) | 2022-12-14 | 2022-12-14 | Piston type aeroengine crankshaft and screw device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219242434U true CN219242434U (en) | 2023-06-23 |
Family
ID=86838833
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223355031.8U Active CN219242434U (en) | 2022-12-14 | 2022-12-14 | Piston type aeroengine crankshaft and screw device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219242434U (en) |
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2022
- 2022-12-14 CN CN202223355031.8U patent/CN219242434U/en active Active
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