CN115727096A - Aviation shaft drive fan torque buffer device - Google Patents
Aviation shaft drive fan torque buffer device Download PDFInfo
- Publication number
- CN115727096A CN115727096A CN202211279756.5A CN202211279756A CN115727096A CN 115727096 A CN115727096 A CN 115727096A CN 202211279756 A CN202211279756 A CN 202211279756A CN 115727096 A CN115727096 A CN 115727096A
- Authority
- CN
- China
- Prior art keywords
- disc
- shaft
- shell
- friction
- spring
- 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.)
- Pending
Links
Images
Abstract
The invention relates to a moment buffering device of an aviation shaft-driven fan, which comprises an input shaft, a shell, a friction disc, a compression spring, an adjusting disc, a cam disc assembly, a bearing and an output shaft, wherein the input shaft is connected with the shell; the roller is pressed on the wave-shaped disc surface of the cam disc, the wave crest of the wave-shaped disc surface can push the adjusting disc to axially move to compress the friction spring when the cam disc rotates, so that the annular convex shoulder of the input shaft and the shell are compressed into a whole, and the wave trough of the wave-shaped disc surface can enable the adjusting disc to axially move to release the compression of the friction spring when the cam disc rotates, so that the annular convex shoulder of the input shaft and the shell are released from a compression state. By adopting the torque buffering device, the stress of the fan transmission shaft can be stably changed in the process of starting or stopping the shaft-driven fan, the condition of fan shaft breakage caused by acceleration, deceleration and over-twisting of the transmission shaft is avoided, and the completeness of the aircraft is improved.
Description
Technical Field
The invention relates to the field of structural design of aviation matched fans, in particular to a moment buffering device of an aviation shaft-driven fan.
Background
The moment buffer device for the aviation shaft-driven fan is arranged on a power receiving shaft of the fan and consists of a power shaft connecting mechanism, an over-torque shearing mechanism, a friction transmission mechanism and an angular acceleration detection and actuation mechanism.
By adopting the aviation shaft-driven fan moment buffering device, the fan shaft breakage condition caused by acceleration, deceleration and overtorque of the transmission shaft can be avoided, and the completeness of the aircraft is improved.
Disclosure of Invention
The purpose of the invention is: the problem of shaft breakage caused by the fact that a power output shaft on the aircraft exceeds the protective torque of the shear shaft due to power fluctuation of an aircraft-mounted shaft driving fan is solved, stress of a transmission shaft is enabled to change stably in the acceleration and deceleration process, and reliability of a rotating shaft and the completeness of an aircraft are improved.
The technical scheme of the invention is as follows:
the moment buffering device for the aviation shaft-driven fan comprises an input shaft 1, a shell 2, a friction disc 3, a compression spring 4, an adjusting disc 5, a cam disc assembly 6, a bearing and an output shaft 7;
the front end of the input shaft 1 and the rear end of the output shaft are coaxially arranged in the shell 2, and the friction disc 3, the compression spring 4, the adjusting disc component 5 and the cam disc component 6 are sequentially sleeved at the front end of the input shaft 1;
an annular convex shoulder is formed at the front end of the input shaft, an axial friction matching surface is formed between the annular convex shoulder and the shell, the annular convex shoulder is axially located between the friction disc 3 and the shell, the compression spring is arranged between the friction disc and the adjusting disc 5, the spring applies axial pre-tightening force to the friction disc, the adjusting disc is in spline fit with the shell, a lug plate axially extends from the adjusting disc, and the lug plate is provided with a roller;
the cam disc assembly 6 comprises a cam disc, a buffer spring and a mass block, the disc surface of the cam disc is in a wave shape and is matched with the roller, the cam disc and the mass block are in annular sliding fit, the mass block is in spline connection with the shell, the buffer spring is arranged between the mass block and the cam disc, and the buffer spring forms annular buffer between the mass block and the cam disc; the bearing is arranged between the cam plate and the output shaft, and the output shaft and the shell are fixed into a whole; under the effect of friction spring, the gyro wheel is pressed on the wave type quotation of cam disc, the crest of wave type quotation can promote the adjusting disk axial displacement when the cam disc rotates and compress tightly friction spring, makes the annular convex shoulder of input shaft with the casing compresses tightly as an organic wholely, the trough of wave type quotation can make the compressing tightly of adjusting disk axial displacement release friction spring when the cam disc rotates, makes the annular convex shoulder of input shaft with the casing is relieved and is compressed tightly the state.
Further, the bearing is a ball bearing.
Furthermore, the mass blocks are multiple and are circumferentially and uniformly distributed.
Furthermore, the buffer springs are multiple and are distributed annularly and uniformly.
Furthermore, the cam disc is a double-layer disc, and the spring and the mass block are positioned between the double-layer disc.
Furthermore, the rollers are multiple and are circumferentially and uniformly distributed.
Furthermore, the friction spring is a disc spring.
Further, the bearing is a thrust bearing.
Furthermore, a plurality of cooling holes are arranged in the friction area of the shell or the annular convex shoulder and are uniformly distributed in the annular direction, and preferably, the cooling holes can be arranged for a plurality of circles; the flow area of the cooling hole of the shell is not completely shielded by the annular shoulder, so that an air flow passage is formed inside the shell.
The moment buffer device of the aviation shaft-driven fan is used as a transmission shaft and is arranged on an aircraft, one end of the moment buffer device is connected with an onboard driving shaft, when the shaft-driven fan is started, the onboard driving shaft is rapidly accelerated, the torque borne by the transmission shaft is larger than that during stable work due to the reasons of low rotational inertia, low temperature of a lubricating system and the like, and a fan rotor starts to do accelerated motion along with the buffer device. Under the action of angular acceleration, a cam disc in the buffer device overcomes the acting force of a return spring, twists a certain angle, and the highest point of the cam staggers the contact point of an adjusting disc component, so that the adjusting disc component moves towards the direction close to the cam disc component under the acting force of a compression spring, the pressing force of the compression spring is reduced, a friction disc slips for a short time, the rotor is accelerated under lower driving force, and the working condition of the rotor is improved.
When the acceleration process is nearly finished, the angular acceleration borne by the buffer device is reduced, the cam disc restores the initial position under the action of the reset spring, the highest point of the cam is restored to be in contact with the contact point of the regulating disc assembly, the regulating disc is far away from the cam disc, the initial deformation of the compression spring is restored, the pressing force of the friction disc is restored to the normal working value, and the fan enters a stable working state. When the rotating speed is reduced before the fan stops working, the buffer device can also avoid the instantaneous high torque caused by the too fast stop of the driving shaft and the rotational inertia of the fan rotor, and the rotor is protected from being slowly decelerated. When the fan is in clamping failure, the friction disc can continuously slip to prevent the driving shaft on the machine from being damaged, for example, after the friction transmission part is damaged due to overheating or is clamped due to other reasons, the shearing shaft is excessively twisted and sheared, and the driving shaft on the machine is protected from being damaged.
The invention has the advantages that: by adopting the torque buffering device, the stress of the fan transmission shaft can be stably changed in the process of starting or stopping the shaft-driven fan, the condition of fan shaft breakage caused by acceleration, deceleration and over-twisting of the transmission shaft is avoided, and the completeness of the aircraft is improved.
Drawings
FIG. 1 is a cross-sectional view of an aircraft shaft drive fan torque damper of the present invention;
FIG. 2 is an assembled view of an aircraft shaft driven fan torque damper assembly;
FIG. 3 is a perspective view of the regulator disk assembly;
FIG. 4 is a perspective view of a cam plate assembly;
FIG. 5 is a perspective view of a circumferential stop block;
FIG. 6 is a schematic illustration of the internal assembly of a cam plate assembly;
FIG. 7 is a perspective view of the housing;
FIG. 8 is a perspective view of a shear axis of example 1;
FIG. 9 is a perspective view of an aircraft shaft driven fan torque damper;
in the figure: 1-input shaft, 2-shell, 3-friction disk, 4-compression spring, 5-adjusting disk, 6-cam disk component, 7-output shaft, 8-bearing, 9-annular convex shoulder, 10-wave disk surface, 11-lug, 12-roller, 13-buffer spring and 14-mass block.
Detailed Description
The disclosed examples will be described more fully with reference to the accompanying drawings, in which some (but not all) of the disclosed examples are shown. Indeed, many different examples may be described and should not be construed as limited to the examples set forth herein. Rather, these examples are described so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
The description of the different advantageous arrangements has been presented for purposes of illustration and description, but is not intended to be exhaustive or limited to the examples in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. Additionally, the different advantageous examples may describe different advantages as compared to other advantageous examples. The example or examples selected are chosen and described in order to best explain the principles of the examples, the practical application, and to enable others of ordinary skill in the art to understand the disclosure for various examples with various modifications as are suited to the particular use contemplated.
In the embodiment, referring to the attached fig. 1-9, the moment buffering device for the aviation shaft-driven fan comprises an input shaft 1, a shell 2, a friction disc 3, a compression spring 4, an adjusting disc 5, a cam disc assembly 6, a bearing and an output shaft 7;
the front end of the input shaft 1 and the rear end of the output shaft are coaxially arranged in the shell 2, and the friction disc 3, the compression spring 4, the adjusting disc component 5 and the cam disc component 6 are sequentially sleeved at the front end of the input shaft 1;
an annular convex shoulder is formed at the front end of the input shaft, an axial friction matching surface is formed between the annular convex shoulder and the shell, the annular convex shoulder is axially located between the friction disc 3 and the shell, the compression spring is arranged between the friction disc and the adjusting disc 5, the spring applies axial pre-tightening force to the friction disc, the adjusting disc is in spline fit with the shell, a lug plate axially extends from the adjusting disc, and the lug plate is provided with a roller;
the cam disc assembly 6 comprises a cam disc, a buffer spring and a mass block, the disc surface of the cam disc is in a wave shape and is matched with the roller, the cam disc and the mass block are in annular sliding fit, the mass block is in spline connection with the shell, the buffer spring is arranged between the mass block and the cam disc, and the buffer spring forms annular buffer between the mass block and the cam disc; the bearing is arranged between the cam plate and the output shaft, and the output shaft and the shell are fixed into a whole; under the effect of friction spring, the gyro wheel is pressed on the wave type quotation of cam disc, the crest of wave type quotation can promote the adjusting disk axial displacement when the cam disc rotates and compress tightly friction spring, makes the annular convex shoulder of input shaft with the casing compresses tightly as an organic wholely, the trough of wave type quotation can make the compressing tightly of adjusting disk axial displacement release friction spring when the cam disc rotates, makes the annular convex shoulder of input shaft with the casing is relieved and is compressed tightly the state.
The bearing is a ball bearing.
The mass blocks are multiple and are circumferentially and uniformly distributed.
The buffer springs are multiple and are circumferentially and uniformly distributed.
The cam disc is a double-layer disc, and the spring and the mass block are positioned between the double-layer discs.
The gyro wheel is a plurality of, and hoop evenly distributed.
The friction spring is a disc spring.
The bearing is a thrust bearing.
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is understood that the embodiments described are part of the invention, and not all of them. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Claims (10)
1. A moment buffering device of an aviation shaft-driven fan is characterized by comprising an input shaft, a shell, a friction disc, a compression spring, an adjusting disc, a cam disc assembly, a bearing and an output shaft;
the front end of the input shaft 1 and the rear end of the output shaft are coaxially arranged in the shell, and the friction disc, the compression spring, the adjusting disc assembly and the cam disc assembly are sequentially sleeved at the front end of the input shaft;
an annular convex shoulder is formed at the front end of the input shaft, an axial friction matching surface is formed between the annular convex shoulder and the shell, the annular convex shoulder is axially located between the friction disc and the shell, the compression spring is arranged between the friction disc and the adjusting disc, the spring applies axial pre-tightening force to the friction disc, the adjusting disc is in spline fit with the shell, a lug plate axially extends from the adjusting disc, and the lug plate is provided with a roller;
the cam disc assembly comprises a cam disc, a buffer spring and a mass block, wherein the disc surface of the cam disc is in a wave shape and is matched with the roller, the cam disc and the mass block are in annular sliding fit, the mass block is in spline connection with the shell, the buffer spring is arranged between the mass block and the cam disc, and the buffer spring forms annular buffer between the mass block and the cam disc; the bearing is arranged between the cam plate and the output shaft, and the output shaft and the shell are fixed into a whole; under the effect of the friction spring, the roller is pressed on the wave-shaped disc surface of the cam disc, the wave crest of the wave-shaped disc surface can push the adjusting disc to axially move to compress the friction spring when the cam disc rotates, so that the annular convex shoulder of the input shaft and the shell are compressed into a whole, and the wave trough of the wave-shaped disc surface can enable the adjusting disc to axially move to release the compression of the friction spring when the cam disc rotates, so that the annular convex shoulder of the input shaft and the shell are released from a compression state.
2. The moment buffering device for shaft driven aviation fan as claimed in claim 1, wherein the bearing is a ball bearing.
3. The moment buffering device for the aviation shaft-driven fan is characterized in that the mass blocks are distributed annularly and uniformly.
4. The moment buffering device for the aviation shaft-driven fan is characterized in that a plurality of buffering springs are uniformly distributed in the circumferential direction.
5. The moment buffering device for the shaft driven aviation fan as claimed in claim 1, wherein the cam disc is a double-layer disc, and the spring and the mass block are located between the double-layer discs.
6. The moment buffering device for the aviation shaft-driven fan is characterized in that the number of the rollers is multiple, and the rollers are circumferentially and uniformly distributed.
7. The moment buffering device for shaft driven aviation fan as claimed in claim 1, wherein the friction spring is disc spring.
8. The moment buffering device for aviation shaft driven fan as claimed in claim 1, wherein the bearing is a thrust bearing.
9. The moment buffering device for aviation shaft driven fan as claimed in claim 1, wherein the friction area of the casing or the annular shoulder has several cooling holes distributed homogeneously,
10. the moment buffering device for shaft driven aviation fan as claimed in claim 9, wherein the cooling hole has multiple turns; wherein the flow area of the cooling hole of the casing is not completely shielded by the annular shoulder, so that an air flow passage is formed inside and outside the casing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211279756.5A CN115727096A (en) | 2022-10-19 | 2022-10-19 | Aviation shaft drive fan torque buffer device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211279756.5A CN115727096A (en) | 2022-10-19 | 2022-10-19 | Aviation shaft drive fan torque buffer device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115727096A true CN115727096A (en) | 2023-03-03 |
Family
ID=85293688
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211279756.5A Pending CN115727096A (en) | 2022-10-19 | 2022-10-19 | Aviation shaft drive fan torque buffer device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115727096A (en) |
-
2022
- 2022-10-19 CN CN202211279756.5A patent/CN115727096A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP0122015B1 (en) | Air compressor | |
| EP2436952B1 (en) | Cone brake load limiter apparatus and the corresponding assembling method. | |
| WO1992009821A2 (en) | An improved pawl and ratchet clutch and method | |
| US4269293A (en) | Engine accessory disconnect | |
| US5419420A (en) | Flyweight actuated clutch | |
| EP4239222A1 (en) | Transmission system for aviation power | |
| CN115727096A (en) | Aviation shaft drive fan torque buffer device | |
| CN108026980B (en) | Safety coupling | |
| EP4239223A1 (en) | Transmission system for use in aviation powering | |
| KR101493053B1 (en) | A device for end-to-end coupling of a supercritical transmission shaft, in particular for driving a rotorcraft rotor | |
| US5362276A (en) | Selective torque clipping mechanism | |
| CN206889150U (en) | A kind of starter inserted type output shaft assembly | |
| US6620066B2 (en) | Drive unit for an alternator of a motor vehicle | |
| CN205099138U (en) | Speed limit protection device | |
| US3555317A (en) | Electric motor and clutch | |
| CN208885812U (en) | Elastic limit torsional square clutch | |
| US4926991A (en) | Actuated spring clutch assembly | |
| JPS6035798Y2 (en) | overload safety device | |
| CN217440637U (en) | Take torque protection function's freewheel clutch | |
| US8696473B2 (en) | Automatic resetting torque limiter capable of high speed continuous operations in released mode | |
| CN219911563U (en) | Unmanned helicopter annular spring centrifugal clutch | |
| CN107514447A (en) | A kind of antioverloading protects deceleration device | |
| EP2864672B1 (en) | Automatic resetting torque limiter capable of high speed continuous operation in released mode | |
| CN108081944A (en) | A kind of torsional vibration damper for hybrid electric vehicle | |
| CN218761143U (en) | Low torsional rigidity torsion-limiting flywheel damper assembly |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |