CN115325152A

CN115325152A - Helicopter main reducer lubricating system that splashes

Info

Publication number: CN115325152A
Application number: CN202211008844.1A
Authority: CN
Inventors: 马艺敏; 郭凯; 王晋华; 张宇; 黄俊通
Original assignee: Zhejiang Huayi Aviation Technology Co ltd
Current assignee: Zhejiang Huayi Aviation Technology Co ltd
Priority date: 2022-08-22
Filing date: 2022-08-22
Publication date: 2022-11-11

Abstract

The invention provides a helicopter main reducer splash lubrication system, aiming at solving the problem of a top bearing of a main reducer with complicated stress working conditions; the existing main speed reducer lubrication is realized by splashing lubricating oil through gear stirring, and the splashed oil mist is difficult to splash to a bearing arranged at the top of the main speed reducer. The helicopter main reducer splash lubrication system comprises a main reducer box body, a rotor shaft, a driving gear, an oil pump assembly and a splash disc; an oil groove is arranged in the main reduction gearbox body; the rotor shaft is rotatably arranged on the main speed reducer box body through a top bearing and a bottom bearing; the driving gear is arranged on the rotor shaft; the splash plate is arranged on the rotor shaft; the oil inlet end of the oil pump assembly is connected with the oil groove, and the oil flowing out of the oil outlet end of the oil pump assembly flows to the upper surface of the splash disc. When the rotor shaft is rotated, the rotor shaft drives the oil pump assembly to operate, and the rotor shaft simultaneously drives the operation of the splash disc, so that lubricating oil splashes to the top bearing through the splash disc.

Description

Helicopter main reducer lubricating system that splashes

Technical Field

The invention belongs to the technical field of helicopters, and particularly relates to a splash lubrication system of a main speed reducer of a helicopter.

Background

The main speed reducer is one of the most critical components of the helicopter, and mainly has the functions of transmitting the power of an engine to a main rotor and reducing and reversing the output of the engine; the main reducer transmits torque through a gear to change the rotating speed; the rotation meshing of gear, the epaxial bearing of rotor all need lubricate and the heat dissipation.

The top bearing of the main reducer is complex in stress working condition, and is a part which is most seriously worn due to very large axial force and lateral force; however, most of the prior main speed reducer lubrication is performed by splashing lubricating oil generated by stirring gears in the main speed reducer, and splashed oil mist is difficult to splash to a top bearing arranged on the main speed reducer; under the condition that the top bearing cannot be lubricated, the service life of the top bearing is greatly reduced, the reliability of the whole system is reduced, and the top bearing is not beneficial to the safe operation of the helicopter.

Disclosure of Invention

The invention provides a helicopter main reducer splash lubrication system, aiming at solving the problem of a top bearing of a main reducer with complicated stress working conditions; the lubrication of the main speed reducer in the prior art is realized by splashing lubricating oil generated by stirring gears in the main speed reducer, and the splashed oil mist is difficult to splash to a bearing arranged at the top of the main speed reducer.

In order to solve the technical problems, the technical scheme adopted by the invention is as follows: a helicopter main reducer splash lubrication system comprises a main reducer box body, a rotor shaft and a driving gear; an oil groove is formed in the bottom in the main reduction gearbox body; the rotor shaft is rotatably arranged on the main speed reducer box body through a top bearing and a bottom bearing, and the bottom bearing is positioned below the oil groove; the driving gear is arranged on the rotor shaft and rotates along with the rotation of the rotor shaft; the helicopter main reducer splash lubrication system also comprises an oil pump assembly and a splash disc; the splash disc is arranged on the rotor shaft, rotates along with the rotation of the rotor shaft, and is positioned below the top bearing and above the driving gear; the oil feed end of oil pump subassembly links to each other with the oil groove, the oil flow that the end of producing oil of oil pump subassembly flows is to the upper surface of splash disc, and when the rotor axle was rotatory, rotor axle drive oil pump subassembly operation.

The further improved scheme is as follows: the oil pump subassembly includes by rotor shaft driven oil pump and the oil pipe and play oil pipe that advances who links to each other with the oil pump, the oil inlet end that advances the oil pipe links to each other with the oil groove, the end setting that goes out oil of play oil pipe just splashes the dish setting at the top of final drive box body towards.

Based on above-mentioned scheme, can transmit the oil in the oil groove to the splash disc through the oil pump subassembly on, the oil that splashes on the splash disc can play lubricated effect to the top bearing, in addition, the oil pump is by rotor shaft drive, need not to dispose extra power, and the weight of cost is just can not additionally improve the helicopter because of the power problem.

The further improved scheme is as follows: the rotor shaft is provided with a step for supporting the lower end of the splash disc, and the upper end of the splash disc is pressed and fixed by an inner ring of the top bearing.

Based on above-mentioned scheme, the dish that splashes adopts this mounting means, can accomplish the installation with the top bearing together, simple to operate, and the upper end that splashes the dish is compressed tightly fixedly by the inner ring of top bearing, and on the one hand, the bearing has fixed the dish that splashes, and on the other hand, the effect that splashes the dish and played the axle sleeve has prescribed a limit to the position of top bearing.

The further improved scheme is as follows: the splash disc comprises a circular disc body, a shaft sleeve sleeved on a rotor shaft is arranged at the center of the circular disc body, and a groove is formed between reinforcing ribs and reinforcing ribs on the upper surface of the circular disc body.

Based on above-mentioned scheme, the recess of strengthening rib and formation can play the effect of splashing oil on the one hand, and the splash dish can be consolidated to the on the other hand strengthening rib.

The further improved scheme is as follows: an oil hole which penetrates through the splash plate up and down is formed in the groove in the splash plate.

Based on above-mentioned scheme, through the oilhole, can be so that the oil that the splash disc did not splash flows to the oil groove in, be favorable to oil to circulate.

The further improved scheme is as follows: the driving gear is located above the oil groove.

Based on above-mentioned scheme, drive gear is located the top of oil groove, and the drive gear can be lubricated to the lubricating oil that drips on the one hand, and on the other hand drive gear can be so that lubricating oil produces the secondary and splashes and lubricate.

The further improved scheme is as follows: the edge of the circular disk body is provided with an annular flange, and the reinforcing rib is arranged between the annular flange and the shaft sleeve.

The further improved scheme is as follows: the oil pump is a cycloid pump and is connected with the rotor shaft through a synchronous belt.

The further improved scheme is as follows: the driving gear is a bevel gear.

The further improved scheme is as follows: the oil groove is the bell jar, and the bottom of bell jar is equipped with the mounting hole, the rotor shaft passes on the mounting hole of oil tank bottom and the bottom bearing installs between the inner wall of rotor shaft and mounting hole.

The beneficial effects of the invention are as follows:

according to the helicopter main reducer splash lubrication system, the splash disc is arranged below the top bearing, oil flowing out of the oil outlet end of the oil pump assembly flows to the upper surface of the splash disc, when the rotor shaft rotates, the rotor shaft drives the oil pump assembly to operate, and the rotor shaft simultaneously drives the splash disc to operate, so that lubricating oil can splash onto the top bearing through the splash disc, the top bearing is lubricated, heat generated by the top bearing of the main reducer under a high-complexity stress working condition is reduced, and the service life is prolonged.

In addition, the splash plate rotates with the rotation of the rotor shaft; when the rotor shaft rotates, the rotor shaft drives the oil pump assembly to operate; make whole helicopter main reducer lubrication system that splashes's operation all by the rotor shaft drive, whole system moves along with the operation of rotor shaft, stops along with the stopping of rotor shaft, need not to increase extra power supply moreover, and the synchronism of operation is better on the one hand, and on the other hand need not because of extra power, raises the cost, simple structure is compact.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and those skilled in the art can also obtain other related drawings based on the drawings without inventive efforts.

Fig. 1 is a schematic sectional structure of the present invention.

FIG. 2 is a schematic view of a splash plate according to the present invention.

The reference numbers in the figures illustrate:

1-a reducer box body; 2-a rotor shaft; 3-bevel gears; 4-a splash plate; 41-circular disk body; 42-oil holes; 43-reinforcing ribs; 44-a rib; 45-shaft sleeve; 5-an oil pump; 6-oil pipe; 7-a bottom bearing; 8-top bearing.

Detailed Description

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 should be understood that the specific embodiments described herein are merely illustrative of the invention and do not delimit the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the invention without inventive step, are within the scope of the invention.

Referring to fig. 1, a helicopter main reducer splash lubrication system includes: the main speed reducer comprises a main speed reducer box body 1, a rotor shaft 2, a driving gear, an oil pump 5 assembly and a splash disc 4; an oil groove is formed in the bottom in the main reduction gearbox body; the rotor shaft 2 is rotatably arranged on the main speed reducer box body 1 through a top bearing 8 and a bottom bearing 7, and the bottom bearing 7 is positioned below the oil groove; the splash disc 4 is arranged on the rotor shaft 2 and is positioned below the top bearing 8, and the splash disc 4 rotates along with the rotation of the rotor shaft 2; the driving gear is arranged on the rotor shaft 2 and is positioned below the splash disc 4, and the driving gear rotates along with the rotation of the rotor shaft 2; the oil inlet end of 5 subassemblies of oil pump links to each other with the oil groove, the oil flow that flows of the end that produces oil of 5 subassemblies of oil pump is to the upper surface of splash pan 4, and when rotor shaft 2 was rotatory, 5 subassemblies of 2 drive oil pumps of rotor shaft ran.

Wherein the top bearing 8 and the bottom bearing 7 are preferably tapered roller bearings; the tapered roller bearing can have a certain bearing capacity in the vertical direction.

Wherein, the oil pump 5 subassembly includes by the oil pump 5 of rotor shaft 2 driven and the oil pipe 6 and play oil pipe 6 that link to each other with oil pump 5, the oil inlet end that advances oil pipe 6 links to each other with the oil groove, the end that produces oil that goes out oil pipe 6 sets up at the top of main reduction box and towards splash plate 4 setting, and the lubricating oil that flows out from the end that produces oil directly flows to the upper surface of splash plate 4 promptly, and after lubricating oil contacted splash plate 4, splashes and gets up to spout on the top bearing 8 of next-door neighbour to play lubricated effect to top bearing 8.

Referring to fig. 1, the installation structure of the splash plate 4 is: the rotor shaft 2 is provided with a step for supporting the lower end of the splash plate 4, and the upper end of the splash plate 4 is pressed and fixed by the inner ring of the top bearing 8. When the device is installed, the splash disc 4 is firstly sleeved on the rotor shaft 2 and positioned on the step, then the bevel gear 3 is installed, and the splash disc 4 is fixed between the inner ring of the bevel gear 3 and the step.

Referring to fig. 2, one specific structure of the splash plate 4 is: the splash disc 4 comprises a circular disc body 41, a shaft sleeve 45 sleeved on the rotor shaft 2 is arranged at the center of the circular disc body 41, reinforcing ribs 43 are arranged on the upper surface of the circular disc body 41, and grooves are formed among the reinforcing ribs 43; an oil hole 42 which penetrates through the splash plate 4 up and down is formed in the groove; an annular rib 44 is arranged on the boundary of the circular disc body 41, and the reinforcing rib 43 is arranged between the annular rib 44 and the shaft sleeve 45. The number of the reinforcing ribs 43 is 6, and the circular tray body 41 is divided into 6 grooves; two oil holes 42 are provided in each groove. When the lubricating oil flows to the splash plate 4, the lubricating oil is splashed under the action of the reinforcing ribs 43 and the annular ribs 44 of the splash plate 4, and the top bearing 8 is fully lubricated.

On the basis of any scheme, the driving gear is positioned above the oil groove; the driving gear is a bevel gear 3; when assembling, the bevel gear 3 is engaged with another bevel gear 3 to which power is inputted from the outside.

On the basis of any scheme, the oil pump 5 is a cycloid pump, and the oil pump 5 is connected with the rotor shaft 2 through a synchronous belt; wherein, the lower extreme of oil pump 5 is equipped with from the driving wheel, the lower extreme of rotor shaft 2 is equipped with the action wheel, the hold-in range setting realizes synchronous drive between follow driving wheel and action wheel.

On the basis of any one of the above schemes, the oil groove is a conical groove, the bottom of the conical groove is provided with a mounting hole, the rotor shaft 2 passes through the mounting hole at the bottom of the oil groove, the bottom bearing 7 is mounted between the inner walls of the rotor shaft 2 and the mounting hole, and the upper end opening of the conical groove is large and the lower end opening is small.

The invention is further described below with reference to the working principle:

when the driving gear drives the rotor shaft 2 to rotate, the rotor shaft 2 drives the oil pump 5 and the splash disc 4 to operate, when the oil pump 5 operates, the lubricating oil in the oil groove is operated to the upper side of the splash disc 4 through the oil inlet pipe 6 and the oil outlet pipe 6, and the lubricating oil is splashed under the action of the splash disc 4, so that the lubricating oil lubricates the top bearing 8.

The invention is not limited to the above alternative embodiments, and any other various forms of products can be obtained by anyone in the light of the present invention, but any changes in shape or structure thereof, which fall within the scope of the present invention as defined in the claims, fall within the scope of the present invention.

Claims

1. A helicopter main reducer splash lubrication system comprises a main reducer box body, a rotor shaft and a driving gear; an oil groove is formed in the bottom in the main reduction gearbox body; the rotor shaft is rotatably arranged on the main speed reducer box body through a top bearing and a bottom bearing, and the bottom bearing is positioned below the oil groove; the driving gear is arranged on the rotor shaft and rotates along with the rotation of the rotor shaft; the helicopter main reducer splash lubrication system is characterized by further comprising an oil pump assembly and a splash disc; the splash disc is arranged on the rotor shaft and rotates along with the rotation of the rotor shaft, and the splash disc is positioned below the top bearing and above the driving gear; the oil feed end of oil pump assembly links to each other with the oil groove, the oil stream that the end of producing oil of oil pump assembly flows is to the upper surface of splash disc, and when the rotor shaft was rotatory, rotor shaft drive oil pump assembly operation.

2. The helicopter main reducer splash lubrication system of claim 1, wherein the oil pump assembly includes an oil pump driven by the rotor shaft and an oil inlet pipe and an oil outlet pipe connected to the oil pump, the oil inlet end of the oil inlet pipe is connected to the oil tank, and the oil outlet end of the oil outlet pipe is disposed at the top of the main reducer housing and is disposed toward the splash plate.

3. The helicopter main reducer splash lubrication system of claim 1, characterized in that the rotor shaft is provided with a step supporting the lower end of the splash plate and the upper end of the splash plate is pressed and fixed by the inner ring of the top bearing.

4. The helicopter main reducing gear splash lubrication system of claim 1, characterized in that the splash disc comprises a circular disc body, the center of the circular disc body is provided with a shaft sleeve sleeved on the rotor shaft, the upper surface of the circular disc body is provided with reinforcing ribs, and grooves are formed between the reinforcing ribs.

5. The helicopter main reducer splash lubrication system of claim 4, characterized in that the grooves on the splash plate are provided with oil holes which penetrate up and down.

6. The helicopter main reducer splash lubrication system of claim 1 or 5, wherein the drive gear is located above an oil sump.

7. The helicopter main reducer splash lubrication system of claim 4, wherein the circular disk body is provided with an annular rib on its boundary, and the reinforcing rib is disposed between the annular rib and the bushing.

8. The helicopter main reducer splash lubrication system of claim 1, characterized in that the oil pump is a gerotor pump, which is connected to the rotor shaft through a timing belt.

9. The helicopter main reducer splash lubrication system of claim 1, wherein the drive gear is a bevel gear.

10. The helicopter main reducing gear splash lubrication system of claim 1, characterized in that the oil groove is a conical groove, and the bottom of the conical groove is provided with a mounting hole, the rotor shaft passes through the mounting hole at the bottom of the oil groove, and the bottom bearing is mounted between the rotor shaft and the inner wall of the mounting hole.