CN207956053U - A kind of mounting structure of lifting airscrew axis - Google Patents
A kind of mounting structure of lifting airscrew axis Download PDFInfo
- Publication number
- CN207956053U CN207956053U CN201820058294.7U CN201820058294U CN207956053U CN 207956053 U CN207956053 U CN 207956053U CN 201820058294 U CN201820058294 U CN 201820058294U CN 207956053 U CN207956053 U CN 207956053U
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- China
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- primary load
- load bearing
- top pressure
- rotor shaft
- bearing nut
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Abstract
The utility model is related to a kind of mounting structures of lifting airscrew axis, including main rotor shaft, shell, taper roll bearing, primary load bearing nut, top pressure bushing, the main rotor shaft is mounted on by taper roll bearing on the shell of helicopter, primary load bearing nut is installed in main rotor shaft, top pressure lining is set between primary load bearing nut and taper roll bearing inner ring, and the top pressure bushing is a section in the L-shaped annulus to center of circle direction protrusion；The material of the top pressure bushing is 1Cr17Ni4Cu4Nb.The utility model does not use hydraulic torque spanner, the frictional force between rotor shaft and primary load bearing nut is greatly reduced, keeps part injury-free when primary load bearing nut mounts and dismounts, and ensures assembling quality, it is ensured that the flight safety of helicopter.
Description
Technical field
The utility model is related to a kind of mounting structure, especially a kind of mounting structure of lifting airscrew axis may be implemented
The convenient installation and removal of each component of coaxial double-rotor helicopter rotor shaft.
Background technology
Coaxial double-rotor helicopter refers generally to coaxial helicopter, and rotor shaft primary load bearing nut main function is
Lock the large-scale taper roll bearing of a pair that is opposite and filling in rotor shaft.In flight course, for ensure bearing roller with it is inside and outside
Effective fitting of ring prevents shaft strength disengagement from bearing failure being caused to damage, and it is more than to go straight up to that rotor shaft primary load bearing nut, which will undertake,
Machine is conducted oneself with dignity and its axial force of load weight, is the vital part in Helicopter Main Reducer.
Assembly and decomposition for primary load bearing nut, main method have using large-scale torque spanner, torque multiplier and liquid
Press the methods of torque spanner, the large-scale torque spanner output torque upper limit is generally less than 2000N.m, in torque multiplier output torque
Limit is generally less than 15000N.m, and under normal circumstances, the primary load bearing nut of Medium Helicopter is needed when reaching requirement
For torque in 50000-80000N.m, device above-mentioned cannot be satisfied the assembly and disassembly requirement of rotor shaft primary load bearing nut.At present
The means being often used are can to provide higher output torque by way of hydraulic torque spanner, and highest output torque can be with
When reaching 100000N.m, but using hydraulic torque spanner, frictional force is excessive between rotor shaft and primary load bearing nut, easily causes spiral shell
Female and rotor axle thread and other associated damages, can not ensure the flight safety of aircraft, and cause huge economic losses.
Invention content
The purpose of this utility model is to provide a kind of mounting structure of lifting airscrew axis, meets coaxial double-rotor helicopter
The requirement of main reducing gear rotor shaft, meanwhile, installation torque when reducing the installation of primary load bearing nut and decomposing and frictional force are real
The convenient installation and removal of each component, improve main reducing gear service life on existing lifting airscrew axis.
The technical solution of the utility model is：The mounting structure of the lifting airscrew axis include main rotor shaft, shell,
Taper roll bearing, primary load bearing nut, top pressure bushing, the main rotor shaft are mounted on helicopter by taper roll bearing
On shell, it is provided with screw thread in main rotor shaft, and primary load bearing nut is installed, top pressure lining is set on primary load bearing nut and circular cone rolling
Between sub- bearing inner ring, the top pressure bushing is a section in the L-shaped annulus to center of circle direction protrusion, L-shaped minimum diameter
Coordinate with rotor shaft crest clearance, the large-sized internal diameter of L-shaped is more than the outer diameter of primary load bearing nut, and the height of bushing is more than primary load bearing
The height of nut；The material of the top pressure bushing is 1Cr17Ni4Cu4Nb.
The utility model is arranged on original architecture basics, is set between primary load bearing bearing and taper roll bearing inner ring
Top pressure bushing has been set, when mounted, first top pressure bushing has been mounted in rotor shaft, by applying axial force to top pressure bushing, and
Axial force is helicopter all-up weight, at this moment will act on the axial force on primary load bearing nut originally, and was transferred on top pressure bushing,
The mounting torque for reducing primary load bearing nut, by way of conventional and means, so that it may primary load bearing nut to be installed in place.
When dismounting, same opposite direction top pressure bushing applies axial force, will act on the axial force on primary load bearing nut originally, and was transferred to top pressure
On bushing, primary load bearing nut does not stress, and can easily disassemble.The material of top pressure bushing is 1Cr17Ni4Cu4Nb, intensity
It is higher, helicopter all-up weight can be born.The utility model does not use hydraulic torque when primary load bearing nut mounts and dismounts
The frictional force between rotor shaft and primary load bearing nut is greatly reduced in spanner, keeps part injury-free, ensures assembling quality, it is ensured that straight
The flight safety of the machine of liter.
Description of the drawings
Fig. 1 is the structural schematic diagram of the utility model.
Specific implementation mode
As shown, the mounting structure of lifting airscrew axis includes main rotor shaft 3, shell 5, taper roll bearing 4, leads and hold
Power nut 2, top pressure bushing 1, the main rotor shaft 3 are mounted on by taper roll bearing 4 on the shell 5 of helicopter, main rotation
It is provided with screw thread on wing axis 3, and primary load bearing nut 2 is installed, top pressure bushing 1 is arranged in primary load bearing nut 2 and taper roll bearing 4
Between inner ring, the top pressure bushing 1 is a section in the L-shaped annulus to center of circle direction protrusion, L-shaped minimum diameter and main rotation
3 crest clearance of wing axis coordinates, and the large-sized internal diameter of L-shaped is more than the outer diameter of primary load bearing nut 2, and the height of top pressure bushing 1 is more than master
The height of load nut 2；The material of the top pressure bushing 1 is 1Cr17Ni4Cu4Nb.
Claims (2)
1. a kind of mounting structure of lifting airscrew axis, which is characterized in that the structure includes main rotor shaft (3), shell
(5), taper roll bearing (4), primary load bearing nut (2), top pressure bushing (1), the main rotor shaft (3) pass through taper roller axis
(4) are held on the shell (5) of helicopter, main rotor shaft is provided with screw thread on (3), and installs primary load bearing nut (2), top pressure
Bushing (1) is arranged between primary load bearing nut (2) and taper roll bearing (4) inner ring, and the top pressure bushing (1) is a section
In the L-shaped annulus to center of circle direction protrusion, L-shaped minimum diameter coordinates with main rotor shaft (3) crest clearance, and L-shaped is large-sized
Internal diameter is more than the outer diameter of primary load bearing nut (2), and the height of top pressure bushing (1) is more than the height of primary load bearing nut (2).
2. the mounting structure of lifting airscrew axis as described in claim 1, which is characterized in that the top pressure bushing (1)
Material is 1Cr17Ni4Cu4Nb.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820058294.7U CN207956053U (en) | 2018-01-12 | 2018-01-12 | A kind of mounting structure of lifting airscrew axis |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820058294.7U CN207956053U (en) | 2018-01-12 | 2018-01-12 | A kind of mounting structure of lifting airscrew axis |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207956053U true CN207956053U (en) | 2018-10-12 |
Family
ID=63732991
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820058294.7U Active CN207956053U (en) | 2018-01-12 | 2018-01-12 | A kind of mounting structure of lifting airscrew axis |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207956053U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108082463A (en) * | 2018-01-12 | 2018-05-29 | 中国航发哈尔滨东安发动机有限公司 | A kind of mounting structure of lifting airscrew axis |
| CN114040873A (en) * | 2019-06-17 | 2022-02-11 | 列奥纳多股份公司 | Anti-torque rotor for helicopter |
-
2018
- 2018-01-12 CN CN201820058294.7U patent/CN207956053U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108082463A (en) * | 2018-01-12 | 2018-05-29 | 中国航发哈尔滨东安发动机有限公司 | A kind of mounting structure of lifting airscrew axis |
| CN114040873A (en) * | 2019-06-17 | 2022-02-11 | 列奥纳多股份公司 | Anti-torque rotor for helicopter |
| CN114040873B (en) * | 2019-06-17 | 2024-05-07 | 列奥纳多股份公司 | Anti-torque rotor for helicopter |
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