CN215890759U - Lightweight titanium alloy eccentric shaft for aviation rotor engine - Google Patents
Lightweight titanium alloy eccentric shaft for aviation rotor engine Download PDFInfo
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- CN215890759U CN215890759U CN202122274971.3U CN202122274971U CN215890759U CN 215890759 U CN215890759 U CN 215890759U CN 202122274971 U CN202122274971 U CN 202122274971U CN 215890759 U CN215890759 U CN 215890759U
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- eccentric shaft
- wear
- resistant coating
- titanium alloy
- rotor engine
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Abstract
The utility model relates to a lightweight titanium alloy eccentric shaft for an aviation rotor engine, which comprises an eccentric shaft body, wherein the eccentric shaft body is made of a titanium alloy material, a wear-resistant coating groove is formed in the outer peripheral surface of the eccentric shaft body matched with a bearing, a hard alloy wear-resistant coating is sprayed in the wear-resistant coating groove, and the surface of the hard alloy wear-resistant coating is flush with the surface of the eccentric shaft body. The lightweight titanium alloy eccentric shaft for the aviation rotor engine can effectively improve the wear resistance of the eccentric shaft, thereby prolonging the service life of the whole engine, simultaneously reducing the weight of the eccentric shaft and meeting the increasing lightweight requirement of the aviation rotor engine.
Description
Technical Field
The utility model belongs to the technical field of aviation rotor engines, and mainly relates to a lightweight titanium alloy eccentric shaft for an aviation rotor engine.
Background
At present, the eccentric shaft material for the domestic aviation rotor engine is made of alloy steel, and the material has high density and cannot meet the increasing light-weight requirement of the aviation engine. The alloy steel eccentric shaft obtains the required strength through integral quenching and tempering, and simultaneously obtains enough surface hardness with the surface of the joint part of the bearing through heat treatment processes such as carburizing and quenching or high-frequency quenching and the like so as to meet the wear-resisting requirement. In order to meet the requirement of light weight, the eccentric shaft material can be replaced by titanium alloy with low density, but the titanium alloy can not adopt the existing heat treatment process to carry out surface strengthening and can not meet the requirement of wear resistance.
Disclosure of Invention
In order to solve the technical problems, the utility model aims to provide a lightweight titanium alloy eccentric shaft for an aero-rotor engine, the scheme can effectively improve the strength and the wear resistance of the eccentric shaft, so that the service life of the whole engine is prolonged, and simultaneously, the weight of the eccentric shaft can be greatly reduced, the power-weight ratio of the whole engine is improved, and the increasing lightweight requirements of the aero-engine are met.
The purpose of the utility model and the technical problem to be solved are realized by adopting the following technical scheme. The light titanium alloy eccentric shaft for the aviation rotor engine comprises an eccentric shaft body, wherein the eccentric shaft body is made of a titanium alloy material, a wear-resistant coating groove is formed in the outer peripheral surface, matched with a bearing, of the eccentric shaft body, a hard alloy wear-resistant coating is sprayed in the wear-resistant coating groove, and the surface of the hard alloy wear-resistant coating is flush with the surface of the eccentric shaft body.
The object of the present invention and the technical problems solved thereby can be further achieved by the following technical measures.
The titanium alloy eccentric shaft for the aviation rotor engine is light in weight, and the thickness of the hard alloy wear-resistant coating is 0.1-1 mm.
The titanium alloy eccentric shaft for the aircraft rotor engine is characterized in that the groove bottom of the wear-resistant coating groove is provided with a groove wall, and an included angle formed between the groove bottom of the wear-resistant coating groove and the groove wall is an obtuse angle.
The angle between the groove bottom of the groove of the wear-resistant coating and the groove wall is 135 degrees.
The lightweight titanium alloy eccentric shaft for the aviation rotor engine is characterized in that a fillet is processed at the joint of the groove bottom and the groove wall of the wear-resistant coating groove.
The weight-reduced titanium alloy eccentric shaft for the aviation rotor engine is characterized in that 3 positions matched with the bearing are arranged on the eccentric shaft body in the axial direction, and each position matched with the bearing is provided with a hard alloy wear-resistant coating.
The titanium alloy eccentric shaft for the aircraft rotor engine is characterized in that the eccentric portion of the eccentric shaft body is further provided with at least one weight-reducing oil hole extending along the axial direction.
Compared with the prior art, the utility model has obvious advantages and beneficial effects. By means of the technical scheme, the utility model can achieve considerable technical progress and practicability, has wide industrial utilization value and at least has the following advantages:
the lightweight titanium alloy eccentric shaft for the aviation rotor engine can effectively improve the strength and the wear resistance of the eccentric shaft, so that the service life of the whole engine is prolonged.
Drawings
FIG. 1 is a cross-sectional view of a lightweight titanium alloy eccentric shaft for an aero rotor engine of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1;
fig. 3 is a right side view of fig. 1.
[ description of main element symbols ]
1. Eccentric shaft body
2. Wear-resistant coating groove
3. Hard alloy wear-resistant coating
4. Weight-reducing oil hole
Detailed Description
To further illustrate the technical means and effects of the present invention adopted to achieve the predetermined objects, the following detailed description will be given to specific embodiments, structures, features and effects of the lightweight titanium alloy eccentric shaft for aviation rotor engine according to the present invention with reference to the accompanying drawings and preferred embodiments.
Please refer to fig. 1-3, which are schematic structural diagrams of parts of a lightweight titanium alloy eccentric shaft for an aviation rotor engine according to the present invention, the eccentric shaft includes an eccentric shaft body 1, the eccentric shaft body 1 is made of a titanium alloy material to meet the requirement of weight reduction, and the eccentric shaft body can obtain higher strength by using a thermal refining process. The outer peripheral surface of the eccentric shaft body 1 matched with the bearing is provided with a wear-resistant coating groove 2 for containing a wear-resistant coating, the groove is an annular groove distributed along the circumferential direction of the eccentric shaft body 1, and the depth of the groove is 0.1-1 mm. The hard alloy wear-resistant coating 3 is sprayed in the wear-resistant coating groove 2, so that the wear resistance can be effectively improved.
In the embodiment of the utility model, 3 positions matched with the bearings are arranged on the eccentric shaft body 1 in total along the axial direction, each position matched with the bearing is provided with the hard alloy wear-resistant coating 3, the hard alloy wear-resistant coatings 3 are all positioned in the wear-resistant coating grooves 2, so that the surfaces of the hard alloy wear-resistant coatings 3 are flush with the surface of the eccentric shaft body 1, and the depth of the wear-resistant coating grooves 2 is 0.1-1mm, so as to ensure the thickness of the wear-resistant coating layer.
In the embodiment of the present invention, the included angle between the groove bottom and the groove wall of the wear-resistant coating groove 2 is an obtuse angle, and preferably, the included angle between the groove bottom and the groove wall is 135 degrees. In order to prevent the stress concentration at the connection part of the groove bottom and the groove wall of the wear-resistant coating groove 2, the connection part is processed with a fillet so as to reduce the stress at the connection part.
In order to further reduce the weight of the eccentric shaft, the eccentric part of the eccentric shaft body 1 of the utility model is also designed with at least one weight-reducing oil hole 4 extending along the axial direction, and the weight-reducing oil hole 4 can reduce the weight of the eccentric shaft and can be used as a lubricating oil cooling channel. Preferably, there are 3 weight-reducing oil holes 4, and the three weight-reducing oil holes may have different sizes.
The utility model provides a lightweight titanium alloy eccentric shaft for an aviation rotor engine, which can effectively improve the strength and the wear resistance of the eccentric shaft and prolong the service life of the engine; the weight of the eccentric shaft can be effectively reduced, so that the power-weight ratio of the whole machine is improved, and the increasing light-weight requirement of the aviation rotor engine is met.
Although the present invention has been described with reference to a preferred embodiment, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the utility model as defined by the appended claims.
Claims (7)
1. The utility model provides an aviation rotor engine is with lightweight titanium alloy eccentric shaft, includes the eccentric shaft body, its characterized in that: the eccentric shaft body is made of a titanium alloy material, a wear-resistant coating groove is formed in the outer peripheral face, matched with the bearing, of the eccentric shaft body, a hard alloy wear-resistant coating is sprayed in the wear-resistant coating groove, and the surface of the hard alloy wear-resistant coating is flush with the surface of the eccentric shaft body.
2. The lightweight titanium alloy eccentric shaft for an aviation rotor engine according to claim 1, wherein: wherein the thickness of the hard alloy wear-resistant coating is 0.1-1 mm.
3. The lightweight titanium alloy eccentric shaft for an aviation rotor engine according to claim 1, wherein: wherein the included angle between the groove bottom of the wear-resistant coating groove and the groove wall is an obtuse angle.
4. The lightweight titanium alloy eccentric shaft for an aviation rotor engine according to claim 3, wherein: wherein the included angle between the groove bottom of the wear-resistant coating groove and the groove wall is 135 degrees.
5. The lightweight titanium alloy eccentric shaft for an aviation rotor engine according to claim 3, wherein: wherein the connecting part of the groove bottom and the groove wall of the wear-resistant coating groove is processed with a fillet.
6. The lightweight titanium alloy eccentric shaft for an aviation rotor engine according to claim 1, wherein: the eccentric shaft body is provided with 3 positions matched with the bearings in the axial direction, and each position matched with the bearing is provided with a hard alloy wear-resistant coating.
7. The lightweight titanium alloy eccentric shaft for an aviation rotor engine according to claim 1, wherein: the eccentric part of the eccentric shaft body is also provided with at least one weight-reducing oil hole extending along the axial direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122274971.3U CN215890759U (en) | 2021-09-18 | 2021-09-18 | Lightweight titanium alloy eccentric shaft for aviation rotor engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122274971.3U CN215890759U (en) | 2021-09-18 | 2021-09-18 | Lightweight titanium alloy eccentric shaft for aviation rotor engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215890759U true CN215890759U (en) | 2022-02-22 |
Family
ID=80349306
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122274971.3U Active CN215890759U (en) | 2021-09-18 | 2021-09-18 | Lightweight titanium alloy eccentric shaft for aviation rotor engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215890759U (en) |
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2021
- 2021-09-18 CN CN202122274971.3U patent/CN215890759U/en active Active
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