CN215890193U - Triangle rotor part welding installation structure for aviation rotor engine - Google Patents
Triangle rotor part welding installation structure for aviation rotor engine Download PDFInfo
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- CN215890193U CN215890193U CN202122312851.8U CN202122312851U CN215890193U CN 215890193 U CN215890193 U CN 215890193U CN 202122312851 U CN202122312851 U CN 202122312851U CN 215890193 U CN215890193 U CN 215890193U
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Abstract
The utility model relates to a triangular rotor part welding and mounting structure for an aviation rotor engine, which comprises a triangular rotor and a phase internal gear pressed in the triangular rotor, wherein a plurality of positioning screw mounting holes are processed between the triangular rotor and the phase internal gear, and positioning screws screwed in the positioning screw mounting holes realize radial limiting between the triangular rotor and the phase internal gear; and the positioning screw is welded with the phase internal gear and the triangular rotor together after being installed in place to realize axial limiting. The utility model can effectively avoid the risk of scratching parts due to the difficulty in mounting the phase internal gear, and improve the mounting efficiency of the phase internal gear; the cam rotor engine can effectively prevent the phase internal gear of the engine from coming out of the cam rotor in the working process, thereby greatly improving the reliability of the cam rotor engine.
Description
Technical Field
The utility model belongs to the technical field of aviation rotor engines, and mainly relates to a triangular rotor part welding and mounting structure for an aviation rotor engine.
Background
At present, a triangle rotor and a phase internal gear in a triangle rotor part for a domestic aviation rotor engine are connected through 9 to 12 elastic pins, and the structure has the defects that the 9 to 12 elastic pins are connected between the triangle rotor and the phase internal gear at the same time, the installation is difficult, the installation efficiency is low, and meanwhile, the quality accident of scratching parts can be caused due to the installation difficulty; the structure has no axial positioning, and the risk that the phase internal gear is pulled out from the triangular rotor exists in the working process of the engine.
Disclosure of Invention
In order to solve the technical problems, the utility model aims to provide a triangle rotor part welding and mounting structure for an aviation rotor engine, which can thoroughly avoid the risk that a phase inner gear is separated from a triangle rotor by additionally arranging a positioning screw between the triangle rotor and the phase inner gear and welding the positioning screw, the triangle rotor and the phase inner gear together, and can effectively solve the risk of scratching parts caused by difficult mounting, improve the mounting efficiency and improve the reliability of the triangle rotor engine.
The purpose of the utility model and the technical problem to be solved are realized by adopting the following technical scheme. According to the utility model, the welding and mounting structure of the triangular rotor part for the aviation rotor engine comprises a triangular rotor and a phase internal gear which is pressed in the triangular rotor, wherein a plurality of positioning screw mounting holes are also processed between the triangular rotor and the phase internal gear, and the positioning screws screwed in the positioning screw mounting holes realize radial limiting between the triangular rotor and the phase internal gear; and the positioning screw is welded with the phase internal gear and the triangular rotor together after being installed in place to realize axial limiting.
The object of the present invention and the technical problems solved thereby can be further achieved by the following technical measures.
According to the welding installation structure of the triangular rotor component for the aviation rotor engine, the welding position of the triangular rotor is provided with the welding pits which are convenient to weld and can avoid the interference of welding spots and adjacent parts.
According to the welding installation structure of the triangular rotor part for the aviation rotor engine, the positioning screw is at least partially located in the welding pit.
In the above-mentioned welding and mounting structure for a delta rotor part of an aviation rotor engine, the set screw is a straight screw, and the head of the set screw is not higher than the surface of the delta rotor.
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 triangular rotor part welding and mounting structure for the aviation rotor engine can effectively avoid the risk of scratching parts due to the difficulty in mounting the phase internal gear, and improve the mounting efficiency of the phase internal gear; the cam rotor engine can effectively prevent the phase internal gear of the engine from coming out of the cam rotor in the working process, thereby greatly improving the reliability of the cam rotor engine.
Drawings
FIG. 1 is a schematic structural view of the present invention;
fig. 2 is a cross-sectional view of fig. 1.
[ description of main element symbols ]
1. Triangular rotor
2. Positioning screw mounting hole
3. Set screw
4. Phase internal gear
5. Welding pit
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 the specific implementation, structure, features and effects of the triangular rotor part welding installation structure for an aviation rotor engine according to the present invention with reference to the accompanying drawings and preferred embodiments.
Please refer to fig. 1 and fig. 2, which are schematic structural diagrams of parts of a welding and mounting structure of a triangular rotor part for an aircraft rotor engine according to the present invention, the welding and mounting structure of the triangular rotor part includes a triangular rotor 1 and a phase internal gear 4 press-fitted in the triangular rotor 1, a plurality of axially extending positioning screw mounting holes 2 are further processed between the triangular rotor 1 and the phase internal gear 4, and a positioning screw 3 screwed in the positioning screw mounting hole 2 realizes radial rotation stop between the triangular rotor 1 and the phase internal gear 4, so as to prevent the triangular rotor 1 and the phase internal gear 4 from sliding relatively in the working process of the rotor engine. In order to realize axial spacing between the phase internal gear 4 and the triangular rotor 1, the positioning screw 3 is welded together with the positioning screw 3, the phase internal gear 4 and the triangular rotor 1 after being installed in place, so that the problem that the phase internal gear 4 is separated from the triangular rotor 1 in the working process of the engine to cause engine faults is avoided.
In order to facilitate welding and avoid the interference between a welding spot and adjacent parts, the welding pit 5 is arranged at the welding part of the triangular rotor 1. The set screw 3 is at least partially located in the welding recess 5 to facilitate welding.
In the embodiment of the present invention, the head of the positioning screw 3 is provided with a straight line for facilitating the application of force, and the head of the positioning screw 3 is lower than the surface of the triangular rotor 1, but the present invention is not limited thereto.
The utility model also provides a horn-shaped matching surface for realizing axial limiting between the outer periphery of the phase internal gear 4 and the inner periphery of the triangular rotor 1.
The utility model relates to a welding and mounting structure of a triangular rotor part for an aviation rotor engine, which is characterized in that when the structure is assembled, a phase inner gear 4 is firstly pressed in a triangular rotor 1, and after the pressing is finished, a positioning screw 3 is screwed into a positioning screw mounting hole between the phase inner gear and the triangular rotor 4, so that the triangular rotor and the phase inner gear are prevented from sliding relatively in the working process of the rotor engine; after the positioning screw is installed in place, the positioning screw, the phase internal gear and the triangular rotor are welded together, so that the problem that the phase internal gear is separated from the triangular rotor in the working process of the engine to cause engine faults is avoided; a welding pit is arranged at the welding position of the triangular rotor, so that welding is facilitated, and the welding spot is prevented from interfering with adjacent parts.
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 (4)
1. The utility model provides an aerorotor part welding mounting structure for engine, its includes the triangle rotor and the pressure equipment phase internal gear in this triangle rotor, its characterized in that: a plurality of positioning screw mounting holes are further processed between the triangular rotor and the phase internal gear, and the positioning screws screwed in the positioning screw mounting holes realize radial limit between the triangular rotor and the phase internal gear; and the positioning screw is welded with the phase internal gear and the triangular rotor together after being installed in place to realize axial limiting.
2. A triangular rotor part welding installation structure for an aviation rotor engine according to claim 1, characterized in that: the welding position of the triangular rotor is provided with a welding pit which is convenient to weld and can avoid the interference of a welding spot and adjacent parts.
3. A triangular rotor part welding installation structure for an aviation rotor engine according to claim 2, characterized in that: the set screw is at least partially located within the weld pocket.
4. A triangular rotor part welding installation structure for an aviation rotor engine according to claim 1, characterized in that: the positioning screw is a straight screw, and the head of the positioning screw is not higher than the surface of the triangular rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122312851.8U CN215890193U (en) | 2021-09-18 | 2021-09-18 | Triangle rotor part welding installation structure for aviation rotor engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122312851.8U CN215890193U (en) | 2021-09-18 | 2021-09-18 | Triangle rotor part welding installation structure for aviation rotor engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215890193U true CN215890193U (en) | 2022-02-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122312851.8U Active CN215890193U (en) | 2021-09-18 | 2021-09-18 | Triangle rotor part welding installation structure for aviation rotor engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215890193U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114542275A (en) * | 2022-03-15 | 2022-05-27 | 洛阳北方企业集团有限公司 | Lightweight triangular rotor structure for aviation rotor engine |
-
2021
- 2021-09-18 CN CN202122312851.8U patent/CN215890193U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114542275A (en) * | 2022-03-15 | 2022-05-27 | 洛阳北方企业集团有限公司 | Lightweight triangular rotor structure for aviation rotor engine |
| CN114542275B (en) * | 2022-03-15 | 2023-01-17 | 洛阳北方企业集团有限公司 | Lightweight triangular rotor structure for aviation rotor engine |
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