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Repairing method of surface scratches of shaft sleeve of connecting shaft of helicopter

A technology for connecting shafts and helicopters, applied in the field of repairing scratches on the surface of shaft sleeves, can solve the problems of helicopter safety hazards, cost waste, stress concentration, etc., and achieve the effects of improving corrosion resistance, reducing scrap costs, and eliminating stress concentration

Inactive Publication Date: 2018-12-18
HARBIN DONGAN ENGINE GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

During the daily use and maintenance of the helicopter, the bushing will inevitably cause scratches on the surface of the bushing
If the scratched position is not repaired, stress concentration will be caused here during work, which will bring hidden dangers to the safety of the helicopter
At the same time, due to the use of conventional grinding methods for such scratches, without proper protective measures, the repaired bushes are often scrapped due to strength or corrosion problems after not working for a long time, which brings a lot of cost waste

Method used

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  • Repairing method of surface scratches of shaft sleeve of connecting shaft of helicopter
  • Repairing method of surface scratches of shaft sleeve of connecting shaft of helicopter

Examples

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Effect test

Embodiment

[0026] The bushing of the 001# connecting shaft of a certain type of helicopter has a scratch at a position 60mm away from the side end face of the main reducer. The scratch depth is 0.1mm, the length is about 5mm, and the width is about 4mm. The repair steps are as follows:

[0027] (1) Disassemble the faulty bushing, the defective position is located 60mm from the end face of the main reducer, and repair it according to step (2);

[0028] (2) The depth e of the surface defect is 0.1mm, and repaired according to the step (3);

[0029] (3) Use 300-mesh sandpaper to perform smooth transition treatment on the defect position within the range of radius R=5mm, and the grinding depth is 0.15mm;

[0030] (4) Alodin treatment is carried out on the polished part, and the coating surface is continuous, uniform and streak-free and does not expose the shaft sleeve substrate;

[0031] (5) The quality of the Alodine coating meets the requirements, and the step (6) is performed;

[0032] ...

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Abstract

The invention relates to a repairing method of surface scratches of a shaft sleeve of a connecting shaft of a helicopter. Whether repairing value exists or not is judged by determining defect positions and degrees, then smooth transition treatment, Alodine treatment and final paint spraying treatment are carried out, inspection is carried out in the whole process, and the surface scratches of theshaft sleeve are repaired. The purpose of eliminating stress concentration is achieved, the requirement of the wall thickness of the shaft sleeve is guaranteed, the working time of the shaft sleeve can be effectively prolonged, and unnecessary retirement expenses are reduced.

Description

technical field [0001] The invention relates to a method for repairing scratches on the surface of a shaft sleeve of a helicopter connecting shaft. Background technique [0002] The connecting shaft is a common part of the helicopter transmission system and is located between the engine and the final drive. The shaft sleeve is wrapped on the outside of the connecting shaft to protect the connecting shaft and seal the torque between the engine and the final reducer. During the daily use and maintenance of the helicopter, the bushing will inevitably cause scratches on the surface of the bushing. If the scratched position is not repaired, stress concentration will be caused here during work, which will bring hidden dangers to the safety of the helicopter. At the same time, due to the use of conventional grinding methods for such scratches, without proper protective measures, the repaired bushes are often scrapped due to strength or corrosion problems after not working for a l...

Claims

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Application Information

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IPC IPC(8): B23P6/00
CPCB23P6/00
Inventor 欧阳可平杨昊王银凤李远许鹏聂必成张小巍
Owner HARBIN DONGAN ENGINE GRP
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