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Process method for remanufacturing shell hole rolling groove through laser direct deposition

A technology of laser direct deposition and process method, which is applied in the direction of additive manufacturing, process efficiency improvement, additive processing, etc. It is difficult to assemble with the shell and other problems, so as to achieve the effect of small thermal deformation, stable speed and stable penetration.

Pending Publication Date: 2022-02-01
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] For housing parts with bearing holes, the bearing sleeves are usually disassembled for bearing replacement or repair during maintenance, but some bearing sleeves are in housing parts with holes, and the edges of the housing holes are rolled in the form of notches The bearing is fixed, so the original rolling fixed edge is often destroyed during disassembly, so that the bearing sleeve can be taken out smoothly
As a result, when the subsequent bearing sleeves are repeatedly installed in the shell parts, the bearing sleeves need to be repositioned by rolling notches. However, the edge material of the bearing holes will become thinner after rolling and the original fixed port material has been destroyed and removed, resulting in The bearing hole lacks the allowance for machining the rolling groove, and the assembly and fixing of the bearing sleeve cannot be realized again
For such defects, manual arc surfacing is used to supplement the local machining allowance. However, due to the repair of local positions by arc surfacing, it is difficult to guarantee the metallurgical quality of the base metal and weld after welding, and defects such as cracks often occur. At the same time, the high heat input during the surfacing process may cause certain deformation to the housing hole, resulting in difficulty in the assembly of the bearing and the housing

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0038] The main rear cover part of a certain type of aircraft, the main rear cover base material is 30CrMnSiNi2A high-strength steel. The joint bearing is installed on this part, and the cooperation between the bearing sleeve and the hole of the main lifting back cover is based on the shaft system, and the diameter of the outer ring of the bearing is up to 60mm. There are grooves on the edge of the bearing sleeve hole of the main rear cover for the original fit. After the bearing sleeve is installed, use steel balls to press evenly along the circumference of the special groove. However, during the maintenance of the aircraft, the worn bearings were replaced. In order to take out the bearings, the pressed special grooves were destroyed before the bearing sleeves could be taken out. This caused the original special grooves to be removed when the bearing sleeves were assembled repeatedly. Destruction, the use of machining methods to reprocess the special groove lacks the base met...

Embodiment 2

[0053] The deflector part of a certain type of aircraft, the base material is TC18 titanium alloy, the strength is about 1250MPa. This part is equipped with a ball bearing, and the cooperation between the bearing sleeve and the hole of the main lifting back cover is a base shaft system, and the diameter of the outer ring of the bearing is 24mm. The original fit is that there is no special groove on the edge of the bearing hole, and the edge of the hole is evenly pressed and positioned by six points of steel balls. However, during the maintenance of the aircraft, the worn bearings were replaced. In order to take out the bearings, the edges of the pressed holes were destroyed before the bearings could be taken out. This resulted in no rolling at the original pressed positions when the bearing sleeves were reassembled. margin. The lack of allowance on the edge of the bearing hole is analyzed, and the remanufacturing material to be selected is clarified. Through the above analysi...

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Abstract

The invention relates to a process method for remanufacturing a shell hole rolling groove through laser direct deposition, and belongs to the technical field of laser processing. The method is mainly used for shell parts with bearing holes and the material strength of 160-1275 MPa, powder which is high in deposition formability, excellent in ductility and close to base metal components is selected as a deposition material, reasonable laser direct deposition process parameters are adopted, and material remanufacturing is conducted on the edges of the shell holes. After deposition, a base material and a remanufactured layer have no crack defect, the marginal margin of a remanufactured hole is sufficient, and the edge of the bearing can be effectively fixed after rolling and closing. When the rolling groove for remanufacturing the shell bearing hole is adopted, shell parts with bearings can be repeatedly assembled when special equipment such as airplanes and ships is overhauled, and reasonable fixation is guaranteed.

Description

technical field [0001] The invention relates to a process method for direct laser deposition to remanufacture rolling grooves of housing holes, which belongs to the technical field of laser processing and is mainly aimed at the bearing holes of housing parts with bearing holes with a material strength of 160-1275MPa Edge remanufacturing. Background technique [0002] For housing parts with bearing holes, the bearing sleeves are usually disassembled for bearing replacement or repair during maintenance, but some bearing sleeves are in housing parts with holes, and the edges of the housing holes are rolled in the form of notches The bearing is fixed, so the original rolling fixed edge is often destroyed during disassembly, so that the bearing sleeve can be taken out smoothly. As a result, when the subsequent bearing sleeves are repeatedly installed in the shell parts, the bearing sleeves need to be repositioned by rolling notches. However, the edge material of the bearing hole...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B22F10/22B22F10/66B22F10/85B33Y10/00B33Y40/20B33Y50/02B33Y80/00B22F5/10
CPCB22F10/22B22F10/66B22F10/85B22F5/10B33Y10/00B33Y40/20B33Y50/02B33Y80/00Y02P10/25
Inventor 张国会孙兵兵秦仁耀高超
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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