Ultrasonic-impact-assisted laser cladding repairing method for ultra-high-strength steel member

An ultra-high-strength steel, ultrasonic impact technology, applied in the field of laser processing, can solve problems such as loss of plastic cracks, and achieve the effect of cost saving

Inactive Publication Date: 2018-02-09
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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AI Technical Summary

Problems solved by technology

Therefore, in order to solve the problem that a single laser cladding repair can easily cause plastic loss cracks, it is

Method used

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Examples

Experimental program
Comparison scheme
Effect test

specific example 1

[0028] Using ultrasonic shock assisted laser cladding technology to repair the crack defect of a certain type of landing gear half shaft

[0029] 1. Confirmation of the cracks on the landing gear half shaft

[0030] The landing gear half shaft of a certain type of aircraft is made of 30CrMnSiNi2A ultra-high strength steel. A crack with a length of 30 mm and a depth of 0.2 mm appears in the mounting groove of the thrust bolt of the half shaft.

[0031] 2. Repair process and inspection

[0032] (1) The ultra-high-strength steel metal powder with better impact toughness and weldability than the half-shaft material is selected as the laser repair material, and all the indicators of the powder meet the requirements.

[0033] (2) Clean the surface before repairing. Under fluorescent light, use a hand-held electric gun to polish and remove crack defects. Visual inspection shows no fluorescence. After removing cracks, the opening angle of the gap is about 80° and the depth is 0.3mm. ...

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Abstract

The invention belongs to the technical field of laser machining and relates to an ultrasonic-impact-assisted laser cladding repairing method for an ultra-high-strength steel member. The ultrasonic-impact-assisted laser cladding repairing method is mainly used for repairing damage such as surface corrosion and micro cracks of the ultra-high-strength steel member of an airplane. In the earlier stage, same metal powder for repairing is adopted for conducting a direct laser cladding repairing test and an ultrasonic-impact-assisted laser cladding repairing test on a 30CrMnSiNi2A ultra-high-strengthsteel undercarriage half-shaft base body, wherein according to the metal powder, the cladding metal impact toughness is larger than or equal to 420 KJ/m<2>, the room-temperature ductility is larger than or equal to 10.8%, and the room-temperature tensile strength is larger than or equal to 1400 MPa; and the room-temperature tensile performance, the room-temperature impact performance and the microhardness performance of two repairing areas are tested. The results are obtained as follows: according to direct laser cladding repairing, the average tensile strength is 1428.6 MPa, the average elongation rate is 11.8%, the average impact toughness is 471 KJ/m<2>, and the average microhardness of repairing metal is 474.3 HV; and according to ultrasonic-impact-assisted laser cladding repairing, the average tensile strength is 1436.2 MPa, the average elongation rate is 14.8%, the average impact toughness is 643 KJ/m<2>, and the average microhardness of the repairing metal is 490.7 HV.

Description

technical field [0001] The invention belongs to the technical field of laser processing, and relates to an ultrasonic shock-assisted laser cladding repair method for ultra-high-strength steel components, which is mainly used for repairing damages such as surface corrosion and microcracks of aircraft ultra-high-strength steel components. Background technique [0002] At present, when the aircraft is being refurbished, it is found that the ultra-high-strength steel components have surface corrosion, micro-cracks and other damage after service. New welding cracks are easy to appear, which leads to the scrapping of components. When the laser cladding method was used to develop the repair process, it was found that the repaired formed metal surface was still prone to post-weld cracks. After analyzing the surface, the cracks were mainly caused by the plastic loss cracks caused by residual stress at high forming temperatures. Therefore, in order to solve the problem that a single ...

Claims

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Application Information

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IPC IPC(8): C23C24/10C21D10/00
CPCC23C24/10C21D10/00
Inventor 孙兵兵秦仁耀周标郭绍庆李能张学军
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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