Laser cladding repairing method for aircraft end-journal part surface

A technology of laser cladding and repair method, applied in the field of laser cladding, can solve the problems of large depth of heat affected zone, large heat input, difficult to meet, etc., and achieves reduced mechanical processing workload, small heat input, and high precision. Effect

Inactive Publication Date: 2016-01-20
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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Problems solved by technology

Obviously, the heat input (≥0.5KJ / mm) of the commonly used fusion welding repair methods (such as manual arc welding, argon arc welding, etc.) is relatively large, which is likely to cause large deformation of the end journal parts during the repair process. The depth of the rear heat-affected zone is also relatively large, and it is difficult to meet the requirements of the factory or the overhaul manual

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  • Laser cladding repairing method for aircraft end-journal part surface
  • Laser cladding repairing method for aircraft end-journal part surface

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Embodiment 1

[0027] 1. Analysis of the defects of the aircraft end journal:

[0028] The end journal is the key load-bearing part of the fixed aircraft engine, which is precision cast and forged from 1Cr15Ni4Mo3N precipitation hardened stainless steel. When the aircraft is in the refurbishment cycle, due to long-term use, obvious mechanical wear or scratch defects appear on the surface of the journal parts at this end, such as figure 1 shown. Due to the different depths of defects on the surface of the end journal, the maximum depth is close to 2.0mm. In order to ensure the mechanical properties of the repaired area of ​​the end journal, and considering the matching of the expansion coefficient of the cladding layer and the base material, it is determined to use a material with a similar expansion coefficient. Precipitation-hardening stainless steel metal powder as filler material for laser cladding repair of end journals.

[0029] 2. Repair of aircraft end journal defects

[0030] (1) ...

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Abstract

The invention belongs to the technical field of laser cladding, relates to a laser cladding repairing method for aircraft end-journal part surface, particularly to a method for repairing the mechanical wear and scrape malfunction of an aircraft end-journal part after long-time service by adopting the laser fused deposition technology. The method aims at mechanical wear, scrape and other defects on the surface of the part, selects spherical precipitation to harden stainless steel metal dust, adopts reasonable laser cladding technological parameters, and removes residual stress of the part after cladding through the specific heat treatment technology to recover the performance of the aircraft end-journal and realize repairing of lengthening the service life. The repaired end-journal part hardly deforms, and the depth of a heat affected area is no more than 0.5mm; the repairing area does not have the defects of cracks, incomplete fusion and slag inclusion; the serviceability of the repaired end-journal is recovered.

Description

technical field [0001] The invention belongs to the technical field of laser cladding, and relates to a laser cladding repair method for the surface of aircraft end journal parts, in particular to a laser fusion deposition technology for mechanical wear and tear of aircraft end journal parts after long-term service. Repair scratches. Background technique [0002] The journal part of the aircraft end is an important load-bearing part used to fix the engine on an aircraft. Its material is usually 1Cr15Ni4Mo3N semi-austenitic precipitation hardening stainless steel. This material has high strength, low notch sensitivity, and excellent transverse mechanical properties. and corrosion resistance. However, after the aircraft went through a refurbishment cycle, it was found that the surface of some end journals had different degrees of axial or circumferential scratches or wear, resulting in rough surfaces and out-of-tolerance phenomena of the parts. The depth of scratches and wea...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C38/50C22C38/48C22C38/44C23C24/10B22F1/00
Inventor 秦仁耀张学军郭绍庆唐思熠孙兵兵
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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