Method for repairing aircraft engine parts scrap mould with broadband laser cladding

A technology of laser cladding and laser repair, which is applied in the field of metallurgy, can solve problems such as cladding layer cracks and impacts, and achieve the effects of uniform grain refinement, high bonding strength, and uniform distribution

Inactive Publication Date: 2008-12-03
GUIZHOU UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantage is that once cracks or stress concentration occur in the front laser cladding track, the crystallization of the subsequent laser cladding track will be affected, so that the crac

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0015] Embodiment 1 of the present invention: Broadband laser lap cladding repair scrapped mold of aero-engine parts: the scrapped mold samples of aero-engine parts are cut with molybdenum wire, and the surface of the sample to be clad is treated with metallographic sandpaper before laser cladding Grinding, derusting and deburring, and cleaning with acetone for later use; laser cladding alloy powder adopts laser cladding special alloy powder HT-1 (weighing alloy powder with a particle size of -140 to 400 mesh: 80.0wt.% Fe, 0.3wt. %C, 1.5wt.%Si, 2.0wt.%B, 1.2wt.%Ni and 15.0wt.%Cr, ground in a mortar for 4 to 8 hours to make them fully mixed, and the alloy powder was sent simultaneously Powder mode; adopt broadband TJ-HL-T5000 continuous CO 2 The laser performs laser repair on the mold sample, selects the mixed low-order mode in the cavity, and focuses on the copper mirror transmission with a focal length of 330mm; the laser lap cladding is carried out according to the first, th...

Embodiment 2

[0017] Embodiment 2 of the present invention: Broadband laser lap cladding repairs scrapped molds for low and medium carbon steel parts: the samples of scrapped molds for low and medium carbon steel parts are cut by molybdenum wire, and metallographic sandpaper is used for laser cladding. The surface of the sample to be clad is polished, derusted and deburred, and cleaned with acetone for later use; the laser cladding alloy powder adopts laser cladding special alloy powder HT-1 (composed of 80.0wt.% Fe, 0.3wt.% C, 1.5wt .%Si, 2.0wt.%B, 1.2wt.%Ni and 15.0wt.%Cr powders are ground and mixed), alloy powders are fed synchronously; broadband continuous CO 2 The laser performs laser repair on the mold sample, selects the mixed low-order mode in the cavity, and focuses on the copper mirror transmission with a focal length of 330mm; the laser lap cladding is carried out according to the first, third, fifth, ... (2n- 1) The first pass, the second pass, the fourth pass, the sixth pass, ...

Embodiment 3

[0019] Embodiment 3 of the present invention: broadband laser lap cladding repair of scrapped molds for low and medium carbon alloy steel parts: the samples of scrapped molds for low and medium carbon alloy steel parts are cut by molybdenum wire, and metallography is used before laser cladding Grind the surface of the sample to be clad with sandpaper, remove rust and burrs, and clean it with acetone for later use; the laser cladding alloy powder adopts laser cladding special alloy powder HT-1; adopts broadband continuous CO 2 The laser performs laser repair on the mold sample, selects the mixed low-order mode in the cavity, and focuses on the copper mirror transmission with a focal length of 330mm; the laser lap cladding is carried out according to the first, third, fifth, ... (2n- 1) The first pass, the second pass, the fourth pass, the sixth pass, ... the 2nth pass are carried out sequentially; the laser cladding process parameters are: laser output power 3.6KW, scanning spee...

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PUM

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Abstract

The invention discloses a method for repairing an aeroengine part scrapping die by broadband laser overlapping cladding, and the application. The method has the characteristics that the laser overlapping cladding is executed according to the sequence that the formulas that are 2*n minus 1 and 2*n (wherein, n is a natural number and n is more than or equal to 1) are based on in turn, and can be used in the scrapping die repair of low and medium carbon steel parts or low and medium carbon alloy steel parts. The method overcomes the disadvantages of the existing multitrack overlapping cladding method, reduces the area of an overlapping zone to the utmost extent, reduces the harmful effects caused by the temper in the overlapping zone, and also reduces the interrelationship among each cladding region, obtains a large-area flawless laser cladding layer easily; in addition, the cladding layer has no inclusions and no pores, and well combines with the metallurgical substrate; because the secondary crystallization occurs in an overlay region which is processed through overlay region, crystal grains are further refined uniformly so as to lead the residual stress of the laser cladding layer to be reduced, thereby effectively increasing the service performance of the aeroengine part scrapping die.

Description

Technical field: [0001] The invention relates to a method and application for repairing scrap molds of aero-engine parts by broadband laser lap cladding and belongs to the technical field of metallurgy. Background technique: [0002] At present, the technological methods used for repairing scrapped molds of aero-engine parts mainly include thermal spraying and laser repairing. Because the coating repaired by thermal spraying process has metallurgical defects such as voids and pores, at the same time, the thermal spraying coating is mechanically or semi-mechanically bonded to the substrate, and the bonding strength is low, and it is easy to fall off during use, which limits its scope of application. The coating repaired by laser cladding has the characteristics of fine structure, no holes, controllable cladding thickness of the coating, metallurgical bonding between the coating and the substrate, and high bonding strength. However, the spot diameter of narrowband laser clad...

Claims

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Application Information

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IPC IPC(8): C23C24/10B23K26/34
Inventor 刘其斌龙运李宝增温书涛何默杜凯
Owner GUIZHOU UNIV
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