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A laser directional additive method for nickel-based directional superalloys

A technology of nickel-based superalloys and superalloys, which is applied in the field of laser directional growth of nickel-based directional superalloys and laser rapid directional growth of nickel-based directional superalloy parts. Welding performance, the effect of dense and uniform structure

Active Publication Date: 2021-02-05
江西瑞曼增材科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a laser directional material addition method for nickel-based directional superalloys, which solves the problem that the size of nickel-based directional superalloy parts fails due to wear and tear.

Method used

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  • A laser directional additive method for nickel-based directional superalloys
  • A laser directional additive method for nickel-based directional superalloys

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0032] In this embodiment, the specific steps of the nickel-based directional superalloy laser directional additive method are as follows:

[0033] 1. The superalloy powder particle size is 100-250 mesh, sphericity ≥ 95%, oxygen content ≤ 300PPM, the alloy powder used is Ni-Cr-Mo powder, and the nominal composition is Ni-19Cr-5Mo-4Nb-Ti (by weight Percentage, Cr 19%, Mo5%, Nb 4%, Ti 1%, Ni).

[0034] 2. Powder drying treatment: temperature 120℃×1.5h.

[0035] 3. Deposition substrate: DZ125 nickel-based superalloy.

[0036] 4. The base body grinds the superalloy deposition plane until it is bright and flat, cleans the plane with alcohol and acetone, and then dries it.

[0037] 5. Laser deposition vacuum glove box environment: H 2 O, O 2 ≤50PPM.

[0038] 6. Process parameters of laser deposition: continuous laser irradiation, laser power 600W, power density 10 5 W / cm 2 , the scanning speed is 6mm / s, the overlapping amount is 50%, and the irradiation spot is Φ2mm; the lase...

Embodiment 2

[0045] In this embodiment, the specific steps of the nickel-based directional superalloy laser directional additive method are as follows:

[0046] 1. The superalloy powder particle size is 100-250 mesh, sphericity ≥ 92%, oxygen content ≤ 300PPM, the alloy powder used is Ni-Cr-Nb powder, and the nominal composition is Ni-18Cr-4Nb-2Mo-Ti (by weight In terms of percentage, Cr 18%, Nb 4%, Mo 2%, Ti 1%, Ni remaining).

[0047] 2. Powder drying treatment: temperature 100℃×2h.

[0048] 3. Deposition substrate: DZ125 nickel-based superalloy.

[0049] 4. The base body grinds the superalloy deposition plane until it is bright and flat, cleans the plane with alcohol and acetone, and then dries it.

[0050] 5. Laser deposition vacuum glove box environment: H 2 O, O 2 ≤50PPM.

[0051] 6. Process parameters of laser deposition: continuous laser irradiation, laser power 800W, power density 2×10 5 W / cm 2 , the scanning speed is 10mm / s, the overlapping amount is 40%, and the irradiatio...

Embodiment 3

[0056] In this embodiment, the specific steps of the nickel-based directional superalloy laser directional additive method are as follows:

[0057] 1. The superalloy powder particle size is 100-250 mesh, sphericity ≥ 94%, oxygen content ≤ 300PPM, the alloy powder used is Co-Cr-Ni powder, and the nominal composition is Co-25Cr-11Ni-8W (by weight percentage , Cr 25%, Ni 11%, W8%, Co more).

[0058] 2. Powder drying treatment: temperature 80℃×2h.

[0059] 3. Deposition substrate: DZ125 nickel-based superalloy.

[0060] 4. The base body grinds the superalloy deposition plane until it is bright and flat, cleans the plane with alcohol and acetone, and then dries it.

[0061] 5. Laser deposition vacuum glove box environment: H 2 O, O 2 ≤50PPM.

[0062] 6. Process parameters of laser deposition: continuous laser irradiation, laser power 700W, power density 5×10 5 W / cm 2 , the scanning speed is 8mm / s, the overlapping amount is 45%, and the irradiation spot is Φ4mm; the laser coa...

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Abstract

The invention belongs to the field of metal laser additive manufacturing, and specifically relates to a nickel-based directional superalloy laser directional additive method, which is suitable for laser rapid directional growth of directional superalloy parts with complex structures, and solves the problem of part failure due to wear. Using Ni-Cr-Mo, Ni-Cr-Nb and Co-Cr-Ni three kinds of powders, laser deposition is carried out by synchronous powder feeding method in a vacuum glove box. During the deposition process, the protective gas is used to cover the laser deposition area. The liquid nitrogen continuous cooling method cools the deposition platform and increases the temperature gradient of the deposition layer cooling, which can realize the rapid directional addition of nickel-based directional superalloys, thereby achieving the recovery of the part size. The invention provides a novel directional growth process method for nickel-based directional alloys. The deposition process of the method adopts automatic control and has high efficiency; the deposited dendrite structure has good orientation, is dense and uniform, has a narrow heat-affected zone and no thermal cracks, and the deposited layer The tensile performance of welding with the matrix reaches more than 80% of that of the matrix.

Description

technical field [0001] The invention belongs to the field of metal laser additive manufacturing, and relates to a laser orientation additive method for a nickel-based directional superalloy, which is suitable for laser rapid directional growth of nickel-based directional superalloy parts with complex structures. Background technique [0002] Superalloys have been mainly used in aero-engines since their birth. In modern advanced aero-engines, superalloy materials account for 40% to 60% of the total amount of the engine. In aero-engines, high-temperature alloys are mainly used in four hot-end components, guides, turbine blades, turbine disks and combustion chambers. At the same time, superalloys are irreplaceable materials for high-temperature hot-end components such as gas turbines and rocket engines. At present, nickel-based oriented superalloys have become the main materials for aviation applications. They are the main materials for jet aeroengine blades and hot end parts....

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B22F10/28B22F10/32B22F1/00C22C1/04C22C19/05C22C19/07B33Y10/00B33Y70/00
CPCB22F1/0003C22C1/0433C22C19/056C22C19/07B33Y10/00B33Y70/00B22F10/00B22F10/36B22F10/34B22F10/25B22F10/38B22F10/322Y02P10/25
Inventor 迟长泰谢玉江陈祖华王明生王德陈新贵
Owner 江西瑞曼增材科技有限公司