Method for plasma oxygen-carbon co-permeation of titanium-based or zirconium-based metal surface

A technology of plasma oxygen and base metal, which is applied in metal material coating technology, air transportation, coating, etc., can solve the problems of high temperature and long treatment time of oxygen carburizing, and achieve low treatment temperature, fast penetration speed, The effect of small workpiece deformation

Active Publication Date: 2017-01-18
NORTHWEST INSTITUTE FOR NON-FERROUS METAL RESEARCH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In view of the disadvantages of "high oxygen carburizing temperature and lon

Method used

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  • Method for plasma oxygen-carbon co-permeation of titanium-based or zirconium-based metal surface
  • Method for plasma oxygen-carbon co-permeation of titanium-based or zirconium-based metal surface
  • Method for plasma oxygen-carbon co-permeation of titanium-based or zirconium-based metal surface

Examples

Experimental program
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Example Embodiment

[0041] Example 1

[0042]The method for plasma oxycarburizing on the surface of the TA2 titanium alloy of the present embodiment includes the following steps:

[0043] Step 1. Pretreatment of pickling, mechanical polishing, degreasing cleaning and dehydration drying is performed on the α-type TA2 titanium alloy workpiece;

[0044] Step 2. Place the pretreated TA2 titanium alloy workpiece described in Step 1 in an ion chemical heat treatment furnace, and pre-evacuated to 1×10 -3 Pa, then pass through Ar and CO at the same time 2 Gas, control Ar and CO 2 The flow ratio is 1:4;

[0045] Step 3. When the vacuum degree in the ion chemical heat treatment furnace in Step 2 reaches 100Pa, load the TA2 titanium alloy workpiece with a negative bias voltage of 300V to generate a glow discharge, clean the workpiece with glow plasma for 10min, and then increase Negative bias voltage to 800V, heat the TA2 titanium alloy workpiece, make the TA2 titanium alloy workpiece heat up to 900 ℃, ...

Example Embodiment

[0048] Example 2

[0049] The method for surface plasma oxycarburization of TA12 titanium alloy (α type) of the present embodiment includes the following steps:

[0050] Step 1. Pretreatment of pickling, mechanical polishing, degreasing cleaning, dehydration and drying is performed on the α-type titanium alloy TA12 titanium alloy workpiece;

[0051] Step 2. Place the pretreated TA12 titanium alloy workpiece in step 1 in an ion chemical heat treatment furnace, and pre-evacuated to 9×10 -3 Pa, pass through Ar and CO, respectively 2 Gas, control Ar and CO 2 The flow ratio is 1:10, and the vacuum degree is adjusted to 1Pa;

[0052] Step 3. When the vacuum degree in the ion chemical heat treatment furnace in step 2 reaches 1Pa, load the TA12 titanium alloy workpiece with a negative bias voltage of 200V to generate a glow discharge, and use the glow plasma to clean the TA12 titanium alloy workpiece for 30min, Then increase the negative bias to 1200V, heat the TA12 titanium alloy...

Example Embodiment

[0054] Example 3

[0055] The method for plasma oxycarburizing of the α+β type TC4 titanium alloy workpiece of the present embodiment comprises the following steps:

[0056] Step 1, carry out the pretreatment of pickling, mechanical polishing, degreasing cleaning, dehydration and drying on the TC4 titanium alloy workpiece;

[0057] Step 2, place the pretreated TC4 titanium alloy workpiece in the ion chemical heat treatment furnace in the step 1, and pre-evacuated to 4×10 -3 Pa, pass through Ar and CO, respectively 2 Gas, control Ar and CO 2 The flow ratio is 10:1;

[0058] Step 3, when the vacuum degree in the ion chemical heat treatment furnace in step 2 reaches 600Pa, load the TC4 titanium alloy workpiece with a negative bias voltage of 500V to generate a glow discharge, and use the glow plasma to clean the TC4 titanium alloy workpiece for 200min, Then increase the negative bias to 800V, heat the TC4 titanium alloy workpiece to 930°C, and undergo 5h ion oxycarburizing tr...

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Abstract

The invention discloses a method for plasma oxygen-carbon co-permeation of a titanium-based or zirconium-based metal surface. The method comprises the steps that 1, the surface of a titanium-based or zirconium-based metal workpiece is pretreated; 2, the metal workpiece is put in an ionic chemical heat treatment furnace, pre-vacuumizing is performed, and Ar and CO2 gases are led; 3, a negative bias pressure is loaded for the metal workpiece to produce glow discharge, a glow plasma is used for cleaning the metal workpiece, and then the titanium-based or zirconium-based metal workpiece is heated to perform ionic oxygen-carbon co-permeation; 4, a grid bias power supply is turned off, gas leading is stopped, so that the titanium metal workpiece is cooled to reach below 100 DEG C with the furnace cooling and is discharged of the furnace, and the titanium-based or zirconium-based metal workpiece subjected to ionic oxygen-carbon co-permeation is obtained, wherein a hardened layer with the thickness of 5-3000 microns is formed on the surface of the titanium-based or zirconium-based metal workpiece, and the hardness is up to 700-2100 HV. The method is high in penetration speed and large in penetration layer depth, the prepared hardened layer is a composite permeation layer, the penetration layer hardness is high, and the composite penetration layer has excellent toughness.

Description

technical field [0001] The invention belongs to the technical field of surface treatment of metal materials, and particularly relates to a method for plasma oxycarburization of titanium-based or zirconium-based metal surfaces. Background technique [0002] Both titanium and zirconium have excellent corrosion resistance, high specific strength and good processability. However, they have poor wear resistance and are prone to sintering when rubbed. Titanium and zirconium have good biocompatibility with human bones, body fluids and brain tissue, and can be used as substitute materials for bones in medicine. In the aviation industry, the spacecraft and its movable components in service under space conditions are subject to the combined effects of extreme environments such as low temperature and alternating temperature, high-energy particle irradiation, atomic oxygen erosion, debris impact, and dust erosion, and their failure behaviors and mechanisms. It is very different from t...

Claims

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Application Information

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IPC IPC(8): C23C8/36C23C8/28
CPCC23C8/28C23C8/36Y02T50/60
Inventor 王浩楠李争显赵文姬寿长王彦峰吕海兵张勇
Owner NORTHWEST INSTITUTE FOR NON-FERROUS METAL RESEARCH
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