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A kind of preparation method of high temperature metal surface anti-high temperature oxidation radiant heat protective coating

A technology for anti-high temperature oxidation and metal surface, which is applied in the direction of surface reaction electrolytic coating, metal material coating process, coating, etc., can solve the problem of low emissivity of metal surface, poor protection ability of high temperature radiation heat dissipation, poor erosion resistance, etc. problems, to achieve the effect of improving high temperature oxidation resistance, uniform and controllable thickness, and good bonding performance

Active Publication Date: 2019-01-18
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition to high-temperature oxidation resistance, aircraft heat protection metal shells or thermal structural components are also subjected to harsh environments such as high-temperature gas friction and particle erosion during high-speed flight, and the surface of the base metal or its diffusion-modified alloyed layer is resistant to erosion The performance is poor, and the emissivity of the metal surface is low (about 0.1-0.3), which makes the protection ability of high temperature radiation and heat dissipation poor

Method used

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  • A kind of preparation method of high temperature metal surface anti-high temperature oxidation radiant heat protective coating
  • A kind of preparation method of high temperature metal surface anti-high temperature oxidation radiant heat protective coating

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0030] The metal substrate is Nb-10Hf-1Zr (brand C103), and the specific operation steps are:

[0031] Step 1: Prepare Si infiltration layer by high temperature chemical infiltration method: 1. Polish the surface of Nb-10Hf-1Zr substrate with 800# SiC sandpaper, remove surface oxide scale and dirt, and clean; 2. Preparation of infiltration agent: 16wt% Si , 5wt% NaF and 5wt% Y 2 o 5 , and the balance Al 2 o 3 powder. Ball mill for 4 hours after configuration; 3. Completely embed the cleaned workpiece in a container with infiltration agent, seal it and place it in a high-temperature chemical infiltration furnace; 4. Introduce high-purity argon into the furnace to Raise the temperature of the furnace to 1300°C at a rate of °C / min, keep the temperature for 8 hours, then cool down to room temperature with the furnace, take out the workpiece, and clean it to obtain a 90 μm Si-infiltrated oxygen barrier transition layer.

[0032] Step 2: In-situ generation of micro-arc oxidatio...

Embodiment 2

[0037] The metal matrix is ​​made of SiC reinforced Nb alloy composite material, and the specific operation steps are as follows:

[0038] Step 1: Preparation of Si infiltration layer by high-temperature chemical infiltration method: 1. Polish the surface of the substrate with 800# SiC sandpaper, remove surface scale and dirt, and clean; 2. Preparation of infiltration agent: 16wt% Si, 5wt% NH 4 Cl, 5wt% CeO 2 and the balance Al 2 o 3 Powder, after ball milling for 4 hours; 3. After the cleaned workpiece is completely buried in the container containing the infiltration agent, seal it and place it in a high-temperature chemical infiltration furnace; 4. Introduce high-purity argon into the furnace, Raise the temperature in the furnace to 1300°C at a rate of 8°C / min. After holding the temperature for 8 hours, cool down to room temperature with the furnace, take out the workpiece, and clean it to obtain a Si-infiltrated oxygen barrier layer with a thickness of 220 μm.

[0039] S...

Embodiment 3

[0044] The metal substrate is 73Ni-15Cr-Ti, Al (brand Inconel 600), and the specific operation steps are:

[0045] Step 1: Prepare the Al infiltration layer by high temperature chemical infiltration method: 1. Polish the surface of the substrate with 800#SiC sandpaper, remove the surface scale and clean it; 2. Preparation of infiltration agent: its weight percentage is: 16wt% Al, 5wt %NaF, 10wt%Y 2 o 3 and 5wt% CeO 2 and the balance Al 2 o 3 Powder, ball milled for 4 hours after preparation; 3. Completely embed the cleaned workpiece in a container with infiltration agent, seal it and place it in a high-temperature chemical infiltration furnace; 4. Introduce high-purity argon into the furnace, The temperature of the furnace was raised to 1000°C at a rate of 8°C / min, and after holding for 8 hours, it was cooled to room temperature with the furnace to obtain an Al-impregnated oxygen barrier layer with a thickness of 80 μm.

[0046] Step 2: Prepare micro-arc oxidation coating...

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Abstract

A preparation method of a high-temperature oxidation resistant radiative thermal protection coating for a metal surface applicable to high temperature is characterized in that a high-temperature oxidation resistant silicide or aluminide transition layer being 30 to 200 microns in thickness is prepared on the metal surface through high-temperature chemical diffusion permeation; and then the surface of the transition layer is in-situ converted into a 3-30 microns outer erosion resistant radiative thermal protection ceramic layer which has high emissivity and strengthened physical phase through micro-arc oxidation, and thus the obtained composite coating combines high-temperature oxidation resistance, erosion resistance and high emissivity. According to the composite coating prepared by the method, the boundary of a base material / the transition layer / the outer ceramic layer is subjected to high-strength metallurgical bonding; with the adoption of the transition layer, the composite coating is outstanding in high-temperature oxidation resistance; with the adoption of the outer ceramic layer which has high emissivity, the metal emissivity of a matrix is increased from 0.2-0.35 to be more than 0.8; due to the improved radiative heat dispersing performance, the temperature of the surface of a metal thermal protection system decreases by 10 to 20%; in addition, the ceramic layer is resistant to strong flow erosion. Therefore, the composite coating has a high application potential in the fields of aerospace thermal structure and external thermal insulation.

Description

technical field [0001] The invention relates to a method for preparing a high-temperature oxidation radiation heat protective coating on a metal surface for high temperature, and belongs to the technical field of composite coating preparation methods. Background technique [0002] The materials of high-temperature structural parts used in aerospace mainly include Ti, TiAl, Ni, Ta, Nb and other alloys and their reinforced composite materials, which are used in jet engines, aerospace vehicles, missile thermal protection and other structural parts that mainly use aerodynamic heating. superior. Although alloying improves the oxidation resistance of the original metal substrate, it is generally difficult to apply in higher temperature, oxidation and erosion environments. For example, the oxidation failure of Nb alloy is still very serious above 900 °C. In addition to high-temperature oxidation resistance, aircraft heat protection metal shells or thermal structural components ar...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C10/52C25D11/26C25D11/34C23F17/00
CPCC23C10/52C23F17/00C25D11/026C25D11/26C25D11/34
Inventor 王亚明葛玉麟蔡槐陈国梁郭立新贾德昌周玉
Owner HARBIN INST OF TECH