Method for preparing hollow blade inner chamber diffusion layer with high temperature resistance, oxidation resistance and corrosion resistance

A high-temperature oxidation-resistant, hollow blade technology, applied in the direction of solid-state diffusion cladding, blade support elements, coatings, etc.

Active Publication Date: 2012-06-06
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The object of the present invention is to provide a method for preparing a high temperature oxidation and corrosion diffusion infiltrated layer in the inner cavity of a hollow blade, so as to solve the problem that the parts with the inner cavity cannot be used in the past. The problem of surface preparation infiltration layer and poor resistance to high temperature oxidation and corrosion

Method used

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  • Method for preparing hollow blade inner chamber diffusion layer with high temperature resistance, oxidation resistance and corrosion resistance

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0033] The gas turbine hollow blade is prepared to resist high temperature oxidation and corrosion diffusion infiltration layer, and the material of the gas turbine hollow blade is K465 nickel-based superalloy. The specific preparation method is as follows:

[0034] ——Preparation of penetrating agent:

[0035] (1) Preparation of nickel chromizing agent: chromium powder, nickel powder, aluminum oxide powder, nickel-yttrium alloy powder, and ammonium chloride are prepared into nickel chromizing agent according to the following weight ratio;

[0036] Chromium powder 7%; Nickel powder 27%;

[0037] Aluminum oxide powder 60%; nickel-yttrium alloy powder 5%;

[0038] ammonium chloride balance;

[0039] (2) Preparation of chrome aluminizing agent: chrome powder, aluminum powder, aluminum oxide powder, nickel-yttrium alloy powder, and ammonium chloride are prepared according to the following weight ratio to prepare a chrome aluminizing agent;

[0040] Chromium powder 38%; Aluminum...

Embodiment 2

[0062] The gas turbine hollow blade is prepared to resist high temperature oxidation and corrosion diffusion infiltration layer, and the material of the gas turbine hollow blade is K465 nickel-based superalloy. The specific preparation method is as follows:

[0063] ——Preparation of penetrating agent:

[0064] (1) Preparation of nickel chromizing agent: chromium powder, nickel powder, aluminum oxide powder, nickel-yttrium alloy powder, and ammonium chloride are prepared into nickel chromizing agent according to the following weight ratio;

[0065] Chromium powder 10%; Nickel powder 24%;

[0066] Aluminum oxide powder 62%; nickel-yttrium alloy powder 3%;

[0067] ammonium chloride balance;

[0068] (2) Preparation of chrome aluminizing agent: chrome powder, aluminum powder, aluminum oxide powder, nickel-yttrium alloy powder, and ammonium chloride are prepared according to the following weight ratio to prepare a chrome aluminizing agent;

[0069] Chromium powder 39.7%; Alumi...

Embodiment 3

[0090] The gas turbine hollow blade is prepared to resist high temperature oxidation and corrosion diffusion infiltration layer, and the material of the gas turbine hollow blade is K465 nickel-based superalloy. The specific preparation method is as follows:

[0091] ——Preparation of penetrating agent:

[0092] (1) Preparation of nickel chromizing agent: chromium powder, nickel powder, aluminum oxide powder, nickel-yttrium alloy powder, and ammonium chloride are prepared into nickel chromizing agent according to the following weight ratio;

[0093] Chromium powder 8%; Nickel powder 25%;

[0094] Aluminum oxide powder 61%; nickel-yttrium alloy powder 4%;

[0095] ammonium chloride balance;

[0096] (2) Preparation of chrome aluminizing agent: chrome powder, aluminum powder, aluminum oxide powder, nickel-yttrium alloy powder, and ammonium chloride are prepared according to the following weight ratio to prepare a chrome aluminizing agent;

[0097] Chromium powder 39%; Aluminum...

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Abstract

The invention provides a method for preparing a hollow blade inner chamber diffusion layer with high temperature resistance, oxidation resistance and corrosion resistance, which is characterized by comprising the following steps: preparing a nickel chromium osmolyte and a chromium aluminum osmolyte; calcining the prepared nickel chromium osmolyte at the temperature of 1000-1050 DEG C for 1-2 hours, then sieving by a 60 meshes sieve, filling in a seal container for next application; then calcining the prepared chromium aluminum osmolyte at the temperature of 1100-1150 DEG C for 1-2 hours and calcining at the temperature of 950-1000 DEG C for 1-2 hours, then sieving by the 60 meshes sieve, filling in the seal container for next application; then preparing the hollow blade diffusion layer, raising the work temperature of the nickel base high temperature alloy blade from 900 DEG C to 1050-1100 DEG C, simultaneously preparing the diffusion layer both in the inner chamber and on the external surface of the blade. The high temperature resistance, oxidation resistance and corrosion resistance capabilities of the blade can be substantially enhanced.

Description

technical field [0001] The invention relates to the field of high-temperature corrosion and protection of alloy surfaces, and in particular provides a method for preparing a high-temperature oxidation-resistant and corrosion-diffusion infiltration layer in a hollow blade inner cavity. [0002] Background technique [0003] During the oxidation process of the K465 alloy blade, a large number of non-protective oxides are formed on the surface, and the substrate also has internal oxidation and internal nitriding. Therefore, the alloy needs to be protected by coating when it is used at high temperature. The single aluminized coating has a certain anti-oxidation ability when oxidized at 1000 ° C; after 300 hours of oxidation at 1100 ° C, the coating degrades seriously and loses its protective effect. Due to the joint action of the columnar nanocrystalline structure and the Cr element, the sputtered NiCrAlY coating forms dense α-Al on the surface when it is oxidized at 1000 °C. ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C10/58F01D5/28
Inventor 张尊礼张凡云史凤岭彭新牛静
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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