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Corrosion method for depletion layer on surface of high-temperature alloy blade

A technology for superalloys and blades, applied in the field of metallographic microstructure detection, can solve problems such as poor reliability, and achieve the effect of optimizing manufacturing parameters and improving the level of microstructure and performance.

Inactive Publication Date: 2016-12-07
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Scientific researchers have invested a lot of time and energy in the inspection of the depleted layer on the surface of the superalloy blade of the engine. Among them, the physical metallographic method is the most intuitive detection method, but this method can only be used for the superalloy material surface. It can only be used when the phenomenon of depletion is obvious
Therefore, for samples whose depletion phenomenon is not obvious on the surface of superalloy materials, it will appear powerless, especially the reliability of detecting the depleted layer depth value on the surface of superalloy materials by physical metallography is poor

Method used

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  • Corrosion method for depletion layer on surface of high-temperature alloy blade
  • Corrosion method for depletion layer on surface of high-temperature alloy blade
  • Corrosion method for depletion layer on surface of high-temperature alloy blade

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Experimental program
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Effect test

Embodiment 1

[0036] After the DZ125 high-temperature alloy blade is heat-treated, the middle part of the blade is selected to detect the surface depletion layer. After the surface to be tested is mechanically ground and polished, it is placed in a solution containing a corrosive agent. The volume ratio of oxalic acid and pure water in the corrosive agent = At 10:90, electrolytic corrosion is carried out, and the corrosion parameters are: the voltage is 1.5V, the current is 0.5A, and the time is 10s. Observed under a metallographic optical microscope, the corrosion effect can be seen figure 1 , it was found that the depleted layer on the surface of the DZ125 superalloy blade was clearly visible, and the corrosion effect was obvious.

Embodiment 2

[0038]After the DZ125 high-temperature alloy blade is heat-treated, the middle part of the blade is selected to detect the surface depletion layer. After the surface to be tested is mechanically ground and polished, it is placed in a solution containing a corrosive agent. The volume ratio of oxalic acid and pure water in the corrosive agent = At 20:80, electrolytic corrosion was carried out, and the corrosion parameters were: voltage 1.5V, current 0.5A, and time 10s. Observed under a metallographic optical microscope, the corrosion effect can be seen figure 2 , found that the depletion layer on the surface of the DZ125 superalloy blade is clearly visible, and the corrosion effect is obvious.

Embodiment 3

[0040] After the DZ125 high-temperature alloy blade is heat-treated, the middle part of the blade is selected for the detection of the surface depletion layer. After the surface to be tested is mechanically ground and polished, it is placed in a solution containing a corrosive agent. The oxalic acid in the corrosive agent: H 2 O volume ratio = 10:90, electrolytic corrosion, corrosion parameters: voltage 1.5V, current 0.5A, time 5s. Observed under a metallographic optical microscope, the corrosion effect can be seen image 3 , found that the depletion layer on the surface of the DZ125 superalloy blade is clearly visible, and the corrosion effect is obvious.

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Abstract

The invention discloses a corrosion method for a depletion layer on the surface of a high-temperature alloy blade. According to purposes, high-power corrosion is conducted on the depletion layer on the surface of the high-temperature alloy material, the depletion layer on the surface of the high-temperature alloy blade obtained after use is better displayed, the element depletion phenomenon generated on the surface of a part in the heat treatment process is better displayed, the form, distribution and depth of the depletion layer on the surface of the high-temperature alloy blade can be objectively reflected, and therefore the conditions of the blade can be correctly judged, and the state of the surface of the high-temperature alloy blade is further reflected. According to the adopted technical scheme, the method includes the steps that firstly, after a metallographic specimen of the high-temperature alloy material in which alloy element depletion happens to the surface is subjected to heat treatment, grinding and polishing are conducted in sequence; and secondly, electrochemical corrosion is conducted on a polishing face of the metallographic specimen, a corrosive adopted in electrochemical corrosion is a mixture of oxalic acid and pure water, the size ratio of the oxalic acid in the corrosive to the pure water in the corrosive is (1-2):(8-9), and therefore the depletion layer on the surface of the high-temperature alloy material can be obtained through corrosion.

Description

technical field [0001] The invention relates to the field of metallographic microstructure detection in the physical and chemical detection technology of high-temperature alloy blades, in particular to a method for corroding a depleted layer on the surface of high-temperature alloy blades. Background technique [0002] As an important symbol to measure the development level of aero-engines and industrial gas turbines, the development level of superalloys has attracted great attention from all countries in the world, and a lot of manpower and material resources have been invested in the research and development of superalloys. Although the research on superalloys has made great progress and obtained many gratifying research results, there are still many problems in the production and processing of superalloy materials, for example: superalloy materials are prone to produce The phenomenon of depletion of surface alloy elements. The depletion phenomenon on the surface of the s...

Claims

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Application Information

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IPC IPC(8): C25F3/02G01N1/32
CPCC25F3/02G01N1/32
Inventor 杨健胡锴李卫军侯春梅刘伟吴楠魏磊徐杏杏
Owner AECC AVIATION POWER CO LTD
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