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A method for removing environmental deposits in air film holes and narrow gaps of blades

A gas film hole and sediment technology, which is applied in the aerospace field, can solve the problems of small gas film hole diameter, damage to the base metal, block gas film cooling holes, etc., and achieve the effect of reducing the scrap rate.

Active Publication Date: 2016-01-20
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

These deposits are hard at normal temperature, and will melt on the surface of the blade at high temperature to block the air film cooling holes, resulting in a decrease in the cooling effect of the blade, and in severe cases, it will cause blade ablation
The traditional removal methods mainly include mechanical grinding and sand blowing, which can effectively remove the deposits on a large area of ​​the blade surface, but due to the small diameter of the air film pores, the traditional methods cannot remove the substances in the pores
From the perspective of sediment composition, the sediment is mostly amphoteric metals, which can be dissolved in acid and alkali, but due to the existence of surface tension, it is difficult for the acid-base solution to react with the substances in the small pores under normal temperature and pressure, and may damage the matrix metal at the same time. Or produce solution residues, which will affect the reliability of parts in later use

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0009] Removal process of environmental deposits in air film holes and narrow gaps of cast nickel-based superalloy high-pressure turbine guide vanes:

[0010] (1) High temperature and high pressure lye removal

[0011] The parts that need to remove the sediment are stacked in the high-pressure reactor with the reaction part facing down without overlapping, and the working solution is 35% (mass concentration) potassium hydroxide solution, the working temperature is 180 ° C, and the working pressure is 4 Atmospheric pressure, the time is 180min. After the parts are taken out from the autoclave, they are washed repeatedly with hot water at 90°C to avoid residual lye.

[0012] (2) Potassium permanganate cleaning

[0013] Soak the parts in a potassium permanganate mixed solution (mass concentration: 10% potassium permanganate, 15% sodium hydroxide) for 60 minutes, the temperature of the solution is 70°C, put it into 90°C hot water immediately after being corroded by potassium perm...

Embodiment 2

[0018] Removal process of environmental deposits in air film holes and narrow gaps of nickel-based superalloy high-pressure turbine blades:

[0019] (1) High temperature and high pressure lye removal

[0020] The parts that need to remove the sediment are stacked in the high-pressure reactor with the reaction part facing down without overlapping. The working solution is 45% (mass concentration) potassium hydroxide solution, the working temperature is 200 ° C, and the working pressure is 4 Atmospheric pressure, the time is 300min. After the parts are taken out from the autoclave, they are washed with hot water at 90°C repeatedly to avoid residual lye.

[0021] (2) Potassium permanganate cleaning

[0022] Soak the parts in potassium permanganate mixed solution (mass concentration: 10% potassium permanganate, 20% sodium hydroxide) for 80min, the temperature of the solution is 90°C, put it into 90°C hot water immediately after being corroded by potassium permanganate Soak for 12...

Embodiment 3

[0027] Removal process of environmental deposits in air film holes and narrow gaps of cast nickel-based superalloy high-pressure turbine guide vanes:

[0028] (1) High temperature and high pressure lye removal

[0029] The parts that need to be removed from the sediment are stacked in the high-pressure reactor with the reaction part facing down without overlapping, and the working solution is 50% potassium hydroxide solution, the working temperature is 300 ° C, and the working pressure is 5 standard atmospheres. The time is 360min. After the parts are taken out from the autoclave, they are washed repeatedly with hot water at 90°C to avoid residual lye.

[0030] (2) Potassium permanganate cleaning

[0031] Soak the parts in potassium permanganate mixed solution (mass concentration: 15% potassium permanganate, 20% sodium hydroxide) for 100min, the temperature of the solution is 105°C, put it into 90°C hot water immediately after being corroded by potassium permanganate Soak fo...

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Abstract

The invention aims to provide a method for effectively removing environmental deposits in various blade air film holes prepared from high-temperature nickel-based alloys and in narrow gaps. The method is characterized by including the specific steps: firstly, soaking a part with deposits to be removed in alkali solution at the temperature of 150-350 DEG C under 3-7 standard atmospheric pressure for 180-480min; secondly, soaking the part in mixed solution of potassium permanganate and sodium hydroxide for 30-240min; thirdly, taking out the part, immediately soaking the part in hot water with the temperature of 50-100 DEG C for at least 120min, neutralizing the part by weak acid and then cleaning the part by a high-pressure water gun; finally, cleaning the part by ultrasonic waves until washing water is detected to be neutral by pH (potential of hydrogen) test paper. The temperature of the mixed solution is 50-110 DEG C. By the method, a part base is not damaged, and post continuous use reliability of the part is ensured.

Description

technical field [0001] The invention belongs to the field of aerospace and particularly provides a method for removing environmental deposits in narrow gaps of various high-temperature working parts in the field of aerospace. Background technique [0002] The high-pressure turbine and guide vanes are the hot-end parts of the aero-engine, and the working temperature is about 1000°C. During the working process of the engine, a large amount of environmental deposits will appear on the blade body and the edge plate, and the main components of these deposits are CAMS (CaO, Al 2 o 3 , MgO, SiO 2 mixture), that is, fuel carbon deposits. These deposits are hard at normal temperature, and will melt on the surface of the blade at high temperature to block the air film cooling holes, resulting in a decrease in the cooling effect of the blade, and in severe cases, it will cause blade ablation. The traditional removal methods mainly include mechanical grinding and sand blowing. This ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B08B3/00B08B3/12B08B3/08B08B3/02B08B3/04
CPCB08B3/04B08B3/08B08B3/10B08B3/12
Inventor 李晗晔张春刚冮冶刘志强杜景源
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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