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Solution for chemically removing carbon deposition on high-pressure turbine blade

A technology of high-pressure turbines and blades, applied in chemical instruments and methods, non-surfactant detergent compositions, detergent compositions, etc.

Inactive Publication Date: 2010-07-07
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, the combination of surfactant-based cleaning agents combined with ultrasonic waves can only produce some effects on the oily dirt on the surface of the high-pressure turbine blades, but it has almost no effect on the oily dirt that has a certain adhesion to the inner cavity of the high-pressure turbine blades.

Method used

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  • Solution for chemically removing carbon deposition on high-pressure turbine blade
  • Solution for chemically removing carbon deposition on high-pressure turbine blade
  • Solution for chemically removing carbon deposition on high-pressure turbine blade

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Embodiment 1

[0051] A solution for chemically removing carbon deposits from high-pressure turbine blades, which is specifically used in conjunction with the external force of ultrasonic waves to perform chemical removal of carbon deposits; the solution for chemically removing carbon deposits from high-pressure turbine blades is specifically composed of organic reagents, surface A mixed solution composed of active agent, inorganic co-solvent and complexing agent.

[0052] The solution is a weakly alkaline mixed solution composed of an organic solvent and a surfactant. It is also a water-based cleaning solution. In addition to the penetrating and wetting functions of the surfactant, the organic solvent contained in it is effective against oily dirt. It also has a certain dissolution effect, so that the carbon deposit is loosened, reducing the adhesion between the carbon deposit and the substrate, and through the external force of the ultrasonic wave, the carbon deposit is separated from the s...

Embodiment 2

[0056] The content of this embodiment is basically the same as that of Embodiment 1, and its difference mainly lies in:

[0057] 1) The basic composition and scope of the solution for the chemical removal of carbon deposits of high-pressure turbine blades are as follows: the basic composition and scope of the reagents used in the chemical removal of carbon deposition methods for high-pressure turbine blades are preferably as follows: sodium hydroxide: 5g / l; Sodium Tripolyphosphate 10g / l; Dichloromethane 40ml / l; Sodium Lauryl Sulfate 4g / l; EDTA-Na 2 : 10g / l; 781 water-based cleaning agent: 15g / l.

[0058] 2) The specific requirements of the method for chemically removing carbon deposits from the high-pressure turbine blades are as follows: first, use reagents for chemical soaking, and the time required for soaking is 5 hours; 30min; the frequency of ultrasonic action is 20KHz; during the process of chemical soaking and ultrasonic cleaning, the working temperature of the reagen...

Embodiment 3

[0060] The content of this embodiment is basically the same as that of Embodiment 1, and its difference mainly lies in:

[0061] 1) The basic composition and scope of the solution used for high-pressure turbine blade chemical removal of carbon deposits are as follows: sodium hydroxide: 20g / l; sodium tripolyphosphate 20g / l; methylene chloride 10ml / l; dodecylsulfuric acid Sodium 1g / l; EDTA-Na 2 : 5g / l; 781 water-based cleaning agent 5g / l.

[0062] 2) The specific requirements of the method for chemically removing carbon deposits from the high-pressure turbine blades are as follows: firstly use reagents for chemical soaking, and the soaking time is required to be 20 hours; then continue to use reagents for ultrasonic cleaning, and the ultrasonic action time is 10 min; the ultrasonic action frequency is 40KHz; During chemical immersion and ultrasonic cleaning, the working temperature of the reagents is 50°C.

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Abstract

The invention provides solution for chemically removing carbon deposition on a high-pressure turbine blade. The solution is characterized in that the solution for chemically removing the carbon deposition on the high-pressure turbine blade is a mixture formed by an organic reagent, a surface active agent, an inorganic cosolvent and a complexing agent. The solution in the invention has the characteristics of high cleaning efficiency and easy operation in the carbon deposition removing operation of the high-pressure turbine blade. Compared with the traditional cleaning solution with 781 as a representative, the solution in the invention achieves more obvious effect and particularly achieves better effect for clearing away the special and stubborn carbon deposition. The solution in the invention can obviously increase the product qualification rate when being used in the production of an engine blade. The effect of removing the internal carbon deposition is obviously improved when a water-base cleaning agent that the solution in the invention requires to protect is utilized to chemically carry out the carbon deposition removing operation for the high-pressure turbine blade.

Description

technical field [0001] The invention relates to the technical field of metal material surface treatment, and in particular provides a solution for chemically removing carbon deposits from carbon deposits on engine parts (such as high-pressure turbine blades) working in high-temperature environments. Background technique [0002] The working temperature of the high-pressure turbine blades of the engine is about 1000°C. Under this high temperature and oxidation, the impurities in the fuel and the soot particles produced by insufficient combustion are deposited on the surface of the substrate, and with the increase of temperature and the extension of working time, further Condensation into a colloidal mixture of asphaltenes, oil cokes and hydrocarbons, the so-called carbon deposits. [0003] Most of the carbon deposits are composed of insoluble or insoluble components, which are hard in texture, firmly attached, and difficult to remove. Especially for the carbon deposit in the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23G1/14C11D7/60
Inventor 冮冶史凤岭窦立军滕志强刘莉张德权李晗晔康军卫刘志强
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION