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Method for removing carbon deposits of aircraft turbine blade through electrolysis

A technology for aircraft turbine blades and turbine blades, applied in liquid cleaning methods, cleaning methods and utensils, chemical instruments and methods, etc., to achieve the effects of simple process methods, reduced surface roughness, and reduced carbon deposition on the surface

Inactive Publication Date: 2021-08-10
SHANGHAI HANGYI HI TECH DEV RES INST CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to solve the technical problem of how to overcome the deficiencies of existing cleaning solutions and obtain a safe and reliable method for removing carbon deposits on aircraft turbine blades

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  • Method for removing carbon deposits of aircraft turbine blade through electrolysis
  • Method for removing carbon deposits of aircraft turbine blade through electrolysis

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Embodiment

[0037] The invention provides a cleaning method for aircraft engine turbine blades, which combines the existing ultrasonic cleaning method with electrolytic polishing technology, and adopts any ultrasonic cleaning equipment available in the market. The electrolytic polishing equipment may be any one of slot-type electrolytic polishing equipment and brush-type electrolytic polishing equipment. The specific cleaning steps are as follows:

[0038] ①Put the turbine blade workpiece into the ultrasonic cleaning equipment, and let the cleaning agent submerge the turbine blade. The cleaning liquid in the ultrasonic cleaning equipment can be water-based metal cleaning agent, semi-water-based metal cleaning agent, and solvent-based metal cleaning agent. Any one, the cleaning temperature is any temperature between 30°C and 50°C, and the cleaning time is between 30min and 1h. The cleaning effect reaches the level where the remaining carbon deposits cannot be removed by ultrasonic cleaning...

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Abstract

The invention relates to a method for removing carbon deposits of an aircraft turbine blade through electrolysis, and belongs to the technical field of cleaning of carbon deposits of aircraft engine turbine blades. According to the method, carbons which are not tightly combined on the surface of the turbine blade are removed in an ultrasonic cleaning manner, part of a nickel alloy substrate is exposed, and then the carbon deposits are made to fall off through an electrolytic polishing technology. According to the electrolytic polishing process, a nickel-based alloy at the joint of a workpiece and the carbon deposits can be oxidized, so that the nickel-based alloy is converted into metal ions to be dissolved in electrolysis, the combination of a carbon deposit substrate and the workpiece is weakened, and therefore surface polishing of the workpiece can be realized while the carbon deposits are removed, and the surface roughness of the workpiece is reduced. The problems that in a cleaning method in the prior art, cleaning is incomplete, the roughness is increased due to workpiece wear, the cleaning speed is low, and the cleaning efficiency is low are solved.

Description

technical field [0001] The invention relates to a method for electrolytically removing carbon deposits on aircraft turbine blades, and belongs to the technical field of cleaning carbon deposits on aircraft engine turbine blades. Background technique [0002] During the working process of the aircraft engine, due to the incomplete combustion of the fuel and the additives in the aviation fuel and other components that cannot be burned into the gas, it is easy to deposit on the turbine blades, and then undergo a series of oxidation, cracking, dehydrogenation and coking such as high temperature sintering And other physical and chemical changes will form a solid layer of carbon deposits on the turbine blades. The main elements of carbon deposits on the surface of turbine blades are oxygen, silicon, aluminum, calcium, magnesium, nickel, etc. Therefore, carbon deposits are mainly insoluble and insoluble components, which are very difficult to remove. [0003] During the maintenan...

Claims

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Application Information

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IPC IPC(8): C25F3/22C25D11/34B08B3/12
CPCC25F3/22C25D11/34B08B3/12
Inventor 钟孚瑶邓阳俊马芳德刘博恩
Owner SHANGHAI HANGYI HI TECH DEV RES INST CO LTD
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