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Method for removing surface adhesive materials of turbine working blades

A technology of attachment and work, applied in the field of mechanical processing, can solve problems such as difficult to remove carbon deposits

Inactive Publication Date: 2018-12-18
HUNAN SOUTH GENERAL AVIATION ENGINE CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0002] The coating on the surface of the turbine working blades of turboshaft engines can effectively improve the thermal corrosion resistance, but a carbon deposit adhesion layer is formed on the surface during subsequent use. Difficulty, the current water cleaning method is difficult to remove carbon deposits

Method used

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  • Method for removing surface adhesive materials of turbine working blades
  • Method for removing surface adhesive materials of turbine working blades

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Embodiment Construction

[0021] The purpose of the present invention is to provide a method for removing surface attachments of turbine working blades. The method for removing surface attachments of turbine working blades can remove carbon on the surface of turbine working blades without damaging the surface coating of turbine working blades.

[0022] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0023] see figure 1 , figure 1 It is a flow chart of a method for removing surface attachments on turbine working blades provided by an embod...

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Abstract

The invention discloses a method for removing surface adhesive materials of turbine working blades. The method comprises the steps that abrasive materials and the turbine working blades are put into aworking groove of a vibrating polishing machine; and the vibrating polishing machine is started, the working groove is vibrated in a reciprocating mode, the vibrating polishing machine is stopped after the abrasive materials and the turbine working blades move in the working groove in the same direction for the preset time, and polishing treatment of the turbine working blades is completed. Therefore, the method is convenient to operate, surface adhesive materials of a large scale of turbine working blades can be removed simultaneously, and the removing effect of surface deposited carbon adhesive layers of the turbine working blades can be selectively examined at any time; and by controlling the polishing treatment time, the condition that the surface coatings of the turbine working blades are damaged by the abrasive materials can be avoided, and therefore the purpose of removing surface deposited carbon of the turbine working blades on the premise that the surface coatings of the turbine working blades are not damaged is achieved.

Description

technical field [0001] The invention relates to the technical field of mechanical processing, in particular to a method for removing surface attachments of turbine working blades. Background technique [0002] The coating on the surface of the turbine working blades of turboshaft engines can effectively improve the thermal corrosion resistance, but a carbon deposit adhesion layer is formed on the surface during subsequent use. Difficulty, the current water cleaning method is difficult to remove carbon deposits. [0003] Therefore, how to provide a method suitable for removing the attachments on the surface of turbine working blades has become an important technical problem to be solved urgently by those skilled in the art. Contents of the invention [0004] In view of this, the purpose of the present invention is to provide a method for removing surface attachments of turbine working blades. [0005] To achieve the above object, the present invention provides the followi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B24B31/10B24B1/00
CPCB24B31/10B24B1/00
Inventor 安国东刘彩虹李赫
Owner HUNAN SOUTH GENERAL AVIATION ENGINE CO LTD
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