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Method for removing remelting layer in electric spark drilling for single crystal turbine blade

A turbine blade and electric spark technology is applied in the field of remelting layer removal of single crystal turbine blade electric spark hole making, which can solve the problems of low efficiency, influence of blade cavity, unfeasible heat treatment method, etc. good effect

Inactive Publication Date: 2015-03-25
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For DD6 single crystal turbine blades, due to the influence of surface recrystallization, the heat treatment is put in the front during the process, so the heat treatment method is not feasible
The abrasive flow method requires large-scale equipment and has low efficiency; at the same time, the residual sand particles will affect the cavity of the blade, so this method is not feasible

Method used

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  • Method for removing remelting layer in electric spark drilling for single crystal turbine blade

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Experimental program
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Effect test

Embodiment 1

[0022] The specific process of a method for removing the remelted layer of single crystal turbine blades by EDM is: mixing hydrochloric acid, water, and hydrogen peroxide in a volume ratio of 100:44:25 to obtain corrosive liquid, and pass DD6 single crystal blades through EDM After the hole, put it into a container filled with corrosive liquid, and then place it in an ultrasonic wave with a power of 2400W to vibrate, and the vibration time is 30min. After that, under observation under a metallographic microscope, the remelted layer in the air film holes on the single crystal blade was completely removed, and the effect was obvious. figure 1 , figure 1 (a) is the scanning electron micrograph before corrosion, figure 1 (b) is the scanning electron micrograph after corrosion, figure 1 (c) is a macroscopic view after corrosion, from which it can be seen that the remelted layer has been completely removed.

Embodiment 2

[0024] The specific process of a method for removing the remelted layer of single crystal turbine blades by EDM is: mixing hydrochloric acid, water, and hydrogen peroxide in a volume ratio of 91:43:22 to obtain a corrosive liquid, and pass the DD6 single crystal blade through the EDM process After the hole, put it into a container filled with corrosive liquid, and then place it in an ultrasonic wave with a power of 2400W and vibrate for 20min. After that, under a metallurgical microscope, the remelted layer in the air film holes on the single crystal blade was completely removed.

Embodiment 3

[0026] The specific process of a method for removing the remelted layer of single crystal turbine blades by EDM is: mixing hydrochloric acid, water, and hydrogen peroxide in a volume ratio of 93:41:20 to obtain corrosive liquid, and pass the DD6 single crystal blade through the EDM process After the hole, put it into a container with corrosive liquid, and then place it in an ultrasonic wave with a power of 2400W to vibrate, and the vibration time is 40min. After that, under a metallurgical microscope, the remelted layer in the air film holes on the single crystal blade was completely removed.

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Abstract

The invention discloses a method for removing a remelting layer in electric spark drilling for a single crystal turbine blade. The method comprises the following steps: mixing hydrochloric acid, water and hydrogen peroxide according to the volume ratio of (91-100) to (40-44) to (20-25) to obtain a corrosive liquid; putting a blade which is subjected to electric spark drilling into the corrosive liquid, and corroding under ultrasonic waves for 20-40 minutes to remove the remelting layer. By adopting a chemical corrosion method, the method is simple, feasible, relatively good in removal effect, and high in efficiency; the corrosion test surface recrystallization procedure in the of manufacturing process of a DD6 single crystal turbine blade proves that the surface of the blade is not affected by chemical corrosion in the invention, and the method is a feasible method.

Description

Technical field [0001] The invention belongs to the technical field of preparation of gas film holes of single crystal turbine blades, and in particular relates to a method for removing remelted layers of single crystal turbine blades by electric spark holes. Background technique [0002] In the aviation industry, the continuous improvement of engine working efficiency and the increase of the temperature capacity of the engine are carried out simultaneously. Every 5°C increase of the engine can increase engine power by 1.3% and thermal efficiency by 0.4%. This requires the engine blade material to have a higher temperature bearing capacity. Compared with casting and directional solidification alloys, single crystal alloys have higher resistance to thermal fatigue, mechanical fatigue, oxidation and creep resistance, which can significantly improve the temperature-bearing capacity of the alloy, and has become the best use for aero engine blade components material. On the other h...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23F1/16C30B33/10
Inventor 杨健侯春梅李卫军何军刚吴楠张太金魏磊赵成成
Owner AECC AVIATION POWER CO LTD
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