A Composite Machining Method for Gas Film Hole of Guide Vane

Abstract

The invention relates to a guide vane air film hole composite machining method which comprises the steps that the surface and a cavity of a to-be-machined high-pressure turbine guide vane are coated with an anti-splashing agent, and the high-pressure turbine guide vane with an anti-splashing coating is obtained through drying; to-be-machined air film holes are located in a blade body and an edge plate of the high-pressure turbine guide blade correspondingly, and the to-be-machined air film holes in the blade body comprise the first air film hole and the second air film hole. A protection plateis placed in a cavity of the blade, the first air film hole and the second air film hole in the blade body are machined through electric sparks, the rest air film holes in the blade body and the airfilm holes in the edge plate are machined through lasers, and laser-electric spark composite machining of the air film holes of the high-pressure turbine guide blade is completed through aftertreatment. The protection plate is adopted for protection and partial machining, the problems that the wall is damaged by the hollow blade and metal splashes are discharged are solved, the percent of pass ofair film hole diameters and the machining efficiency are greatly improved, and the surface quality integrity of parts is improved through an anti-splashing agent.

Description

technical field [0001] The invention relates to the field of aero-engine manufacturing, in particular to a composite processing method for air film holes of guide blades. Background technique [0002] As the thrust and thrust-to-weight ratio of aeroengines continue to increase, the temperature at the outlet of the combustion chamber is getting higher and higher, which leads to an increase in the operating temperature of the engine blades. Machining film cooling holes on the working blades and guide blades of aeroengine turbines is an effective way to reduce the surface temperature of the turbine blades, thereby increasing the temperature before the turbine and increasing the thrust-to-weight ratio of the engine. There are a large number of air film holes distributed on the surface of the turbine cooling blade of the aero-engine, which are used to cool the blade. The diameter of these air film holes is generally 0.5-0.8mm, the space angle is complicated, and the processing i...

AI Technical Summary

Problems solved by technology

[0003] A certain type of aero-engine high-pressure turbine guide vane material is Ni 3 Al-based IC10 directionally solidified superalloy, the blade body and the upper and lower edge plates are integrally cast without allowance, the structure is complex, and more than 600 apertures and space angles are distributed on the curved surface contours of the blade body and upper and lower edge plates. The air film holes on the air inlet side of the blade body are very dense and difficult to process

At the same time, Ni 3 The Al-based alloy IC10 material has an aluminum content as high as 6.5-9.0%, and aluminum metal has a low absorption rate for laser light. The laser is difficult to process and the metal spatter produced is easy to adhere to the surface of the part. Mechanical grinding is required to remove the surface of the part. The removal of metal spatter will damage the surface quality of parts and affect the safety and reliability of blades

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