A method for preparing a wear-resistant layer of a turbine blade sawtooth crown

Abstract

The invention provides a turbine blade sawtooth shroud wear-proof layer preparation method, and belongs to the technical field of aircraft engine part manufacturing. By means of an existing turbine blade sawtooth shroud wear-proof layer preparation method, after the machining step of creep feed grinding, a wear-proof layer is unqualified due to the fact that point and linear fluorescent defects exist in the root concave R region and the surface of the wear-proof layer, the service life of a turbine blade is directly affected due to the non-standard-exceeding fluorescent defects of the root concave R region, cracks are generated extremely easily on the high-stress concentration region due to the fluorescent defects, even chip off-falling risks exist, and the flight safety is affected seriously. By means of the turbine blade sawtooth shroud wear-proof layer preparation method, the point and linear fluorescent defects existing in the root concave R region and the surface of the wear-proof layer are overcome, the one-time preparation yield of the wear-proof layer of the turbine blade can be increased to 90%, the risk that the cracks of the blade are generated in the high-stress concentration region due to the fluorescent defects is reduced, and the service life of the blade is prolonged effectively. The turbine blade sawtooth shroud wear-proof layer preparation method has the advantages of being high in wear-proof layer bonding strength, flexible to operate, low in cost and wide in application range.

Description

Technical field [0001] The invention belongs to the technical field of aero-engine component manufacturing, and particularly relates to a method for preparing a wear-resistant layer of a serrated crown of a turbine blade. Background technique [0002] The low-pressure turbine blades of aero-engines generally adopt a structure with a serrated crown. Each blade is connected to the turbine disk through a tenon, and is matched with adjacent blades through a serrated crown damping surface to form a turbine blade ring. [0003] During the operation of an aero-engine, the turbine blades will withstand complex torque and bending moments, which in turn will cause squeezing and fretting wear on the damping surface of the serrated crown, in order to prevent excessive blade gaps and blade rings caused by excessive wear of the damping surface For the problem of looseness, technicians have adopted the method of preparing a wear-resistant alloy layer on the blade serrated crown to ensure the wear...

AI Technical Summary

Problems solved by technology

[0005] Aiming at the problems existing in the prior art, the present invention provides a method for preparing the wear-resistant layer of the sawtooth crown of the turbine blade, which effectively reduces the point and linear fluorescent defects in the concave R area of ​​the root and the surface of the wear-resistant layer, and can reduce the primary wear-resistant layer of the turbine blade. The qualification rate of grinding layer preparation is increased to more than 90%, which minimizes the risk of cracks in the blade caused by fluorescent defects in the high stress concentration area, and effectively improves the service life of the blade

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