Nine-point control variable margin milling method for thin-walled blades based on newton interpolation

Abstract

The invention provides a thin-walled vane nine-point control variable-allowance milling method based on Newton interpolation. Modeling is carried out by utilizing a three-dimensional modeling software, and an auxiliary surface and a boundary surface are formed, so that a driving surface is determined by utilizing a section line lofting process. Cutter machining paths are generated according to the driving surface, and the machining allowance of each cutter position point on each machining path is determined by adopting a Newton interpolation method. Finally, vanes are cyclically processed according to symmetrical milling rules. Compared with a traditional longitudinal fixed-allowance cutting and spiral milling method, the thin-walled vane nine-point control variable-allowance milling method has the advantages that technical problems, such as large torsional deformation, low contour precision, poor section position tolerance and difficult error control, in the machining process can be solved; and by adopting a Newton interpolation process allowance fine adjustment method, surface quality can be more comprehensively controlled, and problems, such as large bending deformation, poor section position tolerance and low surface contour precision, in the machining process can be effectively solved.

Description

technical field [0001] The invention belongs to the technical field of precision and ultra-precision numerical control milling, and is a 9-point control variable margin precision symmetrical milling process for thin-walled blades of difficult-to-machine materials, which mainly solves the problem of deformation control of the numerically controlled milling finishing of thin-walled blades of aeroengines. The method is especially suitable for precision machining of thin-walled guide blades of aero-engines whose airfoil length is more than 70 mm. Background technique [0002] The aero engine is the "heart" of the aircraft and one of the determining factors of the aircraft's performance. The blade is one of the core components of an aero-engine. It is a typical thin-walled free-form surface part. It is not only a large number, complex shape, high performance requirements, difficult processing, but also a frequent failure part. Therefore, the blade has always been one of the key ...

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Problems solved by technology

[0005] For the problems of the previous processing method in the processing of longer blades, the present invention makes some improvements to the processing of blades with a length greater than 70 mm, and suppresses the influence of bending and torsional deformation on the processing accuracy of blades from the processing technology

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