Numerical control machining method of aero-engine disc-shaft integrated structure part

Abstract

Disclosed is a numerical control machining method of an aero-engine disc-shaft integrated structure part. Main machining processes of the part are four procedures of die forging, rough machining of a big end, rough machining of a small end, vacuum stress relief heat treatment, finish machining of a molded surface of the big end, and finish machining of a molded surface of the small end, and two sets of special clamps are needed. A turn-milling composite machining center with double main shafts is adopted to replace an original ordinary lathe, a numerical control lathe, a five-coordinate machining center and other devices to machine the part, when finish turning machining is carried out, an online measuring function of the turn-milling composite machining center is adopted to carry out part size measurement and automatic compensation of cutter compensation of a cutter, a cutter compensation deviation value is automatically calculated by the numerical control lathe and input into a lathe cutter wear value, the automatic compensation is carried out, and finished size machining of the part is finished. The numerical control machining method of the aero-engine disc-shaft integrated structure part has the advantages that a machining process is stable, quality is improved, once submit qualified rate of the part is obviously improved, single-set machining cycle is reduced by more than 100 hours, production efficiency is improved by 35%, and a solid foundation is laid for machining a part with a homogeneous structure on the turn-milling composite machining center.

Description

technical field [0001] The invention relates to the technical field of numerical control machining, in particular to a numerical control machining method for an aero-engine disc-shaft integrated structural part. Background technique [0002] The integrated structural part of the aero-engine disc and shaft is a complex structural part including dual structural features of the disc part and the journal part. The blank is a die forging, and the material is a difficult-to-machine titanium alloy. Deep cavity and thin radial plate structure engine disc, more than 30 precision holes with strict requirements on reference position and geometric accuracy, so the processing is extremely difficult. The wall thickness tolerance of the radial plate and the connection between the journal and the disc body is 0.05mm, the precision hole diameter tolerance is 0.015mm, the relative reference position is Φ0.05mm, the radial plate end surface and the inner hole are both 0.01mm relative to the re...

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Problems solved by technology

[0003] The purpose of this invention is to complete the processing of multiple parts such as the deep cavity between the journal of the part and the disc body, the inner hole of the disc web, the end surface of the disc, the outer circular profile and the precision hole in one clamping process, so as to solve the problem of Due to technical problems such as long processing cycle of parts, many toolings used, and low pass rate of parts, a NC machining method for aero-engine disc-shaft integral structure parts is specially provided.

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