Machining method of the half case of the compressor of the aero-engine

Abstract

The invention discloses a method for machining half-and-half casings of a gas compressor of an aero-engine. The method comprises the following steps that a, flatness processing is carried out on the longitudinal faying surfaces of the two half-and-half casings, wherein plane processing is carried out on the two half-and-half casings after rough machining in a mode that the base levels abut against each other so as to ensure the flatness of the longitudinal faying surfaces of the two half-and-half casings; b, the mutual location degree processing is carried out on corresponding screw installation holes in the longitudinal faying surfaces of the two half-and-half casings, wherein finish machining is carried out on at least part of screw installation holes which are correspondingly formed, and screws provided with locating cylindrical surfaces are arranged in the screw installation holes after the finish machining in a matched mode; c, the screws are assembled in the screw installation holes of the longitudinal faying surfaces of the two half-and-half casings according to the preset optimized assembly sequence; d, the two half-and-half casings form an integrated casing of the gas compressor. The method for machining the half-and-half casings of the gas compressor of the aero-engine adopts the half-and-half casing combined deformation control technology, combined deformation of the half-and-half casings is eliminated, the accuracy of consistency of repeated combination is good, and the application prospects are wide.

Description

technical field [0001] The invention relates to the technical field of aero-engine processing, in particular to a method for processing a half casing of a compressor of an aero-engine. Background technique [0002] The compressor part of the aero-engine widely adopts the half casing (or called the half casing), which is composed of two half-ring left and right half casings combined with precision positioning screws through the screw holes on the longitudinal bonding surface. The diameter, roundness and coaxiality of the assembled front and rear flanges have very high requirements. Due to the poor rigidity of the two halves of the casing, it is easy to deform during processing, and the longitudinal bonding surface of the two casing halves is prone to warping and deformation; it is difficult to ensure that the position of the precision hole on the longitudinal bonding surface is ≤Φ0.02mm. The mutual position of the holes is poor. These factors lead to the easy deformation of ...

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a method for processing the half casing of the compressor of an aero-engine, so as to solve the technical problems that it is difficult to ensure the position of the precision hole on the longitudinal bonding surface, it is easy to deform after combination, and the accuracy of repeated combination is poor.

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