Machining method of aircraft engine crankcast

An aero-engine and processing method technology, applied in the field of casing processing, can solve problems such as low processing accuracy, long manufacturing cycle, and high processing difficulty, and achieve the effects of high processing efficiency, convenient processing, and improved processing accuracy

Active Publication Date: 2019-11-26
无锡航亚科技股份有限公司
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AI Technical Summary

Problems solved by technology

[0005] Aiming at the technical problems of large casing deformation, low processing precision, long manufacturing cycle and high processing difficulty in the existing casing processing method, the present invention provides a processing method of an aero-engine casing, which has small casing deformation and high processing precision , high efficiency and easy processing

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  • Machining method of aircraft engine crankcast
  • Machining method of aircraft engine crankcast
  • Machining method of aircraft engine crankcast

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Embodiment Construction

[0057] See Figure 1 to Figure 20 , the processing method of a kind of aero-engine casing of the present invention, it comprises the following steps:

[0058] Step 1. Blank size re-inspection: measure the size of the ring blank to ensure that there is a margin on each processing surface, check the surface quality of the blank, and there should be no forging defects such as slag inclusions, cracks, and defects. The structure of the blank is as follows: figure 2 as shown, figure 2 The shape of the internal parts of the hatching represents the shape of the finished casing;

[0059] Step 2. Rough turning of big end and small end: On the CNC lathe, support one end face of the blank, position the outer circle of the blank, rough turn the big end, remove most of the machining allowance of the big end of the blank, and process the inner hole of the big end Reserve a process boss 9, such as image 3 It is shown in the part of the bold line in the middle; then support the large end...

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Abstract

The invention provides a machining method of an aircraft engine crankcast. The machining method can solve the problems that when an existing crankcast machining method is used, crankcast deformation is large, machining precision is low, the manufacturing period is long, and the machining difficulty is large. The method comprises the following steps of blank dimension re-inspection, rough turning of a large end and a small end, rough milling of shape contour, stress relief heat treatment, trimming of a large end datum and a small end datum, finish milling of two side faces of a longitudinal installing side and longitudinal installing side holes, segmentation, grinding and trimming of wire-electrode cut end faces, pre-assembling, semi finish turning of the large end and the small end, drilling of angular locating holes, semi finish milling of the shape, finish turning of the small end, finish milling of the shape and a small end installing side hole, finish reaming of the longitudinal installing side holes, finish turning of the large end, finish milling of a large end installing side hole, thread tapping, laser marking, dying check, fluorescence penetrant inspection and final inspection.

Description

technical field [0001] The invention relates to the field of casing processing, in particular to a processing method for an aero-engine casing. Background technique [0002] There are many casings on the new generation of aero-engines, such as inlet casings, external casings, fan casings, compressor casings, combustion chamber casings, turbine casings, etc., and their metallurgy, manufacturing quality and performance levels are very important for The improvement of the reliability, safety, life and performance of the engine has a decisive impact. [0003] Aeroengine casings are mostly made of materials such as superalloys and titanium alloys. figure 1 It is an aero-engine casing made of high-temperature alloy material. It has a thin-walled ring structure. One end has a small diameter, called the small end, and the other end has a larger diameter, called the big end. The end faces of the small end and the big end are called respectively. It is the small end datum and the bi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P15/00
CPCB23P15/00
Inventor 王颖囡余岩赵朝刚
Owner 无锡航亚科技股份有限公司
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