CN103659276A - Method for numerical control machining of titanium alloy part with deep groove structure - Google Patents

Abstract

The invention discloses a method for numerical control machining of a titanium alloy part with a deep groove structure. The method comprises the steps that a U-shaped drill or a drill bit is used for drilling a corner of a groove cavity of the part, wherein the diameter of the U-shaped drill or the drill bit is equal to that of the corner; a large-diameter bottoming drill is used, the deep groove portion of the part is machined in a drilling mode according to a fixed step pitch between cutters, and a large number of metal materials of the groove cavity are removed; the side wall of a deep groove is machined along the side wall of the deep groove for a circle. According to the method for numerical control machining of the titanium alloy part with the deep groove structure, cutting with small cutting force in the process of machining the parts is achieved, the vibration amplitude can be reduced, the high metal removal rate can be obtained, and high-efficiency precise numerical control machining is achieved.

Description

A kind of to thering is the numerical-control processing method of deep groove structure titanium alloy component

Technical field

The present invention relates to Computerized Numerical Control processing technology field, particularly about thering is the Computerized Numerical Control processing technology of the Titanium Alloy Aircraft part of deep groove structure.

Background technology

The part with deep groove structure is a kind of typical structure in airplane parts, common deep trouth definition is that the cutter draw ratio (outstanding length and the diameter proportion of cutter) that this vallecular cavity of processing need to be used reaches vallecular cavity more than 5:1, the airplane parts of deep groove structure mostly was aluminum alloy materials in the past, but in recent years, due to the designing requirement of performance intensity, the airplane parts of increasing deep groove structure uses titanium alloy material.

For the processing with deep groove structure titanium alloy airplane parts, traditional mode is to adopt layer to fall formula processing mode, the upper surface from vallecular cavity is in layer machined to vallecular cavity bottom, geometric properties due to deep trouth, adopt this traditional processing mode, need to select the cutter that draw ratio is very large, cutter rigidity is very poor, while is due to the processing characteristics of titanium alloy material itself, the cutting force that in working angles, cutter bears is very large, cause often generation cutter vibration in process, the situations such as cutter relieving even ruptures, the parts size precision processing also cannot guarantee, therefore, the feed speed of generally using in the process of this type of deep groove structure titanium alloy component is very low, cutting output is very little, cause the difficulty of processing of this type of deep groove structure titanium alloy component very large, working (machining) efficiency is extremely low.

Summary of the invention

The object of the invention is to disclose a kind of numerical-control processing method of deep groove structure titanium alloy component.The method, for the processing of deep groove structure titanium alloy component provides new approaches, has realized low cutting force cutting in this type of part process, and can reduce vibration trend and obtain very high metal removal rate, has reached numerical control efficient Precision Machining.

A numerical-control processing method with deep groove structure titanium alloy component, is characterized in that:

1) first, in the vallecular cavity corner of part, use the U identical with corner diameter to bore or drill bit, the corner drilling of part vallecular cavity is completed;

2) secondly, adopt cutter draw ratio to be less than the major diameter bottoming drill of 5:1, according to being greater than step pitch between 75% dead knife of tool diameter, with the mode processing parts deep trouth part of drilling, remove a large amount of metal material of vallecular cavity;

3) last, adopt cutter draw ratio to be less than the long sword milling cutter of 5:1, along the sidewall of deep trouth one week, the sidewall of deep trouth is machined.

Beneficial effect of the present invention is, in process, avoided the not enough problem of cutter rigidity of using the very large cutter of draw ratio to cause, overcome low, the ropy defect of conventional machining mode efficiency of deep groove structure titanium alloy component, with drilling, replace traditional milling, can obtain very high metal removal rate.

Below in conjunction with example figure, this application is described in further detail.

Accompanying drawing explanation

Fig. 1 part corner drilling machining sketch chart

Fig. 2 part deep trouth drilling processing tool track machining sketch chart

Fig. 3 part sidewall processing tool track schematic diagram

Fig. 4 part final structure schematic diagram

Number description: step pitch, 6 long sword milling cutters, 7 long sword milling cutter tool tracks between 1 part, 2 corners, 3U brill, 4 bottoming drills, 5 cuttves

The specific embodiment

The present embodiment is for having the processing of deep groove structure part 1 on certain aircraft, part noumenon material is TC21 difficult-to-machine material, in structure, there is deep trouth, degree of depth 205mm, corner R 10mm, if use traditional handicraft processing parts, working (machining) efficiency is extremely low, and adopt new method processing parts, can avoid above problem completely.The method is specific as follows:

1) first, at four corner 2 places of part 1 vallecular cavity, use the U of the D20mm identical with corner diameter to bore 3, four corner drillings of vallecular cavity are completed.

2) secondly, adopt the bottoming drill 4(cutter draw ratio of outstanding long 210mm, diameter D55mm to be less than 5:1), by between fixing cutter between step pitch 42mm(cutter step pitch be greater than tool diameter 75%), between cutter, step pitch 5 refers to the distance between adjacent machining locus center cutter, as shown in Figure 2, drilling processing parts deep trouth, removes a large amount of metal material of vallecular cavity.

3) last, adopt outstanding long 206mm, the long sword milling cutter of diameter D42mm 6(cutter draw ratio to be less than 5:1), along the part sidewall cutter track track 7 of a week, deep trouth sidewall is machined.

After application the present invention, the problems such as the cutter that quivers of having avoided using the very large cutter of draw ratio to cause in the whole NC Machining Process of part 1, cutter relieving, working (machining) efficiency has improved three times than traditional approach simultaneously, has realized the processing of deep groove structure titanium alloy component numerical control efficient.

Claims (1)

1. a numerical-control processing method with deep groove structure titanium alloy component, is characterized in that:

1) first, in the vallecular cavity corner of part, use the U identical with corner diameter to bore or drill bit, the corner drilling of part vallecular cavity is completed;

2) secondly, adopt cutter draw ratio to be less than the major diameter bottoming drill of 5:1, according to being greater than step pitch between 75% dead knife of tool diameter, with the mode processing parts deep trouth part of drilling, remove a large amount of metal material of vallecular cavity;

3) last, adopt cutter draw ratio to be less than the long sword milling cutter of 5:1, along the sidewall of deep trouth one week, the sidewall of deep trouth is machined.

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