【摘要】：為滿足現(xiàn)代航空航天產(chǎn)品高強(qiáng)度、高耐熱性和結(jié)構(gòu)緊湊等要求,鑄造鈦合金整體結(jié)構(gòu)件在此類產(chǎn)品上的應(yīng)用越來越廣泛。然而,此類零件在機(jī)加工過程中容易產(chǎn)生讓刀現(xiàn)象,鈦合金的難加工性會使刀具磨損加快,材料的去除使結(jié)構(gòu)件應(yīng)力重分布,這些因素都會導(dǎo)致結(jié)構(gòu)件產(chǎn)生較大的加工變形。本文以ZTC4鑄造鈦合金整體結(jié)構(gòu)件為研究對象,采用實(shí)驗(yàn)和有限元仿真相結(jié)合的方法,研究了退火及應(yīng)力重分布、切削載荷、刀具磨損等因素對結(jié)構(gòu)件加工變形的影響,并提出了變形控制策略。完成的主要工作如下:1.通過單因素實(shí)驗(yàn)研究了各切削參數(shù)對切削力、切削溫度的影響規(guī)律,并建立了經(jīng)驗(yàn)公式。利用正交試驗(yàn)研究了刀具磨損與切削速度、每齒進(jìn)給量、切削寬度的關(guān)系,指出在研究參數(shù)范圍內(nèi),每齒進(jìn)給量對刀具后刀面磨損影響最為明顯,建立了后刀面磨損量與切削用量和時(shí)間的經(jīng)驗(yàn)公式。2.利用有限元仿真和實(shí)驗(yàn)相結(jié)合的方法,研究了圓盤零件的退火熱處理過程,建立了ZTC4鈦合金退火熱處理的有限元仿真模型�；谠撃Ｐ�,研究了結(jié)構(gòu)件的退火熱處理過程并建立了其初始應(yīng)力場。3.基于有限元仿真,分別研究了退火及應(yīng)力釋放、切削載荷、刀具磨損對加工變形的影響規(guī)律,并耦合上述因素獲得了結(jié)構(gòu)件變形的預(yù)測值;利用三坐標(biāo)測量機(jī)測量實(shí)際加工結(jié)構(gòu)件最終變形量,對比仿真結(jié)果,驗(yàn)證了有限元模型的準(zhǔn)確性。利用遺傳算法進(jìn)行了加工參數(shù)的優(yōu)化,提出了刀具補(bǔ)償?shù)姆椒▉頊p小加工變形,通過有限元仿真,驗(yàn)證了優(yōu)化后的參數(shù)和補(bǔ)償后的路徑確實(shí)能控制變形。
[Abstract]:In order to meet the requirements of modern aerospace products such as high strength, high heat resistance and compact structure, cast titanium alloy integral structural parts are more and more widely used in this kind of products. However, this kind of part is easy to produce the phenomenon of turning tool in the process of machining, the difficult machinability of titanium alloy will speed up the wear of the tool, and the removal of material will cause the stress distribution of the structural part to redistribute, all these factors will lead to the larger machining deformation of the structural part. In this paper, the effects of annealing and stress redistribution, cutting load and tool wear on the machining deformation of ZTC4 cast titanium alloy monolithic structure are studied by means of the combination of experiment and finite element simulation. The deformation control strategy is also proposed. The main work accomplished is as follows: 1. The influence of cutting parameters on cutting force and cutting temperature was studied by single factor experiment, and the empirical formula was established. The relationship between tool wear and cutting speed, feed per tooth and cutting width is studied by orthogonal test. It is pointed out that the influence of feed per tooth on tool surface wear is the most obvious in the range of research parameters. An empirical formula for the amount of wear on the rear tool surface and the cutting parameters and time is established. 2. The annealing heat treatment process of disk parts was studied by means of finite element simulation and experiment, and the finite element simulation model of ZTC4 titanium alloy annealing heat treatment was established. Based on this model, the annealing heat treatment process of structural parts is studied and the initial stress field is established. Based on finite element simulation, the effects of annealing and stress release, cutting load and tool wear on machining deformation are studied, and the predicted deformation values of structural parts are obtained by coupling the above factors. The accuracy of the finite element model is verified by measuring the final deformation of the actual machined structural parts by using the CMM and comparing the simulation results with the simulation results. The genetic algorithm is used to optimize the machining parameters, and a tool compensation method is proposed to reduce the machining deformation. The finite element simulation shows that the optimized parameters and the compensated path can control the deformation.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V261.23

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