發(fā)布時間：2018-08-03 06:41

【摘要】：葉片是航空發(fā)動機(jī)的核心部件之一,在實現(xiàn)發(fā)動機(jī)的能量轉(zhuǎn)換上有著重要作用。作為一類典型的薄壁結(jié)構(gòu)件,葉片在其加工中存在讓刀變形、切削顫振等問題,從而影響加工精度,縮短刀具使用壽命。為了適應(yīng)高溫高壓環(huán)境,渦輪燃燒室中的葉片材料多采用高溫合金。由于高溫合金的切削加工性較差,加上薄壁葉片曲面特征復(fù)雜、剛性差等特點,使得這類葉片的加工難度增大、加工質(zhì)量難以保證。本文以高溫合金薄壁葉片為研究對象,結(jié)合銑削試驗和有限元仿真,對GH2132靜子葉片的加工變形情況進(jìn)行了深入的研究,并提出了相應(yīng)的加工變形控制策略。論文主要研究工作如下:(1)通過正交試驗建立了高溫合金立銑削過程中兩種峰值切削力預(yù)測模型,(fz,ap,ae)模型和(hm,ap)模型;通過試驗驗證了預(yù)測模型的準(zhǔn)確性;通過單因素試驗研究了銑削參數(shù)對切削力的影響規(guī)律,為高溫合金的銑削參數(shù)優(yōu)選提供了依據(jù);通過MATLAB編程實現(xiàn)了切削用量的快速選擇。(2)基于峰值銑削力預(yù)測模型和試驗研究,建立了葉片加工變形有限元仿真模型,通過仿真計算得到了銑削參數(shù)和裝夾方式對葉片加工變形量的影響,結(jié)合工程力學(xué)理論分析驗證了仿真結(jié)果的合理性;對薄壁葉片型面進(jìn)行了銑削加工,驗證了參數(shù)優(yōu)選和裝夾方式優(yōu)化的有效性。(3)采用有限元法和輪廓法對高溫合金GH2132靜子葉片毛坯的初始?xì)堄鄳?yīng)力進(jìn)行了測量和評估,通過對比分析得到了葉片毛坯的應(yīng)力場分布,輪廓法測試結(jié)果與有限元計算結(jié)果表現(xiàn)出一定的一致性,運用有限元仿真研究了初始?xì)堄鄳?yīng)力對葉片銑削加工變形的影響。
[Abstract]:Blade is one of the core components of aero-engine, and plays an important role in the realization of engine energy conversion. As a kind of typical thin-walled structure, the blade has the problems of deforming the cutter and cutting chatter, which affects the machining accuracy and shortens the service life of the tool. In order to adapt to the high temperature and high pressure environment, the blade materials in the turbine combustor are mostly superalloy. Due to the poor machinability of the superalloy, the complicated surface features of thin-walled blade and the poor rigidity, the machining difficulty of this kind of blade is increased and the machining quality is difficult to guarantee. In this paper, the machining deformation of GH2132 stator blade is studied with milling test and finite element simulation, and the corresponding deformation control strategy is put forward. The main research work of this paper is as follows: (1) two kinds of peak cutting force prediction models, (fzapae) model and (hmap) model, are established by orthogonal test, and the accuracy of the prediction model is verified by experiments The influence of milling parameters on cutting force is studied by single factor test, which provides the basis for the optimization of milling parameters of superalloy, and realizes the rapid selection of cutting parameters by MATLAB programming. (2) based on the prediction model of peak milling force and experimental research, The finite element simulation model of blade machining deformation is established, and the influence of milling parameters and clamping mode on blade machining deformation is obtained by simulation calculation. The rationality of simulation results is verified by engineering mechanics theory analysis. The effectiveness of parameter optimization and clamping optimization is verified by milling thin-walled blade surface. (3) the initial residual stress of GH2132 stator blade blank is measured and evaluated by finite element method and contour method. The stress field distribution of blade blank is obtained by contrast analysis. The results of contour method and finite element method show some agreement. The effect of initial residual stress on blade milling deformation is studied by finite element simulation.
【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】：2016
【分類號】：TG54

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