本文關(guān)鍵詞： 渦輪軸 有限元分析 疲勞壽命 壽命試驗　出處：《電子科技大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

【摘要】：航空發(fā)動機作為飛機重要的動力裝置,其工作狀態(tài)的穩(wěn)定性及可靠性直接影響到飛機的正常使用。其中,航空發(fā)動機主軸主要包括風(fēng)扇軸、低壓渦輪軸和高壓渦輪軸等,承擔(dān)著連接發(fā)動機周圍零部件和傳遞循環(huán)工作載荷的作用。在工作狀態(tài)下,渦輪軸長期處在高溫環(huán)境中,并隨飛行狀態(tài)的變化不斷承受高、低周疲勞載荷復(fù)合作用。渦輪軸傳遞載荷最大,工作環(huán)境較為惡劣,極易發(fā)生疲勞失效。因此,渦輪軸的疲勞壽命將直接影響航空發(fā)動機的正常使用,一旦發(fā)生疲勞失效將引起重大事故。為了提高發(fā)動機工作的安全性及使用壽命,給予發(fā)動機渦輪軸有關(guān)維修及更換提供指導(dǎo)意見,航空發(fā)動機渦輪軸的疲勞可靠性問題受到廣泛關(guān)注和研究。本文結(jié)合國內(nèi)外航空發(fā)動機主軸疲勞壽命研究現(xiàn)狀,對某型渦扇航空發(fā)動機渦輪軸的疲勞壽命問題進行研究。本文研究內(nèi)容主要包含以下幾個部分:首先,根據(jù)航空發(fā)動機渦輪軸的工作原理、結(jié)構(gòu)及裝配情況,確定渦輪軸的約束情況和外部高、低周疲勞載荷的類型及計算方法,如軸向力、扭矩和彎矩等。根據(jù)飛機飛行狀態(tài)確定需要分析的工作任務(wù)剖面,并得到對應(yīng)工作條件下的外部載荷值及載荷施加位置。結(jié)合ANSYS Workbench有限元軟件,建立并簡化渦輪軸的有限元模型,然后確定恰當(dāng)?shù)牟牧陷斎肽Ｐ图斑吔鐥l件,模擬渦輪軸的實際工作狀態(tài),分別完成渦輪軸在低周疲勞載荷和高低周疲勞載荷復(fù)合下的有限元分析,計算分析得到渦輪軸危險部位及其應(yīng)力應(yīng)變分布情況。其次,考慮到外部載荷對渦輪軸疲勞壽命的影響,結(jié)合國內(nèi)外航空發(fā)動機主軸疲勞壽命預(yù)測方法研究現(xiàn)狀,分別研究了基于局部應(yīng)力應(yīng)變法的高、低周疲勞壽命預(yù)測模型,基于臨界面法的高、低周疲勞壽命預(yù)測模型,以及線性疲勞累積損傷原理。然后結(jié)合有限元分析結(jié)果,利用上述方法分別完成渦輪軸危險部位的高、低周疲勞壽命預(yù)測,并對預(yù)測計算結(jié)果進行了對比分析。最后,為驗證渦輪軸疲勞壽命預(yù)測結(jié)果的準(zhǔn)確性,研究了渦輪軸疲勞壽命試驗載荷的確定方法以及具體試驗實施方案。根據(jù)疲勞試驗條件和要求,對渦輪軸進行有限元分析,并計算渦輪軸危險部位的疲勞壽命,以此驗證疲勞試驗設(shè)計的準(zhǔn)確性。
[Abstract]:The stability and reliability of aeroengine, as an important power device of aircraft, have a direct impact on the normal use of aircraft. Among them, the main axis of aeroengine mainly includes fan shaft. The low-pressure turbine shaft and the high-pressure turbine shaft bear the function of connecting the parts around the engine and transferring the cyclic working load. In the working state, the turbine shaft is in the high temperature environment for a long time. With the change of flight state, the turbine shaft is subjected to high and low cycle fatigue loading. The turbine shaft has the largest transfer load, and the working environment is relatively bad, so fatigue failure is easy to occur. The fatigue life of turbine shaft will directly affect the normal use of aero-engine, once the fatigue failure will cause serious accidents, in order to improve the safety and service life of the engine. Provide guidance on maintenance and replacement of engine turbine shafts. The fatigue reliability of aeroengine turbine shafts has received extensive attention and research. In this paper, the research status of fatigue life of aeroengine spindle at home and abroad is considered. The fatigue life of turbine shaft of a turbofan aero-engine is studied. The main contents of this paper are as follows: firstly, according to the working principle, structure and assembly of turbine shaft of aero-engine. Determine the constraints of the turbine shaft and the external high and low cycle fatigue load types and calculation methods, such as axial force, torque and bending moment, etc. According to the flight status of the aircraft to determine the work mission profile to be analyzed. The external load value and load applied position under the corresponding working conditions are obtained, and the finite element model of turbine shaft is established and simplified with ANSYS Workbench finite element software. Then the proper material input model and boundary conditions are determined to simulate the actual working state of turbine shaft and the finite element analysis of turbine shaft under low cycle fatigue load and high and low cycle fatigue load is completed respectively. The dangerous part of turbine shaft and its stress-strain distribution are obtained by calculation and analysis. Secondly, the influence of external load on fatigue life of turbine shaft is considered. Combined with the current research situation of fatigue life prediction method for aeroengine spindle at home and abroad, high and low cycle fatigue life prediction models based on local stress-strain method and high fatigue life prediction model based on critical plane method are studied respectively. The prediction model of low cycle fatigue life and the principle of linear fatigue cumulative damage are used to predict the high and low cycle fatigue life of turbine shaft respectively. The prediction results are compared and analyzed. Finally, to verify the accuracy of the prediction results of turbine shaft fatigue life. According to the fatigue test conditions and requirements, the finite element analysis of turbine shaft is carried out, and the fatigue life of turbine shaft is calculated. The accuracy of fatigue test design is verified.
【學(xué)位授予單位】：電子科技大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V235.13

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