本文選題：風(fēng)電行星架 + 微動疲勞��； 參考：《大連理工大學(xué)》2012年碩士論文

【摘要】：微動疲勞經(jīng)常發(fā)生在伴有相對微小滑動的接觸構(gòu)件中,在工程實際中很常見,我們通常所見的螺栓連接、鉚接以及過盈連接等,在相互接觸表面都很容易發(fā)生微動,從而導(dǎo)致微動疲勞破壞,微動疲勞會大大降低零部件的使用壽命,因此在進行設(shè)計時必須要高度注意。 風(fēng)力發(fā)電行星架與法蘭的連接結(jié)構(gòu),設(shè)計時采用了過盈連接,經(jīng)有限元分析在過盈配合的接觸面兩端產(chǎn)生了微動滑移,為了確保行星架的使用壽命,需要對行星架和法蘭的過盈連接處進行微動疲勞分析并計算微動疲勞壽命。首先通過均勻試驗的方法對原始載荷譜進行篩選,得到能夠使行星架產(chǎn)生滑移的載荷,經(jīng)過有限元計算后,根據(jù)接觸表面一周的應(yīng)力分布確定最危險截面。然后根據(jù)接觸界面端的奇異應(yīng)力場中心路徑的應(yīng)力分布情況通過應(yīng)力奇異性參數(shù)來判定裂紋的萌生。分析微動疲勞破壞的機理,選擇最危險的載荷加載順序。最后計算微動磨損量并對有限元模型進行修正,建立分步施加磨損量與直接施加最大磨損量兩種修正模型,分別得到接觸界面的接觸應(yīng)力和切向應(yīng)力分布,繼而求得應(yīng)力強度因子變化范圍,并將其與材料的臨界應(yīng)力強度因子變化范圍進行比較來判斷裂紋的擴展情況。比較兩種不同施加磨損量的計算結(jié)果,得到實際載荷作用下的疲勞裂紋擴展情況。 結(jié)果表面：在實際載荷以最危險的加載順序加載情況下,分步施加磨損與直接施加最大磨損情況下裂紋分別擴展至279μm和300.4μm后都將停止擴展,直接施加磨損的計算結(jié)果裂紋長度較長,用這種方法計算的結(jié)果偏于保守。最終計算得到的結(jié)果顯示,行星架的微動疲勞壽命滿足設(shè)計要求。
[Abstract]:Fretting fatigue often occurs in contact members with relatively minor slippage. It is very common in engineering practice. We usually see bolt connections, rivets, interference joints, etc., which are easily fretted on contact surfaces. This will lead to fretting fatigue failure, fretting fatigue will greatly reduce the service life of parts, so we must pay close attention to the design. In order to ensure the service life of the planetary frame, the contact structure between the planetary frame and the flange of wind power generation is designed with interference fit, and the finite element analysis results in the fretting slippage at the two ends of the contact surface of the interference fit, so as to ensure the service life of the planetary frame. Fretting fatigue analysis and calculation of fretting fatigue life are needed for the interference joint of planetary frame and flange. First, the original load spectrum is screened by uniform test method, and the load which can make the planetary frame slip is obtained. After finite element calculation, the most dangerous section is determined according to the stress distribution of one week on the contact surface. Then according to the stress distribution of the central path of the singular stress field at the contact interface, the crack initiation is determined by the stress singularity parameter. The mechanism of fretting fatigue failure is analyzed and the most dangerous loading sequence is chosen. Finally, the fretting wear amount is calculated and the finite element model is modified, and two kinds of modified models are established. The contact stress and the tangential stress distribution of the contact interface are obtained, respectively, when the wear amount is applied step by step and the maximum wear quantity is applied directly. Then the range of stress intensity factor is obtained and compared with the variation range of critical stress intensity factor of material to judge the crack propagation. The fatigue crack propagation under actual load is obtained by comparing the calculated results of two different wear amounts. Results Surface: when the actual load is loaded in the most dangerous loading sequence, the crack growth will stop when the crack expands to 279 渭 m and 300.4 渭 m respectively when the wear is applied step by step and the maximum wear is applied directly. The crack length is longer when wear is applied directly, and the results obtained by this method are conservative. The calculated results show that the fretting fatigue life of the planetary frame meets the design requirements.
【學(xué)位授予單位】：大連理工大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2012
【分類號】：TH123.3

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本文編號：2093552