【摘要】：微動疲勞損傷廣泛存在于各種連接結(jié)構(gòu)的緊密配合件中。據(jù)統(tǒng)計,在航空發(fā)動機中,榫連接結(jié)構(gòu)的破壞占發(fā)動機破壞率的17%以上,所以對航空發(fā)動機榫連接結(jié)構(gòu)進行微動疲勞性能研究具有重要意義。本文針對航空發(fā)動機壓氣機燕尾榫連接結(jié)構(gòu)的微動疲勞壽命進行研究,論文的主要內(nèi)容包括以下三個方面:首先,針對航空發(fā)動機壓氣機燕尾榫結(jié)構(gòu)的微動疲勞問題,對榫頭和榫槽分別為圓弧-平面和平面-平面兩種接觸形式的鈦合金模擬試驗件,進行了微動疲勞試驗。結(jié)果表明,微動疲勞壽命隨著疲勞載荷的增加而降低;圓弧-平面接觸形式榫連接結(jié)構(gòu)的微動疲勞壽命明顯高于平面-平面接觸形式結(jié)構(gòu);在試驗所選取的榫頭接觸面圓弧半徑分別為30mm、50mm和100mm的三種結(jié)構(gòu)中,圓弧半徑為30mm的燕尾榫結(jié)構(gòu)微動疲勞壽命最長。其次,使用損傷力學理論,通過對榫連接結(jié)構(gòu)的接觸有限元分析,基于Lemaitre提出的熱力學耗散余勢能模型,從鈦合金材料的基本特性入手,通過引入微動損傷區(qū)域局部塑性應變率進行修正,提出了適用于榫連接結(jié)構(gòu)的微動疲勞壽命預測模型,通過對平面-平面和3種平面-圓弧接觸形式的燕尾榫結(jié)構(gòu)微動疲勞壽命預測,所得預測結(jié)果與試驗壽命均在2倍誤差分散帶之內(nèi)。最后,利用本文建立的微動疲勞壽命預測模型,預測了不同榫頭圓弧半徑的圓弧-平面接觸形式榫連接結(jié)構(gòu)的微動疲勞壽命,分析結(jié)果表明,圓弧-平面接觸形式結(jié)構(gòu)中,榫頭接觸圓弧半徑在50~80mm之間時,微動疲勞壽命較長。
[Abstract]:Fretting fatigue damage is widely used in all kinds of close fit parts of joint structures. According to statistics, in aero-engine, the damage of tenon structure accounts for more than 17% of the engine failure rate, so it is of great significance to study the fretting fatigue performance of aero-engine tenon connection structure. In this paper, the fretting fatigue life of the joint structure of the tail tenon of the aero-engine compressor is studied. The main contents of this paper include the following three aspects: firstly, the fretting fatigue problem of the tenon structure of the aero-engine compressor is discussed. Fretting fatigue tests were carried out on titanium alloy simulation specimens with mortise and tenon grooves in arc plane and plane respectively. The results show that the fretting fatigue life decreases with the increase of the fatigue load, and the fretting fatigue life of the circular arc plane contact joint structure is obviously higher than that of the plane contact structure. The fretting fatigue life of dovetail tenon structure with arc radius of 30mm is the longest among the three structures whose arc radius is 30mm / 50mm and 100mm respectively. Secondly, using the damage mechanics theory, through the contact finite element analysis of the tenon joint structure, based on the thermodynamic dissipative potential energy model proposed by Lemaitre, starting with the basic characteristics of the titanium alloy material. By introducing the local plastic strain rate in the fretting damage region, a prediction model of fretting fatigue life for tenon joint structure is proposed. The fretting fatigue life of dovetail tenon structures with plane-plane and three plane-arc contact forms is predicted. The predicted results and test life are within the error dispersion band of 2 times. Finally, using the fretting fatigue life prediction model established in this paper, the fretting fatigue life of the circular arc plane contact joint structure with different mortise arc radius is predicted. The analysis results show that in the circular arc plane contact structure, When the contact arc radius of tenon is between 50~80mm, the fretting fatigue life is longer.
【學位授予單位】：南京航空航天大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：V231.9

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