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TC21鈦合金板孔冷擠壓殘余應(yīng)力與疲勞性能研究
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南京航空航天大學(xué),南京航空航天大學(xué),南京航空航天大學(xué),南京航空航天大學(xué),成都飛機工業(yè)(集團)有限責(zé)任公司

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TG376

基金項目:

國家商用飛機制造工程技術(shù)研究中心創(chuàng)新基金（No. SAMC12-JS-15-021）；江蘇省普通高校研究生科研創(chuàng)新計劃資助項目（No. CXLX12_0137）


Investigation on Residual Stress and Fatigue Properties of the Cold Hole Expansion Process in Titanium Alloy TC21 Plates
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Nanjing University of Aeronautics and Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing University of Aeronautics and Astronautics,Chengdu Aircraft Industrial Corporation

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    摘要:

    針對飛機后機身框TC21損傷容限鈦合金帶孔零件在服役過程中易過早產(chǎn)生疲勞裂紋的問題，采用開縫襯套冷擠壓強化工藝進行了不同擠壓量下的孔強化試驗，并對擠壓強化后的試樣進行疲勞試驗研究，得到了擠壓量對TC21鈦合金疲勞增益的影響規(guī)律。通過有限元仿真的方法研究了擠后孔邊殘余應(yīng)力分布規(guī)律，從宏觀和微觀兩方面觀察和分析了不同擠壓量下的疲勞斷口形貌，探討了冷擠壓對孔邊疲勞裂紋的萌生和擴展的影響，揭示了疲勞增益機理。研究結(jié)果表明，冷擠壓強化后的孔邊存在明顯的切向壓縮殘余應(yīng)力，改變了孔邊裂紋萌生位置，延長了交變載荷作用下的疲勞裂紋擴展壽命，疲勞壽命隨著擠壓量的增大而明顯提高，擠后試樣疲勞壽命均提高50%以上。

    Abstract:

    The perforated parts of damage tolerant titanium alloy TC21 in rear fuselage frame were easy to prematurely suffer fatigue crack in the service process. With the purpose of resolving the problem mentioned above, different expansion degrees were applied to the hole of plate specimens of TC21 in the split sleeve cold expansion experiment。The effect of expansion degree to fatigue life was achieved in the fatigue tests. By the method of 3D finite element simulation, the distribution regularity of residual stress was obtained around the hole after cold expansion. The surface feature of fatigue fracture has been observed and analyzed from macroscopic aspect and microscopic aspect with different expansion degree. The examination of fractured sections show that cold expansion can change fatigue crack initiation position around the hole surface, and extend the fatigue crack propagation life under cyclic loading. It was further show that fatigue life increase as expansion degree, furthermore, the fatigue life is increased more than 50%.

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葛恩德,傅玉燦,蘇宏華,徐九華,陳雪梅. TC21鈦合金板孔冷擠壓殘余應(yīng)力與疲勞性能研究[J].稀有金屬材料與工程,2016,45(5):1189~1195.[Ge Ende, Fu Yucan, Su Honghua, Xu Jiuhua, Chen Xuemei. Investigation on Residual Stress and Fatigue Properties of the Cold Hole Expansion Process in Titanium Alloy TC21 Plates[J]. Rare Metal Materials and Engineering,2016,45(5):1189~1195.]
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  • 收稿日期:2014-05-13
  • 最后修改日期:2014-06-06
  • 錄用日期:2014-07-01
  • 在線發(fā)布日期: 2016-06-02
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