摘要
研究了钛合金压气机叶片在大幅值低频主循环上迭加高频小幅值振动后的影响．试验研究是用预制裂纹的压气机叶片作为试件在室温下进行．低循环载荷是采用液压伺服机构加以拉应力来完成．由直流马达带动一曲柄联杆机构以１００～１５０Ｈｚ的频率对叶片试件施加以交变弯矩迫使它弯曲振动．试验结果表明：线性迭加法对压气机叶片疲劳寿命预测是有效的，并且高循环的频率及高循环的幅值变化对叶片裂纹扩展的影响十分显著．
The influence of ralatively high frequency low amplitude vibrations superimposed on higher amplitude low frequency mojor cycles is studied for titanium alloy(TC-11) compressor blade.Experimental studies are conducted in room temperature using precracked compressor blades as test specimens The low cycle load is carried out by servo hydraulic unit with tensile stress.A crankshaft-connecting rod mechanism drived by a D.C.motor provides an alternating bending moment on the blade specimen at frequencies of 100～150 Hz,which forces the blade specimen in bending vibration. Experimental result shows that the linear summation method is effective on fatigue life prediction for compressor blade,and the frequency of high cycles as well as the variation in the high cycle amplitude are expected to influence the crack growth of blade significantly.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
1996年第1期33-38,共6页
Journal of Beijing University of Aeronautics and Astronautics
