%0 Journal Article %T 转子裂纹对叶尖间隙动态变化规律的影响<br>The Influence of Rotor Crack on Dynamic Changes Rule of Turbine Tip Clearance %A 贾丙辉 %A 冯勇 %A 闫国栋 %A 张杰 %J 振动.测试与诊断 %D 2016 %R 10.16450/j.cnki.issn.1004-6801.2016.06.019 %X 为指导叶尖间隙的动态测量和主动控制,建立了航空发动起涡轮转子缩减模型,在考虑转子部件所受热应力、离心力基础上,重点考虑了不同深度的裂纹发生在叶片和转子盘不同位置时对叶尖间隙的影响。结果表明:叶尖间隙变化范围随裂纹深度变大而变大;保持裂纹深度与叶片宽度比为0.5,分别取裂纹距离叶尖0.005,0.025和0.04 m时,叶尖间隙变化范围较正常工况下最大偏移量分别为0.11,0.38和0.9mm;裂纹位于叶根时叶尖间隙的变化范围较均匀应力作用下叶尖间隙变化范围明显增大,且在发动机加、减速过程中的叶尖轨迹呈现明显不对称现象。<br>In order to guide tip clearance dynamic measurement and active control, a model of the turbine rotor of an air engine was built, and the effects of cracks of different depths and locations in the blade or disk were investigated, considering the thermal stress and centrifugal force of the rotor. The results show that the variation range of tip clearance increases with crack depth: the range increased by 0.11, 0.38 and 0.9 mm compared to the normal condition when the distance of crack to blade tip was 0.005, 0.025 and 0.04 m, respectively, with the ratio of the crack’s depth to width maintained at 0.5. Meanwhile, when the crack occurred at the blade root, the tip clearance variation range significantly increased compared with the effect of uniform stress, and the tip locus was greatly dissymmetric during the period of engine acceleration and deceleration. %K 叶尖间隙 %K 航空发动机 %K 转子裂纹 %K 动态模型< %K br> %K blade tip clearance %K aero-engine %K crack rotor %K dynamic model %U http://zdcs.nuaa.edu.cn/ch/reader/view_abstract.aspx?file_no=201606019&flag=1