某燃气轮机压气机叶片振动特性研究
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摘要
针对某燃气轮机压气机叶片断裂故障,通过理论计算和试验方法,对故障级叶片在与轮盘耦合条件下的振动特性进行了研究分析。理论计算叶片动频时考虑了旋转离心力和温度载荷的影响,利用有限元计算程序ANSYS WORKBENCH循环对称分析功能和接触分析功能,完成了压气机叶片振动分析,通过坎贝尔图得到叶片1阶弯曲共振转速为6 900 r/min。随后,在整机状态下,利用非接触式微波测量方法,对该级动叶进行了振动测试,获得的叶片1阶弯曲共振转速为6 988 r/min,实测得到的共振转速与理论计算结果吻合,为故障的进一步排查提供有利的理论和试验依据。
For the failure of the compressor blade in a gas turbine,the vibration analysis of the compressor blade under disc coupled structure is performed through theoretical calculation and experimental.Through the use of the cyclic symmetry function and the contact function of the ANSYS WORKBENCH,a computational analysis on vibration of the blade disc in low compressor has been conducted.During the calculation,the effect has been taken into account of the rotating centrifugal force and temperature-dependent material parameters on the dynamic frequency characteristic of the blade.The resonance rotational speed obtained by Campbell diagram is 6 900 r/min.Then,vibration testing on the failed rotor blade under the whole gas turbine running has been completed by using non-contact microwave method.The resonance rotational speed obtained through the method is 6 988 r/min.The results show that the obtained harmonic resonance rotational speed is found to be in agreement with the theoretical calculation results,providing useful foundation for further failure analysis.
For the failure of the compressor blade in a gas turbine,the vibration analysis of the compressor blade under disc coupled structure is performed through theoretical calculation and experimental.Through the use of the cyclic symmetry function and the contact function of the ANSYS WORKBENCH,a computational analysis on vibration of the blade disc in low compressor has been conducted.During the calculation,the effect has been taken into account of the rotating centrifugal force and temperature-dependent material parameters on the dynamic frequency characteristic of the blade.The resonance rotational speed obtained by Campbell diagram is 6 900 r/min.Then,vibration testing on the failed rotor blade under the whole gas turbine running has been completed by using non-contact microwave method.The resonance rotational speed obtained through the method is 6 988 r/min.The results show that the obtained harmonic resonance rotational speed is found to be in agreement with the theoretical calculation results,providing useful foundation for further failure analysis.
引文
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[14] 李其汉,王延荣.航空发动机结构强度设计问题[M].上海:上海交通大学出版社,2014.LI Qi-han,WANG Yan-rong.The design problem of aero-engine structure strength[M].Shanghai:Shanghai Jiao Tong University Press,2014.
[15] 刘江,葛永庆,安连锁,等.高速旋转叶片振动非接触测量的研究[J].振动与冲击,2006,25(8):1077-1079.LIU Jiang,GE Yong-qing,AN Lian-suo,et al.Study of non-contact monitoring for high-speed rotating blade vibration[J].Journal of Vibration and Shock ,2006,25(8):1077-1079.
[2] 黄海鹰,王建明.新型高推比涡轮风扇发动机盘片耦合振动分析[J].北京航空航天大学学报,1994,20(2):169-173.HUANG Hai-ying,WANG Jian-ming.Modal analysis of disc-blade coupling system of a turbofan aeroengine[J].Journal of Beijing University of Aeronautics and Astronautics,1994,20(2):169-173.
[3] 周传月,邹经湘,闻雪友,等.燃气轮机叶片-轮盘耦合振动特性计算[J].航空学报,2000,21(6):545-547.ZHOU Chuan-yue,ZOU Jing-xiang,WEN Xue-you,et al.Calculation of the blade disc coupled vibration characteristics of gas turbine[J].Acta Aeronautica Et Astronautica Sinica.2000,21(6):545-547.
[4] 王春洁,宋顺广,宗晓.压气机叶片轮盘耦合结构振动分析[J].航空动力学报,2007,22(7):1065-1068.WANG Chun-jie,SONG Shun-guang,ZONG Xiao.Vibration analysis of the blade disc coupled structure of compressor[J].Journal of Aerospace Power,2007,22(7):1065-1068.
[5] 李其汉,胡碧刚,徐志怀.航空发动机强度振动测试技术[M].北京:北京航空航天大学出版社,1995.LI Qi-han,HU Bi-gang,XU Zhi-huai.Aeroengine vibration testing technology [M].Beijing: Beihang University Publishing House,1995.
[6] 胡伟,王德友,杜少辉,等.非接触式数字光纤叶片测振系统的研究及应用[J].航空发动机,2010,36(1):38-41.HU Wei,WANG De-you,DU Shao-hui,et al.Investigation and application of non-contact digital optical fiber rotor blade vibration measurement system [J].Aeroengine,2010,36(1): 38-41.
[7] 陈飞翔.叶尖定时测振系统与仿真研究[D].南京:南京航空航天大学,2015.CHEN Fei-xiang.Blade tip-timing measurement system and simulation research[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2015.
[8] 屈玉池,刘军仓,张永峰,等.叶片振动应力的叶根振动监测法及实现技术[J].航空动力学报,2008,23(1): 44-49.QU Yu-chi,LIU Jun-cang,ZHANG Yong-feng,et al.Blade-root vibration monitoring method for blade vibration stress monitoring and its implementation techniques[J].Journal of Aero-space Power,2008,23(1): 44-49.
[9] 方志强,段发阶,张玉贵,等.反射式光纤在高速旋转叶片振动测量中的应用[J].光电子·激光,2007,18(11):1348-1350.FANG Zhi-qiang,DUAN Fa-jie,ZHANG Yu-gui,et al.Application of reflective optical fiber in vibration measurement for high-speed rotating blades[J].Journal of Optoelectronics Laser,2007,18(11):1348-1350.
[10] LAWSON G.Capacitance tip timing techniques in gas tur-bines[D].Cranfield:School of Engineering,Cranfield University,2003.
[11] CARDWELL D N,CHANA K S,RUSSHARD P.The use of eddy current sensors for the measurement of rotor blade tip timing-sensor development and engine testing[C]//Proceedings of the ASME Turbo Expo.Power for Land,Sea and Air,Berlin,2008.
[12] BROUCKAERT J F,MARSILI R,ROSSI G,et al.Development and experimental characterization of a new noncontact sensor for blade tip timing[C]//AIP Conference Proceedings.10th International Conference on Vibration Measurements by Laser and Noncontact Techniques—Aivela2012, Ancona,2012.
[13] 付娜,王三民,郭伟超.某燃气轮机叶片-轮盘耦合振动特性研究[J].汽轮机技术,2005,47(5):362-364.FU Na,WANG San-min,GUO Wei-chao.Calculation of the blade-disc coupled vibration characteristics of a gas turbine[J].Turbine Technology,2005,47(5):362-364.
[14] 李其汉,王延荣.航空发动机结构强度设计问题[M].上海:上海交通大学出版社,2014.LI Qi-han,WANG Yan-rong.The design problem of aero-engine structure strength[M].Shanghai:Shanghai Jiao Tong University Press,2014.
[15] 刘江,葛永庆,安连锁,等.高速旋转叶片振动非接触测量的研究[J].振动与冲击,2006,25(8):1077-1079.LIU Jiang,GE Yong-qing,AN Lian-suo,et al.Study of non-contact monitoring for high-speed rotating blade vibration[J].Journal of Vibration and Shock ,2006,25(8):1077-1079.