叶片缘板阻尼结构阻尼效果分析
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摘要
基于谐波平衡法,分别通过理论分析和有限元数值仿真分析对某涡轮叶片缘板阻尼结构进行了阻尼效果分析,并与试验结果进行了对比,两者吻合性较好。研究发现叶片频率随着阻尼块离心力的增大呈非线性增大,但叶片振型基本不变;叶片最大振动应力出现在伸根处进气端;阻尼块起到了明显的阻尼效果,且在高量值激励下,阻尼块起到的阻尼效果更加明显。
By using harmonic balance method,the damping effect of a turbine blade platform damping structure was analyzed by theoretical analysis and finite element numerical simulation respectively,and compared with the test results. It showed that the two results are in good agreement. It is found that the blade frequency increases nonlinearly with the increase of the centrifugal force of the damping block. But the blade vibration pattern is basically unchanged. The maximum vibration stress of the blade appears at the inlet end of the extension root. The damping block has a significant damping effect. And the damping effect of the damping block is more obvious under the excitation of high quantity value.
By using harmonic balance method,the damping effect of a turbine blade platform damping structure was analyzed by theoretical analysis and finite element numerical simulation respectively,and compared with the test results. It showed that the two results are in good agreement. It is found that the blade frequency increases nonlinearly with the increase of the centrifugal force of the damping block. But the blade vibration pattern is basically unchanged. The maximum vibration stress of the blade appears at the inlet end of the extension root. The damping block has a significant damping effect. And the damping effect of the damping block is more obvious under the excitation of high quantity value.
引文
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[2]郝燕平,单颖春,朱梓根.叶片摩擦阻尼器的优化设计方法研究[J].航空动力学报,2002,17(3):349-356.
[3]范天宇,廖明夫.转子干摩擦阻尼器及其减振机理[J].机械科学与技术,2003,22(5):743-746.
[4]单颖春,郝燕平,朱梓根,等.干摩擦阻尼块在叶片减振方面的应用与发展[J].航空动力学报,2001,16(3):218-223.
[5]漆文凯,高德平.带摩擦阻尼装置系统振动响应分析方法研究[J].航空动力学报,2006,21(1):161-167.
[6]慕琴琴,燕群,黄文超.航空发动机旋转叶片-机匣碰摩动力学特性研究[J].航空计算技术,2017,47(6):9-13.
[7]季葆华,王乐天,袁奇,等.汽轮机叶片干摩擦阻尼机理及其数学描述[J].汽轮机技术,1997,39(6):345-349.
[8] Sanliturk K Y,Imregun M,Ewins D J. Harmonic Balance Vibration Analysis of Turbine Blades with Friction Dampers[J]. Journal of Vibration and Acoustics,1997,119(1):96-103.
[9]何尚文,任兴民,秦卫阳,等.基于整体-局部统一滑动模型的叶片缘板阻尼器减振特性分[J].西北工业大学学报,2010,28(6):872-876.
[10]古远兴,龚梦贤,曹磊,等.叶片缘板阻尼器设计分析中的一些问题[J].燃气涡轮实验与研究,2000,13(4):31-37.
[11]孙莹.干摩擦阻尼减振技术在叶片结构设计中的应用研究[D].北京:中国航空研究院,2013.
[12] Panning L,Popp K,Sextro W,et al. Asymmetrical Underplatform Dampers in Gas Turbine Blades:Theory and Application[R]. ASME-2004-GT-53316,2004.
[13]庄茁,由小川.基于ABAQUS的有限元分析和应用[M].北京:清华大学出版社,2008.
[2]郝燕平,单颖春,朱梓根.叶片摩擦阻尼器的优化设计方法研究[J].航空动力学报,2002,17(3):349-356.
[3]范天宇,廖明夫.转子干摩擦阻尼器及其减振机理[J].机械科学与技术,2003,22(5):743-746.
[4]单颖春,郝燕平,朱梓根,等.干摩擦阻尼块在叶片减振方面的应用与发展[J].航空动力学报,2001,16(3):218-223.
[5]漆文凯,高德平.带摩擦阻尼装置系统振动响应分析方法研究[J].航空动力学报,2006,21(1):161-167.
[6]慕琴琴,燕群,黄文超.航空发动机旋转叶片-机匣碰摩动力学特性研究[J].航空计算技术,2017,47(6):9-13.
[7]季葆华,王乐天,袁奇,等.汽轮机叶片干摩擦阻尼机理及其数学描述[J].汽轮机技术,1997,39(6):345-349.
[8] Sanliturk K Y,Imregun M,Ewins D J. Harmonic Balance Vibration Analysis of Turbine Blades with Friction Dampers[J]. Journal of Vibration and Acoustics,1997,119(1):96-103.
[9]何尚文,任兴民,秦卫阳,等.基于整体-局部统一滑动模型的叶片缘板阻尼器减振特性分[J].西北工业大学学报,2010,28(6):872-876.
[10]古远兴,龚梦贤,曹磊,等.叶片缘板阻尼器设计分析中的一些问题[J].燃气涡轮实验与研究,2000,13(4):31-37.
[11]孙莹.干摩擦阻尼减振技术在叶片结构设计中的应用研究[D].北京:中国航空研究院,2013.
[12] Panning L,Popp K,Sextro W,et al. Asymmetrical Underplatform Dampers in Gas Turbine Blades:Theory and Application[R]. ASME-2004-GT-53316,2004.
[13]庄茁,由小川.基于ABAQUS的有限元分析和应用[M].北京:清华大学出版社,2008.