某风机叶片的弯扭耦合颤振问题分析与验证

吴长波; 崔海涛; 徐拓; 王春健

某风机叶片的弯扭耦合颤振问题分析与验证

1.
南京航空航天大学, 能源与动力学院, 南京 210016
2.
中国燃气涡轮研究院强度技术研究室, 成都 610500
3.
中国燃气涡轮研究院强度技术研究室, 成都 610500

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出版历程
- 收稿日期: 2011-04-16
- 修回日期: 2011-09-08
- 刊出日期: 2012-03-28

Analysis and experiment on coupled flutter of a wide-chord blade

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016 China
2.
The Strength Research Office, China Gas Turbine Establishment, Chengdu 610500, China
3.
The Strength Research Office, China Gas Turbine Establishment, Chengdu 610500, China

摘要

摘要: 研究了某风机宽弦转子叶片系统本身的耦合颤振问题,针对该风机转子叶片,理论分析表明原始型叶片存在典型的一阶弯曲与一阶扭转耦合颤振问题.改进型叶片则从转子叶片结构上采取了措施,调整了宽弦转子叶片的一阶弯曲与一阶扭转频率,有效地避免了转子叶片的耦合颤振问题.可靠性累积试车对转子叶片的耦合颤振问题进行了验证,原始型转子叶片80h后因耦合颤振导致转子叶片发生了高周疲劳断裂问题,改进型转子叶片顺利通过了200h的试车考核.
- 转子叶片 /
- 弯曲与扭转 /
- 耦合颤振 /
- 可靠性累积试车 /
- 断裂
Abstract: The coupled flutter of a pinwheel wide-chord blade was studied.In view of the pinwheel blade,the theoretical analysis made for the original pinwheel blade showed that some typicaly coupled flutter problems between the first-order bending vibration and the first-order torsion vibration occured on the blade.The blade was re-designed and the frequencies of the first-order bending vibration and the first-order torsion of the modified blade were changed so as to effectively avoid the coupled flutter.The cumulative test of the reliability shows that the cracks are found in the original pinwheel blade after running 80 hours,while the modified blade can run safely over 200 hours.
- wide-chord blade /
- bending and torsion /
- coupled flutter /
- the cumulative test of reliability /
- cracks

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参考文献(12)

[1]	陶春虎,钟培道,王仁智,等.航空发动机转动部件的失效与预防[M].北京:国防工业出版社,2000.
[2]	周盛.叶轮机气动弹性力学引论[M].北京:国防工业出版社,1989.
[3]	周盛,袁巍,郭恩民.跨音弯掠风扇转子叶片的气动弹性剪裁[J].航空动力学报,1998,13(1):1-6. ZHOU Sheng,YUAN Wei,GUO Enmin.Aeroelastic tailoring for rotor blades of transonic swept fans[J].Journal of Aerospace Power,1998,13(1):1-6.( in Chinese)
[4]	陈佐一,吴晓峰.确定颤振叶片动应力的数值方法[J].航空动力学报,1998,13(4):431-434. CHEN Zuoyi,WU Xiaofeng.Numerical method for determining dynamic stresses in flutter blades[J].Journal of Aerospace Power,1998,13(4):431-434.(in Chinese)
[5]	Sadeghi M,Liu F.Computation of cascade flutter by uncoupled and coupled methods[J].International Journal of Computational Fluid Dynamics,2005,19(8):559-569.
[6]	Sadeghi M,Liu F.Investigation of mistuning effects on cascade flutter using a coupled method[J].Journal of Propulsion and Power,2007,23(2):266-272.
[7]	Reddy T S R,Bakhle M A,Trudell J J,et al.LINFLUX-AE:a turbomachinery aeroelastic code based on a 3-D linearized Euler solver.NASA TM-2004-212978,2004.
[8]	Vahdati M,Sayma A I,Marshall J G,et al.Mechanisms and prediction methods for fan blade stall flutter[J].Journal of Propulsion and Power,2001,17(5):1100-1108.
[9]	Namba M,Nishino R.Flutter analysis of a rotating blade row under aerodynamic interaction with a neighboring blade row.AIAA 2005-0019,2005.
[10]	张正秋,邹正平,王延荣,等.叶轮机械颤振稳定性工程预测方法在跨声风扇中的进一步探讨[J].航空动力学报,2010,25(3):537-548. ZHANG Zhengqiu,ZOU Zhengping,WANG Yanrong,et al.Investigation of flutter prediction method for transonic fan[J].Journal of Aerospace Power,2010,25(3):537-548.(in Chinese)
[11]	Tran D M,Liauzun C,Labaste C.Method of fluid structure coupling in frequency and time domains using linearlized aerodynamics for turbomachinery[J].Journal of Fluids and Structures,2003,17(8):1161-1180.
[12]	Sadeghi M,Liu F.Coupled fluid-structure simulations for turbomachinery blade rows.AIAA 2005-0018,2005.