航空发动机叶片-机匣碰摩过程的数值模拟

刘书国; 洪杰; 陈萌

航空发动机叶片-机匣碰摩过程的数值模拟

北京航空航天大学能源与动力工程学院,北京 100191

计量
- 文章访问数: 2022
- HTML浏览量: 187
- PDF量: 26
- 被引次数: 0
出版历程
- 收稿日期: 2010-11-04
- 修回日期: 2011-03-02
- 刊出日期: 2011-06-28

Numerical simulation of the dynamic process of aero-engine blade-to-case rub-impact

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

摘要

摘要: 提出了基于隐式-显式相结合的积分方法对航空发动机叶片-机匣碰摩过程进行数值模拟,充分考虑了结构的低频线性稳态响应和碰摩引起的高频非线性瞬态响应.以某高压涡轮结构为例,仿真叶片-机匣碰摩的瞬态动力学过程,分析叶片的动力响应特征.研究结果表明:叶片-机匣碰摩过程中将产生影响应力分布的应力波并在叶身传导,碰摩结束后叶片将以低阶固有模态频率进行振动衰减.
- 叶片 /
- 碰摩 /
- 应力波 /
- 动力响应 /
- 数值模拟
Abstract: Numerical simulation of the dynamic process of aero-engine blade-to-case rub-impact was conducted by explicit-implicit integration scheme.This took full account of low-frequency liner steady-state response and high-frequency nonliner time-transient response due to the rub-impact.By taking the structure of a certain high-pressure turbine as example,the process of blade-to-case rub-impact was simulated,and the dynamic response characteristic of the blade during the process was analyzed.The results show that,the stress wave,which affects the stress distribution of blade,will be generated and propagated on the body of blade during the process of rub-impact;after the process of rub-impact,the dynamic response of blade is a decaying harmonic motion at the damped low-order natural frequency.
- blade /
- rub-impact /
- stress wave /
- dynamic response /
- numerical simulation

HTML

参考文献(15)

[1]	Chupp R E,Hendricks R C,Lattime S B,et al.Sealing in turbomachinery[J].Journal of Propulsion and Power,2006,22(2):313-349.
[2]	沈自尹.F110涡轮封严件的改进[J].国际航空杂志,1995(3):51-52. SHEN Ziyin.The improvement of the seal structure in turbine[J].International Aviation,1995(3):51-52.(in Chinese)
[3]	Ikeda T,Ishida Y,Yamamoto T,et al.Nonlinear forced oscillations of an unsymmetrical shaft and an unsymmetrical rotor with quartic nonlinearity[J].Bulletin of the JSME,1988,31(3):530-538.
[4]	Sawicki J T,Padovan J,Al-Khatib R.The dynamics of rotor with rubbing[J].International Journal of Rotating Machinery,1999,5(4):295-304.
[5]	Muszynska A.Rotor-to-stationary element rub-related vibration phenomena in rotating machinery:literature survey[J].Shock and Vibration Digest,1989,21(3):3-11.
[6]	Padova C,Barton J,Dunn M G,et al.Experimental results from controlled blade tip/shroud rubs at engine speed[J].Journal of Turbomachinery,2007,129(4):713-723.
[7]	Ahrens J,Ulbrich H,Ahaus G.Measurement of contact forces during blade rubbing //Proceedings of the Seventh International Conference on Vibration in Rotating Machinery.Nottingham:IMechE,2000:259-268.
[8]	Young G.Development of a general predictive model for blade tip/shroud interference;interactive forces .Columbus,OH:The Ohio State University,2006.
[9]	Ferguson J L.A moving load finite element-based approach to determining blade tip forces during a blade-on-casing incursion in a gas turbine engine .Columbus,OH:The Ohio State University,2008.
[10]	Jiang J,Ahrens J,Ulbrich H,et al.A contact model of a rotating rubbing blade //Proceedings of the 5th International Conference on Rotor Dynamics.Darmstadt:IFToMM,1998:478-489.
[11]	Turner K E,Adams M L,Dunn M G.Simulation of engine blade tip-rub induced vibration .ASME Paper 2005-GT-68217,2005.
[12]	Garza J W.Tip rub induced blade vibrations:experimental and computational results .Columbus,OH:The Ohio State University,2006.
[13]	Sinha S K.Dynamic characteristics of a flexible bladed-rotor with coulomb damping due to tip-rub[J].Journal of Sound and Vibration,2004,273(4-5):875-919.
[14]	Turner K E,Dunn M G,Padova C.Airfoil deflection characteristics during rub events .ASME Paper 2010-GT-22166,2010.
[15]	Hallquist J O.LS-DYNA theory manual[M].California:Livermore Software Technology Corporation,1998.