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双层模型机匣和叶片的包容性问题数值模拟 被引量：1

Numerical Simulation of the Double- layered Aero- engine Case and Blade Containment
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摘要 采用显式动力分析有限元技术，研究了飞断叶片模型与机匣模型的撞击过程，并且计算了不同类型机匣模型包容情况下的临界转速。计算结果表明，双层机匣模型的包容能力明显地优于单层机匣模型，间隙情况对双层机匣模型的包容能力有一定的影响。研究结果对多层航空发动机机匣的包容性设计有一定的参考价值。 The process of breaking off blade impact on modeled case and critical revolving velocity of different casing containments are investigated in dynamic explicit finite element method. The calculation results show that the containment capability of double- layered case is better than single- layered case. Clearance are of great influence on the containment capability of double- layered ease. The study can be used as a reference for the multilayered aero- engine casing containment design.
作者 曹俊俊 陈爱军 章定国 廖连芳 段明晨 陈思佳
机构地区 南京理工大学力学与工程科学系 中国航空工业集团沈阳发动机设计研究所
出处 《航空计算技术》 2009年第6期33-36,共4页 Aeronautical Computing Technique
基金 基金项目：中国-航航空推进技术验证项目（APTD-1104-02）
关键词 双层机匣模型 叶片模型 包容性 显示动力有限元法 数值模拟 double- layered modeled case modeled blade containment capability explicit dynamic finite element method numerical simulation
分类号 V232.4 [航空宇航科学与技术—航空宇航推进理论与工程]
  • 相关文献

参考文献10

  • 1范志强,高德平,覃志贤,王维,纪永汉.航空发动机真实机匣的包容性试验[J].航空动力学报,2007,22(1):18-22. 被引量：18
  • 2Frankenberger C E. FAA T53 - L - 13L Turbine Fragment Containment Test [ R ]. DOT/FAA/AR - 98/22,1998.
  • 3Sarkar S, Atluri S N. Effects of Multiple Blade Interaction on the Containment of Blade Fragments During a Rotor Failure [ J]. Finite Element in Analysis and Design, 1996,23:211 - 223.
  • 4Kraus A, Frischbier J. Containment and Penetration Simulation in Case of Blade Loss in a Low Pressure Turbine [ A ].DYNAmore LS- DYNA Forum 2002 [ C ]. 2002.
  • 5Carney K, Pereira M, Revilock D, et al. Jet Engine Fan Blade Containment Using Two Alternate Geometries [ A ]. 4th European LS-DYNA Users Conference[ C]. 2003.
  • 6宣海军,洪伟荣,吴荣仁.航空发动机涡轮叶片包容试验及数值模拟[J].航空动力学报,2005,20(5):762-767. 被引量：34
  • 7于亚彬,陈伟.模型机匣/叶片的包容性数值分析[J].航空动力学报,2005,20(3):429-433. 被引量：24
  • 8肖荣清,周艳平,肖文凯.活塞环用钢6Cr13Mo异型截面轧制的显式动力学有限元分析[J].武汉大学学报（工学版）,2005,38(2):91-94. 被引量：2
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二级参考文献21

  • 1Dewhurst T B.Impact load on containment rings during a multiple blade shed in aircraft gas turbine engines[R].Finite Elements in Analysis and Design,1991,23:211～223.
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  • 8Carney K,Pereira M,Revilock D,etc.Jet Engine Fan Blade Containment Using Two Alternate Geometries[A].4th European LS-DYNA Users Conference[C].2003.
  • 9Sarkar S,Atluri S N.Effects of Multiple Blade Interaction on the Containment of Blade Fragments During a Rotor Failure[J].Finite Elements in Analysis and Design,1996,23(2～4):211～223.
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共引文献56

同被引文献9

  • 1于亚彬,陈伟.模型机匣/叶片的包容性数值分析[J].航空动力学报,2005,20(3):429-433. 被引量：24
  • 2宣海军,洪伟荣,吴荣仁.航空发动机涡轮叶片包容试验及数值模拟[J].航空动力学报,2005,20(5):762-767. 被引量：34
  • 3范志强,高德平,姜涛,覃志贤,王维.模型机匣的包容性试验和数值模拟[J].南京航空航天大学学报,2006,38(5):551-556. 被引量：16
  • 4Frankenberger C E. FAA T53-L-13L turbine fragment con tainment test[R]. DOT/FAA/AR-98/22,1998.
  • 5Sarkar S,Atluri S N. Effects of multiple blade interaction on the containment of blade fragments during a rotor fail ure[J]. Finite Element in Analysis and Design, 1996,23(2 4) :211-223.
  • 6Kraus A,Frischbier J. Containment and penetration simu lation in case of blade loss in a low pressure turbine[R]. Bad Mergentheim, Germany: DYNAmore LS-DYNA Forum 2002.
  • 7Carney N, Pereira M, Revilock D, et al. Jet engine fan blade con tainment using two alternate geometries[R]. ULM, Germany: 4th European LS DYNA Users Conference, 2003.
  • 8Rice J R. Some remarks on elastic crack-tip stress fields[J]. Int. Journal Solids Structures, 1972,8(6) : 751-758.
  • 9Petroski H J, Achenbach J D. Computation of the weight function from a stress intensity factor[J]. Engineering Fracture Mechanics, 1978,10(2) : 257 -266.

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航空计算技术
2009年 第6期

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