风扇叶片飞失下的结构降载机理

虞磊; 耿景艳; 曹冲; 万召; 李百洋; 王卫国

doi:10.13224/j.cnki.jasp.2019.08.019

风扇叶片飞失下的结构降载机理

doi: 10.13224/j.cnki.jasp.2019.08.019

中国航空发动机集团有限公司商用航空发动机有限责任公司,上海 200241

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出版历程
- 收稿日期: 2019-03-24
- 刊出日期: 2019-08-28

Load reducing mechanism under fan blade out event

摘要

摘要: 利用简化的转子有限元分析模型,从转子临界转速、支点动态载荷响应和转子轴心轨迹等方面进行了有无降载设计的对比分析,研究了风扇叶片飞失下的结构降载机理。结果表明:由于1#支点的熔断设计,低压转子支承由3个支点变为2个支点,风扇振型的临界转速降低,使得风扇转子运行在超临界转速上,轴心轨迹半径减小,从而降低高转速下的载荷响应,同时该机理研究采用的方法可用于熔断结构载荷阀值范围的确定以及其降载效果的评估。
- 涡扇发动机 /
- 风扇叶片飞失(FBO) /
- 熔断 /
- 降载结构装置(LRD) /
- 机理
Abstract: By using a simplified rotor finite element model，comparative analyses with and without load reduce device (LRD) design were carried out,including the critical speed,dynamic load response and the axis trajectory of the rotor. The mechanism of structural load reduction under fan blade out was studied. Analysis results indicated that due to the fuse design of the 1# bearing,the low-pressure rotor support changed from three bearings to two bearings.As a result, the critical speed of fan mode was reduced, the radius of axis trajectory was decreased,and fan rotor ran at supercritical speed,which reduced load response at high speed.The method adopted in this mechanism study can be used to determine the load threshold range of fused structure and to evaluate its load reduction effect.
- turbofan engine /
- fan blade out(FBO) /
- fuse /
- load reduce device(LRD) /
- mechanism

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参考文献(19)

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