Low pressure rotor dynamic behavior simulation of Trent 900 engine after fan blade out

XU Xue; LI Hongxin; FENG Guoquan

doi:10.13224/j.cnki.jasp.2020.04.008

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Low pressure rotor dynamic behavior simulation of Trent 900 engine after fan blade out

更新时间：2026-07-07

- Low pressure rotor dynamic behavior simulation of Trent 900 engine after fan blade out
- Vol. 35, Issue 4, Pages: 744-756(2020)
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- DOI：10.13224/j.cnki.jasp.2020.04.008
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- Published：2020
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徐雪, 李宏新, 冯国全. Trent 900发动机风扇叶片飞失后低压转子动力学行为仿真[J]. 航空动力学报, 2020, 35(4): 744-756.

doi: 10.13224/j.cnki.jasp.2020.04.008
徐雪, 李宏新, 冯国全. Trent 900发动机风扇叶片飞失后低压转子动力学行为仿真[J]. 航空动力学报, 2020, 35(4): 744-756. DOI： 10.13224/j.cnki.jasp.2020.04.008.

doi: 10.13224/j.cnki.jasp.2020.04.008 DOI：

摘要

为深入理解三转子大涵道比涡扇发动机风扇叶片飞失情况下的低压转子及结构保险的动力学行为特征

选取Trent900发动机为研究对象，分析了对于风扇叶片飞失(FBO)有重要影响的结构设计特点

进而开展了转子之间动力学耦合影响、结构保险的模拟、风扇叶片简化方法研究。构建了满足Trent 900发动机FBO模拟的三维转/静子简化模型。完成了FBO之后转子旋转约360°的动力学行为模拟

并与Trent 900发动机公布的FBO试验录像进行了对比。结果表明:①仿真结果与FBO试验录像在宏观现象的时间顺序一致;②主结构保险完全失效后，外传振动载荷较失效前降低约45%;③次级结构保险为低压转子提供新的前支点并保护风扇轴。

Abstract

To enhance the understanding of the dynamic behavior of the low pressure rotor and structural fuse in three-shaft high bypass ratio turbofan engine during a fan blade off （FBO） event

the Trent 900 was selected as the research sample.The structural characteristics which may cause important influence was analyzed

and the research on the influence of the dynamic coupling between the rotors

the simulation of structural fuse

and fan blade simplification was conducted. The three-dimensional rotor/stator simplified model for the FBO simulation was built. The simulation of 360 degree rotating of the fan rotor was performed and compared with the video of Trent 900 engine FBO rig test. The results revealed that: (1) the simulation results matched the video of FBO rig test in the time sequence of macro phenomena. (2) The breakage of main structural fuse can reduce the output vibration load by about 45%. (3) Secondary structural fuse can form a new front support for the low pressure rotor and protect the fan shaft.

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Related Institution

Commercial Aircraft Engine Company Limited, Aero Engine Corporation of China

Suzhou Automotive Research Institute, ,Tsinghua University

西北工业大学动力与能源学院

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics

Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China

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