叶片飞脱下转子动力学响应实验

侯理臻; 廖明夫; 王卫国; 王四季; 马会防; 虞磊; 黄巍; 熊雨浓; 王珏

doi:10.13224/j.cnki.jasp.2019.05.006

叶片飞脱下转子动力学响应实验

doi: 10.13224/j.cnki.jasp.2019.05.006

1.
西北工业大学动力与能源学院,西安 710129
2.
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: 2018-11-21
- 刊出日期: 2019-05-28

Experiment of rotor dynamics under fan blade off

摘要

摘要: 为了研究大涵道比涡扇发动机叶片飞脱时动力学响应,更好地进行发动机安全性设计,根据相似理论设计了包含叶片飞脱装置的突加不平衡实验系统并进行了实验验证。研究结果表明:设计的突加不平衡实验系统,与某型验证机相似度高,代表性强,能够有效可控地进行突加不平衡实验,重复性好,机理清晰且飞脱不平衡量大,能够真实地模拟发动机叶片飞脱响应。通过实验发现,当大突加不平衡发生时,频谱出现超次谐波并且冲击系数由于挤压油膜阻尼器限幅作用并不呈现线性关系,因而在后续研究中还应注意限幅导致的碰摩问题。
- 叶片飞脱 /
- 突加不平衡 /
- 相似理论 /
- 实验验证 /
- 安全性设计
Abstract: In order to research the dynamic response of the high bypass ratio turbofan engine under fan blade off, and finish the safety design better, the sudden unbalance experimental system with fan blade off device based on similarity theory were designed and experimental verification was finished. Research shows that the sudden unbalance experimental system has high similarity to some demonstration engines, which can finish the sudden unbalance experiment with good repeatability, clear mechanism and big unbalance, furthermore, it can simulate the fan blade off of the engine really. Through the experiment, it was found that when the large sudden unbalance occurred, the superharmonic frequency spectrum appeared and the impact coefficient didn’t show a linear relationship due to the limiting effect of the squeezed film damper, so the rubbing problem caused by the limiting should be concerned in the subsequent research.
- fan blade off /
- sudden unbalance /
- similarity theory /
- experimental verification /
- safety design

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参考文献(18)

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