首页|基于显式动力学的发动机涡轮组件动态特性仿真与故障分析

基于显式动力学的发动机涡轮组件动态特性仿真与故障分析

扫码查看
原文链接
  • NETL
  • NSTL
  • 万方数据
针对某型发动机高压涡轮叶片断裂导致的低压涡轮组件损伤破坏故障,开展了故障机理研究.在对故障现象进行总结分析的基础上,建立了断裂叶片冲击低压涡轮组件的显式动力学模型,仿真分析了断裂叶片在低压涡轮组件的运动过程、接触特征及涡轮叶盘摆动响应.结果表明:高压涡轮断叶飞出后将卡在导向器叶片与涡轮转子间做圆周运动,并与前后各部件发生碰撞接触,这是低压涡轮组件损伤破坏的主要原因;而低压涡轮叶盘在断裂叶片飞入后受其冲击发生摆动,摆动角位移仅有0.005 rad,因而低涡叶片不会与导向器叶片发生碰撞接触造成其损伤.本文分析方法和仿真结果对于类似叶片飞失故障再现具有一定的参考价值.
Simulation and fault analysis of dynamic characteristics of engine turbine components based on explicit dynamics
A mechanistic study is conducted to investigate the damage caused by the fracture of high-pressure turbine blades which further impact the low-pressure turbine components.Based on the summary and analysis of the failure phenomenon,an explicit dynamic model is established to simulate the motion process,contact characteristics and turbine disk oscillation response of the fractured blades impacting the low-pressure turbine components.The results indicate that after the high-pressure turbine blade fractures and flies out,it wedges between the stator vanes and turbine rotor,performing a circular movement,and collides with the adjacent components,which is the main cause of damage and failure to the low-pressure turbine components.On the other hand,when the fractured blade enters the low-pressure turbine disk,the disk swings due to the impact,with a swing angle displacement of only 0.005 rad,thus the low-pressure turbine blade does not collide with the stator vanes,preventing damage.The analytical method and simulation results have certain reference value for the reproduction of similar blade loss failures.

blade lossexplicit dynamicsturbine componentsdynamic characteristicsfault analy-siscontact characteristicsengine

陈素荣、张家锷、于平超、蒋科、陶玄君、张大义

展开 >

北京动力机械研究所,北京 100074

南京航空航天大学民航学院,南京 211106

北京航空航天大学能源与动力工程学院,北京 100191

叶片飞失 显式动力学 涡轮组件 动态特性 故障分析 接触特征 发动机

国家自然科学基金国家自然科学基金前瞻布局科研专项中央高校基本科研业务费-民航飞机健康监测与智能维护重点实验室自主基金江苏省自然科学基金

52372387521750711007-ILA22010NJ2024022BK20211187

2024

10.16358/j.issn.1009-1300.20240029

战术导弹技术
中国航天科工飞航技术研究院（中国航天科工集团第三研究院）

战术导弹技术

CSTPCD北大核心
影响因子：0.304
ISSN：1009-1300
年,卷(期)：2024.(3)