摘要
航空发动机涡轮叶片常受到离心力、气动力等多重耦合的作用,叶片断裂失效等事故经常发生。本文以某航空发动机涡轮叶片为研究对象,开展流固耦合作用下模态分析,发现最大等效应力位于叶片与叶盘连接处,并得到复合力场作用下的动频和振型云图。分析表明:离心力场下叶片因动力刚化效应使各阶模态频率提升;离心-气动复合力场因载荷变形方向相异削弱刚化效应,动频及相对偏差较单独离心力场下降,但仍高于静态固有频率,为涡轮叶片振动设计与优化提供参考。
Aero-engine turbine blades are often subjected to the coupling effect of centrifugal force,aerodynamic force and other multiple loads,leading to frequent accidents such as blade fracture and failure.This paper takes a certain aero-engine turbine blade as the research object and conducts modal analysis under fluid-structure interaction.It is found that the maximum equivalent stress is located at the joint between the blade and the disk,and the dynamic frequencies and mode shape nephograms under the action of composite force fields are obtained.The analysis shows that under the centrifugal force field,the blade's modal frequencies of all orders are increased due to the dynamic stiffening effect;in the centrifugal-aerodynamic composite force field,the dynamic stiffening effect is weakened because the deformation directions of the two loads are different,so the dynamic frequencies and relative deviations are lower than those under the single centrifugal force field,but still higher than the static natural frequencies.This research provides a reference for the vibration design and optimization of turbine blades.
作者
朱永亮
张姝
Zhu Yong-liang;Zhang Shu(School of Mechanical Power and Engineering,Shenyang University of Chemical Technology,Liaoning Shenyang 110142)
出处
《内燃机与配件》
2026年第4期54-56,共3页
Internal Combustion Engine & Parts
关键词
涡轮叶片
流固耦合
预应力
模态分析
Turbine blades
Fluid-structure interaction
Prestress
Modal analysis
