摘要
航空发动机轮盘在工作过程中容易出现危险的共振情况,为了研究高压涡轮级间封严盘的振动特性,通过振动特性结果来分析判断轮盘的可靠性,对航空发动机高压涡轮级间封严盘进行有限元分析,并设计完成模态试验,识别出高压涡轮封严盘振动模态参数,比对模拟与试验结果之间的差别,讨论了边界条件对模态结果的影响。结果表明:所设计的模拟盘和转接段合理,数值计算与试验结果之间误差小于0.2%,可结合二者结果用于高压涡轮级间封严盘调频、减振和排故方面。
Because the aero-engine turbine disk is apt to resonate in procession of work,we need to study the vibration property of high-pressure turbine interstage sealing disk,and analyse and judge the reliability of disk.We do finite element analysis for the disk,and design and complete the modal test,then modal parameters are identified,furthermore,compare the results between analysis and test and discuss the influence of boundary conditions on the modal results.The result shows that the simulated disk and switching section is reasonable,and the error between numerical calculation and modal test is less than 0.2%,furthermore,the conclusion can be used for frequency adjustment,vibration attenuation and removal of faults.
作者
李静
陈亚龙
LI Jing;CHEN Ya-long(AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai 201108,China)
出处
《机械设计与制造》
北大核心
2020年第4期21-23,27,共4页
Machinery Design & Manufacture
关键词
高压涡轮级间封严盘
振动特性
数值计算
模态试验
High-Pressure Turbine Interstage Sealing Disk
Vibration Property
Numerical Calculation
Modal test
作者简介
李静(1986-),女,湖北人,硕士研究生,工程师,主要研究方向:航空发动机强度设计。
