摘要
针对某型燃气轮机临界转速设计裕度不足的问题,结合测试结果,使用假设模态法和数值拟合法,对多种方案进行了计算分析,提出并采用了合理的改进设计方案,即将前支点安装边前移,增加轴承机匣轴向长度,将机匣厚度由16mm减小为10mm;使第2阶临界转速距额定工作转速的裕度从5%增加到10%,达到了改善振动特性的目的。
The computational analysis of variety concepts for improving critical speed design margin of a gas turbine was performed using assumed mode method and numerical fitting method. Combining measurement results, the reasonable improved design concept was presented and adopted which mov＇ed forward the flange of front support and increased the axial length of bearing casing and decreased the casing thickness from 16mm to lOmm. The second order critical speed margin to rated speed was increased from 5% to 10% and then vibration characteristics were improved.
出处
《航空发动机》
2010年第1期7-9,共3页
Aeroengine
关键词
燃气轮机
振动
临界转速
支点刚度
裕度
假定模态法
数值拟合法
gas turbine
vibration
cdtical speed
support rigidity
margin
assumed mode method
numerical fitting
