摘要
航空发动机采用可调静子叶片可以有效地提高发动机喘振裕度、改善发动机非设计点工作性能。航空发动机叶片导叶叶柄和叶尖采用常规的设计方法,在非设计点可调导叶旋转一定角度,容易出现叶柄凸出机匣流道形成倒台阶、叶尖与机匣干涉导致调节角度范围不足的情况,对气动性能产生不利影响。本文对导叶的叶柄采用防倒台阶设计,对叶尖采用防干涉设计,可以有效避免上述情况。并对新设计的导叶进行性能计算,结果表明,叶柄防倒台阶设计和叶尖防干涉设计对性能的综合影响有利。
The stator vane adjusting mechanism,specifically the multi-stage adjusting mechanism,has considerably more parameters.The results are verified by using the motion simulation.The results indicate that,the simulation verification results and design values have a significant correlation in terms of the regular patterns of combined 0-stage and 1-stage,which further illustrates that the practicality of accessory parametric design can satisfy the aerodynamic regulation performance.
作者
李永建
张稳
吴靓昕
LI Yong-jian;ZHANG Wen;WU Jing-xin(Hunan Key Laboratory of Turbomachinery on Small and Medium Aero-Engine,AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002)
出处
《航空精密制造技术》
2021年第6期54-58,共5页
Aviation Precision Manufacturing Technology
关键词
导叶
倒台阶
防干涉
仿真
vane
anti-reversal step
anti-interference
simulation
