摘要
涡轮叶尖间隙影响着发动机的性能,涡轮典型部件的冷热态尺寸换算是间隙设计的重要内容。介绍了应用优化设计将涡轮典型部件热态尺寸换算到冷态尺寸的方法,应用此方法对某型涡轮叶片进行分析,比较了优化算法与简化算法的结果,表明优化算法的结果是合理的,此方法是可行的。同时将其应用于某涡轮盘的冷、热态尺寸换算,从而成功地解决了涡轮典型部件冷、热态尺寸换算问题。
Tip clearance of the turbine plays an important role on the aeroengine performance. Dimension conversion from hot state to cold state of the turbine components is an important content of tip clearance research. In this paper, dimension conversion method using design optimization was introduced. Based on this method,a blade was analyzed. Compared with simplified method,the result is reasonable and feasible. A turbine disc was also successfully calculated with the design optimization method. Thus ,the problem of dimension conversion was solved.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2006年第1期190-194,共5页
Journal of Aerospace Power
关键词
航空、航天推进系统
涡轮
尺寸换算
优化设计
aerospace propulsion system
turbine
dimension conversion
design optimization
