摘要
利用中国科学院工程热物理研究所和哈尔滨汽轮机厂合建的暂冲式超音速平面叶栅风洞,在详细校核进口流动均匀性、出口流动周期性及叶栅中部流动二元性的基础上,详细测试了三套超音速涡轮叶栅在设计和非设计等三个攻角状态下的气动性能及叶片表面压力分布,为超音速涡轮叶栅的后续研究积累了翔实的实验资料。
A blow-down wind tunnel of transonic turbine cascades,built by Institude of Engineering Thermophysics,Chinese Academy of Scinence and Harbin steam turbine factory was used for exper- iment,based on the investigations on inlet uniformity,outlet periodicity,and mid-span 2D flow field. The aerodynamic performance and blade surface pressure distributions in design or off-design condi- tions at three different incidences of three transonic turbine cascades were tested in detail.A great deal of basic experiment data was got together for subsequent research.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2006年第z1期125-128,共4页
Journal of Engineering Thermophysics
关键词
叶栅
跨音速
测量
cascade
transonic
test
