摘要
通过对WZ8A轴流压气机出口静子串列叶片叶尖和叶中二截面平面叶栅实验,得出:①叶尖截面叶栅不适用于高进口Ma;低速时正常工作攻角范围为-30°～-12°,相应的落后角为5°～7°。②叶中截面叶栅在高速时(Ma=0.65),正常工作攻角范围为-1°～10°,落后角为7°～8°;低速时正常工作攻角范围为2.5°～20°,落后角为5°～7°。
The tandem cascade can perform at relative large flow turning angle, but not at the cost of any loss increase. Therefore, it is suitable to use it for the last stage stator of the axial compressor or fan of the airplane engine, where flow turning angle is generally large. The WZ8A compressor is composed of one stage axial and one stage centrifugal compressor. The tandem blades are set on the axial compressor stator. To explore the flow characteristics of the blades, two plane tandem-cascades are constructed; one is of the tip section, and the other is of midspan section. By experiments, the correlations of flow turning angle and total pressure loss coefficient with attack angle and the distribution of blade surface pressure, at high subsonic speed and low speed respectively, are also obtained.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1993年第10期B532-B535,共4页
Acta Aeronautica et Astronautica Sinica
关键词
串列叶栅
总压损失系数
压气机
tandem cascade, total pressure loss coefficient, flow turning angle
