摘要
为测量压气机跨声叶栅表面压力场,选择美国ISSI公司的Binary FIB PSP(压敏涂料),并根据涂料和跨声叶栅合理搭配相机和光源系统,对涂料进行标定。设计了两种不同的光路布局和拍照方案,获取了吸力面与压力面在多个攻角和马赫数下的试验数据。结果表明:对于压气机叶栅试验,打光和相机采取侧向布局效果更好。在0°攻角下,吸力面的吸力峰靠近前缘;随着攻角的变大,吸力面气流在靠近前缘很短距离完成加速和静压下降过程,然后沿弦长方向开始减速,压力面气流在叶片前缘附近很短距离内完成减速增压过程。当马赫数达到0.8时,叶栅通道出现了激波;随着进口马赫数的提高,叶片吸力面和压力面表面的静压值变小。
In order to measure transonic cascade surface pressure field, Binary FIB pressure sensitive paint of ISSI company USA was chosen, optical system and CCD camera were configured to calibrate pressure sensitive paint. Test data of suction surface and pressure surface had been obtained under several attack angles and Mach numbers. Pressure contours illustrated that optical arrangement can obtain better result in side direction. Test results indicated that the peak value was near inlet edge of suction surface in the 0° attack angle. The air stream near the inlet edge of suction surface completed acceleration and static pressure fall within a very short distance, and then the stream velocity decreased along the chord direction. The air stream near the inlet edge of pressure surface completed speed-down and static pressure increase within a very short distance. Cascade passage appeared shock wave in 0.8 Mach. The static pressure in suction surface and pressure surface decreased as Math number inereased.
出处
《燃气涡轮试验与研究》
北大核心
2015年第4期57-62,共6页
Gas Turbine Experiment and Research
关键词
压气机
压力敏感涂料
跨声叶栅
压力测量
激波
光路布局
compressor
pressure sensitive paint
transonic cascade
pressure measurement
shock wave
optical arrangement
