激光测速仪测量定子的汽车液力变矩器

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定子的流场明显变矩器使用激光测速技术进行了研究。五架飞机的定子进行了研究速度比0.800和三个平面进行了研究速度比率为0.065。数据补充以前可用的水泵和涡轮机数据。流在定子入口平面是高度不均匀由于复杂流退出涡轮机。0.800的速度比,分离地区位于1/4和中层corepressure角落里的地区。在3/4和退出飞机,分离地区位于shellsuction角落。在入口平面高速度的一个区域是位于外壳压力面附近的速度比0.800。高速地区迁移到shell-suction角落和吸力面1/4和中层。总体速度场的速度比0.065从入口平面变化显著变化。速度大小通常减少从吸入口平面的压力面和切向速度的大方向是从pressure-to-suction表面。 At the speed ratio of 0.065 a strong secondary flow in the inlet from suction surface to pressure surface was seen. However, at the high speed ratio a moderate secondary flow in the inlet from pressure surface to suction surface was observed. Mass flow rates at the different planes are within the experimental uncertainty and also within the uncertainty of pump and turbine mass flow rates. The flow in the stator inlet plane are significantly influenced by the turbine relative blade position. The turbine influence on the mid-plane data is significantly less than on the inlet plane data. The influence of the pump blade position on the stator exit plane is small.

旋转机械的国际期刊

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