摘要
在回流式传热风洞中，用五孔针对单气膜孔射流下游的流场进行了三维测量，观察到了复合角射流时产生的一对具有明显强度和大小差别的流向耦合双涡结构，并发现γ＝１５°的扇形孔较圆孔具有较弱的射流穿透能力和旋涡强度，其射流冷气可更利于贴近壁面。
The effects of blowing ratio at M=10 and 20 on downstream flow field single film cooling hole with compound-angle orientations have been investigated experimentally.It is found that a pair of counterrotating vortices,one of which is strong and another is weak,were observed in the downstream region of jet exit.The hole with a fan-shaped angle of 0° or 15° was oriented so that its angles with respect to the test surface are 60° in a stream/normal plane projection,and 30° or 45° in a spanwise/normal plane projection.Contours of longitudinal velocity show asymmetric kidney shape.The fan-shaped hole effectively decreases the strength of longitudinal vortex and increases the spreading of jet so that the film cooling effectiveness would be much greater than that found in the downstream of a circular hole.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1998年第1期69-71,共3页
Journal of Aerospace Power
