摘要
在低 Ma情况下 ,对两种方案的排气扩压器和排气管 1/ 5模型进行了试验与研究。一种是大扩压角内有分割锥的扩压器 ;一种是小角度扩压器 ,其扩压比分布在直扩压段和转向叶片两个部分上。得出了不同的试验结果 ,同时对一方案的不同结构分别测定了压力损失系数和总压恢复系数 ,并进行了分析。文中引用了 Sovron等人推荐的曲线进行研究 ,又解释了预旋叶片的作用 ,得出一些有益的设计思想。
At Mach numbers ranging form 0 2 to 0 35,two schemes 1/5th scale models of exhaust diffusers and elbow exhausts have been researched.The first scheme was a diffuser with wide cone angle.In order to reduce the separation losses,the concentric splitter cones were set to augment the diffusibility.The splitter cones were made by subdividing the short wide angle diffuser into a series of smaller,more optimal ones.The second scheme was a diffuser with smalle r cone angle,in order to reduce the length,the diffuser ratio was distributed between the linear diffuser and the turning vane to improve the overall performence.The results of the model test show that total pressure re covery coefficient C P of the second scheme is rather high and the pressure loss coefficient ΔP/Q 1 is reduced.At the same time,the ΔP/Q 1 of different constructions of the first scheme were measured separately,and the measurements were analysed.The function of the splitter cones was demonstrated.Se veral test curves were used to prove the certain effect of the pre swirl cascade in some diffuser angle ranging.Therefrom the beneficial design ideas are obtained.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1993年第2期195-198,共4页
Journal of Aerospace Power
