带肋壁与出流孔内流通道中肋角度对流量系数的影响  

Effect of Rib Turbulator Orientation on the Discharge Coefficient of Suction Hole in the Internal Passage

作　　者：裘云[1] 朱惠人[1] 倪萌[1] 刘松龄[1] 

机构地区：[1]西北工业大学航空动力与热力工程系,陕西西安710072

出　　处：《航空动力学报》2003年第2期235-238,共4页Journal of Aerospace Power

基　　金：西北工业大学博士论文创新基金资助项目(200114)

摘　　要：在根据相似理论放大的模型上,测量了带肋壁与出流孔内流通道中沿主流流向分布的各出流孔的流量系数Cd。实验在内流通道进口雷诺数为40000～80000,通道总出流比为0.30～0.60的范围内进行,重点分析了肋角度、内流通道进口雷诺数Re和通道总出流比SR对Cd的影响规律。结果显示:在本实验的工况范围内,沿内流通道布置的各出流孔Cd的变化幅度不大,在中后部略有上升;在相同流动状况下,Cd随肋角度的增大而增大,在120°时达到最大值;通道进口雷诺数和通道总出流比对Cd的影响都不显著。Measurement of suction holes' discharge coefficients (Cd) in an internal passage with rib turbulators and suction holes are presented.The internal passage is a rectangular channel with two opposite ribbed walls,the aspect ratio is 05,and the rib turbulators are arranged in a staggered way on the two wider walls.The cylindrical suction holes are 45° inclined and perpendicularly oriented,they are placed on one ribbed wall.Tests were run by varying rib tubulators' angles as 45°,60°,90° and 120°,with Reynolds numbers (Re) changing from 40000 to 80000 and suction ratios (SR) changing from 030 to 060.Influences of rib tuburlators angles,Reynolds number and suction ratio on Cd are studied. Results indicate:(1) Cd increases a little along the internal passage;(2) increasing rib turbulator's angle leads to higher Cd,and the maximum Cd is obtained when the rib angle is 120°;(3) varying suction ratio contributes no remarkable effect on changing discharge coefficients;(4) Reynolds number also has no obvious influence on discharge coefficients.

关 键 词：带肋壁 出流孔 内流通道 肋角度 流量系数 影响 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]