摘要
本研究通过实验的手段在前置扩压器的结构和进口马赫数不变的条件下 ,改变内、外环突扩角和相对突扩间隙 ,研究总压损失和静压恢复的变化规律。结果表明 :在本研究的参数范围内 ,存在有最佳的内外环突扩角的组合 (βi=4 0～ 4 5°,βo=4 5～ 50°)及相应的相对突扩间隙 (δ=1 .8) ,使得总压损失系数 σ*有最小值 ,约为 1 .7～ 1 .8。在 βi/βo=4 5.5°/4 5°时 ,有最大的静压恢复系数 cp=0 .
An experimental investigation has been carried out to reveal the variations of total pressure loss and static pressure recovery with the inner and outer dump angles and the distance between prediffuser exit and the head of the flame tube (i.e.dump gap) at inlet Ma =0 265.The system comprised a straight walled prediffuser,a simple flame tube,five different inner and outer dump angles and four different dump gaps.The results demonstrate that there exist the minimum total pressure loss ( σ *=1 7% ～1 8%) and the maximum static pressure recovery ( Cp =0 33) in the case of relative dump gap δ =1 8,inner angle β i =40°～45° and outer angle β o =45°～50°.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2001年第2期115-118,共4页
Journal of Aerospace Power
