摘要
采用一种研究双燃式（超燃）冲压发动机进气道和燃烧室冷态内流场的实验方法：将进气道内流场的起始截面直接与型面喷管的出口截面相连，即将进气道和燃烧室的实验模型当作风洞的试验段，观察流场和波系的变化，并采用该方法进行了实验研究。内流场的压力测量和光学流场显示结果表明，在文中所示实验状态下风洞能启动，超燃冲压发动机模型处于双燃式所要求的冷态工作状态，即燃烧室外涵道为超声速流动，燃烧室内涵道（亚燃室）为亚声速流动。
In this paper,an experimental method was presented for the investigation of cold internal flow field of supersonic inlet/combustor of a dualcombustion scramjet by taking the experiment model as the test section of wind tunnel and directly connecting the beginning of internal inlet of the scramjet model to the exit of a contoured nozzle.The results of pressure measurements and optical flow visualization show that under the experimental condition described in this paper,the shock tunnel could be started and the scramjet model worked in the right state required by the cold internal flow of dualcombustion scramjet,that means the flow in the supersonic duct was supersonic while the flow in the pilot duct was subsonic.
出处
《流体力学实验与测量》
CSCD
1998年第2期51-54,63,共5页
Experiments and Measurements in Fluid Mechanics
基金
国家自然科学基金
中科院重点基金
