摘要
针对空天飞机组合发动机进气道的冷却要求，采用冲击－对流复合冷却技术对进气道进行强化冷却试验，按照得出的冷却结构各部分传热经验公式，用温度200K，压力1MPa低温氢作冷却剂，算出进气道的冷却热流密度，证明所用结构可以满足进气道冷却要求。
In this paper the enhanced cooling technology for the combined ramjet engine inlet of space craft was presented. The throat part of inlet test piece was cooled by one row of air jet from holes with diameter 3 mm. Then about 2/3 flow rate of air coolant passed through the narrow gap width 1.5 mm for the convective cooling of inlet front inner wall. The other stream of air coolant passed through and cooled the inlet rear part. Using obtained experimental formula 'the safe heat flux for the hypersonic inlet cooling has been calculated when hydrogen with temperature 200 K and pressure 1 MPa was used as a coolant.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
1997年第3期342-345,共4页
Journal of Engineering Thermophysics
关键词
进气道
强化冷却
飞机发动机
冷却
inlet, enhanced cooling, impinging jet, heat flux
