摘要
利用西北工业大学电阻加热超声速燃烧室直连式实验设备，针对自行设计的超声速燃烧室模型，在燃烧室入口马赫数Ma=2.0、入口流量m=0.73-1.0kg／s、入口总压Pt≈（7-8）×10^5Pa、入口总温Tt为室温条件下，开展了不同燃烧室进口流量、隔离段长高比以及燃烧室出口堵塞比情况下的燃烧室冷流实验；采用CFD商用软件对燃烧室冷流流场进行了数值模拟，并将计算结果与实验数据进行了对比和分析。研究结果表明，增加隔离段的长高比，可以提高燃烧室抗反压的能力，燃烧室出口压力场的畸变对燃烧室内部流场有较大的影响，同时通过计算结果与实验数据的对比验证了计算方法的适用性。
The scramjet combustor cold flow was researched in Northwestern Polytech-nical University direct-connected resistance heated facility. The cold flow experimental was performed, for the designed supersonic combustor model with different isolator length, different combustor inflow and different exit back pressure. The combustor inlet Ma=2.0, inflow m=0.73-1.0 kg/s, total pressure Pt≈（7-8）×10^5Pa, total temperature Tt=300 K. The cold flow field of the supersonic combustor is also simulated with computational fluid dynamics （CFD） software and is analyzed and compared with experimental results. The experimental and computational results show： The length/height ratio of isolator increases, the capacity of resist back pressure for the scramjet combustor increases. The exit pressure distortion of combustor has greater effect on the internal flow field of combustor. The comparison of computational results and experimental results also verify the applicability of numerical simulation method.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第6期1135-1140,共6页
Journal of Aerospace Power
关键词
超声速燃烧室
冷流
隔离段
数值模拟
scramjet combustor
cold Flow
isolator
numerical simulation
作者简介
王靛（1979-），男，湖南株洲人，博士生，主要从事超燃冲压发动机燃烧室研究。
