双燃烧室冲压发动机亚燃模块进气道非设计点工作特性

Investigation of Ramjet Inlet for an Axisymmetric Dual-combustor Ramjet on Off-design Conditions

对适用于轴对称双燃烧室冲压发动机的亚燃模块进气道非设计点工作特性进行了风洞实验和数值计算研究,获得了该进气道的非设计点性能,并分析了其流态特征和再起动特性。实验数据显示,该进气道的马赫数4临界状态性能为:总压恢复系数0.425,出口截面平均马赫数0.519,可承受反压为自由流静压的56.52倍,而马赫数5的相应临界性能参数则分别为0.240,0.486和125.94。非设计状态下,该进气道的流量系数下降显著,马赫数5时的流量系数为0.813,马赫数4时则进一步下降至0.593,为此对高超声速进气道非设点综合性能的改善迫在眉睫。另外,该进气道在马赫数4时具有再起动能力。

In this paper, both experimental and computational investigation are conducted on the hypersonic inlet for ramjet module of the dual-coubustion ramjets （DCR） to obtain the off-design performance and to analyze the internal flow pattern and the restarting characteristics. The results show that while operating at the critical state of Mach 4, at the exit section of the inlet the total pressure coefficient is 0. 425, the average Mach number is 0. 519 and the back pressure is 56.52 times of the free stream pressure. The corresponding critical performance parameters of Mach 5 are 0. 240, 0. 486 and 125.94 respectively. The mass flow ratio of the inlet decreases substantially at off-design condi- tions with a value of 0. 813 at Mach 5 and a value of 0. sga at Mach 4. Therefore, it is an urgent task to improve the off-design performance of hypersonic inlets. The studied inlet has the ability of self-starting at Mach 4.