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在小型激波风洞中采用动态压力测量的方法。研究了双燃式液体冲压发动机进气道和燃烧室的冷态内流场。采用连管实验方法,将进气道内压段的起始截面与风洞的型面喷管的出口截面直接相连,在进气道内压段进口截面处,气流马赫数Ma=3.15,雷诺数Re=3.3×10~7/m。内流场中毕托压和静压测量结果表明,在文中实验条件下该冲压发动机模型以双燃式工况运行,外涵道为超音速通道;内涵道(亚燃室)为亚音速通道。在亚燃室中测得的毕托压数值较低,气流总压损失较大。这是由于超音速通道中能量较低的附面层气流全部流入亚燃燃烧室,同时又在亚燃燃烧室进口区出现激波与厚附面层相互作用的结果。实验中还发现隔板的支撑肋对该现象影响不大。
The method of dynamic pressure measurement in small shock wind tunnel. The cold internal flow field in the inlet port and the combustion chamber of a dual-fuel liquid ramjet engine is studied. Adopting the connecting pipe experiment method, the initial section of the inlet pressure section is directly connected with the outlet section of the nozzle of the wind tunnel. At the inlet section of the inlet section of the inlet section, the Mach number of the gas flow Ma = 3.15, the Reynolds number Re = 3.3 × 10 ~ 7 / m. The results of Biotin pressure and static pressure in the internal flow field show that under the experimental conditions, the ramjet engine operates in dual-combustion mode and the outer bypass channel is supersonic channel. The internal tunnel (sub-chamber) is subsonic channel . The lower Biotin pressure measured in the sub-combustion chamber, the greater the total pressure loss of the gas stream. This is due to the supersonic flow in the lower energy stratified flow into the entire combustion of the sub-combustion chamber, but also in the sub-combustion chamber inlet zone shock and thick surface of the interaction results. In the experiment, it was also found that the supporting rib of the partition had little effect on the phenomenon.