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为了满足RBCC推进系统需求,进行了气氧/煤油引射火箭燃烧室的设计和试验研究。燃烧室室压为2MPa,氧燃比为1.6,火箭流量在95~285g/s范围内变化。通过火箭单独的冷、热态试验,对其流量控制、点火、喷注及面板和身部热防护进行了考核验证,均得到了较满意的结果。在此基础上研究了RBCC联试中火箭燃烧室的工作性能,试验结果表明:燃烧室的特征速度燃烧效率能达到88%~98%,且受到流量、氧燃比、动量通量比和喷注压降的影响较大,在适合的范围内选取大的动量通量比和喷注压降,能得到更好的雾化、掺混及燃烧性能;气氧/煤油的内直外旋喷嘴构型在煤油压降仅为设计点的11%时,仍能通过有效的气动作用,获得88%以上的特征速度燃烧效率;点火器的吹除气在占到火箭流量5%时,会造成燃烧室3%的性能损失,需要在试验中进行控制并在性能计算时予以考虑。在对火箭单试和联试的比较中发现,联试中由于其特征长度长燃烧更充分,火箭得到了近7%的特征速度燃烧效率增长。
In order to meet the demand of RBCC propulsion system, the design and experimental study of the gas oxygen / kerosene rocket combustion chamber was carried out. Combustion chamber pressure was 2MPa, oxygen combustion ratio was 1.6, rocket flow in the range of 95 ~ 285g / s. Through rocket alone cold and hot test, its flow control, ignition, injection and panel and body thermal protection were tested and verified, have been more satisfactory results. On this basis, the working performance of rocket combustion chamber in RBCC test was studied. The experimental results show that the combustion speed of the combustion chamber can reach 88% ~ 98% at the characteristic velocity, and is affected by the flow rate, oxygen fuel ratio, The pressure drop has a greater impact. Selecting a large flux ratio and injection pressure drop within a suitable range can achieve better atomization, blending and combustion performance. The internal oxygen injection / kerosene internal direct external nozzle When the pressure drop of kerosene is only 11% of the design point, it still can get 88% of the characteristic speed combustion efficiency through the effective aerodynamic effect. The igniter’s purge gas can cause combustion when it accounts for 5% of the rocket flow rate A 3% loss of performance in the room needs to be controlled in the test and taken into account in performance calculations. In a comparison of single rocket tests and pilot tests, it was found that the rocket got nearly 7% of the characteristic speed and the combustion efficiency increased due to its long and characteristic combustion.