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为探索磁流体发电技术在高超声速飞行器上的应用,研制了基于燃气发生器的高温燃气实验系统。介绍了燃烧工质的选取、工况的选择以及实验系统的调试机理、运行情况。结果表明,采用航空煤油做燃料,气氧做氧化剂,混合比为1.2~12的条件下满足温度大于2600K的要求;煤油流量作为基准值,通过调节氧气路孔板流量计前压力能很好地调节燃气发生器的温度;通过调试确定了系统运行的时序,并进行了燃烧温度为3278.5K的点火实验。电导率的测试实验表明,在燃气温度2750K的情况下,燃气电导率的平均值达到10S/m,峰值15S/m,满足磁流体发电的技术要求。
In order to explore the application of MHD technology in hypersonic vehicle, a high temperature gas experimental system based on gas generator was developed. The choice of combustion medium, the selection of operating conditions and the debugging mechanism and operation of the experimental system are introduced. The results show that the use of aviation kerosene as fuel, oxygen and oxygen as the oxidant, the mixing ratio of 1.2 to 12 to meet the requirements of the temperature is greater than 2600K; kerosene flow rate as a reference value, by adjusting the Oxygen orifice orifice flow meter pressure well Adjust the temperature of the gas generator; through the debugging to determine the timing of the system operation, and the combustion temperature of 3278.5K ignition experiment. Conductivity tests show that at a gas temperature of 2750K, the average gas conductivity reaches 10S / m and a peak value of 15S / m, meeting the technical requirements for magnetoelectric power generation.