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为了有效地应用气动谐振管加热现象的热效应 ,以发展液体火箭发动机的气动谐振管点火新技术 ,需要获得谐振管热效应的变化规律。实验测量了三种谐振管 ,即圆柱型、阶梯型和锥柱型谐振管间的表面加热温度。实验中主要考虑喷嘴与谐振管间的分离距离以及供气压力的变化。所获得的谐振加热特性可用于实际谐振加热装置的设计。
In order to effectively apply the thermal effect of the heating phenomenon of the pneumatic resonance tube and to develop the new technology of ignition of the pneumatic resonance tube of the liquid rocket motor, the variation rule of the thermal effect of the resonance tube needs to be obtained. Three kinds of resonant tubes were measured experimentally, that is, the surface heating temperature between cylindrical, stepped and cone-type resonant tubes. In the experiment, the separation distance between the nozzle and the resonance tube and the change of the supply pressure were mainly considered. The resonant heating characteristics obtained can be used in the design of an actual resonant heating device.