气/液同轴喷嘴常压雾化燃烧实验研究

【作者】 何浩波；

【导师】 李进贤；

【作者基本信息】 西北工业大学 ， 火炮、自动武器与弹药工程， 2003， 硕士

【摘要】 在液体火箭发动机中，推进剂组元迅速而高效的气化和混和是产生高质量燃烧所必须的重要条件。达到这一目标的关键在于通过喷嘴使推进剂组元产生良好的雾化，因此，喷嘴是液体火箭发动机推力室最关键的部件之一，对其进行充分的理论和实验研究十分必要。由于喷嘴雾化及其喷雾流的蒸发、混和和燃烧是一个非常复杂的物理化学过程，目前国内外对喷嘴的研究仍以模型实验研究为主。 本文应用激光多普勒技术对三种气／液同轴模型喷嘴的流量特性和雾化特性进行了冷流模拟实验研究，并在常压燃烧条件下对其喷雾流的液滴参数和燃烧性能进行了实验测量。此外，应用红外热成像技术对喷雾流火焰温度分布进行了初步分析。确定了这些喷嘴在冷流模拟条件和常压燃烧条件下的流量特性、雾化特性以及喷雾流火焰的温度场特性，比较分析了不同喷嘴结构形式、不同工况对雾化性能和燃烧性能的影响。实验结果表明，喷雾液滴速度小于40m／s时，所研究的同轴喷嘴可以获得稳定燃烧的火焰。更多还原

【Abstract】 For liquid propellant rocket engine, it is an important condition for effective combustion that propellant be evaporated and mixed quickly. The key is atomizing the propellant perfectly through nozzles, which are the most important elements in the chamber of liquid propellant rocket engine. It is very necessary of the experimental and theoretic to research on them. The physical and chemical processes of nozzle atomization and the evaporation, mixing and combustion of propellant drop flow are very complex. For the reason, the researches on nozzle are still based on the experimental research now in or abroad.This article has a particular research on three kind of Gas/Liquid coaxial nozzles for their flow performance and atomization performance under cold-flow-simulated experiment with the supply of Laser Doppler technology, and the measurement of the drop parameter and combustion performance under normal pressure and burning condition. Furthermore, primary analyse of temperature distribution has been done with Infrared Thermal Imager technology. Results of atomization performance in cold-flow-simulated experiment and burning experiment and temperature distribution are reached, influence of nozzle stucture and working condition with atomization performance and conbustion performance are analyzed. The experiment results indicate: when the velocity of propellant drops belows 40 m/s, the researched nozzles can obtain stably burning blaze.更多还原