Gas / Liquid Coaxial Nozzle At Atmospheric Pressure Atomization Combustion Experimental Study

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.