Publicou 12 edições por ano
ISSN Imprimir: 1044-5110
ISSN On-line: 1936-2684
Indexed in
SHEAR COAXIAL INJECTOR LOX DROPLET MEASUREMENTS AS A FUNCTION OF HYDROGEN INJECTION TEMPERATURE
RESUMO
A hydrogen gas chiller was designed and fabricated in order to simulate the hydrogen temperature ramping test for liquid rocket engines in a single-element gaseous hydrogen/liquid oxygen combustion chamber. Hot fire PDPA measurements of droplet sizes and velocities as a function of the gaseous hydrogen temperature for a fixed mass flow and shear coaxial injector configuration were obtained as the hydrogen temperature was varied from 130 to 290 K, resulting in a doubling of the hydrogen/oxygen velocity and momentum flux ratios. Measured droplet Sauter and arithmetic mean diameters decreased as the hydrogen temperature increased. However, even though the hydrogen temperature change resulted in a doubling of the velocity and momentum flux ratios, the droplet Sauter mean diameter only decreased by 12.5%. These results indicate that the increase in droplet size as the injected hydrogen temperature is decreased may not be a significant contributor to the resulting combustion instability for liquid rocket engines operating at the conditions examined in this study.
-
Feng Songjiang, Nie Wansheng, He Bo, Zhuang Fengchen, Control Effects of Baffle on Combustion Instability in a LOX/GH2 Rocket Engine, Journal of Spacecraft and Rockets, 47, 3, 2010. Crossref
-
Manfletti Chiara, Low Ambient Pressure Injection and Consequences on Ignition of Liquid Rocket Engines, 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2012. Crossref
-
Feng Songjiang, Cheng Yufeng, Nie Wansheng, Combustion Instability Analysis in a Hydrogen-Oxygen Rocket Engine, 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2009. Crossref
-
Feng Songjiang, Nie Wansheng, A Numerical Study of Oxygen/Hydrogen Mixing and Combustion of a Shear Coaxial Injector, 42nd AIAA Thermophysics Conference, 2011. Crossref
-
Manfletti Chiara, Laser Ignition of an Experimental Cryogenic Reaction and Control Thruster: Pre-Ignition Conditions, Journal of Propulsion and Power, 30, 4, 2014. Crossref
-
Gröning Stefan, Hardi Justin, Suslov Dmitry, Oschwald Michael, Influence of hydrogen temperature on the stability of a rocket engine combustor operated with hydrogen and oxygen, CEAS Space Journal, 9, 1, 2017. Crossref
-
Gröning Stefan, Hardi Justin S., Suslov Dmitry, Oschwald Michael, Injector-Driven Combustion Instabilities in a Hydrogen/Oxygen Rocket Combustor, Journal of Propulsion and Power, 32, 3, 2016. Crossref
-
Hardi Justin, Oschwald Michael, Dally Bassam B., Study of LOx/H2 Spray Flame Response to Acoustic Excitation in a Rectangular Rocket Combustor, 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2013. Crossref