Combustion Characteristics of Ducted Rocket Engine in the Mars

2011 ◽  
Author(s):  
Hideki Hara ◽  
Masamichi Ushijma ◽  
Akinori Muramatsu ◽  
Takuo Kuwahara
Keyword(s):  
Rocket Engine ◽  
Combustion Characteristics ◽  
Ducted Rocket

Experimental study on combustion characteristics of powder magnesium and carbon dioxide in rocket engine

2019 ◽  
Vol 155 ◽  
pp. 334-349 ◽  
Author(s):  
Yue Li ◽  
Chunbo Hu ◽  
Xiaofei Zhu ◽  
Jiaming Hu ◽  
Xu Hu ◽  
...  
Keyword(s):  
Carbon Dioxide ◽  
Experimental Study ◽  
Rocket Engine ◽  
Combustion Characteristics

Performance Demonstration of a Variable Flow Ducted Rocket Engine by Test Flight

2009 ◽  
Author(s):  
Yoshihiro Yamano ◽  
Yoshiyuki Ikegami ◽  
Hisahiro Nakayama ◽  
Eishu Kimura ◽  
Junich Sato ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Variable Flow ◽  
Test Flight ◽  
Ducted Rocket ◽  
Performance Demonstration

scholarly journals Effects of LOX Particle Diameter on Combustion Characteristics of a Gas-Liquid Pintle Rocket Engine

2020 ◽  
Vol 2020 ◽  
pp. 1-16
Author(s):  
Xuan Jin ◽  
Chibing Shen ◽  
Rui Zhou ◽  
Xinxin Fang
Keyword(s):  
Rocket Engine ◽  
Oscillation Amplitude ◽  
Three Dimensional ◽  
Particle Diameter ◽  
Low Frequency ◽  
Pressure Oscillation ◽  
Combustion Efficiency ◽  
Combustion Characteristics ◽  
Rocket Engines ◽  
Liquid Rocket

LOX/GCH4 pintle injector is suitable for variable-thrust liquid rocket engines. In order to provide a reference for the later design and experiments, three-dimensional numerical simulations with the Euler-Lagrange method were performed to study the effect of the initial particle diameter on the combustion characteristics of a LOX/GCH4 pintle rocket engine. Numerical results show that, as the momentum ratio between the radial LOX jet and the axial gas jet is 0.033, the angle between the LOX particle trace and the combustor axial is very small. Due to the large recirculation zones, premixed combustion mainly occurs in the injector wake region. As the initial LOX particle diameter increases, the LOX evaporation rate and the combustion efficiency decrease until the combustion terminates with the initial LOX particle diameter greater than 110 μm. The oscillation amplitude of the combustor pressure increases significantly along with the increase of the initial LOX particle diameter, and the low-frequency unstable combustion occurs when the initial LOX particle diameter exceeds 60 μm. The combustor pressure oscillation at about 40 Hz couples with the swinging process of spray and flame, while the unsteady LOX evaporation amplifies the combustor pressure oscillations at 80 Hz and its harmonic frequency.

An investigation of four-inlet ducted rocket engine flameholding characteristics

1997 ◽  
Author(s):  
Christopher Brophy ◽  
Clark Hawk ◽  
John Bush ◽  
Christopher Brophy ◽  
Clark Hawk ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Ducted Rocket

Combustion Characteristics of Ethanol/Liquid-Oxygen Rocket-Engine Combustor with Planar Pintle Injector

2017 ◽  
Vol 33 (2) ◽  
pp. 514-521 ◽  
Author(s):  
Kazuki Sakaki ◽  
Hiromitsu Kakudo ◽  
Shinji Nakaya ◽  
Mitsuhiro Tsue ◽  
Kyohei Suzuki ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Combustion Characteristics ◽  
Liquid Oxygen
Sign in / Sign up

Export Citation Format

Share Document