Optical Measurement for Injection-Coupled Unsteady Combustion Behaviors of a Shear Coaxial Injector in Liquid Oxygen/Hydrogen Rocket Engine Combustor

2020 ◽  
Vol 68 (2) ◽  
pp. 72-81
Author(s):  
Kazuki Sakaki ◽  
Yoshio Nunome ◽  
Takeo Tomita
Keyword(s):  
Optical Measurement ◽  
Rocket Engine ◽  
Liquid Oxygen ◽  
Unsteady Combustion ◽  
Shear Coaxial Injector ◽  
Combustion Behaviors ◽  
Coaxial Injector

Spray and Combustion Modeling in High Pressure Cryogenic Jet Flames

2012 ◽  
Author(s):  
Maria Grazia De Giorgi ◽  
Aldebara Sciolti ◽  
Antonio Ficarella
Keyword(s):  
Supercritical Pressure ◽  
Liquid Oxygen ◽  
Rocket Engines ◽  
Liquid Propellant ◽  
Combustion Modeling ◽  
Discrete Phase ◽  
Real Behavior ◽  
Shear Coaxial Injector ◽  
Coaxial Injector ◽  
Propellant Rocket

The aim of the present work is the investigation of the combustion phenomenon in liquid-propellant rocket engines. The combustion of liquid oxygen and gaseous methane in a shear coaxial injector under supercritical pressure was analyzed. To realize an efficient numerical description of the phenomena, it is important to treat the LOx jet in a manner which takes into account its real behavior. In the present work different kinetics, combustion models and thermodynamics approaches were used in association with the description of the jet as a discrete phase. For all the approaches used, a comparison with experimental data from literature was performed.

Measurements of shear coaxial injector sprays - Cold flow and hot fire experiments

1996 ◽  
Author(s):  
M. Ferraro ◽  
R. Kujala ◽  
J.-L. Thomas ◽  
M. Glogowski ◽  
M. Micci
Keyword(s):  
Cold Flow ◽  
Shear Coaxial Injector ◽  
Coaxial Injector ◽  
Fire Experiments

Critical Suction Peformance Test of Turbopump Assembly for a Liquid-Propellant Rocket Engine

2018 ◽  
Author(s):  
Hang Gi Lee ◽  
Ju Hyun Shin ◽  
Suk Hwan Yoon ◽  
Dae Jin Kim ◽  
Jun Hwan Bae ◽  
...  
Keyword(s):  
Liquid Nitrogen ◽  
Performance Test ◽  
Rocket Engine ◽  
Lightweight Design ◽  
Cavitation Number ◽  
Inlet Pressure ◽  
Liquid Oxygen ◽  
Pump Failure ◽  
Critical Cavitation ◽  
Suction Performance

This study investigates the behavior of a turbopump assembly during critical cavitation of the propellant pumps in the upper rocket engine of the Korea Space Launch Vehicle-II. Turbopumps operate under conditions involving low pressure at the pump inlet and high rotational speeds to allow for a lightweight design. This severe environment can easily cause cavitation to occur in the pump. This cavitation can then cause the pump operation to fail. As the cavitation number in the pump decreases below the critical point, the pump fails to operate. There is concern regarding the behavior of the turbopump assembly arising from pump failure due to cavitation. It is necessary to verify the problems that may occur if the turbopump assembly operates under extreme conditions, such like the critical cavitation. This study performed tests to investigate the breakdown of pumps in the turbopump assembly. Tests were conducted with liquid nitrogen, water, and high-pressure air instead of the mediums used during actual operation of liquid oxygen, kerosene, and hot gas. The turbopump was tested at the design point of 27,000 rpm, while the inlet pressure of each pump was controlled to approach the critical cavitation number. The turbine power output was maintained during the tests. The results show that the breakdown point of the oxidizer pump using liquid nitrogen, which is a cryogenic medium, occurred at a lower cavitation number than during an individual component suction performance test using water. The fuel pump using water, meanwhile, experiences breakdown at similar cavitation numbers in both tests. As the breakdown of the pump occurs, the power required by that pump decreases, and the rotational speed of the turbopump increases. Compared with individual pump suction performance tests, this breakdown test can be used to determine the limit of the propellant inlet pressure of the turbopump and to characterize the behavior of the turbopump assembly when a breakdown occurs. Vibrations were also analyzed for tests at a high cavitation number and at the critical cavitation number. The vibration increased with breakdown and notable frequencies were analyzed.

scholarly journals Effect of excitation on gas centered swirl coaxial injectors

2017 ◽  
Author(s):  
Youngbin Yoon ◽  
Gujeong Park ◽  
Sukil Oh ◽  
Jinhyun Bae
Keyword(s):  
Momentum Flux ◽  
Rocket Engine ◽  
Combustion Instability ◽  
Electrical Conductance ◽  
Flux Ratio ◽  
Xenon Lamp ◽  
Momentum Flux Ratio ◽  
Conductance Method ◽  
Liquid Rocket ◽  
Coaxial Injector

Studies on combustion instability in liquid rocket engines are important in improving combustion efficiency andpreventing combustion chamber losses. To prevent combustion instability, methods such as baffles and cavities are used. The injector is located in the middle of the perturbation-propagation process in the rocket engine, so it is important to study the suppression of combustion instability using the design of the injector. Much research has been focused on the study of liquid excitation in a single injector; however, the actual injector used in a liquid rocket engine is a coaxial injector. In this study, the dynamic characteristics of a gas-centred swirl coaxial injector were investigated by varying the gap thickness and momentum-flux ratio. Spray photographs were captured by synchronizing a stroboscope and digital camera, and a high-speed camera and Xenon lamp were also used. To measure the liquid film, a measurement system was implemented using the electrical conductance method. For excitation of the gas, an acoustic speaker was used to impart a frequency to the gas. The gGas velocity and effect of excitation were measured by hot-wire anemometry. A mechanical pulsator was used for liquid flow excitation. Liquid fluctuation was measured by a dynamic pressure sensor. In both gas and liquid excitation cases, the gain increased as the gap thickness decreased and the momentum-flux ratio increased. From these results, it can be concluded that gap thickness and momentum-flux ratio are major factors in suppressing combustioninstability. DOI: http://dx.doi.org/10.4995/ILASS2017.2017.4653

Infrared radiation characteristics of liquid oxygen/kerosene rocket engine plume with different number of nozzles

2019 ◽  
Vol 52 (3-4) ◽  
pp. 159-167
Author(s):  
Hong-Hua Cai ◽  
Wan-Sheng Nie ◽  
Ling-Yu Su ◽  
Tian-yi Shi ◽  
Kang-Kang Guo
Keyword(s):  
Infrared Radiation ◽  
Rocket Engine ◽  
Liquid Oxygen ◽  
Radiation Characteristics
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