scholarly journals Numerical simulation of operation processes in the combustion chamber and gas generator of oxygen-methane liquid rocket engine

2009 ◽  
Author(s):  
G. P. Kalmykov ◽  
A. A. Larionov ◽  
D. A. Sidlerov ◽  
L. A. Yanchilin
Keyword(s):  
Numerical Simulation ◽  
Combustion Chamber ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Gas Generator ◽  
Liquid Rocket

scholarly journals Investigating the Specifics of Work Cycle Evolution in the Combustion Chamber of an Oxygen/Kerosene Liquid Rocket Engine

2019 ◽  
pp. 34-46 ◽  
Author(s):  
S.V. Mosolov ◽  
D.A. Sidlerov
Keyword(s):  
Numerical Simulation ◽  
Combustion Chamber ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Work Cycle ◽  
Recirculation Zones ◽  
Liquid Rocket

The paper considers the specifics of gasification, mixing and burnout processes for propellant components in a combustion chamber featuring coaxial bicentrifugal injectors and operating in the liquid/liquid mode employing oxygen and the T-1 and T-6 kerosene types. Numerical simulation revealed that when using the T6 fuel, the structure of recirculation zones appearing in the leading region of the combustion chamber may provide more efficient oxygen and kerosene mixing and burnout as compared to a chamber running on the T-1 fuel

scholarly journals Failure mechanism and life evaluation of liquid rocket engine combustion chamber under severe multi-physics conditions

2015 ◽  
Vol 81 (826) ◽  
pp. 14-00674-14-00674
Author(s):  
Miki NISHIMOTO ◽  
Hideyo NEGISHI ◽  
Shinobu YOSHIMURA ◽  
Naoto KASAHARA ◽  
Hiroshi AKIBA ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Failure Mechanism ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Life Evaluation ◽  
Engine Combustion ◽  
Liquid Rocket

Numerical Simulation of the Spray Characteristics in Small Scale Liquid Rocket Engine Combustion Chamber

2011 ◽  
Vol 383-390 ◽  
pp. 7729-7733
Author(s):  
Na Zhao ◽  
Yong Gang Yu ◽  
Yu Qiang Wang
Keyword(s):  
Numerical Simulation ◽  
Surface Tension ◽  
Rocket Engine ◽  
Nozzle Diameter ◽  
Small Scale ◽  
Liquid Rocket Engine ◽  
Liquid Droplets ◽  
Liquid Propellant ◽  
Fluent Software ◽  
Liquid Rocket

The mathematical and physical model of the liquid propellant spray in straight nozzle was proposed for studying the performance characteristics of the small-scale liquid rocket engine. With the Fluent software, the numerical simulation was carried out. Sauter mean diameter (SMD) of the HAN-based liquid propellant (LP1846) in the engine combustor changing with spray pressure, nozzle diameter and the liquid surface tension were analyzed. The results indicate that: in the spray pressure region of 1.8MPa~3.0MPa, at a fixed spray pressure, the smaller is the nozzle diameter, the smaller is the droplets’ SMD and the relationship between the SMD and the nozzle diameter is approximately linearity; for the same nozzle diameter and spray pressure, the larger is the surface tension, the larger is the liquid droplets’ SMD.

Performances Study of Liquid Rocket Engine

2014 ◽  
Vol 555 ◽  
pp. 84-90
Author(s):  
Grigore Cican ◽  
Daniel Eugeniu Crunteanu ◽  
Mohamed Yassir El Azzioui
Keyword(s):  
Combustion Chamber ◽  
Firing Temperature ◽  
Rocket Engine ◽  
Thermal Dissociation ◽  
Liquid Hydrogen ◽  
Combustion Reaction ◽  
Liquid Rocket Engine ◽  
Liquid Rocket

The article presents the performance of the liquid rocket engine. It will study the combustion reaction of the liquid hydrogen and oxygen without thermal dissociation. The main elements studied are the influence of the exces of the oxidant on firing temperature, on exhaust velocity, on the evacutation temperature from the engine and on the ishotermal coefficient. The pressure influence from the combustion chamber on the evacuation velocity, on the temperature from the evacuation from the exhaustion section and on the isentropic index.

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