Intense vibration mechanism analysis and vibration control technology for the combustion chamber of a liquid rocket engine

2018 ◽  
Vol 437 ◽  
pp. 53-67
Author(s):  
Dahua Du ◽  
Erming He ◽  
Daoqiong Huang ◽  
Guangxu Wang
Keyword(s):  
Vibration Control ◽  
Combustion Chamber ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Control Technology ◽  
Mechanism Analysis ◽  
Vibration Mechanism ◽  
Liquid Rocket ◽  
Intense Vibration

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

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.

Mathematical simulation of coolant flow in the cooling channel of a liquid rocket engine combustion chamber featuring an extremely high degree of ribbing

2019 ◽  
Author(s):  
V.P. Aleksandrenkov ◽  
K.E. Kovalev ◽  
D.A. Yagodnikov
Keyword(s):  
Combustion Chamber ◽  
Mass Flow Rate ◽  
Flow Rate ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Cooling Channel ◽  
Additive Technology ◽  
Engine Combustion ◽  
Liquid Rocket ◽  
High Degree

The paper presents a computational analysis of coolant distribution in the cooling channel of a liquid rocket engine combustion chamber, performed in order to develop a set of practical guidelines towards increasing efficiency of a cooling system featuring an extremely high degree of ribbing. We created a three-dimensional mathematical model comprising a closed system of hydrodynamic equations as well as initial and boundary conditions for an element of the liquid rocket engine chamber we modelled, the chamber featuring longitudinal cooling channel arrangement manufactured via additive technology. We computed velocity and pressure fields in characteristic cooling channel regions for various levels of coolant mass flow rate, which confirmed the feasibility of the layout proposed in terms of uniform coolant distribution in the cooling channel of the liquid rocket engine modelled. We obtained the friction loss ξ as a function of coolant mass flow rate and particle size of the powder used in the additive technology to manufacture the combustion chamber wall and cooling channel.

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