GS38 Failure Mechanism of Liquid Rocket Engine Combustion Chamber with Outer Shell : Crack Generation Mechanism in Upper Stage Engine

2013 ◽  
Vol 2013 (0) ◽  
pp. _GS38-1_-_GS38-3_
Author(s):  
Miki NISHIMOTO ◽  
Hideyo NEGISHI ◽  
Koji OGURA ◽  
Hideo SUNAKAWA ◽  
Shinobu YOSHIMURA ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Failure Mechanism ◽  
Rocket Engine ◽  
Outer Shell ◽  
Generation Mechanism ◽  
Liquid Rocket Engine ◽  
Crack Generation ◽  
Engine Combustion ◽  
Upper Stage ◽  
Liquid Rocket

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

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.

Sign in / Sign up

Export Citation Format

Share Document