Numerical Simulation of a Pintle Variable Thrust Rocket Engine

2011 ◽  
pp. 477-481 ◽  
Author(s):  
Chun-guo Yue ◽  
Xin-Long Chang ◽  
Shu-jun Yang ◽  
You-hong Zhang
Keyword(s):  
Numerical Simulation ◽  
Rocket Engine

Numerical simulation of cryotechnic rocket engine ignition

1991 ◽  
Author(s):  
P. BAUDART ◽  
V. DUTHOIT ◽  
J. HARLAY
Keyword(s):  
Numerical Simulation ◽  
Rocket Engine

Numerical Simulation of the Two-Phase Turbulent Combustion Flow in the Multicomponent Propellant Rocket Engine

2012 ◽  
Vol 452-453 ◽  
pp. 1334-1338
Author(s):  
De Song Liu ◽  
Hong Fu Qiang ◽  
Xue Li Xia ◽  
Guang Wang
Keyword(s):  
Numerical Simulation ◽  
Turbulent Combustion ◽  
Gas Flow ◽  
Rocket Engine ◽  
Two Phase ◽  
Fuel Droplets ◽  
Simulation Based ◽  
Combustion Flow ◽  
Simulation Programme ◽  
Propellant Rocket

The numerical simulation, based on computational fluid dynamics methodology, has been performed to study the two-phase turbulent combustion flow in rocket engine using non-metallized multicomponent propellant. A reduced reaction mechanism is developed for modelling combustion of fuel droplets in the absence of metal. Gas governing equations are two dimensional axisymmetric N-S equations in Eulerian coordinates. The trajectory model is adopted to analyse the droplet-phase including the droplet collision, breakup and evaporation. The gas flow is influenced by the droplets by adding source term to N-S equations. The reliability of the simulation programme is validated by comparing numerical simulation result with engine test data.

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.

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