Numerical Simulation of 3-D Chemical Non-Equilibrium Flow in the Afterburning Chamber of Solid Ducked Rocket

2011 ◽  
Vol 130-134 ◽  
pp. 3151-3154
Author(s):  
Li Kun Cui ◽  
Yong Zhi Zhang ◽  
Zhuo Li
Keyword(s):  
Numerical Simulation ◽  
Radical Reaction ◽  
Combustion Efficiency ◽  
Equilibrium Flow ◽  
Air Inlet ◽  
Afterburning Chamber ◽  
Inlet Angle ◽  
Fundamental Equations ◽  
Combustion Processes ◽  
Non Equilibrium

In order to reveal the complex turbulent combustion processes in the afterburning chamber of Solid Ducked Rocket (SDR), Based on the fundamental equations of hydrokinetics and elementary principles of radical reaction kinetics, using multi-component chemical reaction equation of containing Mg and Al components, the numerical simulation of chemical non-equilibrium flow in the afterburning chamber of SDR is processed and effects of the air inlet angle on the afterburning chamber is studied by using Fluent software. The results show that pressure distribution is more balanced, temperature distribution is very uneven and flow is extremely complicated in the afterburning chamber. Combustion efficiency can be increased by improving the air inlet angle.

Numerical Simulation on Two Phase Combustion Characteristic in Solid Rocket Ramjet Afterburning Chamber

2013 ◽  
Vol 774-776 ◽  
pp. 737-742
Author(s):  
Nai Fei Zhang ◽  
Yi Hua Xu ◽  
Zhuo Xiong Zeng ◽  
Ben En Xu
Keyword(s):  
Numerical Simulation ◽  
Particle Trajectory ◽  
Particle Diameter ◽  
Combustion Efficiency ◽  
Combustion Characteristic ◽  
Two Phase ◽  
Afterburning Chamber ◽  
Solid Rocket ◽  
Inlet Angle ◽  
Particle Trajectory Model

Numerical simulation on two-phase combustion characteristic in afterburning chamber of solid rocket ramjet was carried out by applying particle trajectory model. It was analyzed that the nozzle number of secondary combustion chamber, inlet angle of air and particles diameter impact on efficiency of combustion. Results show that the combustion efficiency in the afterburning chamber is highest, achieving 99.6% when the angle between both air inlets is 180°, particle diameter is 15μm, and 5-hole nozzle is used. By contrary, when the angle between both air inlets is 90°, particle diameter is 5μm, and 5-hole nozzle is used, the afterburning chamber has a lowest combustion efficiency of 70.3%.

2D numerical simulation for non-equilibrium flow in gasdynamic laser nozzle

2010 ◽  
Vol 22 (5) ◽  
pp. 959-962 ◽  
Author(s):  
赖林 Lai Lin ◽  
周进 Zhou Jin ◽  
雷静 Lei Jing ◽  
邵艳 Shao Yan
Keyword(s):  
Numerical Simulation ◽  
Gasdynamic Laser ◽  
Equilibrium Flow ◽  
2D Numerical Simulation ◽  
Non Equilibrium

scholarly journals Experimental investigation of the effect of the air inlet angle and the combustion pressure in a ducted rocket combustor

2019 ◽  
Author(s):  
V. Laguzzi ◽  
F. Molinaro ◽  
B. Natan
Keyword(s):  
Flow Direction ◽  
Combustion Efficiency ◽  
Air Injection ◽  
Injection Angle ◽  
Combustion Pressure ◽  
Air Inlet ◽  
Main Flow Direction ◽  
Inlet Angle ◽  
Ducted Rocket ◽  
Energetic Performance

The scope of the study is to evaluate the combustion efficiency of a ducted rocket combustor operating at different conditions, using a connected-pipe testing setup. An experimental parametric investigation was conducted to evaluate the effect of the inlet air-injection angles and the effect of the combustion pressure for different fuel-to-air ratios. The experimental results indicate that best energetic performance was obtained for an injection angle of 120°, i. e., against the main flow direction. The reason is that this way better mixing was obtained and the residence time increased. Characteristic velocity was found to decrease with decreasing the combustion pressure.

scholarly journals Test of aero-heating in hypersonic non-equilibrium flow and numerical simulation study

2018 ◽  
Vol 48 (8) ◽  
pp. 845-852 ◽  
Author(s):  
ChunSheng NIE ◽  
Yu LI ◽  
JianDong HUANG ◽  
WenBo MIAO
Keyword(s):  
Numerical Simulation ◽  
Simulation Study ◽  
Equilibrium Flow ◽  
Non Equilibrium

scholarly journals Numerical Simulation of Non-equilibrium Flow in the Nozzle of VAT-104 Wind Tunnel

2018 ◽  
Vol 19 (2) ◽  
pp. 1-19
Author(s):  
Boris E. Zhestkov ◽  
◽  
Alexander Yu. Kireev ◽  
Aleksey V. Zaytsev ◽  
Sergey V. Chertnov ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Wind Tunnel ◽  
Equilibrium Flow ◽  
Non Equilibrium

Numerical Simulation of Chemical Non-Equilibrium Flow in Hydrocarbon Fuel Scramjet Nozzle

2013 ◽  
Vol 717 ◽  
pp. 342-346
Author(s):  
Bin Zhang ◽  
Bin Yu ◽  
Hong Liu ◽  
Fang Chen
Keyword(s):  
Numerical Simulation ◽  
Dynamic Characteristics ◽  
Great Influence ◽  
Hydrocarbon Fuel ◽  
Equilibrium Flow ◽  
Finite Rate ◽  
Reaction Models ◽  
Nozzle Inlet ◽  
Equilibrium Effect ◽  
Non Equilibrium

Based on 8-specice, 12-step finite-rate chemical reaction models, the chemical non-equilibrium flows of hydrocarbon fuel scramjet single expansion ramp nozzle (SERN) were numerical simulated. The chemical dynamic characteristics of flow in SERN were analyzed in detail. The performances of SERN were compared at various inlet static temperatures. The numerical results show that the chemical non-equilibrium effect had great influence on the performance of the nozzle at the relatively high inlet static temperature. However, influence induced by chemical non-equilibrium effect can be neglected when nozzle inlet static temperature is less than 2500K.

Effect of tangential swirl air inlet angle on the combustion efficiency of a hybrid powder-solid ramjet

2019 ◽  
Vol 159 ◽  
pp. 87-95 ◽  
Author(s):  
Yihua Xu ◽  
Rui Jia ◽  
Humberto Medina ◽  
Haijun Sun
Keyword(s):  
Combustion Efficiency ◽  
Air Inlet ◽  
Inlet Angle
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