Numerical analysis of supersonic combustion ramjet with upstream fuel injection

2003 ◽  
Vol 43 (2) ◽  
pp. 165-181 ◽  
Author(s):  
Raffaele Savino ◽  
Giuseppe Pezzella
Keyword(s):  
Numerical Analysis ◽  
Fuel Injection ◽  
Supersonic Combustion ◽  
Supersonic Combustion Ramjet

Numerical Studies on the Performance of Scramjet Combustor with Alternating Wedge-Shaped Strut Injector

2017 ◽  
Vol 34 (1) ◽  
Author(s):  
Gautam Choubey ◽  
K. M. Pandey
Keyword(s):  
Numerical Analysis ◽  
Flow Structure ◽  
Fuel Injection ◽  
Angle Of Attack ◽  
Supersonic Combustion ◽  
Scramjet Combustor ◽  
Numerical Studies ◽  
Scramjet Engine

AbstractNumerical analysis of the supersonic combustion and flow structure through a scramjet engine at Mach 7 with alternating wedge fuel injection and with three angle of attack (

Computational investigation of multi-cavity fuel injection on hydrogen mixing at supersonic combustion chamber

2020 ◽  
Vol 45 (15) ◽  
pp. 9077-9087 ◽  
Author(s):  
Zhixiong Li ◽  
Tran Dinh Manh ◽  
M. Barzegar Gerdroodbary ◽  
Nguyen Dang Nam ◽  
R. Moradi ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Fuel Injection ◽  
Supersonic Combustion ◽  
Computational Investigation

Investigation of the Formation of Microbubbly Liquid Fuel

2009 ◽  
Author(s):  
Emine Celik ◽  
Joseph Katz ◽  
David M. Van Wie
Keyword(s):  
Liquid Fuel ◽  
Gas Bubbles ◽  
Supersonic Combustion ◽  
Short Chain ◽  
Experimental Facility ◽  
Second Stage ◽  
Thermal Pyrolysis ◽  
New Type ◽  
Supersonic Combustion Ramjet ◽  
Long Chain

There are several obstacles encountered during combustion in Supersonic Combustion Ramjet (SCRAMJET) engines such as mixing, ignition, and flame holding. In order to overcome these difficulties, a new type of fuel is generated with the use of combination of two methods namely an effervescent (barbotage) and thermal pyrolysis of the fuel. In the first step of the process, during effervescent method, small gas bubbles are introduced into liquid fuel to improve the spraying characteristics of the fuel. At the second stage, long-chain hydrocarbons are broken down into short-chain hydrocarbons that burn faster. An experimental facility has been designed and developed to study the underlying physics in each process.

Effect of Fuel Injection Locations with a Hyper Mixer in Supersonic Combustion

2011 ◽  
Author(s):  
Chae-Hyoung Kim ◽  
In-Seuck Jeung ◽  
Byungil Choi ◽  
Toshinori Kouchi ◽  
Goro Masuya
Keyword(s):  
Fuel Injection ◽  
Supersonic Combustion

Effects of Chemical Reaction Models on Simulations of Scramjet Nozzle Flow

2014 ◽  
Vol 490-491 ◽  
pp. 931-935
Author(s):  
Xiao Yuan Zhang ◽  
Li Zi Qin ◽  
Yu Liu
Keyword(s):  
Kinetic Models ◽  
Chemical Kinetic ◽  
Numerical Results ◽  
Supersonic Combustion ◽  
Equilibrium Flow ◽  
Reaction Models ◽  
Total Temperature ◽  
Supersonic Combustion Ramjet ◽  
Quantity Of Heat ◽  
Non Equilibrium

The chemical non-equilibrium flow of supersonic combustion ramjet (scramjet) nozzle is numerical simulated with different chemical kinetic models to research the effects on numerical results of the nozzle performance. The numerical results show that total temperature is increased due to the recombination of dissociation compositions and the combustion of the residual fuel. The effect of the combustion of the residual fuel is more obvious in this paper, and the effect to the performance of the nozzle is noticeable. The species of the compositions in the models influence the quantity of heat sending out when it get equilibrium, so the 9-species chemical kinetic models are more suitable in the simulation of the scramjet nozzle chemical non-equilibrium flows.

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