Supersonic combustion ramjet missile

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.

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Effects of Chemical Reaction Models on Simulations of Scramjet Nozzle Flow

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.490-491.931 ◽

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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Finite Rate Chemistry Large-Eddy Simulation of Self-Ignition in Supersonic Combustion Ramjet

AIAA Journal ◽

10.2514/1.43746 ◽

2010 ◽

Vol 48 (3) ◽

pp. 540-550 ◽

Cited By ~ 107

Author(s):

M. Berglund ◽

E. Fedina ◽

C. Fureby ◽

J. Tegnér ◽

V. Sabel'nikov

Keyword(s):

Large Eddy Simulation ◽

Supersonic Combustion ◽

Finite Rate ◽

Eddy Simulation ◽

Large Eddy ◽

Supersonic Combustion Ramjet

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Investigation of flow characteristics in supersonic combustion ramjet combustor toward improvement of combustion efficiency

International Journal of Energy Research ◽

10.1002/er.5257 ◽

2020 ◽

Vol 45 (1) ◽

pp. 231-253

Author(s):

Prasanth P. Nair ◽

Amsha S ◽

Abhilash Suryan ◽

Sandro Nizetic

Keyword(s):

Flow Characteristics ◽

Combustion Efficiency ◽

Supersonic Combustion ◽

Ramjet Combustor ◽

Supersonic Combustion Ramjet

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Supersonic Combustion Ramjet Research

10.21236/ada563331 ◽

2012 ◽

Cited By ~ 2

Author(s):

Campbell D. Carter

Keyword(s):

Supersonic Combustion ◽

Supersonic Combustion Ramjet

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Scramjets

The Aeronautical Journal ◽

10.1017/s0001924000004796 ◽

2007 ◽

Vol 111 (1124) ◽

pp. 605-619 ◽

Cited By ~ 50

Author(s):

M. Smart

Keyword(s):

Three Dimensional ◽

Supersonic Combustion ◽

Space Vehicles ◽

Hypersonic Flight ◽

Recent Advances ◽

Multi Stage ◽

Operational Systems ◽

Supersonic Combustion Ramjet ◽

Engine Cycle

Abstract The supersonic combustion ramjet, or scramjet, is the engine cycle most suitable for sustained hypersonic flight in the atmosphere. This article describes some of the challenges facing scramjet designers, and the methods currently used for the calculation of scramjet performance. It then reviews the HyShot 2 and Hyper-X flight programs as examples of how sub-scale flights are now being used as important steps towards the development of operational systems. Finally, it describes some recent advances in three-dimensional scramjets with application to hypersonic cruise and multi-stage access-to-space vehicles.

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