1. Design and analysis of a Scramjet combustion Chamber

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Introduction
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Introduction
Developing scramjet is a multi disciplinary task
In aerodynamics related to scramjet the free stream flow has to be decelerated to Mach number close to 2 at the combustor entry
This deceleration has to be done with minimum pressure loss
Developing efficient fuel injection system plays one of the key roles in the development of scramjet engine.
A good fuel injector design delivers optimum mixing, penetration with minimum total pressure loss.
Wall injection offers simplicity, rapid penetration and mixing accompanied by higher total pressure loss
Normal injection offers maximum mixing efficiency and flame holding by upstream recirculation region
Staged injection offers better mixing than the single injector due to the strong interaction between the injectors
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Introduction
The efficiency of the fuel injector configuration determines the length of the combustor
Counter rotating vortex pair to be the important mechanism for mixing
Organised longitudinal vorticity is necessary for mixing enhancement
The near field mixing is dominated by the vortices generated due to the jets and is affected by the combustor geometry
Far field mixing is dominated by the small scale turbulence diffusion and is insensitive to combustor geometry, free stream Mach number and the injectant molecular weight.
The transition of vortex driven mixing in the near field to turbulence diffusion in the far field occurs between 10 to 20 jet diameters downstream of the injectors.
Decay of maximum concentration is inversely proportional to the square of downstream distance.
Higher momentum flux ratio results in slower mixing rate, higher penetration and more loss in total pressure
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Aim
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Objectives
To design a scramjet engine model without nozzle and aft body
To design the wall fuel injector geometry for an injection angle of 90°
To find the difference in mixing efficiency and total pressure loss ratio between 45° and 90° injection
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Design of high ICR inlet
Separation control
Combustion chamber design
Optimisation
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11. Variation of flight speed with time
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12. Physical characteristics of hypersonic flow
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Engine performance
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Road Map
Literature Survey
Design of supersonic intake
Enhancing the starting of the intake
Design of 90 ° injection geometry
To Compare 90° and 45° injection results
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Finished Project
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Flow Development
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