Supersonic Combustion

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PERFORMANCE CHARACTERISTICS OF SUPERSONIC COMBUSTION CHAMBER 1PG student, department of mechanical engineering, Bannari amman institute of technology, tamilnadu -638401 Abstract Index terms: scramjet and supersonic combustion, flame holder, design methodology. INTRODUCTION Due to the high velocities in a scramjet combustor the residence time of air and fuel in the combustion chamber is extremely short. Additionally the mixing rates at high flow Mach numbers are inherently low [1]. There are mainly two concepts of fuel injection: 1. wall injectors 2. Strut injectors. Some recent research papers have brought to light the subject of cavity flows and their relevance to flame holding in supersonic combustion engines [2]. The design of a …show more content…

Figure CATIA modeling of DLR scramjet combustion chamber and planer strut injector. Figure 2: combustion chamber model 1 3D planer strut injector A wedge-shaped strut is placed in the combustion chamber downstream of the nozzle. The height of the 32 mm long strut is 0.295 mm and mass flow rate of strut is 1.5 to 4.0g/s. BOUNDARY CONDITIONS In the present study three different types of boundaries are applied: inflow, outflow and fixed walls. The flow fields under consideration here are supersonic. According to the theory of characteristics all variables are prescribed at inflow boundaries, i.e. Dirichlet boundary conditions, and neumann boundary conditions are used for all variables at outflow boundaries.[12] At fixed walls the no slip condition are applied. All computations are initialized with the state of the incoming air. Variables Air H2 Ma 2.0 1.0 U(m/s) 730 1200 T(k) 340

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