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Evaluation of a ramp cavity based concept supersonic combustor using CFD
A. Rajasekaran,
Published in
2009
Volume: 9
   
Issue: 1
Pages: 16 - 29
Abstract
In this paper, numerical simulations of a full scale concept supersonic combustor using kerosene fuel are presented. Results are reported first for a baseline model. These results are then used for identifying the shortcomings in this model, which allows improvements to be made. In particular, the spacing between the ramps is widened so that the heat addition is not confined to a short region and is distributed over a larger volume. Also the design of fuel supply lines has been reworked so that they do not obstruct the supersonic flow. Details of the flow field inside the combustor such as contours of static pressure, static temperature, species mass fraction, reaction rate and Mach number are discussed. Wall static pressure distribution along the top wall of the combustor is presented. Intricate details of the flow field such as separation zones, shocks and expansion fans and their interaction are also brought out. Finally, thrust developed by the combustor is calculated using two different methods. Copyright © 2009 Inderscience Publishers.
About the journal
JournalProgress in Computational Fluid Dynamics
ISSN14684349
Open AccessNo
Concepts (28)
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    Combustion
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    Computer simulation
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    Flow fields
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    Flow of fluids
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    Kerosene
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    Mach number
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    Mathematical models
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    RAMJET ENGINES
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    Reaction rates
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    Supersonic aerodynamics
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    Thermochemistry
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    BASELINE MODELS
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    EXPANSION FANS
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    FUEL SUPPLIES
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    FULL SCALES
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    KEROSENE FUELS
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    MASS FRACTIONS
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    Numerical simulations
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    Scramjet
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    SEPARATION ZONES
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    SHORT-COMINGS
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    STATIC PRESSURE DISTRIBUTIONS
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    Static pressures
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    STATIC TEMPERATURES
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    Supersonic combustion
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    SUPERSONIC COMBUSTORS
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    TWO DIFFERENT METHODS
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    Combustors