Numerical simulations of the 3D reacting flow in a model supersonic combustor with kerosene as the fuel have been carried out. The combustor entry Mach number is nominally 2.5. Tetrahedral grids with wall y+ less than 75 have been used. 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. Also, the variation of metrics such as combustion efficiency and total pressure loss along the length of the combustor are presented. Predicted values of wall static pressure along the top wall of the combustor are compared with previously reported experimental data. The calculations over predict the pressure rise due to combustion in the cavity region, but the overall pressure rise is predicted well. Copyright © 2009 Inderscience Publishers.

Viswanathan T. Babu

Department of Mechanical Engineering

A. Rajasekaran

Aerodynamics

Combustors

compressibility

Computer simulation

Flow simulation

Kerosene

Mach number

Mathematical models

RAMJET ENGINES

Reaction rates

smoke

Thermochemistry

three dimensional

CAVITY REGIONS

Combustion efficiencies

Experimental datums

MASS FRACTIONS

MODEL COMBUSTORS

Numerical simulations

Predicted values

PRESSURE RISES

Reacting flows

Scramjet

Static pressures

STATIC TEMPERATURES

Supersonic combustion

SUPERSONIC COMBUSTORS

TOTAL PRESSURES

combustion

IIT Madras is a public technical and research university located in Chennai, Tamil Nadu. Founded in 1959, it is recognised as an Institute of National Importance.

IIT Madras has been ranked as the top engineering institute in India for four years in a row by the National Institutional Ranking Framework of the MHRD

It currently offers undergraduate, postgraduate and research degrees across 16 disciplines in Engineering, Sciences, Humanities and Management. About 596 faculty belonging to science and engineering departments and centres of the Institute are engaged in teaching, research and industrial consultancy.

IIT Madras

Numerical simulation of the supersonic combustion of kerosene in a model combustor

Progress in Computational Fluid Dynamics

In this numerical study, supersonic combustion of liquid kerosene in a strut-based combustor is investigated. To this end, three-dimensional compressible, turbulent, nonreacting and reacting flow calculations with a single-step chemistry model have been carried out. For the nonreacting flow calculations, fuel droplet trajectories, degree of mixing, and mixing efficiency are presented and discussed. For the reacting flow calculations, contours of heat release and Mach number and the variation of combustion efficiency, total pressure loss, and thrust profile along the combustor length are used to identify the regions of mixing and heat release inside the combustor. Furthermore, the predicted variation of static pressure along the combustor top wall is compared with experimental data. The significance of the lateral spread of the fuel and the extent of the mixing process, especially for a liquid fuel such as kerosene, on the prediction of heat release is discussed in detail. Copyright © 2010 by Luca Boccaletto.

Journal of Propulsion and Power

Numerical investigation of the supersonic combustion of kerosene in a strut-based combustor

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.

Evaluation of a ramp cavity based concept supersonic combustor using CFD

In this numerical study, supersonic combustion of kerosene in three model combustor configurations is investigated. To this end, 3-D, compressible, turbulent, nonreacting, and reacting flow calculations with a single step chemistry model have been carried out. For the nonreacting flow calculations, the droplet diameter distribution at different axial locations, variation of the Sauter mean diameter, and the mixing efficiency for three injection pressures are presented and discussed. In addition, the effect of turbulent dispersion on the mixing efficiency is studied using a stochastic model in conjunction with the two-equation shear stress transport κ-ω turbulence model. For the reacting flow calculations, contours of heat release and axial velocity at several axial locations are used to identify regions of heat release inside the combustor. Combustion efficiency predicted by the present results is compared with earlier predictions for all the combustor models. Furthermore, the predicted variation of static pressure along the combustor top wall is compared with experimental data reported in the literature. Calculations show that the penetration and spreading of the fuel increases with an increase in the injection pressure. Predicted values of the combustion efficiency are more realistic when the spray model is used for modelling the injection of the fuel. The importance of the mixing process, especially for a liquid fuel such as kerosene, on the prediction of heat release is discussed in detail.

Mixing and combustion characteristics of kerosene In a model supersonic combustor

Numerical simulations of the three-dimensional reacting flow in a staged supersonic combustor (Mach 2.5) have been carried out. The combustor has a strut for the first stage and wall-mounted injectors for the second stage (S. Tomioka, A. Murakami, K. Kudo, and T. Mitani, "Combustion Tests of a Staged Supersonic Combustor with a Strut," Journal of Propulsion and Power, Vol. 17, No. 2, 2001, pp. 293-300). The Spalart-Allmaras model has been used for modeling turbulence and single-step finite-rate chemistry has been used for modeling the H 2/Air kinetics. The grid has been refined to achieve average value for wall y + less than 20. The predicted static-pressure profile along the centerline of the combustor is compared with experimental data for different injection schemes. Details of the flowfield inside the combustor as well as variation of mixing efficiency, combustion efficiency, and total pressure loss along the length are presented and discussed.

Numerical simulation of three-dimensional reacting flow in a model supersonic combustor

42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &amp; Exhibit

Numerical Simulation of Kerosene Combustion in a Dual Mode Supersonic Combustor

On the effect of Schmidt and Prandtl Numbers in the Numerical Predictions of Supersonic Combustion

International Journal of Heat and Mass Transfer

Numerical study on supersonic combustion with cavity-based fuel injection

12th AIAA International Space Planes and Hypersonic Systems and Technologies

CFD Analysis of the SCHOLAR Scramjet Model

Journal	Progress in Computational Fluid Dynamics
ISSN	14684349
Open Access	No