Research progress on strut-equipped supersonic combustors for scramjet application

Effect of variation of angle of attack on the performance of two-strut scramjet combustor

Effect of different wall injection schemes on the flow-field of hydrogen fuelled strut-based scramjet combustor

Effect of different strut + wall injection techniques on the performance of two-strut scramjet combustor

Effect of parametric variation of strut layout and position on the performance of a typical two-strut based scramjet combustor

Investigation of the effect of chemistry models on the numerical predictions of the supersonic combustion of hydrogen

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 k-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

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,andmixingefficiencyarepresentedanddiscussed.Forthereacting flowcalculations,contoursofheatrelease 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.

K. Kumaran

Papers

Investigation of the effect of chemistry models on the numerical predictions of the supersonic combustion of hydrogen

Mixing and combustion characteristics of kerosene In a model supersonic combustor

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