Numerical Analysis of Integrated Liquid Ramjet Engine

The numerical simulation of an integrated, liquid-fuelled ramjet engine comprising supersonicair intake, subsonic combustor and a convergent-divergent nozzle has been carried out and theresults are discussed in this paper. These results include cold flow studies, heat addition in thecombustor and full engine analysis with coupled simulation of supersonic air-intake andcombustion chamber along with the nozzle. Overall ramjet operation depends on the performanceof the air intake and the combustion chamber.  The coupling phenomena are very dominant andperformance of air intake is affected vastly by the combustor operation and vice versa. In thispaper, a numerical analysis of integrated liquid ramjet engine considering coupling phenomenabetween various sub-systems viz., air intake, combustor and nozzle has been reported

Numerical Modelling of Liquid Ramjet Combustors

The liquid fuel ramjet system employing a subsonic side-dump combustor is simulated inthe present study, and the predictions are compared with the available experimental data. Thecomplex combustion phenomenon in a ramjet combustor has been carried out using probabilitydensity function (PDF)  approach. The complexity arises because of the mixing of fuel and airstreams, and the burning of the resultant mixture, within the confined space of the combustionchamber. The predicted numerical results have been validated with the results available in openliterature for a two-dimensional case and with in-house experimental data for a three-dimensionalcase. The methodology allows different designs to be evaluated quantitatively based on theperformance metrics such as combustion efficiency, flame stability, etc.Defence Science Journal, 2008, 58(1), pp.3-14, DOI:http://dx.doi.org/10.14429/dsj.58.162

Numerical Investigation of the Intake Flow Characteristics for a Ramjet Engine with and without Heat Addition in the Combustion Chamber

The flow field in the supersonic mixed compression axisymmetric as well as two-dimensional intake have been investigated numerically. The flow characteristics, such as pressure, temperature, and velocity have been obtained. An enlarged chamber with a supersonic convergent-divergent nozzle has been integrated at the air intake exit to simulate the ramjet engine. Suitable heat addition at the inner surface of the wall has enabled the simulation of combustion chamber condition. The well-known modes of operation of the ramjet engine air intake have been predicted by the mathematical simulations. A comparative study for supercritical, critical, and subcritical -; conditions has been presented. The predicted flow features including shock locations and the static pressure distributions along the cowl, as well as the centre body are in agreement with the available experimental results in the published literature. The effect of thermal input in the combustion chamber on the flow characteristics of the air intake has been studied in detail. The characteristic curve of generic supersonic air intake can be obtained through these numerical studies