ABSTRACT The secondary combustion chamber is a critical issue in the design, development, and efficiency of solid-propellant ducted rocket engines. In these engines, the propellant, which is fuel-rich, is incompletely combusted in the first chamber. This incomplete combustion produces a hot gas mixture containing solid particles. These solid particles, after mixing with the hot air stream entering from the air intake in the secondary chamber, complete their combustion, and the final combustion products create thrust by passing through the nozzle. Due to the very short residence time in the secondary combustion chamber, it is essential to study the exact combustion kinetics of the gas-phase fuel and solid particles, as well as the interaction of reaction mechanisms with turbulent flow. In this article, for the first time, the Eddy Dissipation Concept (EDC) approach has been studied to simulate the two-phase reactive flow field in the secondary combustion chamber of a ducted rocket. This approach helps solve the interaction of reactive mechanisms and turbulent flow more accurately and provides a more precise estimate of the combustion chamber’s performance. In this approach, a chemical reaction is considered not only for the gas phase but also for the solid particle phase (DPM), and the chemical reactions of both phases are solved simultaneously and coupled. A 9-step mechanism is used for chemical reactions, including solid carbon particles and 7 gaseous species. Additionally, radiative heat transfer phenomena are considered. The simulation based on the EDC-DPM approach is compared with simulations based on three other combustion approaches: One-stream Non-Premixed (One-stream), Two-stream Non-Premixed (Two-stream), and Finite Rate/Eddy Dissipation Model (EDM/FR). The results show that the simulation based on the EDC-DPM approach is a better match with the experimental data. The estimated temperature, pressure, and engine thrust exhibit only small prediction errors of 3.2%, 3.25%, and 4.78%, respectively. Moreover, the predicted reactive flow field is closer to reality. In contrast, the prediction errors for the One-stream, Two-stream, and EDM/FR combustion models for chamber temperature are 12.54%, 18.56%, and 4.2%, chamber pressure is 3.47%, 17.03%, and 1.48%, respectively, and engine thrust is 4.81%, 22.2%, and 2%, respectively.
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