نوع مقاله : مقاله پژوهشی
نویسندگان
1 دانشکده فنی و مهندسی، دانشگاه جامع امام حسین(ع)، تهران، ایران
2 عضو هیأت علمی
چکیده
کلیدواژهها
عنوان مقاله [English]
نویسندگان [English]
Dinitrogen oxide oxidizer is used to cover the weakness of hybrid systems in the low rate of regression due to the combustion of propellant rich in (solid) paraffin fuel. In this research, the solution field focused on a combustion chamber connected to a peripheral area inside is included. A three-dimensional steady-state simulation with the Reynolds-averaged Navirastox (RANS) approach and using the standard κ-ε turbulence model together with the Eddy Dissipation Model (EDM) is used for the chemistry-turbulence interaction (TCI). A regular and fixed network is considered for the oxidizer and fuel flow in the gas phase. The simulation results are validated with experimental data. The results show that with an increase of 35.71% in the diameter of the sprinklers and an increase of 27.76% in the O/F ratio in the three-dimensional simulation, the average pressure of the combustion chamber has increased by 37.61%, the average thrust by 51.46% and the average specific impulse by 19.41%. . Other results obtained from the simulation of the mentioned engine are promising and the numerical investigation of the effect of the number of placement arrangement and orifice diameter in the oxidizing injector (nitrogen oxide), mass percentage of fuel and O/F ratio on the amount of chamber pressure and thrust of the hybrid rocket has been compared.
کلیدواژهها [English]
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