Numerical Investigation on the Injection Effects of Swirl Injector in a Hybrid Rocket Motor

Abstract Because of their complexity and technical significance in heat transfer, combustion, mixing, and other processes, swirling flows are a significant class of flows. Swirling flows may experience various circumstances and show distinct dynamical properties based on the boundary conditions. The work's goal is to use ANSYS-CFD software to computationally analyze the impact of swirl injection of gaseous oxygen as an oxidizer in a hybrid rocket. This work focuses on designing a swirl injector and then using gaseous oxygen as a working fluid to numerically simulate an injector with a swirl injection mechanism. The designed swirl injector has 12 holes, each measuring 3 mm diameter, encircling it at a 30° angle to the vertical and a 5° angle to the horizontal. The height of the swirl injector is 40 mm and the outer and inner diameters are 59 and 41 mm respectively. The swirl injection rocket's performance involves variations in pressure and velocity at different points in the combustion chamber at varied injection velocities, as well as cold swirl flow at variable injection velocities.