Year: 2025
Type: article
Abstract: Hybrid rocket engines that use hydroxyl-terminated polybutadiene (HTPB) fuel and liquid oxygen (LOX) oxidiser are appealing because they are safe, work well, and are good for the environment. Nevertheless, combustion efficiency is still low because the oxidiser and fuel are not mixed well enough. This study offers a computational and experimental analysis of the internal ballistics of LOX–HTPB hybrid motors, focusing on injector design and chamber flow dynamics. CFD simulations validated with experimental data were used to compare swirl and pintle injectors to baseline injectors. The results show that pintle and tangential swirl injectors make combustion more efficient by improving the distribution of oxygen, turbulence, and pressure uniformity. The results show how to make the design of injectors and chambers better in hybrid propulsion systems.
Source: Acceleron Aerospace Journal
Authors: Aditi Atul Hiray, Abhinav Iyer, Purna Sravani Kankatala, Srishti Chakraborty, Hariharan G M, D Suhitha Reddy
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: diamond
OpenAlex ID: W4413922580