Turbopump Design for Pressurizing and Pumping of Propellants in Liquid Rocket Engine

The design of a turbopump for effective propellant pumping and pressurization in liquid rocket engines is the primary objective of this study. The impeller, turbine, and casing all essential components of the turbopump are modeled to have optimal efficiency and low energy losses. Lightweight materials are used to create a scaled prototype, which is then tested to see how well it performs at various pressures and flow rates. Advanced sealing mechanisms are incorporated into the design to ensure dependable functioning and stop leaks. During testing, sensors are utilized to measure RPM, pressure, and flow rate. This study highlights how important turbopumps are to supplying propellants to the combustion chamber at the proper pressure and flow rate, which provides steady thrust production.