MORE | Spring 2025

Analysis of RS-25 Staged-Combustion Turbopump-Driven Propellant Feed System

This project analyzes the flow path of the fuel and oxidizer throughout the RS-25 rocket engine. It analyzes the temperatures, pressures, and mass flow rates in each section of the engine, ranging from the several turbopumps to the main combustion chamber and exit nozzle, and measures the performance of the engine in the nozzle section. Meticulously measuring these states provides a better understanding of the overall engine propulsion system due to its significance in the world of developing new rocket engine technologies. Understanding the flow path and performance of the RS-25 creates a foundation for success in designing new rocket propulsion systems in the future as the necessity of access to space continues to grow in governmental and commercial ventures.