Cycle Analysis of Lox/Lh2 Rocket Engine

This paper presents a comprehensive cycle analysis of a LOX/LH₂ rocket engine operating on a gas-generator cycle. The methodology integrates spreadsheet-based power matching and NASA CEA (CEARUN) thermodynamic tools to evaluate engine performance. Key engine parameters such as chamber pressure, mixture ratio, thrust, and specific impulse were studied under various conditions. Results demonstrate the critical impact of chamber pressure and mixture ratio on performance, while power balance equations validate the turbopump efficiency and turbine work requirements.