Parametric design of rocket engine turbopumps with genetic algorithms

In a rocket engine, the main turbopump parameters must be estimated considering that the power output of the turbine essentially has to equal the power demand of the pump. Considering the properties of the turbine drive gas (specific heat, temperature and other features), the strength limits of the turbine materials, and the likely pressure drop, it is possible to determine the basic dimensions of the blades like pitch line velocity, turbine nozzle outlet velocity, number of rows of blades, turbine type or turbine efficiency. The particular arrangement or geometry of the major turbopump components is related to their selection process. Most propellant pumps have a single-stage main impeller. Usually some design limit is reached which requires one or more iterations, each with a new changed approach or parameter. The present work considers the development of a software tool based on genetic algorithms to assist the determination of the excellent parameters of configuration of turbopumps in engines for liquid propellant rockets. We present results for alcohol/LOX propellant mixture, some discussion on its applications on rocket engines.