Multiobjective Optimization of Rocket Engine Pumps Using Evolutionary Algorithm

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Abstract
Design optimization method for turbopumps of cryogenic rocket engines has been developed. Multiobjective Evolutionary Algorithm is used for multiobjective pump design optimizations. Performances of design candidates are evaluated by using the meanline pump flow modeling method based on the Euler turbine equation coupled with empirical correlations for rotor efficiency. To demonstrate the feasibility of the present approach, single stage centrifugal pump design and multistage pump design optimizations are presented. In both cases, present method obtains very reasonable Pareto- optimal solutions that include some designs outperforming the original design in total head as well as input power by 1%. Detailed observation of the design results also reveals some important design policies in turbopump design of cryogenic rocket engines. These results ensure the feasibility of EA- based design optimization method in this field.