Print Email Facebook Twitter Rocket engine inducer design optimisation to improve its suction performance Title Rocket engine inducer design optimisation to improve its suction performance Author Lubieniecki, Marek (TU Delft Aerospace Engineering) Contributor Lettieri, C. (mentor) Cervone, A. (mentor) Degree granting institution Delft University of Technology Programme Aerospace Engineering Date 2018-12-07 Abstract This thesis presents the results of a design optimisation of an inducer for a rocket engine turbopump. Its main goal was to optimise a shape of the inducer blades to enlarge an operating range of the entire pump that is limited by cavitation. The blade was parameterised with four parameters: sweep angle, sweep radius, incidence angle and blade solidity at the tip. The performance of the given pump design is evaluated with a two-phase CFD simulation. The optimisation process is based on a surrogate model that interpolates the simulation results in the entire design space from a fixed number of samples. The results show 17% improvement of the suction performance, which is caused by reduced vapour volume in the flow channel and higher inducer head. Sweep radius proved to be the most important parameter as it increases the minimal pressure at the leading edge. Subject CavitationTurbopumpsOptimisatiomInducer To reference this document use: http://resolver.tudelft.nl/uuid:74143194-7174-4bcb-98c7-632e24b70d88 Part of collection Student theses Document type master thesis Rights © 2018 Marek Lubieniecki Files PDF MSc_Thesis_M_Lubieniecki_ ... sation.pdf 9.16 MB Close viewer /islandora/object/uuid:74143194-7174-4bcb-98c7-632e24b70d88/datastream/OBJ/view