Abstract
Rotor vibration of the liquid rocket turbopump may cause not only the functional failures but also catastrophic failures of
the rocket engine that leads to the mission failure. It is generally considered that the rotor vibration characteristics depend on
the length of the overhang part of the rotor, bearing support stiffness, bearing span and system damping. This study aims at
proposing the morphological design method of the turbopump for considering the rotor dynamic properties. In the first, a
typical turbopump rotor linear dynamic simulation model was constructed by using finite element method. Its vibration
characteristics were validated by the published data. In the second, component based modeling for the morphological design
was proposed. Available different component arrangements were generated based on the selection rules. Each arrangement
estimated from the view point of the rotor weight and its critical speed. Illustrative design simulation performed for a trial
turbopump design example.
