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. Authors have proposed the morphological design method of the turbopump for considering the rotor dynamic properties. In this study, authors are formulating the optimum shaft configuration design problem for the rocket engine turbopump rotor system based on the numerical optimization. Illustrative optimum design performed for a trial turbopump design example.
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