INTGRATED DESIGN METHOD OF A ROCKET ENGINE TURBOPUMP SUB-SYSTEM FOR SUPPRESSING ROTOR LATERAL VIBRATION

摘要

A rocket turbopump is the high-speed and high-power turbomachinery that raise the pressure of cryogenic fluid to higher than the combustion chamber pressure. Various rotor vibration problems had occurred caused by rotation in the development phase of the turbopumps for the Japanese rocket engines. In order to suppress the rotor instability vibrations, rotordynamic fluid forces induced by the turbomachinery components should be taken account in the rotordynamics analysis. The design method is a kind of multi-disciplinary optimum design and is formed in two steps. This paper presents a new the integrated design method concept developed to provide good stability for rotor lateral vibration while rotating at all operation range.