DYNAMIC ANALYSIS OF A LIQUID ROCKET TURBOPUMP UNIT
Everaldo de Barros1; Daniel Fraga Sias2; Carlos dAndrade Souto1; Daniel Soares de Almeida2
1 IAE/AIE; 2 IAE/APE
doi:10.20906/CPS/COB-2015-1034
Resumo
The use of liquid rocket engines in space launchers offers many advantages over its solid counterparts: higher specific impulse; the possibility of re-ignition in flight and the control of thrust vector magnitude. Pressurized tanks or turbopumps are used to inject fuel and oxidizer into the combustion chamber which pressure must be lower than the propellant lines pressure. More efficient engines require higher combustion chamber pressure and only turbopumps systems can provide pressures high enough to the feed lines. These systems operate at very high velocities and suffer intense dynamic loads. Therefore its rotor-dynamic behavior must be evaluated during the design stage. In this work a turbo-pump turbopump shaft was modeled numerically by building a finite element model of flexible shaft with rigid disks and a finite element model with flexible shaft and disks (solid elements) and also experimentally by a modal test. The results for the three approaches were compared and discussed. Also, the full rotor - bearing system was analyzed and classical rotor-dynamics results like Campbell's diagram, response to unbalance and mode shapes of the whirling modes were obtained.
Palavras-chave: rotordynamics; liquid propellant rocket engines; finite elements; experimental modal analysis