A MODELING FRAMEWORK CAPABLE OF CHARACTERIZING THE DYNAMICS OF POGO OSCILLATIONS IN SPACE ROCKET TURBOPUMPS

摘要

A modeling framework defined in the time-domain has been developed to characterize the steady state and dynamic behavior of each component of a typical feeding system for liquid rocket engine. A typical water loop for experimental characterization of liquid rocket turbopumps has been modeled according to the modeling framework in order to understand which is the best way to perform forced experiments for the characterization of the transfer matrix of cavitating turbopumps necessary for understanding the POGO instability phenomena that affect rocket launchers. The best results in terms of capability of generating mass flow rate and pressure oscillations at the inlet of the inducer have been obtained by means of a device that produces a volume oscillation located downstream of the pump.