A computational study for characterizing cavitating flow in hydrofoils operating at cryogenic conditions.

In our previous research [1], we have identified the potential regimes of flow instabilities such as tip vortex cavitation, backflow vortices at different design and off-design condition for the inducer of a LOX booster turbopump. Cavitation is the development of vapor structures in an originally liquid flow due to localized pressure depression. In general, cryogenic propellants used in modern rocket engines have high vapour–liquid density ratio and with a small latent heat of vaporization are operated close to the thermodynamic critical point. The temperature depression due to the latent heat of vaporization suppresses the growth of cavitation and alleviates cavitation instability in space inducers. Hence, designing a turbopump needs a proper understanding of the cavitation phenomenon. In this paper, an attempt has been made to simulate cryogenic cavitating flow aimed at liquid rocket propulsion applications and to estimate the temperature and pressure profiles for different operating conditions for different fluids. The physical implications of the existing cavitation models are re-examined for the 0.5 caliber hydrofoil from the standpoint of cryogenic fluids.