터보펌프 주변 극저온 공동 유동장의 호율적이고 정확한 해석

Abstract

This paper deals with the numerical computations of cryogenic cavitating flows around turbopump inducer in liquid rocket. Recently, accurate and efficient baseline numerical schemes have been developed for the computations of all-speed two-phase flows. The baseline numerical schemes – RoeM and AUSMPW+ schemes for multi-phase flows – are extended for treating general equation of state, and improved preconditioning techniques are developed for more robust and efficient computations in low-speed region. As a validation step for such progress, two-dimensional/axi-symmetric cryogenic cavitating flows around hydrofoil and ogive are computed with different working fluids and cavitation models. Finally, numerical simulations of three-dimensional KARI turbopump inducer are carried out under various flow conditions with water and cryogenic fluids, and the differences in inducer flow physics depending on the working fluids are examined.