Towards the simulation of cavitating flows in inducers through a homogeneous barotropic flow model

摘要: The present paper describes the starting efforts made for constructing a numerical frame aimed at simulating propellant flows occurring in feed turbopumps of modern liquid rocket engines. A homogeneous-flow cavitation model, accounting thermal effects and active nuclei concentration, is considered, which leads to barotropic state law. 3D continuity momentum equations compressible inviscid are discretized by finite-volume approach, applicable unstructured grids. fluxes computed through shock-capturing Roe-type upwind scheme, defined flows. accuracy proposed method low Mach numbers ensured ad-hoc preconditioning, only modifies part flux; thus, time consistency maintained can also be used unsteady problems. Time advancing carried out an implicit linearized linearization exploits properties Roe matrix. Examples applications provided flow configurations increasing geometric complexity, viz. some 1D validation benchmarks, around hydrofoil mounted tunnel turbo-pump inducer.