This study was led in collaboration with the French Space Agency (CNES) and the Rocket Engine Division of Snecma. The main aims were the simulations and the analyses of cavitating flows in the rocket engine turbopump inducers, where the operating fluids are LH2 and LOx under cryogenic conditions. A ρ(P,T) state law modeling the cavitation phenomenon was integrated by the laboratory LEGI in the commercial computational fluid dynamics (CFD) code FINE/TURBO™, developed by Numeca International. Various 3D numerical results are given for an inducer geometry and comparisons are made with experimental data (head drop curves) obtained by NASA.

Issue Section:
Multiphase Flows
Keywords:
cavitation, chemically reactive flow, computational fluid dynamics, cryogenics, hydrogen, oxygen, propellants, rocket engines, thermodynamics
Topics:
Blades, Cavitation, Flow (Dynamics), Fluids, Geometry, Hydrogen, Pressure, Suction, Temperature, Wall temperature, Vapors, Computation, Computational fluid dynamics, Rocket engines, Cavities, Water, Temperature distribution
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