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A time marching algorithms, which is used to solve incompressible internal flow fields in turbomachinery, has beendeveloped. By using Chorin’s method of artificial compressibility, the governing equations are transformed fromelliptic type into hyperbolic form in order to extend the time marching technique to very low Mach number flows.Viscous effects can be predicted by using the distributed body force method and Baldwin-Lomax eddy viscosityturbulence model. Some accelerating convergence techniques such as multi-grid and local time step method areemployed. The applicahon to a flow field within a low-solidity rocket pump inducer is presented and discussed.
A time marching algorithms, which is used to solve incompressible internal flow fields in turbomachinery, has beendeveloped. By using Chorin’s method of artificial compressibility, the governing equations are transformed fromelliptic type into hyperbolic form in order to extend the time marching technique to very low Mach number flows.Viscous effects can be predicted by using the distributed body force method and Baldwin-Lomax eddy viscosity model. Some accelerating convergence techniques such as multi-grid and local time step methods are developed. The applicahon to a flow field within a low-solidity rocket pump inducer is presented and discussed.