This study presents a numerical method for solving the three-dimensional, Navier-Stokes equations for unsteady, viscous low through multiple turbomachinery blade rows. The method solves the fully three-dimensional Navier-Stokes equations with an implict scheme which is based on a control volume approach. A two-equation turbulence model with a low Reynolds number modification is employed in the present study. A third-order accurate upwinding scheme is used to approximate convection terms while a second order accurate central difference scheme is used for the discretization of viscous terms. A second-order accurate scheme is employed for the temporal is critization. The numerical method is applied to study the unsteady flow field of the High Pressure Fuel side Turbo Pump (HPFTP) of the Space Shuttle Main Engine (SSME). The stage calculation is performed by coupling the stator and the rotor flow fields at each time step through an over-laid grid. Numerical results for the complete geometry with the vane trailing edge cutback are presented and compared with the available experimental data.
Navier-Stokes analysis of three-dimensional unsteady flows inside turbine stages
Navier-Stokes Untersuchung dreidimensionaler instationärer Strömungen innerhalb Turbinenstufen
AIAA-Papers ; 1-9
1992
9 Seiten, 9 Bilder, 20 Quellen
Conference paper
English
British Library Conference Proceedings | 1993
|Unsteady Navier-Stokes Rocket Nozzle Flows
AIAA | 2005
|