NUMERICAL-ANALYSIS OF 3-DIMENSIONAL VISCOUS INTERNAL FLOWS

A three-dimensional Navier-Stokes code has been developed for analysis of turbomachinery blade rows and other internal flows. The Navier-Stokes equations are written in a Cartesian coordinate system rotating about the x axis, then mapped to a general body-fitted coordinate system. Streamwise viscous terms are neglected and turbulence effects are modeled using the Baldwin-Lomax model. A finite-difference discretization is used on stacked C-type grids. The equations are solved using a multistage Runge-Kutta algorithm with a spatially varying time step and implicit residual smoothing. Calculations were made of a horseshoe vortex formed in front of a blunt flat plate standing in a turbulent endwall boundary layer. Comparisons are made with experimental data for a circular cylinder under similar conditions. Calculated details of the primary vortex show good agreement with the experimental data. The calculations also show a small secondary vortex that was not seen experimentally. Calculations were also made of a subsonic annular turbine stator and compared to experimental data. Computed surface pressure distributions compare well with measured values at three spanwise locations. The endwall boundary layers produce horseshoe vortices at the leading edge of the blade. Computed wake profiles resemble the measured profiles, but computed efficiencies are lower than that of measured values by a factor of two. © 1990 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.