Influence of axial spacing on spanwise efficiency of a transonic axial compressor rotor stage.

摘要

This study numerically examined the span-wise efficiency of a transonic compressor stage representative of a modern jet engine. Two simulations of a compressor stage with different axial spacing between blade-rows were studied to determine the influence on the fluid flow. The two spacing are denoted as Close and Far. The time-accurate Reynolds-averaged Navier-Stokes computational algorithm MSU-TURBO with a CMOTT turbulence model was used for both cases. All solutions are three-dimensional and model WG-rotor relative motion through a sliding-mash interface and phase-lagged boundary conditions.;The conclusions reached in this analysis are: the upstream wakes interact with the rotor boundary layer and the tip flow is a major factor at reduced spacings. The purpose of this study was to identify the reasons for efficiency losses, therefore further investigations into the correlation between axial spacing and efficiency loss are needed. (Abstract shortened by UMI.)