Abstract
Numerical prediction of the Stage 67 transonic fan stage
employing wall jet tip injection flow control and study of the
physical mechanisms leading to stall suppression and stability
enhancement afforded by endwall recirculation/injection
is the focus of this paper. Reynolds averaged Navier-Stokes
computations were used to perform detailed analysis of the
Stage 67 configuration experimentally tested at NASA’s Glenn
Research Center in 2004. Time varying prediction of the stage
plus recirculation and injection flowpath were performed utilizing
the Nonlinear Harmonic approach. Significantly higher
grid resolution per passage was achieved than what has been
generally employed in prior reported numerical studies of spike
stall phenomena in transonic compressors. This paper focuses
on characterizing the physics of spike stall embryonic stage
phenomena and the impact of tip injection, resulting in experimentally
and numerically demonstrated stall suppression
