Fig. 1 Meridional view of the fan stage. Geometry is correct for the computational domain and annotated with differences in the experiment. More

Fig. 2 Detail schematic view of the front 1% chord of the rotor blade at three spanwise sections showing damaged leading edge (solid lines) compared with baseline (dotted lines) More

Fig. 3 Computational grid for damaged fan LE More

Fig. 4 Measured rig characteristics, measured stability limit, and predicted rig blade characteristics with baseline blade More

Fig. 5 Measured rig characteristics, measured stability limit, and predicted engine blade characteristics with baseline and damaged blades More

Fig. 6 Computed unsteady static pressure traces on the rig rotor casing at 50% axial chord upstream of the LE around the moment of stall inception at three speeds. Time is measured from the moment of the nozzle closure leading to rotating stall. More

Fig. 7 Contours of static pressure, limiting streamlines, and green isosurface of zero axial velocity on rotor suction surface at the last stable operating point from steady CFD More

Fig. 8 Contours of static pressure, limiting streamlines, and green isosurface of zero axial velocity on rotor suction surface during stall inception. View of upper part of sectors of three blades extracted from full-annulus unsteady simulations. More

Fig. 9 Rotor isentropic Mach number distributions at 95% span at 95% speed from steady CFD at last stable point More

Fig. 10 Overall and detailed views of contours of relative Mach number in the rotor at 95% span at 95% speed from steady CFD at the last stable point More

Fig. 11 Rotor tip leakage axial momentum flux distribution at 95% speed from steady CFD at last stable point More

Fig. 12 Contours of static pressure, limiting streamlines, and green isosurface of zero axial velocity on rotor suction surface at near-stall operating point from steady CFD at 95% speed at last stable point More

Fig. 13 Computed unsteady static pressure traces on the rotor casing around the moment of stall inception for baseline and damaged blades at 95% speed. Time is measured from the moment of the nozzle closure leading to stall. More

Fig. 14 Rotor isentropic Mach number distributions at 95% span at 85% speed from steady CFD at two operating points More

Fig. 15 Overall and detailed views of contours of relative Mach number in the rotor at 95% span at 85% speed from steady CFD at two operating points More

Fig. 16 Rotor tip leakage axial momentum flux distributions at 85% speed from steady CFD at two operating points More

Fig. 17 Contours of static pressure, limiting streamlines, and green isosurface of zero axial velocity on rotor suction surface at two near-stall operating points from steady CFD at 85% speed at two operating points More