Effect of hub clearance of cantilever stator on aerodynamic performance and flow field of a transonic axial-flow compressor

Engineering

• Flow Distribution 100%
• Aerodynamic Performance 100%
• Axial-Flow Compressors 100%
• Leakage Flow 60%
• Suction Surface 40%
• Vortex 20%
• Rotor Blade 20%
• Boundary Layer 20%
• Pressure Ratio 20%
• Chord Length 20%
• Leakage Loss 20%
• Blade Root 20%
• Blade Span 20%
• Provide Support 20%
• Stage Compressor 20%
• Blade Row 20%