Effect of incidence on wall heating rates and aerodynamics on a film cooled transonic turbine blade

Keyphrases

• Aerodynamics 100%
• Turbine Blade 100%
• Heating Rate 100%
• Stagnation Point 100%
• Cooling Hole 100%
• Pressure Side 66%
• Heat Transfer 66%
• Film Cooling 66%
• Free Stream 66%
• Convective Heat Transfer 66%
• Suction Side 66%
• Computational Study 33%
• Ejection 33%
• Coolant 33%
• Inviscid 33%
• Mach number 33%
• Gas Turbine 33%
• Flow Condition 33%
• Mass Flow Rate 33%
• Precise Location 33%
• Transitional Behavior 33%
• Flow Direction 33%
• Fluid Dynamics 33%
• Transfer Center 33%
• Showerhead 33%
• Curved Surface 33%
• Exit Mach number 33%
• Von Karman 33%
• Convective Heat Transfer Coefficient 33%
• Suction Surface 33%
• Pressure Surface 33%
• Separation Bubble 33%
• Flow Separation 33%
• Wall Heat Flux 33%
• Heat Transfer Experiment 33%
• Turbine Flow 33%
• Two-row 33%
• Blade Surface 33%

Engineering

• Cooling Hole 100%
• Heating Rate 100%
• Blade Turbine 100%
• Stagnation Point 100%
• Pressure Side 66%
• Convective 66%
• Suction Side 66%
• Leading Edge 33%
• Gas Turbine 33%
• Mach Number 33%
• Flow Condition 33%
• Mass Flowrate 33%
• Isothermal 33%
• Rotor Blade 33%
• Flow Direction 33%
• Fluid Dynamics 33%
• Exit Mach Number 33%
• Convective Heat Transfer Coefficient 33%
• Pressure Surface 33%
• Suction Surface 33%
• Separation Bubble 33%
• Flow Separation 33%
• Heat Transfer Data 33%
• Iso 33%
• Blade Surface 33%
• Turbine 33%
• Shower Head 33%