Experimental heat transfer investigation around the film-cooled leading edge of a high-pressure gas turbine rotor blade

Keyphrases

• Free Stream 100%
• High-pressure Gas 100%
• Gas Turbine Rotor Blade 100%
• Temperature Ratio 100%
• Experimental Heat Transfer 100%
• High Pressure 50%
• Incidence Angle 50%
• Coolant 50%
• Heat Transfer 50%
• Reynolds number 50%
• Mach number 50%
• Film Cooling 50%
• Calculation Method 50%
• Platinum Thin Film 50%
• Weight Ratio 50%
• Aero-engine 50%
• Wall Temperature 50%
• Thin Film Gauge 50%
• Angle Variation 50%
• Isentropic Compression 50%
• Cooled Gas Turbine 50%
• Pressure Film 50%
• Stationary Frame 50%
• Compression Tube 50%
• Transfer Data 50%

Engineering

• Leading Edge 100%
• Gas Turbine 100%
• Rotor Blade 100%
• Free Flow 100%
• Thin Films 50%
• Mach Number 50%
• Incidence Angle 50%
• Heat Transfer Data 50%
• Aeroengine 50%
• Cooled Gas 50%
• Mass Weight 50%
• Isentropic Compression 50%