An experimental study of combustor exit profile shapes on endwall heat transfer in high pressure turbine vanes

Keyphrases

• Air Force 33%
• Aircraft Propulsion 33%
• Airfoil 33%
• Combustor 100%
• Convective Heat Transfer Coefficient 33%
• Elevated Pressure 33%
• Elevated Temperature 33%
• Endwall 66%
• Endwall Heat Transfer 100%
• Gas Turbine Engine 33%
• Harmful Emissions 33%
• Heat Transfer 66%
• High Pressure Turbine 100%
• Inlet Pressure 66%
• Inlet Profiles 66%
• Inlet Temperature 33%
• Pressure Profile 66%
• Profile Shape 100%
• Radial Profile 33%
• Research Laboratories 33%
• Temperature Profile 66%
• Thermal Operating Conditions 33%
• Turbine Vane 100%
• Vane Endwall 33%

Engineering

• Airfoil 33%
• Combustor 100%
• Convection Heat Transfer Coefficient 33%
• Elevated Pressure 33%
• Elevated Temperature 33%
• Gas Turbine Engine 33%
• High-Pressure Turbine 100%
• Inlet Pressure 66%
• Inlet Temperature 33%
• Pressure Profile 66%
• Profile Generator 33%
• Research Laboratories 33%
• Temperature Profile 66%