The effect of the combustor-turbine slot and midpassage gap on vane endwall heat transfer

Keyphrases

• Vane Endwall 100%
• High-temperature Heat Transfer 66%
• Turbine Disk 66%
• Combustion Flow 33%
• Airfoil Section 33%
• Surface Heat Transfer Coefficient 33%
• Leakage Path 33%
• High-pressure Coolant 33%
• Gas Path 33%
• Vortical Flow 33%
• Gap Flow 33%

Engineering

• Disc Turbine 50%
• Airfoil Section 25%
• Gap Heat Transfer Coefficient 25%
• Flowrates 25%
• Individual Section 25%