Investigation on the showerhead film cooling of the turbine vane considering combustor swirling outflow

Engineering

• Combustor 100%
• Turbine 100%
• Cooling Scheme 100%
• Pressure Distribution 50%
• Leading Edge 50%
• Flow Characteristic 50%
• Negative Impact 50%
• Aero-Engines 25%
• Pressure Sensitive Paint 25%
• Area Coverage 25%
• Cooling Effect 25%
• Mutual Interference 25%
• Effective Solution 25%