Numerical investigation on cooling performance of a twisted gas turbine blade with leading edge cooling holes

The new and advance technologies for higher performance and lower maintenance are required to operate  gas turbines at higher operating temperatures. Higher turbine inlet temperature results in higher blade metal temperatures. These variations in temperatures of the blade material must be limited such that the blades have a sufficient life span. To make blade material temperature within the limits, the coolant air is bled from the compressor to protect the outer surface of the turbine blade from the hot gases. The purpose of this study  is to investigate the cooling performance of a blade with leading edge cooling holes. The numerical simulation approach using ANSYS Fluent has been considered. The analysis is performed by taking different hole geometries namely cylindrical (model ۱) and tapered (model ۲) on the leading edge of the turbine blade for different blowing ratios. The analysis also compares the cooling effectiveness of the blade for two different coolants namely air and nitrogen. The results show that for highest effectiveness hole (E۳ hole), Model ۱ and Model ۲ comparison suggest that Model ۱ has ۱.۲% more cooling effectiveness for air as coolant. For E۳ hole, the comparison of Model ۱ between two coolants show that film cooling effectiveness of the air gives ۰.۶% more film cooling effectiveness compared to nitrogen. The presented work helps researchers and blade manufacturers to select the correct hole geometry, coolant type, and determine the best blowing ratio to improve the film cooling efficiency of gas turbine blades with leading edge holes.

کلیدواژه ها:

Blowing ratios ، Coolant density ، Cooling performance ، Numerical Approach ، Gas turbine blade ، Hole geometry