The modern trends of gas turbine engines focus on increased turbine inlet temperatures in order to reduce the specific fuel consumption and increase the overall performance of the engine. However, operation at very high temperatures reduces the life time of turbine vanes and blades while the allowable temperature level of the cycle is limited by the melting point of the materials. Therefore, turbine blade cooling is necessary to reduce the blade metal temperature to acceptable levels for the materials increasing the thermal capability of the engine. Due to the contribution and the development of turbine cooling systems, the turbine entry temperature (TET) has been over doubled over the last 60 years.
The objective of the analysis is to study the effect of reduction of temperature and to attain the maximum cooling efficiency on gas turbine blade cooling by varying the geometry of the cooling passages. An attempt is made to compare the performance of turbine blade configurations with and without turbulators. While comparing the temperature distribution across the blade, it is evident that overall comparison analyzed from CFD results shows that the net temperature distribution as well as the net heat transfer rate taken by the cooing air is significantly more in the case of turbulator configuration. Based on the results obtained by the CFD calculations it is found that: The temperature variation along the coolant passage with turbulators indicates that the temperature distribution is effective in the middle passage while comparing the side passage. As we use turbulators the blade leading edge temperature will decreases. Temperature will minimum for N155 material with turbulator i.e. 867.95K. Heat Transfer rate will maximum for N155 material with turbulator i.e. 8810.078 Using turbulator is better option as compared to staggered holes and inline holes. Average blade temperature reduces by 12.30 % when turbulators are used.