Gas turbine vane cooling plays an important role for increasing the thermal performance of engine. In present computational analysis gas turbine vane is cooled internally passing coolant through ribbed passages, the effect of coolant flow in rib turbulators has been simulated by ANSYS FLUENT. The temperature contours of vane are observed by varying the mass flow of air through passages and results were compared. The heat transfer characteristic such as Nusselt number, Heat transfer coefficient and skin friction coefficient are noted. It observed that cooling performance increases by increasing mass flow rate, but pressure loss increases at high mass flow rates and it's not feasible to have high flow for ribbed passages.
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