Numerical analysis of effect of thermal performance of gas turbine nozzle guide vane

Abstract

The present gas turbine engines requires higher entry turbine entry temperatures as engines are operating at higher thrust and thermal efficiency at the same time by operating a turbine at higher temperature reduces the life of blades or vanes because of thermal stresses. Sometimes, the turbine entry temperatures may nearly equal to melting point turbine blade material. Therefore, it is required to determine the blades or vanes to a temperature which gives need to cool the blades optimal condition. In typical gas turbine engines nozzle guide vanes are (NGV) endure the highest operating temperatures. There exists a great drive in the turbine industry to increase the turbine entry temperature leading to higher thermal efficiency.A thermal analysis has been carried out to investigate the direction of the temperature flow which is been develops due to the thermal loading. The present work aims to determine a temperature distribution on blade surface. Heat transfer analysis has been carried out to find out the performance and thermal distribution on the existing blade without internal cooling on nozzle guide vane by using CFD code ANSYS CFX. In this work, CFD analysis has been carried out using Reynolds average Navier stokes equations. The analysis was done without cooling channel on the Nozzle Guide Vane and average temperature on the nozzle guide vane surface will be estimated.