Effects of New Cooling Hole Arrays and Thermal Barrier Coating on Insert Ring in V۹۴.۲ Gas Turbine Combustor

In order to increase insert ring lifetime in V۹۴.۲ gas turbine combustor, new upgrades have been presented in the current study. Since this part of the combustor is in direct contact with propagating flames produced by burner, it is important to consider a state-of-the-art cooling strategy. Based on the working condition of the insert ring, on the hot side, thermal barrier coating (TBC) has been considered. For lowering the temperature of the insert ring’s body, new sets of cooling holes have been taken into account. The results have indicated that by using TBC, heat flux rate dropped significantly. The maximum temperature happened to be less than ۱۱۱۰ K due to usage of TBC. But the temperature gradient remained unchanged. By increasing the cooling holes surface area through distortion of cooling holes, the temperature gradient in insert ring had dropped substantially. In addition, among the three presented cases, the best case for lowering the temperature gradient is the one with ۴۸ oblique L -shaped cooling holes which dropped the maximum temperature by ۱۵.۷%.

کلیدواژه ها:

V۹۴.۲ ، Insert ring ، TBC ، Cooling holes ، Combustion