Abstract
The gas turbine is an indispensable part of technology and it is commonly used in electric power, aviation and marine mechanical. However, the gas combustion temperature was higher than the melting point of metal, which prevents further increase in efficiency in a gas turbine. To enhance the turbine inlet temperature greatly, an advanced cooling technology has been essentially required to protect the material of high thermal components. The final numerical results are compare with each other and show the characteristics of heat transfer and pressure drop. In these investigations, different cases evaluate that the adiabatic cooling effectiveness (ηc ) indicates a downward curvature in the following descending order: circular pin fin with mist case = circular pin fin only case > normal with mist cooling case > normal with air only case. Mist/air impiangement cooling with circular pin fins not only maintain the superiorities of air cooling jets, but more effective than pin fins technique. Accordingly, renewing the air impingement cooling systems with pin fins and mist cooling seems to be more attractive. The inspire application of the circular pin fins and mist/air impingement cooling will make it a reference for designing a new cooling structure in marine gas turbine combustor.
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