Thermally Effective and Efficient Cooling Technologies for Advanced Gas Turbines

The objective of this University of North Dakota project is to research and develop three cooling methods for improved turbine airfoil cooling performance. The cooling technologies include incremental impingement for the leading edge, counter cooling for the pressure and suction surfaces, and sequential impingement for the pressure and suction surfaces of the vane. These methods are designed to improve the internal thermal effectiveness of the cooling air used before discharging the spent air onto the surface to form an optimal film cooling layer to thermally protect (i.e., reduce the heat load) the surface.

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Picture of the LSU warm cascade. Pressure taps and thermocouples extensionsare extracted through sealing glands on the left. Combustor is upstream of the picture. Flow is from bottom to top

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Thermally Effective and Efficient Cooling Technologies for Advanced Gas Turbines (2014)
Presented by Sumanta Acharya, University of Memphis at the 2014 University Turbine Systems Research Workshop.

Principal Investigator

Forrest Ames

forrestames@mail.und.nodak.edu

Project Benefits

This project will research three cooling methods for improved turbine airfoil cooling performance. Turbine aerodynamics and heat transfer research will develop advanced cooling technology that will allow for higher firing temperatures which translate into increased cycle efficiency. Specifically, this project will investigate incremental impingement for the leading edge, counter cooling for the pressure and suction surfaces, and sequential impingement for the pressure and suction surfaces of the vane.

Project ID

FE0011875

Website

University of North Dakota

http://www.und.edu/