A Thermodynamic Model to Quantify the Impact of Cooling Improvements on Gas Turbine Efficiency

[+] Author and Article Information
Selcuk Can Uysal

National Energy Technology Laboratories, Morgantown, WV, USA

Eric Liese

National Energy Technology Laboratories, Morgantown, WV, USA

Andrew C. Nix

West Virginia University, Morgantown, WV, USA

James Black

National Energy Technology Laboratories, Pittsburgh, PA, USA

1Corresponding author.

ASME doi:10.1115/1.4038614 History: Received November 14, 2017; Revised November 20, 2017


To quantify the effect of different internal and external blade cooling techniques and their combinations on engine performance, a cooled engine model has been developed for industrial gas turbines and aero-engines using MATLAB Simulink®. The model has the flexibility to be used for both engine types, and consists of uncooled on-design, turbomachinery design and a cooled off-design analysis in order to evaluate the engine performance parameters by using operating conditions, polytropic efficiencies, material information and cooling system information. The cooling analysis algorithm involves a Second Law analysis to calculate losses from the cooling technique applied. The effects of variations in engine parameters such as turbine inlet temperature, by-pass ratio, and operating temperature are studied. The impact of variations in metal Biot number, thermal barrier coating Biot number, film cooling effectiveness, internal cooling effectiveness and maximum allowable blade temperature on engine performance parameters are analyzed. Possible design recommendations based on these variations, and direction of use of this tool for new cooling design validation, are presented.

Section 5: Non-US Gov Employees
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