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http://dx.doi.org/10.5293/kfma.2014.17.6.052

Design Optimization of Fan-shaped Film Cooling Hole Array on Pressure Side Surface of High Pressure Turbine Nozzle  

Lee, Sanga (Seoul National University, Department of Mechanical and Aerospace Engineering)
Rhee, Dong-Ho (Korea Aerospace Research Institute, Engine component technology team)
Kang, Young-Seok (Korea Aerospace Research Institute, Engine component technology team)
Kim, Jinuk (Hanyang University, Department of Mechanical Engineering)
Seo, Do-Young (Pusan National University, Department of Aerospace Engineering)
Yee, Kwanjung (Seoul National University, Department of Mechanical and Aerospace Engineering)
Publication Information
The KSFM Journal of Fluid Machinery / v.17, no.6, 2014 , pp. 52-58 More about this Journal
Abstract
In the present work, design optimization of film-cooling hole array on the pressure side of high pressure turbine nozzle was conducted. There are four rows of fan-shaped film cooling holes on the nozzle pressure side surface and each row has a straight array of holes in the spanwise direction for baseline model. For design optimization, hole distributions in streamwise and spanwise directions for three rows of holes except first row are parameterized as a 2nd-order shape function. Three-dimensional compressible RANS equations are used for flow and thermal analysis around the nozzle surface and optimization technique using Design of Experiment, Kriging surrogate model and Genetic Algorithm is used. The results shows that averaged adiabatic wall temperature at the whole nozzle surface decreases about 2.7% and averaged film cooling effectiveness at the pressure side of nozzle increased about 8.2%.
Keywords
Gas turbine; High pressure turbine; Film-Cooling; Design optimization;
Citations & Related Records
Times Cited By KSCI : 3  (Citation Analysis)
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