A high-fidelity yet affordable design procedure is proposed for a film-cooling hole array optimization and subsequently applied to the array on the nozzle pressure side of the high-pressure turbine. To make this possible, the efficient array shape parameterization method combined with the efficient global optimization method is introduced. As a result of optimization, the average and variation of the wall temperature are reduced by approximately 10 and 25%, respectively. Also, it is confirmed from the results that the superior cooling performance is obtained when the array has smaller hole distances at the hub rather than at the shroud and when the array is disposed on the upstream position rather than on the downstream position. Finally, it is concluded that the performance improvement due to the optimized hole array amounts to the equivalent effects of increasing cooling air by 1.66% of the main passage mass flow.
Optimization of the Array of Film-Cooling Holes on a High-Pressure Turbine Nozzle
Journal of Propulsion and Power ; 33 , 1 ; 234-247
2016-07-20
14 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Optimization of the Array of Film-Cooling Holes on a High-Pressure Turbine Nozzle
Online Contents | 2016
|Optimization of the Array of Film-Cooling Holes on a High-Pressure Turbine Nozzle
Online Contents | 2017
|Deposition Near Film Cooling Holes on a High Pressure Turbine Vane
Online Contents | 2012
|Genetic Algorithm Optimization of a High-Pressure Turbine Vane Pressure Side Film Cooling Array
Online Contents | 2014
|