Saeil Lee

TL;DR: In this paper, a reliability-based design optimization (RBDO) of the NASA stage 37 axial compressor is performed using an uncertainty model for stall margin in order to guarantee stable operation of the compressor.

TL;DR: In this paper, a single-stage transonic axial compressor with genetic algorithm was used for the exploration of the Pareto front to find the maximum objective function value, and the final design was chosen after a second stage gradient-based optimization process to improve the accuracy of the optimization.

TL;DR: In this paper, the Kriging method was used to construct a surrogate model for finding aerodynamically improved three dimensional single stage turbine, which has complicated physical phenomena and demands many design variables for finding optimum three dimensional blade shapes.

TL;DR: In this paper, a single-stage transonic axial compressor with genetic algorithm was used for the exploration of the Pareto front to find the maximum objective function value, and the final design was chosen after a second stage gradient-based optimization process.

TL;DR: In this paper, a three-dimensional aerodynamic optimization of high pressure turbine nozzle for turbofan engine was performed, where Kriging surrogate model was built iteratively by supplying additional experimental points until the surrogate model and CFX result has effective difference on objective function.