#TITLE_ALTERNATIVE#

• 主要作者: Amalinadhi Putra (NIM: 13613042), Cahya
• 格式: Final Project
• 語言: Indonesia
• 在線閱讀: https://digilib.itb.ac.id/gdl/view/21474

Reducing weight and size of a jet engine could make a big saving for the airplane industry. <br /> <br /> <br /> This could be achieved by increasing the performance of jet-engine compressor. Total pressure <br /> <br /> <br /> ratio and adiabatic efficiency were two important parameters that decided the performance of <br /> <br /> <br /> compressor. But, there was a problem in the optimization process, which was as the total pressure <br /> <br /> <br /> ratio value increases, the value of efficiency decreases, vice versa. Hence, multi-objective <br /> <br /> <br /> optimization was needed to do the optimization of compressor performance that has opposite <br /> <br /> <br /> objective function. This thesis presented the study of multi-objective optimization of a transonic <br /> <br /> <br /> compressor, NASA Rotor 37, by deforming its blade to maximize two opposite-objectivefunction, <br /> <br /> <br /> which were total pressure ratio and efficiency, using NSGA-II assisted by surrogate <br /> <br /> <br /> model and multi-objective Expected Improvement (EI) methods to cut-off optimization timebudget. <br /> <br /> <br /> There were two optimization cases in which blades were parameterized by two and three <br /> <br /> <br /> variables. The optimization succeded to obtain several optimum solutions termed as pareto optima. <br /> <br /> <br /> Two of them were the total pressure ratio-optimum blade increasing the pressure ratio <br /> <br /> <br /> to 2.03% with 2.08% decrease in efficiency while the efficiency-optimum blade increasing the <br /> <br /> <br /> efficiency ratio to 1.39% but decrease the total pressure ratio about 2.84%. Furthermore, the <br /> <br /> <br /> optimized blades found in this study yield lower losses performance because of the movement <br /> <br /> <br /> of the separation line toward the downstream direction. Also, the optimized blade had 0.39% <br /> <br /> <br /> improvement on total pressure ratio and 0.14% improvement of efficiency.