http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
Optimization of energy saving device combined with a propeller using real-coded genetic algorithm
Ryu, Tomohiro,Kanemaru, Takashi,Kataoka, Shiro,Arihama, Kiyoshi,Yoshitake, Akira,Arakawa, Daijiro,Ando, Jun The Society of Naval Architects of Korea 2014 International Journal of Naval Architecture and Oc Vol.6 No.2
This paper presents a numerical optimization method to improve the performance of the propeller with Turbo-Ring using real-coded genetic algorithm. In the presented method, Unimodal Normal Distribution Crossover (UNDX) and Minimal Generation Gap (MGG) model are used as crossover operator and generation-alternation model, respectively. Propeller characteristics are evaluated by a simple surface panel method "SQCM" in the optimization process. Blade sections of the original Turbo-Ring and propeller are replaced by the NACA66 a = 0.8 section. However, original chord, skew, rake and maximum blade thickness distributions in the radial direction are unchanged. Pitch and maximum camber distributions in the radial direction are selected as the design variables. Optimization is conducted to maximize the efficiency of the propeller with Turbo-Ring. The experimental result shows that the efficiency of the optimized propeller with Turbo-Ring is higher than that of the original propeller with Turbo-Ring.
Optimization of energy saving device combined with a propeller using real-coded genetic algorithm
Tomohiro Ryu,Takashi Kanemaru,Shiro Kataoka,Kiyoshi Arihama,Akira Yoshitake,Daijiro Arakawa,Jun Ando 대한조선학회 2014 International Journal of Naval Architecture and Oc Vol.6 No.2
This paper presents a numerical optimization method to improve the performance of the propeller with Turbo-Ring using real-coded genetic algorithm. In the presented method, Unimodal Normal Distribution Crossover (UNDX) and Minimal Generation Gap (MGG) model are used as crossover operator and generation-alternation model, respectively. Propeller characteristics are evaluated by a simple surface panel method “SQCM” in the optimization process. Blade sections of the original Turbo-Ring and propeller are replaced by the NACA66 a = 0.8 section. However, original chord, skew, rake and maximum blade thickness distributions in the radial direction are unchanged. Pitch and maximum camber distributions in the radial direction are selected as the design variables. Optimization is conducted to maximize the efficiency of the propeller with Turbo-Ring. The experimental result shows that the efficiency of the opti-mized propeller with Turbo-Ring is higher than that of the original propeller with Turbo-Ring.