日本航空宇宙学会論文集
Online ISSN : 2432-3691
Print ISSN : 1344-6460
ISSN-L : 1344-6460
論文
超音速燃焼器燃料噴射孔形状の設計問題における最適化と設計情報の知識発見
佐々木 康友松尾 亜紀子
著者情報
ジャーナル フリー

2004 年 52 巻 607 号 p. 371-376

詳細
抄録

A Multi-Objective Genetic Algorithm (MOGA) is applied in search of the optimal fuel injector shape in the supersonic combustor. The optimal shape is investigated in terms of rapid mixing of fuel jet and supersonic airstream. Two goals, those are to maximize the jet core height and to minimize the total pressure loss, are adopted for the optimization. The numbers of maximum injector holes are restricted to 1, 2 and 3 during the evolutive process. Pareto fronts under the 2 and 3 maximum holes restriction evolve successfully. Self-Organizing Map (SOM) is applied, in order to realize the role of optimal solutions in actual design, to analysis of structure on design space by means of design database obtained in evolutive process of optimization. The design database is mapped onto the two-dimensional SOM, where design space is successfully visualized. The visualization that clarifies relativity of performance parameters acquires valuable design information.

著者関連情報
© 2004 The Japan Society for Aeronautical and Space Sciences
前の記事 次の記事
feedback
Top