JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
63161000.pdf6.4 MB
Other TitleDesign of mixed-flow type compressor for the Cluster Fan Engine by using computational fluid dynamics
Author(jpn)岩瀬 識; 才木 一寿
Author(eng)Iwase, Shiki; Saiki, Kazuhisa
Author Affiliation(jpn)宇宙航空研究開発機構 航空プログラムグループ; 宇宙航空研究開発機構 総合技術研究本部
Author Affiliation(eng)Japan Aerospace Exploration Agency Aviation Program Group; Japan Aerospace Exploration Agency Institute of Aerospace Technology
Issue Date2007-03-23
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication date2007-03-23
AbstractThe 'Cluster Fan Engine' was designed for personal aircrafts and VTOL aircrafts, having many merits including reliability of operation, flexibility of mounting, maintainability, extremely low development costs and initial costs, and wide variety of potential applications. Because new concepts were applied to aerodynamic components of the engine to reduce number of parts for itself, it is difficult to design the component based on the existing experimental data. Therefore, numerical simulations are conducted to validate the design process for the aerodynamic components. This report describes the design process of the mixed flow compressor based on the results of the numerical simulations.
DescriptionJAXA Research and Development Report
Keywordsturbofan engine; aircraft engine; compressor; compressor blade; engine design; computational fluid dynamics; Navier-Stokes equation; numerical analysis; cluster fan engine; mixed flow compressor; tip clearance; velocity triangle; compression ratio; ターボファンエンジン; 航空機エンジン; 圧縮機; 圧縮機ブレード; エンジン設計; 計算流体力学; ナビエ・ストークス方程式; 数値解析; クラスターファンエンジン; 斜流圧縮機; 翼端すきま; 速度3角形; 圧縮比
Document TypeTechnical Report
JAXA Category研究開発報告
Report NoJAXA-RR-06-005

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