Structural and fluidic investigation and instability suppression mechanism in the configuration of tip-driven electric fan for aircraft

2017 Fiscal Year Final Research Report

• Project/Area Number: 26420809
• Research Category: Grant-in-Aid for Scientific Research (C)
• Allocation Type: Multi-year Fund
• Section: 一般
• Research Field: Aerospace engineering
• Research Institution: Japan Aerospace EXploration Agency (2016-2017); The University of Tokyo (2014-2015)
• Principal Investigator: OKAI KEIICHI 国立研究開発法人宇宙航空研究開発機構, 航空技術部門, 主任研究開発員 (00358516)
• Co-Investigator(Kenkyū-buntansha): 渡辺 紀徳 東京大学, 大学院工学系研究科(工学部), 教授 (10201211)
• Co-Investigator(Renkei-kenkyūsha): YOKOZEKI TOMOHIRO 東京大学, 大学院工学系研究科, 准教授 (50399549) ; HIMENO TAKEHIRO 東京大学, 大学院工学系研究科, 准教授 (60376506) ; TAGASHIRA TAKESHI 宇宙航空研究開発機構, 航空技術部門, 主任研究開発員 (00344250)
• Project Period (FY): 2014-04-01 – 2018-03-31
• Keywords: 電動推進 / 外周駆動電動ファン / 構造解析 / 流体解析 / 翼変形 / 不安定性抑制

Outline of Final Research Achievements

Tip-driven electric fans have been investigated as a propulsion fan configuration for aircraft. The fan differs in the structural load configuration in the fan blade compared with the conventional fans. A structural and fluidic investigation for two baseline cases was investigated. Results show that the shroud with finite fillet radius gives lower performance, both in terms of pressure ratio and efficiency. For structural standpoint, there is an optimum shell thickness for each fan design baselines.
An instability suppression mechanism with tip-located electromagnetic device is proposed. The study presents description of analytical and experimental investigations using a simplified single blade model with a tip-located electromagnetic force mechanism. Force mechanisms of three types are proposed and compared. Results show that the force input on the occasion of simulated-blade instability, phase shift, and suppression of the instability can be attained using the proposed mechanism.

Free Research Field

総合工学・航空宇宙工学