Effects of multi-section swirl injection method on fuel regression rate of high density polyethylene fueled hybrid rocket engine

Sho Ohyama, Y. Hirata, K. Araki, K. Ohe, Shigeru Aso, Yasuhiro Tani, T. Shimada

研究成果: Chapter in Book/Report/Conference proceedingConference contribution

1 被引用数 (Scopus)

抄録

Low fuel regression rate is fatal disadvantage for hybrid rocket. To overcome this problem, a lot of methods have been proposed. In Kyushu university multi-section swirl injection method has been proposed to increase the fuel regression rate and combustion efficiency. This method generates swirling flow in combustion chamber through injector ports located on the some cross-sections over a fuel grain. High density polyethylene and gaseous oxygen were used as propellant. Multi-section swirl injection method shows twice higher fuel regression rate than that of the conventional method with no swirl in the previous study. In the present study, the effects of the number and the diameter of injector ports was investigated under constant total injector ports area condition. To decrease interference of oxidizer flow, the average regression rate increased at low oxidizer mass flux region.

本文言語英語
ホスト出版物のタイトル49th AIAA/ASME/SAE/ASEE Joint PropulsionConference
出版ステータス出版済み - 9 16 2013
イベント49th AIAA/ASME/SAE/ASEE Joint PropulsionConference - San Jose, CA, 米国
継続期間: 7 14 20137 17 2013

出版物シリーズ

名前49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

その他

その他49th AIAA/ASME/SAE/ASEE Joint PropulsionConference
Country米国
CitySan Jose, CA
Period7/14/137/17/13

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

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