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titleMHD 発電技術のスクラムジェットエンジンへの適用に向けた数値解析
Other TitleNumerical Analysis of Application of MHD Generator Technology to Scram-jet Engine
Author(jpn)前原, 義明; 鈴木, 宏二郎
Author(eng)Maehara, Yoshiaki; Suzuki, Kojiro
Author Affiliation(jpn)東京大学大学院新領域創成科学研究科; 東京大学大学院新領域創成科学研究科
Author Affiliation(eng)Department of Advanced Energy, Graduate School of Frontier Science, University of Tokyo; Department of Advanced Energy, Graduate School of Frontier Science, University of Tokyo
Issue Date2010-02-26
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication titleJAXA special publication: Proceedings fo 41st Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2009
宇宙航空研究開発機構特別資料: 第41回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2009論文集
VolumeJAXA-SP-09-011
Publication date2010-02-26
Languagejpn
eng
AbstractTo realize the hypersonic transport or the low-cost fully reusable space transportation system, it is necessary to develop the SCRAM-jet engine. However, the performance of the SCRAM-jet engine is known to be quite sensitive to the air conditions at the inlet. In this research, we consider the use of the electromagnetic devices for the flow control and make the numerical research on the system. By setting the MHD generator and the MHD accelerator at the inlet and the nozzle of the SCRAM-jet engine, respectively, the flow inside the engine is appropriately controlled with small amount of the energy loss, when the flow has sufficient electric conductivity by the seeding technique. As the preliminary study, the two dimensional Euler analyses with MHD effects have been conducted to demonstrate that the inlet flow can be controlled by putting a MHD generator in the upstream region. From the analyses, it is confirmed that by setting the MHD generator and adding Lorenz force to the flow, the total pressure loss across the shock wave can be reduced, while the total pressure itself is decreased by the Lorenz force. To estimate the efficiency of such MHD energy-bypass SCRAM-jet engine, the totally coupled flow analysis of the inlet, combustion chamber and nozzle flows is necessary.
DescriptionOriginal contains color illustrations
Meeting Information: 18 June-19 June, 2009, Japan Aerospace Exploration Agency
形態: カラー図版あり
会議情報: 平成21年6月18-19日. 宇宙航空研究開発機構調布航空宇宙センター
Document TypeConference Paper
JAXA Category特別資料
ISSN1349-113X
NCIDAA11609371
SHI-NOAA0064672003
Report NoJAXA-SP-09-011
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/21389


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