Numerical investigation of an RBCC combustor during ramjet/scramjet mode transition

Joseph Salloum, Michael Candon, Andrew Ridings, Hideaki Ogawa, Masatoshi Kodera, Shuichi Ueda

研究成果: 書籍/レポート タイプへの寄稿会議への寄与

1 被引用数 (Scopus)


Rocket-based Combined-Cycle (RBCC) engines offer a promise for efficient and flexible propulsion over a large Mach number range by combining rocket and ramjet/scramjet technology. To achieve this, an RBCC engine uses four different modes of operation: rocket, ramjet, scramjet and dual-mode. During operation, the engine must make the transition from subsonic to supersonic combustion, i.e., ramjet to scramjet mode. The objective of this study is to gain physical insight into the ramjet-scramjet-ramjet mode transition by elucidating the underlying mechanics. Numerical simulations with chemical reactions have been performed for the transient flowfields of a two-dimensional RBCC combustor by using an unsteady Reynolds-Averaged Navier-Stokes solver. Mode transition is effected by changing the flow rate of the secondary hydrogen fuel injectors installed on the top and bottom walls of the combustor. A parametric study was conducted to investigate the characteristic and behavior of RBCC combustion in mode transition. The results indicated that transition is affected considerably by the presence and development of flow separation and pseudo-shock structures near fuel injectors. The complex effects of aerodynamic and aerothermal interactions on the transient flowfields and performance, along with a hysteresis observed between the scramjet-to-ramjet and ramjet-to-scramjet transition processes.

ホスト出版物のタイトルAIAA Aerospace Sciences Meeting
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
出版ステータス出版済み - 2018
イベントAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, 米国
継続期間: 1月 8 20181月 12 2018


名前AIAA Aerospace Sciences Meeting, 2018


その他AIAA Aerospace Sciences Meeting, 2018

!!!All Science Journal Classification (ASJC) codes

  • 航空宇宙工学


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