국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Hydrogen Combustion Tests Simulating a Subsonic Ram-Combustor for a Hypersonic Plane
저자	Takashi TAMARU, Kazuo SHIMODAIRA, Takashi SAITO, Hideshi YAMADA
Keyword
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltr01193.pdf?id=NALTR0001193
보고서번호	NAL TR-1193
발행년도	1993.3
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	To obtain design data of a subsonic ram-combustor for a hypersonic plane,hydrogen combustion tests were made using an approximately onetenth scale model.The model was composed of a constant area combustion duct 150 mm in diameter,flame holders and a centerbody which simulates the turbo-fan engine part to be used as a booster for the take-off mode.The tested conditions of supplied air velocity,air temperature and mixture strength were equivalent to those of the combustor inlet at flight speeds ranging from take-off to Mach 3.Gas velocity and temperature distributions along the axis,and the values of totalon in the combustor exerts a significant effect on combustion efficiency,particularly near the stoichiometric mixture condition.