국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Combustion Characteristics of LOX-hydrogen with High Mixture Ratio
저자	Hiroshi SAKAMOTO, Masaki SASAKI,Mamoru TAKAHASHI, Kazuo SATO
Keyword	Liquid Rocket Engine; Dual Mixture Ratio; Combustion Efficiency
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltr01278.pdf?id=NALTR0001278
보고서번호	NAL TR-1278
발행년도	1995.9
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	A dual mixture ratio LOX-hydrogen engine is proposed for application to the singel-srage-to-orbit vehicles (SSTO).The engine operates at a high mixture ratio,providing a high thrust-to-weight ratio in the booster mode ; at a low mixture ratio,it provies a high specific impulse in the high altitude operation.The application of this engine to the SSTO is expected to remarkably increase the payload of the vehicle.The present study investigated the combusion and heat transfer characteristics of dual mixture ratio LOX-hydrogen conbustors.Experiments were conducted with three coaxial injectors : one configuration with a conventional straight fuel annulus and two configurations with an angular fuel annulus.The data were obtained at a chamber pressure of 4.5 MPa and an oxidant to fuel ratio from 4.6 to 17 with single-element combustors.The conbustion test results were analyzed by using a ”simplified direct” method which directly uses pressure-distribution data along the chamber axis to solve one-dimensional stdy-state equations.By using the analysis,the distances required to vaporize the LOX spray for each injector were obtained.It was shown that the angular fuel annulus is effective in improving the combustion performance.Some of the heat transfer characteristics observed for each injector were also explained by the proposed simplified model.