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Other TitleAutoignited combustion performance in a water-cooled scramjet combustor
Author(jpn)村上 淳郎; 工藤 賢司; 平岩 徹夫; 鎮西 信夫; 苅田 丈士
Author(eng)Murakami, Atsuo; Kudo, Kenji; Hiraiwa, Tetsuo; Chinzei, Nobuo; Kanda, Takeshi
Author Affiliation(jpn)宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部 事業推進部; 宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部
Author Affiliation(eng)Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Japan Aerospace Exploration Agency Program Management and Integration Dept., Inst. of Space Tech. and Aeronautics; Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Issue Date2005-03-28
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication date2005-03-28
AbstractA water-cooled scramjet combustor was tested to study the effects of pressure, combustor length, fuel-injection style, and wall temperature on autoignited combustion performance. The tests were conducted with an inflow Mach number of 2.5; total pressure of air of 1, 1.5, and 2 MPa; and total temperature of air from 1,200 to 2,600 K. High-enthalpy air was produced using a vitiation heater. The combustion condition was detected by a temperature increase in the combustor, which was related to a local combustion condition. When hydrogen fuel was supplied transversely to the combustor wall downstream of the backward-facing step, the autoignited combustion performance degraded with increasing airflow pressure at a low total temperature of the vitiated air. The ignition region was around the second explosion limit. The presence of H2O in the air further retarded ignition under the high-pressure condition. In high-temperature conditions, the combustion performance improved with increasing pressure. With a long combustor with a downstream extension, the autoignited combustion limit of the air temperature became lower. A long separation region was presumed to exist downstream of the transverse fuel jet. Under such conditions, the potential for autoignited combustion could be improved. This effect of the extension of the combustor length decreased with increasing pressure. Parallel fuel injection from the step base showed a low autoignition tendency. In the parallel injection, autoignition would initiate at the base of the step, where the pressure was low and the size of the base was small. In the water-cooled combustor, the autoignited combustion limit of air temperature was higher than that in the uncooled combustor. This fact suggested that an ignition source existed near the wall, for example, in the separation region.
DescriptionJAXA Research and Development Report
Keywordswater-cooled scramjet; combustion chamber; ignition; burning process; combustion efficiency; water-cooled combustor; autoignited performance; fuel injection style; combustion test; finite element method; pressure; wall temperature; transverse injection; parallel injection; 水冷スクラムジェット; 燃焼室; 着火; 燃焼過程; 燃焼効率; 水冷燃焼器; 自発着火性能; 燃料噴射法; 燃焼試験; 有限要素法; 圧力; 壁温度; 横方向噴射; 平行噴射
Document TypeTechnical Report
JAXA Category研究開発報告
Report NoJAXA-RR-04-034

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