並列タイトル等Research on scramjet engine at hypervelocity condition
タイトル（掲載誌）宇宙航空研究開発機構特別資料: 平成16年度総合技術研究本部宇宙領域宇宙科学研究本部合同研究成果報告書:宇宙輸送系基盤技術 = JAXA Special Publication: FY2004 Report of Joint Research Achievements of the Space Division of Institute of Aerospace Technology and Institute of Space and Astronautical Science: Basic Technologies of Space Transportation Systems
一般注記To improve scramjet combustor performance at the hypervelocity condition corresponding to flight Mach number from 10 to 15, optimization possibility of the combustion gas temperature was investigated based on combustion experiment of a large-scale scramjet engine using a large free-piston driven shock tunnel. A previous engine model was designed so that the gas temperature at the combustor entrance would become around 1,200 K at the hypervelocity condition to prevent excessive loss in the net heat release due to thermal dissociation of the combustion gas. The results showed that the pressure rise due to combustion was large at the beginning of the test time but dropped drastically as time progressed. It was considered that the heat release obtained in the combustor was not sufficient to maintain intensive combustion. Following the discussion above, a new scramjet engine model (M12-02) was designed with an aim of promoting combustion heat release and establishing steady intensive combustion. The inlet compression ratio of the M12-02 WZLS increased to raise the static temperature and density of the flow at the combustor entrance. As a result of the design modification, the pressure rise due to combustion increased and the duration of intensive combustion was extended. The combustor performance became the highest at stagnation enthalpy of 7 MJ/kg, which was the design condition of the M12-02, and it was considered that the remarkable improvement in the combustor performance was achieved by establishing both adequately low gas temperature in the combustor and fairly stable combustion. Application of a Hyper-Mixer (HM) injector to the M12-02 was attempted with an aim of further improvement in the combustion stability and the combustor performance. The combustion test results showed that the HM injector was quite effective in establishing steady intensive combustion at the hypervelocity condition. In addition to the improvement in the mixing rate, capability in ignition and flame-holding at very low gas temperature condition was improved and high combustor performance was obtained at the low enthalpy condition. However, the combustor performance with the HM injector dropped as the stagnation enthalpy increased and became almost the same as that with a simple back-step injector at the enthalpy condition of 7 MJ/kg or higher.
資料番号: AA0049056017
レポート番号: JAXA-SP-05-010
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=6248&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ