並列タイトル等An Experimental Investigation of Combustion Performance of LOX/GH2 Rocket Combustor with Coaxial Injectors
タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-473
一般注記An experimental investigation of combustion performance was conducted in a LOX/GH2 rocket combustor with coaxial type injectors at a thrust level of 300 kgf with a nominal chamber pressure of 20 atm. The oxidant-fuel ratios ranged from approximately 2 to 10. The combustion chambers were of the segmented, heat-sink type. The chamber geometry varied in lengths from 11 to 26 cm and contraction rations of 2.03, 3.41 and 4.46, with a constant nozzle throat area. The injector had twelve coaxial elements with no recess and three replaceable faceplates having different hydrogen port areas. The attendant hydrogen-oxygen injection velocity ratio ranged from approximately 10 to 50. Observed C* efficiencies were correlated as a function of an equivalent chamber length, Le, in which the injection velocity ratio, VR, and the chamber length, L, are expressed as Le=L+αVR where α was considered nearly constant throughout the experiment. The correlation takes the form of ηc*=1-A exp(-BLe) where the constants A and B depend on the chamber contraction ratio. The variations of all experimental data from the relation were within approximately ± 1.8 percent.
資料番号: NALTR0473000
レポート番号: NAL TR-473
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44726&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