並列タイトル等燃料噴射方向の異なるガスタービン筒形燃焼器の内部ガス温度および濃度分布の検討
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-906
一般注記The direction of fuel injection in a gas turbine combustor produces significant effects on the performance. Effects on the flame blow-off characteristics are especially large. Combustion by two kinds of fuel injection nozzles in the same combustion liner was investigated experimentally by measuring the temperature and gas composition. The combustor using the fuel nozzle which injects fuel inward around the center axis showed good performance under weak mixture conditions but exhibited a sudden flame blow-off at equivalence ratio 0.30 under high pressure conditions. Present results reveal that it has a poor flame holding structure without recirculation of hot gas under moderate mixture conditions, whereas it has a stable diffusion type flame under lean mixture conditions. The accuracy and the nature of the obtained temperature and the gas concentration data are discussed in this paper.
資料番号: NALTR0906000
レポート番号: NAL TR-906
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45165&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