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-1080
一般注記Autoignition and plasma-torch forced-ignition of hydrogen in a scramjet combustor were examined using a direct-connect test apparatus with various fuel injection patterns. Ignition behavior fell into three distinct categories, separated by the three bounding curves on an air temperature-fuel flow rate plane. The lowest boundary was independent of fuel injection patterns, while the other boundaries significantly depended on these patterns. Compared with injection from a single orifice, injection from multiple orifices appreciably enhanced autoignition, because fuel jets from adjacent orifices and from those on the opposite wall tended to attenuate the local flame quenching. A new plasma torch with a feed stock of air or oxygen was developed, which is desirable for a spaceplane from the viewpoint of total system design. The new plasma torch with air or oxygen stably operated without argon as a support gas. It was shown that the effectiveness of an air or oxygen plasma torch was comparable to that of a nitorogen or argon-hydrogen plasma torch, with the exception of an argon-hydrogen plasma torch in single-wall injection. A single plasma torch on a wall was able to ignite all the fuel jets injected from the same wall, but failed to ignite those from the opposite wall.
資料番号: NALTR1080000
レポート番号: NAL TR-1080
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45339&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