{"created":"2023-06-20T15:08:03.144526+00:00","id":37442,"links":{},"metadata":{"_buckets":{"deposit":"3677101d-0360-4263-a7ba-b0fdf1306d97"},"_deposit":{"created_by":1,"id":"37442","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37442"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037442","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["480790","480795","480794","480789","480792","480791","480793","480796"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"On the combustion and unstart processes of a scramjet engine model"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1999-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"70","bibliographicPageStart":"65","bibliographicVolumeNumber":"44","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所特別資料"},{"bibliographic_title":"Special Publication of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_5_description_14":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）","attribute_value_mlt":[{"subitem_description":"航空宇宙技術研究所 16-18 Jun. 1999 東京 日本","subitem_description_type":"Other"}]},"item_5_description_15":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）（英）","attribute_value_mlt":[{"subitem_description":"National Aerospace Laboratory 16-18 Jun. 1999 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"この実験的および数値的研究の主な目的は、RJTF(ラムジェット試験設備)を用いて、マッハ数4、6、8の条件下でのエンジン燃焼実験で観測された弱燃焼と強燃焼と呼ばれる2つの代表的な燃焼モード間の遷移過程を明らかにすることである。この目的のために、コールドフロー実験とエンジンノズル内のフロープラグを用いた燃焼圧の数値シミュレーションを行い、燃焼器内の流れの構造と燃焼モード間遷移の際に起こる構造の変化を研究する。これらの結果および燃焼実験の結果から、以下のことが明らかになった。(1)主流中での自発着火は不可能である。すなわち、着火は境界層とストラットの後流の狭い領域内に限られる。(2)弱燃焼は、燃焼器下流部の付着境界層でしかも少し剥離気味の境界層において起こり、燃焼は反応律速下で行われる。(3)強燃焼は、主に、大規模に剥離した境界層および再循環領域で発生する。(4)弱燃焼から強燃焼への遷移は、燃料/空気の混合の促進と境界層内燃焼の相互作用の結果であり、燃焼により境界層剥離域領域は成長する。このような燃焼特性は、現在の燃料/空気混合エンジンでは推力を支える主燃焼が、大規模な境界層剥離と剥離領域内部での亜音速燃焼で見られような乱流混合に強く依存する。混合や燃焼の境界層剥離への依存性は、遷移の初期においてインレット不始動を生ずる。エンジン特性の改善には、燃焼器内の超音速主流内での効率的な超音速混合・着火・燃焼制御がまさに重要である。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Main purpose of this experimental and numerical study is to reveal a transition mechanism between two typical combustion modes called 'weak combustion' and 'intensive combustion' which have been observed in the engine firing tests at Mach four, six, and eight conditions using RJTF (Ramjet Engine Test Facility). For this purpose, flow structures in the combustor and their changes during the transition of combustion mode are investigated by means of cold flow tests as well as numerical simulations in which combustion pressure is simulated using flow plug set in the engine nozzle. Based on these results as well as the firing test results, it is revealed: (1) that self ignition in the core flow is impossible; ignition is possible only within the narrow regions of the boundary layer and the strut wake; (2) that combustion in the weak mode occurs within the attached and slightly separated boundary layer at the downstream part of the combustor and the combustion is kinetically controlled; (3) that combustion in the intensive mode mainly occurs within the largely separated boundary layer and recirculation area; and (4) that transition from 'weak mode' to 'intensive mode' is the consequence of mutual interaction between enhancement of fuel/air mixing and combustion within the boundary layer and the growth of the boundary layer separation area due to the combustion. Such combustion characteristics are due to the fact that in the present engine fuel/air mixing and principal combustion supporting the engine thrust strongly depend on the occurrence of large scale boundary layer separation and on the turbulent mixing as well as subsonic combustion within the separated boundary layer. The dependence of mixing and combustion on the boundary layer separation results in the early transition into inlet unstart. For improvement of engine performance, it is indeed important to carry out efficient supersonic mixing, ignition and combustion control in supersonic core flow in the combustor.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001961009","subitem_description_type":"Other"}]},"item_5_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: NAL SP-44","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0289-260X","subitem_source_identifier_type":"ISSN"}]},"item_5_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN10097345","subitem_source_identifier_type":"NCID"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuta Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuta Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuta Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuta Research Center"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"須浪, 徹治"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"櫻中, 登"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"志村, 隆"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"小寺, 正敏"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sunami, Tetsuji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sakuranaka, Noboru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Shimura, Takashi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kodera, Masatoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2020-02-10"}],"displaytype":"detail","filename":"nalsp0044009.pdf","filesize":[{"value":"1.7 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0044009.pdf","url":"https://jaxa.repo.nii.ac.jp/record/37442/files/nalsp0044009.pdf"},"version_id":"88593490-ac5d-4570-8736-73b1938dca48"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"燃焼","subitem_subject_scheme":"Other"},{"subitem_subject":"スクラムジェットエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"不始動","subitem_subject_scheme":"Other"},{"subitem_subject":"RJTF","subitem_subject_scheme":"Other"},{"subitem_subject":"ラムジェット試験設備","subitem_subject_scheme":"Other"},{"subitem_subject":"弱燃焼","subitem_subject_scheme":"Other"},{"subitem_subject":"強燃焼","subitem_subject_scheme":"Other"},{"subitem_subject":"コールドフロー実験","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD","subitem_subject_scheme":"Other"},{"subitem_subject":"数値流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"combustion","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"scramjet engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"unstart","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"RJTF","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"ramjet engine test facility","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"weak combustion","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"intensive combustion","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"cold flow test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computational fluid dynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"jpn"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"conference paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"スクラムジェットエンジンの燃焼・不始動過程に関する考察","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"スクラムジェットエンジンの燃焼・不始動過程に関する考察"}]},"item_type_id":"5","owner":"1","path":["1891","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"37442","relation_version_is_last":true,"title":["スクラムジェットエンジンの燃焼・不始動過程に関する考察"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:18:45.536796+00:00"}