{"created":"2023-06-20T15:11:29.560181+00:00","id":41162,"links":{},"metadata":{"_buckets":{"deposit":"89c7109e-7f05-48a2-9bac-efaa0b40ce12"},"_deposit":{"created_by":1,"id":"41162","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41162"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041162","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["450853","450847","450848","450851","450855","450854","450849","450846","450850","450852","450842","450845","450843","450844"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Effects of hydrogen addition on combustion performance of a LOX/kerosene rocket"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1992-09","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"15","bibliographicPageStart":"1","bibliographicVolumeNumber":"1177","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"液体酸素-ケロシン(RJ-1J)を主推進剤とするロケット燃焼器に少量の水素を混焼することによって、燃焼効率(特性速度効率η｛C*｝)が改善されるか否かを実験的に調べた。実験には、燃焼圧力10MPaにおいて公称推力7kNを発生する燃焼器を用いた。主推進剤の噴射器としては、FOFトリプレット型(ケロシン2噴流と液体酸素1噴流が1点で衝突する)要素を持つものを2個、OFOトリプレット型(液体酸素2噴流とケロシン1噴流が1点で衝突する)要素を持つものを1個用いた。混焼用の気体水素は、多孔質性とした噴射器面を通して、あるいは噴射器直近の燃焼室周囲に設けたスリットを通して噴射した。総燃料に対する添加水素の割合は、0〜13％の範囲で変化させた。本実験の結果から、使用したすべての噴射器および水素添加方法について、測定された特性速度は上昇するがその効率の改善には結びつかないことが分かった。すなわち、主推進剤の噴射形式としてFOF型の噴射要素を用い、水素を燃焼室壁のスリットから噴射した場合あるいは水素を多孔質性の噴射器面から噴射した場合には、10％の水素の添加によりη｛C*｝は約2％低下した。また、OFO型の噴射要素を用い、水素を噴射器面から噴射した場合には、水素の添加によってη｛C*｝はほとんど変化しなかった。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The effect of the addition of hydrogen on the combustion performance of a LOX/kerosene rocket combustor was experimentally studies. Combustors with a seven kN thrust force at a nominal chamber pressure of 10 MPa were employed for the firing tests. Liquid OXygen (LOX) and kerosene (RJ-1J) were used as the main propellants and gaseous hydrogen added as auxiliary fuel. Two types of Fuel Oxidizer Fuel (FOF) triplet injectors (type A, type B) and one type of Oxidizer Fuel Oxidizer (OFO) triplet injector (type C) were used for main propellants injection. Hydrogen was added to each combustor either from a slit located on the chamber wall near the injector face (type A) or through the injector's porous face plate (type B, type C). The mass fraction of hydrogen to the total amount of fuel was varied from zero to 13 percent. Results indicated that such hydrogen to LOX/kerosene combustion does not improve combustor efficiency, e.g., when FOF injectors (type A, type B) were used and 10 percent hydrogen was added, combustion efficiency decreased approximately two percent. In addition, when the OFO injector (type C) was used and hydrogen was added through the injector face, the combustion efficiency remained the same under all tests conditions.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0004192000","subitem_description_type":"Other"}]},"item_3_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: NAL TR-1177","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所 角田支所"},{"subitem_text_value":"航空宇宙技術研究所 角田支所"},{"subitem_text_value":"航空宇宙技術研究所 角田支所"},{"subitem_text_value":"航空宇宙技術研究所 角田支所"},{"subitem_text_value":"航空宇宙技術研究所 角田支所"},{"subitem_text_value":"航空宇宙技術研究所 角田支所"},{"subitem_text_value":"航空宇宙技術研究所 角田支所"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"小野, 文衛"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"田村, 洋"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"熊川, 彰長"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"坂本, 博"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"佐藤, 和雄"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"佐々木, 正樹"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"八柳, 信之"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ono, Humiei","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tamura, Hiroshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kumakawa, Akinaga","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sakamoto, Hiroshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sato, Kazuo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sasaki, Masaki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yatsuyanagi, Nobuyuki","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":"2020-01-27"}],"displaytype":"detail","filename":"naltr01177.pdf","filesize":[{"value":"1.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01177.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41162/files/naltr01177.pdf"},"version_id":"8ea8bfca-5d3f-44a9-bbcc-8bef7f5da787"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"液体ロケットエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"推進剤","subitem_subject_scheme":"Other"},{"subitem_subject":"液体酸素ケロシン推進剤","subitem_subject_scheme":"Other"},{"subitem_subject":"水素燃料","subitem_subject_scheme":"Other"},{"subitem_subject":"炭化水素ロケットエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"燃焼試験","subitem_subject_scheme":"Other"},{"subitem_subject":"燃焼性能","subitem_subject_scheme":"Other"},{"subitem_subject":"燃焼効率","subitem_subject_scheme":"Other"},{"subitem_subject":"3噴流型噴射器","subitem_subject_scheme":"Other"},{"subitem_subject":"噴流衝突型噴射器","subitem_subject_scheme":"Other"},{"subitem_subject":"燃焼速度増加","subitem_subject_scheme":"Other"},{"subitem_subject":"燃焼安定化","subitem_subject_scheme":"Other"},{"subitem_subject":"2元燃料システム","subitem_subject_scheme":"Other"},{"subitem_subject":"水素添加","subitem_subject_scheme":"Other"},{"subitem_subject":"liquid rocket engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"propellant","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"LOX kerosene propellant","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hydrogen propellant","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hydrocarbon rocket engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"firing test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"combustion performance","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"combustion efficiency","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"triplet injector","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"impinging stream injector","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"combustion velocity acceration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"combustion stabilization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"dual fuel system","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hydrogen addition","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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"水素を混焼した液体酸素-ケロシンロケットの燃焼特性","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"水素を混焼した液体酸素-ケロシンロケットの燃焼特性"}]},"item_type_id":"3","owner":"1","path":["1893","1917"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"41162","relation_version_is_last":true,"title":["水素を混焼した液体酸素-ケロシンロケットの燃焼特性"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:12:53.522092+00:00"}