{"created":"2023-06-20T15:14:11.889778+00:00","id":44170,"links":{},"metadata":{"_buckets":{"deposit":"d9f6d607-bca0-4c84-8174-cb429320cd34"},"_deposit":{"created_by":1,"id":"44170","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"44170"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00044170","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["468104","468105","468106","468103","468108","468109","468102","468107"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Experimental Investigation on the Effect of Coolant Injection on Turbine Aerodynamic Characteristics.Part II: Effects of Injection from Rotor Casing with 30° Slanted Holes"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1988-06","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"23","bibliographicVolumeNumber":"587","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所資料"},{"bibliographic_title":"Technical Memorandum of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"ガスタービン入口温度の高温化に伴い翼及び翼周辺の冷却が必然となっているが,この冷却の為の吹出し空気が主流に及ぼす影響を調べるために,空冷タービン回転試験機を設計製作し,実験を行った。第一報では空力回転試験機と装置について報告した。本報告は,タービン動翼先端のシュラウドリングから二次空気(冷却空気に相当)を吹出した場合,吹出し空気が主流に及ぼす影響について述べたものである。なお,本研究は通商産業省工業技術院の大型省エネルギ技術研究開発制度(ムーンライト計画)による高効率ガスタービンの研究開発の一環として,航空宇宙技術研究所で進めている「タービン技術の研究開発」として行ったものである。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Using a test turbine, the authors investigated the effects of coolant injection on turbine aerodynamic characteristics. In this paper, part II, the effects of the coolant injection from a rotor casing with 30° slanted holes are described. The discussed turbine efficiency introduced herein is based on torque, rotational speed and mass flow rate, and the radial and tangential distributions of total pressure and flow angles. It may be concluded that there are some reductions in total pressure losses and increases in outlet flow angles in the tip region caused by the coolant injection.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTM0587000","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 TM-587","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":"0452-2982","subitem_source_identifier_type":"ISSN"}]},"item_3_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN00314334","subitem_source_identifier_type":"NCID"}]},"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原動機部"},{"subitem_text_value":"航空宇宙技術研究所原動機部"},{"subitem_text_value":"航空宇宙技術研究所原動機部"},{"subitem_text_value":"航空宇宙技術研究所原動機部"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"臼井, 弘"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"井上, 重雄"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"蓑田, 光弘"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"能瀬, 弘幸"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"USUI, Hiroshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"INOUE, Shigeo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"MINODA, Mitsuhiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"NOSE, Hiroyuki","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":"2020-01-29"}],"displaytype":"detail","filename":"naltm00587.pdf","filesize":[{"value":"1.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltm00587.pdf","url":"https://jaxa.repo.nii.ac.jp/record/44170/files/naltm00587.pdf"},"version_id":"e6873d3b-28f1-4ff3-b43b-dd6b8fc3706b"}]},"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":"空冷タービンの空力特性に関する研究(II)動翼シュラウドリングからの吹出しの影響(吹出し角30°の場合)","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"空冷タービンの空力特性に関する研究(II)動翼シュラウドリングからの吹出しの影響(吹出し角30°の場合)"}]},"item_type_id":"3","owner":"1","path":["1893","1916"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"44170","relation_version_is_last":true,"title":["空冷タービンの空力特性に関する研究(II)動翼シュラウドリングからの吹出しの影響(吹出し角30°の場合)"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T22:01:31.067517+00:00"}