{"created":"2023-06-20T15:14:05.638963+00:00","id":44067,"links":{},"metadata":{"_buckets":{"deposit":"b9ac1a89-20c0-4d70-a9ac-31cf686e9011"},"_deposit":{"created_by":1,"id":"44067","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"44067"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00044067","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["467407","467410","467402","467401","467408","467404","467415","467413","467414","467409","467405","467416","467411","467406","467412","467403"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1983-03","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"28","bibliographicVolumeNumber":"484","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":"通省産業省工業技術院の大型工業技術研究開発制度による航空機用ジェットエンジンの研究開発の一環として,ターボファンエンジンFJR710/10用に開発した高圧タービンの初段(計画タービン入口温度1.353K)を,高温タービン試験機HT-10Hとして組み,非燃焼空気ならびに燃焼ガスを作動流体として広い作動範囲にわたって空力性能試験を行った。供試タービン翼には,静翼にインピンジ冷却と対流冷却を,動翼に細孔による対流冷却を用いた。本報告には,試験機HT-10Hとその試験装置および供試タービンの構造,試験方法ならびに空力性能試験結果について述べる。","subitem_description_type":"Abstract"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTM0484000","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-484","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 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