{"created":"2023-06-20T15:14:05.837211+00:00","id":44071,"links":{},"metadata":{"_buckets":{"deposit":"9af94e34-9739-4755-a858-a169d47014aa"},"_deposit":{"created_by":1,"id":"44071","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"44071"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00044071","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["467468","467458","467457","467466","467469","467460","467471","467462","467472","467463","467465","467459","467464","467461","467467","467470"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1983-03","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"42","bibliographicVolumeNumber":"488","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":"通商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,当研究所ではエンジン要素の性能向上を図るための種々の研究を進めてきた。これ等のうち,高圧タービンの研究に関しては,冷却タービン翼の性能,信頼性,耐久性の向上を図ることを重要な目標の一つと定めて,研究を行ってきた。本報告では,高圧タービン冷却翼の二次元翼列ないしは三次元セクター翼例模型について,高圧高温条件の下に定常ならびに非定常冷却性能の実験解析を行うために設計製作した高温高圧翼列風胴試験装置の構成ならびに仕様について述べる。なお,本風胴の主な設計仕様は次の通りである。 主流空気流量 1.7kg/sec(最大) 入口ガス 圧力1.072MPa(9.9kgf/cm2,G)(最高) 入口ガス温度 約1,300K(1,027℃)(最高) 試験部 寸法100mm×60mm","subitem_description_type":"Abstract"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTM0488000","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 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