{"created":"2023-06-20T15:14:44.563572+00:00","id":44734,"links":{},"metadata":{"_buckets":{"deposit":"25e13bab-5d56-4af0-b59a-5d0cb6710724"},"_deposit":{"created_by":1,"id":"44734","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"44734"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00044734","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["470971","470979","470972","470978","470975","470973","470977","470980","470976","470974"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Analysis of Temperature Distribution and Thermal Stress by The Finite Element Method and Application to Turbine Blade and Disk"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1976-12","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"24","bibliographicVolumeNumber":"481","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-481","bibliographic_titleLang":"en"}]}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The location and configuration effects of cooling passages, in an air-cooled turbine blade, on blade thermal transient stress under engine operating conditions were investigated using a finite-element Fortran program written to provide a solution to two-dimensional, unstable temperature distribution and thermal stress in a homogeneous material under several kinds of thermal boundary conditions. The results indicate that greater periodic stress and strain occur in the material around the coolant passages located either in the blade hub and near the blade leading edge during the operating cycle. The results suggest that the location and configuration of the cooling passages affect, to a great extent, the fatigue life of the turbine blade. Mechanical and thermal stresses in a turbine disk with eccentric holes near the periphery of the disk were also analyzed using the same computer program. The results indicate that thermal stress was not dominant even near the periphery of the disk.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR0481000","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-481","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"},{"subitem_text_value":"航空宇宙技術研究所計算センター"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Aeroengine Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Aeroengine Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Aeroengine Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Aeroengine Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Computer Center, National Aerospace Laboratory(NAL)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"松末, 勝利"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"吉田, 豊明"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"橋本, 良作"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"小河, 昭紀"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"磯部, 俊夫"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"MATSUSUE, Katsutoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"YOSHIDA, Toyoaki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"HASHIMOTO, Ryosaku","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"OGAWA, Akinori","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"ISOBE, Toshio","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":"naltr00481.pdf","filesize":[{"value":"1.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr00481.pdf","url":"https://jaxa.repo.nii.ac.jp/record/44734/files/naltr00481.pdf"},"version_id":"55898ffd-0536-4804-b64d-07a8f3cf1346"}]},"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":"有限要素法による二次元熱伝導計算とタービン翼およびディスクの熱応力解析","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"有限要素法による二次元熱伝導計算とタービン翼およびディスクの熱応力解析"}]},"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":"44734","relation_version_is_last":true,"title":["有限要素法による二次元熱伝導計算とタービン翼およびディスクの熱応力解析"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:51:45.299408+00:00"}