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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
https://jaxa.repo.nii.ac.jp/records/44734
https://jaxa.repo.nii.ac.jp/records/4473454ecab7f-0b6d-4bdd-b93c-11d7f12b85db
名前 / ファイル | ライセンス | アクション |
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naltr00481.pdf (1.9 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 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 | |||||
言語 | ||||||
言語 | jpn | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||
資源タイプ | technical report | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Analysis of Temperature Distribution and Thermal Stress by The Finite Element Method and Application to Turbine Blade and Disk | |||||
著者 |
松末, 勝利
× 松末, 勝利× 吉田, 豊明× 橋本, 良作× 小河, 昭紀× 磯部, 俊夫× MATSUSUE, Katsutoshi× YOSHIDA, Toyoaki× HASHIMOTO, Ryosaku× OGAWA, Akinori× ISOBE, Toshio |
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著者所属 | ||||||
航空宇宙技術研究所原動機部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所原動機部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所原動機部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所原動機部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所計算センター | ||||||
著者所属(英) | ||||||
en | ||||||
Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Computer Center, National Aerospace Laboratory(NAL) | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory(NAL) | |||||
書誌情報 |
航空宇宙技術研究所報告 en : Technical Report of National Aerospace Laboratory TR-481 巻 481, p. 24, 発行日 1976-12 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 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. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0389-4010 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: NALTR0481000 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL TR-481 |