並列タイトル等Analysis of Temperature Distribution and Thermal Stress by The Finite Element Method and Application to Turbine Blade and Disk
タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-481
一般注記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.
資料番号: NALTR0481000
レポート番号: NAL TR-481
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44734&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ