@techreport{oai:jaxa.repo.nii.ac.jp:00044734,
 author = {松末, 勝利 and 吉田, 豊明 and 橋本, 良作 and 小河, 昭紀 and 磯部, 俊夫 and MATSUSUE, Katsutoshi and YOSHIDA, Toyoaki and HASHIMOTO, Ryosaku and OGAWA, Akinori and ISOBE, Toshio},
 month = {Dec},
 note = {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},
 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},
 year = {1976}
}