Aeroengine Division, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
Computer Center, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-481
巻
481
ページ
24
発行年
1976-12
抄録（英）
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.
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
naltr00481.pdf
(1.89MB)
