@inproceedings{oai:jaxa.repo.nii.ac.jp:00006158,
 author = {大庭, 芳則 and 荒川, 忠一 and 松尾, 裕一 and Oba, Yoshinori and Arakawa, Chuichi and Matsuo, Yuichi},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2005論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2005},
 month = {Feb},
 note = {In small gas turbine engines, the boundary layer separation-reattachment phenomena on low pressure turbine blade surfaces are strongly affected by the upstream wakes at low Reynolds number conditions (O is approximately 10(exp 5)). It is well known that it is difficult to predict the phenomena using Reynolds Averaged Navier-Stokes (RANS) approach because of the assumptions of the turbulence modeling and of the complicated flow structure. On the other hand, Large Eddy Simulation (LES) will be the powerful tool to predict the phenomena, because LES enables to correctly predict the detailed flow structures that occur in turbulent boundary layers. In the study, LES was carried out to predict the phenomena of a wake blade interaction. The wake was generated by a moving cylinder which interacted periodically with a turbine blade. The flow field was discussed for a Reynolds number of 130,000 based on the chord length of the blade. The LES results were evaluated by comparing with measured data. From the results, it was found that the time averaged static pressure (Cp) profiles on the blade agree with the experimental data. More detailed comparisons using velocity root mean square (RMS) values on the different locations of the blade suction surface were conducted. Accurate prediction of the separation-reattachment phenomena of the boundary layer on the blade suction surface was obtained., 資料番号: AA0049212025, レポート番号: JAXA-SP-05-017},
 pages = {150--155},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {上流ウェークの影響を受けるタービン翼面境界層の剥離:再付着現象のLES解析},
 volume = {JAXA-SP-05-017},
 year = {2006}
}