@inproceedings{oai:jaxa.repo.nii.ac.jp:00006473,
 author = {冨永, 卓司 and 谷口, 伸行 and Tominaga, Takuji and Taniguchi, Nobuyuki},
 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2004論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2004},
 month = {Mar},
 note = {In this study, the Large Eddy Simulation with the G-equation model is performed in the geometry of an axially staged annular combustor of a gas turbine engine. The propagation of flames in turbulent flow field depending on the equivalence ratios are represented by the extended G-equation model. The difference of the flame behaviors in the combustor is predicted for various equivalence ratios as observed in the experiment. While, the limit for the flame propagation toward the lean combustion region in the combustor is predicted to be leaner than the experimental data. The turbulent velocity field predicted by LES is also compared with the experimental data. Although the length of recirculation region generated by a swirling inlet flow is overestimated, the LES provided reasonable results in the averaged velocity field. The predicted results in the geometries of an experimental test piece and the modeled whole combustor are compared with each other. To investigate the affect of cut-out model of the annular combustor, the results for the turbulent flow field, the mixture fluctuation distribution and flame propagation did not greatly differ in the region where the experimental measurements conducted., 資料番号: AA0048469033, レポート番号: JAXA-SP-04-012},
 pages = {196--201},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {G方程式を用いたガスタービン燃焼器内の乱流燃焼場のLES},
 volume = {JAXA-SP-04-012},
 year = {2005}
}