| タイトル | Modeling of a Sequential Two-Stage Combustor |
| 本文（外部サイト） | http://hdl.handle.net/2060/20050175874 |
| 著者（英） | Brankovic, A.; Liu, N.-S.; Hendricks, J. A.; Ryder, R. C.; Hendricks, R. C.; Gallagher, J. R. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2005-03-01 |
| 言語 | eng |
| 内容記述 | A sequential two-stage, natural gas fueled power generation combustion system is modeled to examine the fundamental aerodynamic and combustion characteristics of the system. The modeling methodology includes CAD-based geometry definition, and combustion computational fluid dynamics analysis. Graphical analysis is used to examine the complex vortical patterns in each component, identifying sources of pressure loss. The simulations demonstrate the importance of including the rotating high-pressure turbine blades in the computation, as this results in direct computation of combustion within the first turbine stage, and accurate simulation of the flow in the second combustion stage. The direct computation of hot-streaks through the rotating high-pressure turbine stage leads to improved understanding of the aerodynamic relationships between the primary and secondary combustors and the turbomachinery. |
| NASA分類 | Aircraft Propulsion and Power |
| レポートNO | NASA/TM-2005-212631
ISROMAC10-2004-037
E-14193 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/220196 |
