| タイトル | CFD analysis of jet mixing in low NOx flametube combustors |
| 本文（外部サイト） | http://hdl.handle.net/2060/19910016832 |
| 著者（英） | Lai, M. C.; Holdeman, J. D.; Smith, C. E.; Talpallikar, M. V. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1991-01-01 |
| 言語 | eng |
| 内容記述 | The Rich-burn/Quick-mix/Lean-burn (RQL) combustor was identified as a potential gas turbine combustor concept to reduce NO(x) emissions in High Speed Civil Transport (HSCT) aircraft. To demonstrate reduced NO(x) levels, cylindrical flametube versions of RQL combustors are being tested at NASA Lewis Research Center. A critical technology needed for the RQL combustor is a method of quickly mixing by-pass combustion air with rich-burn gases. Jet mixing in a cylindrical quick-mix section was numerically analyzed. The quick-mix configuration was five inches in diameter and employed twelve radial-inflow slots. The numerical analyses were performed with an advanced, validated 3-D Computational Fluid Dynamics (CFD) code named REFLEQS. Parametric variation of jet-to-mainstream momentum flux ratio (J) and slot aspect ratio was investigated. Both non-reacting and reacting analyses were performed. Results showed mixing and NO(x) emissions to be highly sensitive to J and slot aspect ratio. Lowest NO(x) emissions occurred when the dilution jet penetrated to approximately mid-radius. The viability of using 3-D CFD analyses for optimizing jet mixing was demonstrated. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 91N26146
E-6313
ASME-91-GT-217
NAS 1.15:104466
NASA-TM-104466 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/131897 |
