| タイトル | Preliminary investigation of a two-zone swirl flow combustor |
| 本文（外部サイト） | http://hdl.handle.net/2060/19840014497 |
| 著者（英） | Biaglow, J. A.; Smith, J. M.; Johnson, S. M. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1984-01-01 |
| 言語 | eng |
| 内容記述 | The effect of full-annular swirling-flow on a flow-zone combustor design is investigated. Swirl flow angles of 25, 35, and 45 degrees were investigated in a combustor design envelope typical of those used in modern engines. The two-zone combustor had 24 pilot-zone fuel injectors and 24 main-fuel injectors located in the centerbody between the pilot and swirl passage. Combustor performance was determined at idle, and two parametric 589 K inlet temperature conditions. Combustor performance was highest with the 45 degree swirl vane design; at the idle condition, combustion efficiency was 99.5 percent. The 45 degree swirl vane also produced the lowest pattern factor of the three angles and showed a combustor lean blowout limit below a 0.001 fuel-air ratio. Combustor total pressure drop varied from a low of 4.6 percent for the 25 degree swirl to a high of 4.9 percent for the 45 degree swirl. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 84N22565
NAS 1.15:83637
E-2029
NASA-TM-83637 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/159717 |
