| タイトル | Experimental investigation of the low NO/sub x vortex airblast annular combustor |
| 本文（外部サイト） | http://hdl.handle.net/2060/19840014499 |
| 著者（英） | Biaglow, J. A.; Smith, J. M.; Johnson, S. M. |
| 著者所属（英） | NASA Goddard Space Flight Center |
| 発行日 | 1984-01-01 |
| 言語 | eng |
| 内容記述 | A low oxides of nitrogen vortex airblast annular combustor was evaluated which has attained the goal of 1 gm NO2/kg fuel or less during operation. The experimental combustor test conditions were a nominal inlet-air temperature of 703 K, inlet total pressures between 0.52 to 0.83 MPa, and a constant inlet Mach number of 0.26. Exit temperature pattern factors for all test points were between 0.16 and 0.20 and exit swirl flow angles were 47 degrees at isothermal conditions and 23 degrees during combustion. Oxides of nitrogen did not exceed 1.05 gm NO2/kg fuel at the highest inlet pressure and exhaust temperature tested. Previous correlations have related NOx proportionally to the combustor inlet pressure raised to some exponent. In this experiment, a band of exponents between 0.5 and 1.0 resulted for fuel-air ratios from 0.023 to 0.027 and inlet pressures from 0.52 to 0.83 MPa. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 84N22567
E-2046
NAS 1.15:83615
NASA-TM-83615 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/159715 |
