| タイトル | Effect of flame stabilizer design on performance and exhaust pollutants of a two-row 72-module swirl-can combustor |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760013057 |
| 著者（英） | Biaglow, J. A.; Trout, A. M. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1976-03-01 |
| 言語 | eng |
| 内容記述 | A test program was conducted to evaluate the effects of four flame stabilizer designs on the performance and gaseous pollutant levels of an experimental full-annular swirl-can combustor. Combustor operating parameters, including inlet-air temperature, reference velocity, and fuel-air ratio, were set to simulate conditions in a 30:1 pressure ratio engine. Combustor inlet total pressure was held constant at 6 atm due to the facility limit. Combustor performance and gaseous pollutant levels were strongly affected by the geometry and resulting total pressure loss of the four flame stabilizer designs investigated. The addition of shrouds to two designs produced an 18 to 22% decrease in the combustion chamber pressure loss and thus resulted in doubling the exit temperature pattern factor and up to 42% higher levels of oxides of nitrogen. A previously developed oxides of nitrogen correlating parameter agreed with each model within an emission index of plus or minus 1 but was not capable of correlating all models together. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 76N20145
NASA-TM-X-3373
E-8564 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/186591 |
