| タイトル | Evaluation of an experimental short-length annular combustor: One-side-entry dilution airflow concept |
| 本文（外部サイト） | http://hdl.handle.net/2060/19730010240 |
| 著者（英） | Biaglow, J. A.; Humenik, F. M. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1973-03-01 |
| 言語 | eng |
| 内容記述 | A test program was conducted to evaluate an experimental short-length annular combustor that uses a one-side-entry dilution airflow concept. The combustor design features scoops on the outer liner for controlling the primary- and secondary-zone airflow distribution. Combustor inlet total pressures were limited to 62 N/sq cm (90 psia) with inlet-air temperatures from 590 K (600 F) to 890 K (1150 F). At a diffuser inlet Mach number of 0.25, the exit temperature pattern factor was 0.44 with an average exit temperature of 1436 K (2124 F) and a total pressure loss of 4.3 percent. At a diffuser inlet Mach number of 0.31, the exit temperature pattern factor was reduced to 0.29 with an average exit temperature of 1450 K (2151 F) and a total pressure loss of 6.1 percent. Nominal combustion efficiencies of 100 percent were obtained with the ASTM A-1 fuel. Exhaust gas emissions, smoke, and altitude relight data are included with exit-temperature profiles and distribution patterns. |
| NASA分類 | THERMODYNAMICS AND COMBUSTION |
| レポートNO | 73N18967
E-7267
NASA-TN-D-7225 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/200249 |
