| タイトル | Reduction of aircraft gas turbine engine pollutant emissions |
| 本文（外部サイト） | http://hdl.handle.net/2060/19780014155 |
| 著者（英） | Diehl, L. A. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1978-01-01 |
| 言語 | eng |
| 内容記述 | To accomplish simultaneous reduction of unburned hydrocarbons, carbon monoxide, and oxides of nitrogen, required major modifications to the combustor. The modification most commonly used was a staged combustion technique. While these designs are more complicated than production combustors, no insurmountable operational difficulties were encountered in either high pressure rig or engine tests which could not be resolved with additional normal development. The emission reduction results indicate that reductions in unburned hydrocarbons were sufficient to satisfy both near and far-termed EPA requirements. Although substantial reductions were observed, the success in achieving the CO and NOx standards was mixed and depended heavily on the engine/engine cycle on which it was employed. Technology for near term CO reduction was satisfactory or marginally satisfactory. Considerable doubt exists if this technology will satisfy all far-term requirements. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 78N22098
E-9601
NASA-TM-78870 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/179094 |
