| タイトル | Effect of diffuser bleed on performance of an annular swirl can combustor |
| 本文（外部サイト） | http://hdl.handle.net/2060/19740015361 |
| 著者（英） | Juhasz, A. J. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1974-05-01 |
| 言語 | eng |
| 内容記述 | A full-scale annular swirl can combustor equipped with diffuser bleed capability was tested at low fuel-air ratio, burning natural gas fuel. Test results show that, by drawing off a small amount of air on the inner or outer diffuser wall, the radial profile of combustor exit temperature could be changed from a strongly tip biased, to a strongly hub biased shape. Furthermore, combustor total pressure loss could be reduced by about one third by using a total bleed rate equal to 6 percent of diffuser inlet flow. At simulated engine idle conditions combustion efficiency was increased from 64 percent to nearly 100 percent by using 3 percent outer wall bleed. Combustor blowout performance was also improved significantly by using this diffuser bleed scheme. |
| NASA分類 | THERMODYNAMICS AND COMBUSTION |
| レポートNO | 74N23474
NASA-TM-X-3056
E-7854 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/194619 |
