| タイトル | Experimental combustor study program |
| 本文（外部サイト） | http://hdl.handle.net/2060/19800020810 |
| 著者（英） | Ekstedt, E. E.; Kasper, J. M. |
| 著者所属（英） | General Electric Co. |
| 発行日 | 1980-07-01 |
| 言語 | eng |
| 内容記述 | Advanced combustor concepts are evaluated as a means of accommodating possible future broad specification fuels. The three advanced double annular combustor concepts consisted of (1) a concept employing high pressure drop fuel nozzles for improved atomization, (2) a concept with premixing tubes in the main stage, and (3) a concept with the pilot stage on the inside and the main stage on the sideout, which is the reverse of the other two concepts. All of the advanced concepts show promise for reduced sensitivity to fuel hydrogen content. Some hardware problems were encountered, but these problems could be quickly resolved if refinement tests were conducted. The design with the premixing main stage was selected for a parametric test because of its low NOx emissions level, carbon free dome, and very low dome temperatures which were essentially independent of fuel type. The other advanced designs also had low done temperatures. The premixing dome design liner temperatures exhibited less sensitivity to fuel type than did the base-line combustor, although more sensitivity than observed for concept 1. The inner liner hot spot and the observed smoke results for the premixing design suggest that the fuel-air mixture was not as uniform as desired. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 80N29311 |
| 権利 | No Copyright |
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