| タイトル | Experimental clean combustor program; noise measurement addendum, Phase 2 |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760024143 |
| 著者（英） | Emmerling, J. J.; Bekofske, K. L. |
| 著者所属（英） | General Electric Co. |
| 発行日 | 1976-01-01 |
| 言語 | eng |
| 内容記述 | Combustor noise measurements were performed using wave guide probes. Test results from two full scale annular combustor configurations in a combustor test rig are presented. A CF6-50 combustor represented a current design, and a double annular combustor represented the advanced clean combustor configuration. The overall acoustic power levels were found to correlate with the steady state heat release rate and inlet temperature. A theoretical analysis for the attenuation of combustor noise propagating through a turbine was extended from a subsonic relative flow condition to include the case of supersonic flow at the discharge side. The predicted attenuation from this analysis was compared to both engine data and extrapolated component combustor data. The attenuation of combustor noise through the CF6-50 turbine was found to be greater than 14 dB by both the analysis and the data. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 76N31231
R75AEG147-13-ADD
NASA-CR-135045 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/184646 |
