A JT8D-17R engine with inverted primary and fan flows was tested under static conditions as well as in the NASA Ames 40 by 80 Foot Wind Tunnel to determine static and flight noise characteristics, and flow profile of a large scale engine. Test and analysis techniques developed by a previous model and JT8D engine test program were used to determine the in-flight noise. The engine with inverted flow was tested with a conical nozzle and with a plug nozzle, 20 lobe nozzle, and an acoustic shield. Wind tunnel results show that forward velocity causes significant reduction in peak PNL suppression relative to uninverted flow. The loss of EPNL suppression is relatively modest. The in-flight peak PNL suppression of the inverter with conical nozzle was 2.5 PNdb relative to a static value of 5.5 PNdb. The corresponding EPNL suppression was 4.0 EPNdb for flight and 5.0 EPNdb for static operation. The highest in-flight EPNL suppression was 7.5 EPNdb obtained by the inverter with 20 lobe nozzle and acoustic shield. When compared with the JT8D engine with internal mixer, the inverted flow configuration provides more EPNL suppression under both static and flight conditions.
Flight Effects on Noise by the JT8D Engine with Inverted Primary/Fan Flow as Measured in the NASA-Ames 40 by 80 Foot Wind Tunnel
1978
246 pages
Report
Keine Angabe
Englisch
Jet & Gas Turbine Engines , Noise Pollution & Control , Flow characteristics , Jet aircraft noise , Jet flow , Noise measurement , Turbofan engines , Wind tunnel tests , Conical nozzles , Effective perceived noise levels , Noise reduction , Nozzle flow , Supersonic transports , Noise pollution , T-8 engines , JT8D-17R engines