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Acoustics and thrust of separate flow exhaust nozzles with mixing devices investigated for high bypass ratio engines
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Saiyed, Naseem H. |
| Copyright Year | 2000 |
| Description | Typical installed separate-flow exhaust nozzle system. The jet noise from modern turbofan engines is a major contributor to the overall noise from commercial aircraft. Many of these engines use separate nozzles for exhausting core and fan streams. As a part of NASA s Advanced Subsonic Technology (AST) program, the NASA Glenn Research Center at Lewis Field led an experimental investigation using model-scale nozzles in Glenn s Aero-Acoustic Propulsion Laboratory. The goal of the investigation was to develop technology for reducing the jet noise by 3 EPNdB. Teams of engineers from Glenn, the NASA Langley Research Center, Pratt & Whitney, United Technologies Research Corporation, the Boeing Company, GE Aircraft Engines, Allison Engine Company, and Aero Systems Engineering contributed to the planning and implementation of the test. |
| File Size | 45361 |
| File Format | |
| Language | English |
| Publisher Date | 2000-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Exhaust Nozzles Jet Aircraft Noise Noise Reduction Systems Engineering Aerodynamic Noise Aeroacoustics Turbine Exhaust Nozzles Thrust Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
