NDLI: Advanced subsonic technology (ast) separate-flow high-bypass ratio nozzle noise reduction program test report

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Advanced subsonic technology (ast) separate-flow high-bypass ratio nozzle noise reduction program test report

Content Provider	NASA Technical Reports Server (NTRS)
Author	Premo, John W. Barber, Thomas J. Schweiger, Paul S. Saiyed, Naseem Technical Monitor Low, John K. C.
Copyright Year	2000
Description	NASA s model-scale nozzle noise tests show that it is possible to achieve a 3 EPNdB jet noise reduction with inwardfacing chevrons and flipper-tabs installed on the primary nozzle and fan nozzle chevrons. These chevrons and tabs are simple devices and are easy to be incorporated into existing short duct separate-flow nonmixed nozzle exhaust systems. However, these devices are expected to cause some small amount of thrust loss relative to the axisymmetric baseline nozzle system. Thus, it is important to have these devices further tested in a calibrated nozzle performance test facility to quantify the thrust performances of these devices. The choice of chevrons or tabs for jet noise suppression would most likely be based on the results of thrust loss performance tests to be conducted by Aero System Engineering (ASE) Inc. It is anticipated that the most promising concepts identified from this program will be validated in full scale engine tests at both Pratt & Whitney and Allied-Signal, under funding from NASA s Engine Validation of Noise Reduction Concepts (EVNRC) programs. This will bring the technology readiness level to the point where the jet noise suppression concepts could be incorporated with high confidence into either new or existing turbofan engines having short-duct, separate-flow nacelles.
File Size	87214092
File Format	PDF
Language	English
Publisher Date	2000-12-01
Access Restriction	Open
Subject Keyword	Acoustics Jet Aircraft Noise Bypass Ratio Ducts Noise Reduction Nacelles Engine Tests Data Reduction Jet Engines Microphones Phased Arrays Nozzle Design Exhaust Nozzles Subsonic Flow Technology Assessment Combustion Chambers Separated Flow Aeroacoustics Mach Number 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

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