A test to measure the acoustic noise and static pressure environment on a structure exposed to engine exhaust flow was conducted at the NASA Lewis Research Center Propulsion Systems Laboratory by using an F100 derivative engine with a two-dimensional convergent-divergent (2D/CD) non-flight-weight demonstrator nozzle. A highly instrumented, water cooled flat panel was placed behind the 2D/CD nozzle, and tests were conducted at simulated Mach/altitude flight conditions with the engine at military or maximum-afterburner power setting. The panel instrumentation consisted of acoustic pressure microphones, thermocouples, and static-pressure pickups. Measurements indicated that the exhaust environment may excite structural resonances up to 10,000 HZ and that overall sound pressure levels decrease with increasing altitude.
Exhaust Environment Measurements of a Turbofan Engine Equipped with an Afterburner and 2D Nozzle
1990
59 pages
Report
No indication
English
Jet & Gas Turbine Engines , Engine Studies, Energy Related , Air Pollution & Control , Noise Pollution & Control , Afterburning , Divergent nozzles , Exhaust gases , Exhaust nozzles , Jet aircraft noise , Noise measurement , Pressure measurement , Structural vibration , Turbofan engines , Altitude , Simulation , Static pressure
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