An analytical study was performed which predicted the noise generated from the interaction of the wake of an inlet probe with a rotor. Absolute SPL predictions (Sound Pressure Level) of the BPF (Blade-Passage Frequency) were based on engine and probe geometry for the Boeing 18-inch fan ring. The interaction between the fan rotor and the wake of an inlet probe was shown to produce noise at the BPF which may introduce significant noise during approach conditions when the rotor/stator interaction is cut off. Predictions from this study showed rotor/probe-wake interaction noise to be greater than 10 dB above the rotor/stator interaction noise in some regions. The radiated noise was found to have a well-structured, highly three-dimensional character. For an azimuthal probe location of 0 deg of angle, peak far field SPL's were concentrated in the region bounded by the engine axis and a sideline angle of 50 deg of angle and azimuthal angles from 270 deg of angle to 360 deg of angle as measured in the direction of rotor rotation.
Noise predictions for rotor/inlet-probe wake interactions
Lärm-Vorhersagen für Rotor/Drucksensor-Wirbel-Interaktionen
1998
11 Seiten, 18 Bilder, 4 Tabellen, 14 Quellen
Aufsatz (Konferenz)
Englisch
Rotor Wake-Stator Interaction Noise--Predictions vs Data
Online Contents | 1993
|Rotor Wake/Stator Interaction Noise-Predictions vs Data
AIAA | 1993
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