Abstract
The Paper deals with the investigation of the effect of multiple facets of pulse detonation combustors on its acoustic signature. First, the acoustic signature is characterized in both the near- and far-field regimes in an anechoic test facility. The shock strength and speed are mapped as functions of radial distance and direction (60–180 deg) from the combustor exhaust plane. The generated pressure field is then compared to a theoretical point-source explosion model. Second, the far-field sound pressure level is obtained, at different directivity angles, generated by a combustor tube at varied conditions of operating frequency, equivalence ratio, fill fraction, nitrogen dilution for a mixture of ethylene–oxygen–nitrogen and exit nozzle geometries. Shadowgraphy is performed to qualitatively account for the impact of these nozzle geometries on the shock wave and supersonic jet that characterize the combustor exhaust flow. Finally, the far-field acoustic signature of a system composed of two pulse detonation combustors is investigated. The firing time delay between the detonation tubes is varied to determine if any leading shock interactions affect the far-field noise. Further investigation is made into the cross-talk and separation distance between the detonation tubes.
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