Abstract
The effects of flow rate, combustor temperature rise, inlet temperature, nozzle exit diameter, and duct length on spectral content, directionality, radiated sound power, and thermoacoustic efficiency are deduced experimentally using an 8-in.-diam combustor. Even at a high exit velocity of 900 fps, the combustor-on noise is seen to dominate jet noise. Internal and far-field spectra are similar below 1000 Hz (broadband with spikes at longitudinal duct resonance frequencies). Directionality is weak except at exit velocities in excess of 550 fps. At a given nozzle exit temperature and diameter, the internal overall sound pressure levels appear to be related linearly to the far-field levels. The thermoacoustic efficiencies vary from 10 ~ to 10 ~ 4 .
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