Abstract
To obtain baseline data, first the sound power spectrum of jet exiting from a nozzle of 2.5-in. throat diameter was measured with high accuracy as a function of the pressure ratio (up to 3) and temperature (up to 3300°F) utilizing the reverberation chamber method. Subsequently, the effect of augmeter tubes and subsonic diffusers on the noise generation process was investigated utilizing a test setup consisting of two adjacent reverberation chambers (burner room and exhaust room) connected to each other by the augmenter tube. The sound power was measured simultaneously in both rooms in order to evaluate both the change in total sound power output, and the split of the sound power between the burner room and exhaust rooms as a function of nozzle augmenter entrance distance for various ratios of the augmenter nozzle diameter. The paper will report the result of the acoustical and pumping performance tests. [This work was supported in part by the United States Navy, Southern Division Naval Facilities Engineering Command.]
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