Abstract
Studies have been made to determine sound intensities and frequency distribution of axial-flow compressor noise and their relation to compressor stage loading and blade passage rates. Inlet noise measurements of several turbo-jet engines at compressor speeds from idle to maximum power indicate good correlation of peak noise frequencies of the first five stages of the compressor. Measurements on several engines of the lt 000-lb thrust class indicate no significant difference of inlet noise levels. A very intense low-frequency tone, not explicitly related to blade passage frequency, has been measured during part- and full-speed operation of two jet engines. Mechanisms which produce this peculiar noise may include the little understood phenomenon known as “rotating stall.”
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