Noise reduction by means of inlet-guide-vane choking in an axial-flow compressor
David Chestnutt, United States. National Aeronautics and Space Administration, Langley Research Center
National Aeronautics and Space Administration, 1968 - Technology & Engineering - 30 pages
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0.06 guide vanes 0.12 inlet guide 1/2-chord axial location 1/2-chord spacing 100 percent speed airflow airfoil anechoic chamber angle of 15 axial Mach number AXIAL-FLOW COMPRESSOR back-pressure valves blade passage frequency choking occurs compressor performance configuration corrected compressor speed data points relate decibels discharge effects of inlet-guide-vane enthalpies feet/second meters/second first-stage rotor ft/sec 671 ft/sec function of corrected guide vanes removed guide vanes set guide-vane angle higher speeds increased inlet bellmouth Inlet Flow inlet guide vanes inlet-guide-vane angle INLET-GUIDE-VANE CHOKING inlet-guide-vane thickness Langley Research Center levels as function maximum noise reductions Maximum overall sound NASA TN noise levels obtained operating condition overall noise overall sound pressure overall-sound-pressure-level radiation patterns partial choking percent Figure performance losses plotted pressure ratio pressure-ratio losses probe microphone research air compressor rotor blade passage setting and 1/2-chord shown in figure sound pressure level spectra spectrum analysis static-pressure thermocouple transitional shock region Typical back-pressure setting velocity