Noise studies of inlet-guide-vane: rotor interaction of a single-stage axial-flow compressor
National Aeronautics and Space Administration, 1965 - Technology & Engineering - 38 pages
9 pages matching octave at blade in this book
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3.39-chord spacing 53 guide vanes 6.25-chord spacing 62-guide-vane assembly Airflow airfoil anechoic chamber angle of attack axial spacing azimuth angle blade passage frequency calculated patterns calculated radiation patterns chord spacing Compressor Noise cut-off Mach number cut-off ratio data control room drag coefficient effect of rotor—inlet-guide-vane experimental data Figure 15 Figure 17 fundamental blade passage inlet guide vanes inlet-guide-vane configuration Jet Engine Langley Research Center levels when analyzed lobe number main data control multiple-stage compressor noise pressure noise radiation patterns NOISE STUDIES number of lobes number of rotor octave at blade oscillograph overall noise radiation peak noise level pitot-static tubes propagation range of rotor reduction in noise rotational speed rotor and guide rotor shaft speed rotor tip Mach rotor tip speed rotor—53-guide-vane configuration rotor—guide-vane spacing rotor—inlet-guide-vane spacing shown in figure spacer ring spacing on one-third spectra spinning modes stream velocity test setup tip Mach number turning angle velocity defect wave number