Turbojet-engine noise studies to evaluate effects of inlet-guide-vane--rotor spacing
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35-percent rpm 50-hertz constant-bandwidth filter 80-percent rated rpm 80-percent speed axial-flow compressor azimuth angle azimuth location broadband noise circumferential Mach number Crigler cut-off ratio downstream stator engine dashed curve engine performance first-stage rotor first-stage stator Frequency analysis frequency spectra fundamental blade-passage frequency harmonic number hertz IGV and rotor IGV assembly increased IGV-rotor spacing Increased inlet-guide-vaneórotor spacing increased spacing inlet duct interaction noise Langley Research Center lobe patterns mean rotor-blade chords measured at 30 modified engine dashed noise level noise measurements noise peaks noise reductions noise-radiation patterns number of lobes overall noise peak corresponding percent presented in figure pulsating flows quency radiation patterns radius rotational speed rotor blades rotor-blade chords ahead Rotor-shaft speed rpm Mt second harmonic second-stage rotor sources of noise speed of 80-percent spinning-mode patterns standard and modified standard engine stationary vanes struts table II(a table n(a three engine speeds turbojet turbojet engine upstream stator