Effect of Rotor Meridional Velocity Ratio on Response to Inlet Radial and Circumferential Distortion
National Aeronautics and Space Administration, 1979 - 69 pages
Three single transonic fan stages, each having a different meridional velocity ratio across its rotor, were tested with two magnitudes of tip radial distortion and with a 90 deg circumferential distortion imposed on the inlet flow. The rotor with the lowest meridional velocity ratio (less than 0.9 at the tip) demonstrated the least degradation of performance due to these distortions. Loss and deviation angle data (as needed for performance prediction with radial distortion) calculated along actual streamlines for radially distorted flow and correlated against diffusion factor, showed consistent agreement with data calculated along design streamlines for undistorted flow.
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70 percent ajnssajd axial velocity backup screen BLADE GEOMETRY blade-element performance BUS levels circumferential distortion Circumferential distributions Circumferential location compressor D-factor DESIGN BLADE-ELEMENT PARAMETERS design speed design streamlines deviation angle Diffusion factor distorted flow Distortion screen energy addition flow conditions flow field flow parameters high MVR rotor high MVR stage incidence angle leading edge loss coefficient low MVR rotor Mach number Magnitude of distortion MEAN ss TOT meridional velocity ratio midspan MVR rotor 11 MVR stage 11-4 N/cm NASA near-stall operating operating tip outlet total pressure Overall performance overall pressure ratio PEAK SS RP percent of design Percent of span RATIO TIP reference MVR stage rotor 20 rotor inlet rotor outlet span from tip SPAN MEAN ss stall pressure ratio static pressure stator 16 STREAMLINE SLOPE suction-surface TEMP TOTAL PRESS tip radial distortion tip region TOTAL TEMP TOTAL total temperature trailing edge undistorted sector undistorted-flow