Effect of rotor meridional velocity ratio on response to inlet radial and circumferential distortion
Nelson L. Sanger, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Lewis Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1979 - Technology & Engineering - 69 pages
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70 percent axial velocity backup screen BETAM TOTAL TEMP BLADE GEOMETRY blade-element performance BUS levels circumferential distortion compressor D-factor DESIGN BLADE-ELEMENT PARAMETERS design speed design streamlines deviation angle Diffusion factor distorted flow distortion screens energy addition Figure flow conditions flow field flow parameters high MVR rotor high MVR stage incidence angle leading edge loss coefficient low MVR rotor low MVR stage MACH NO REL Mach number Magnitude of distortion MERID meridional velocity ratio midspan MVR ROTOR 11 N/cm near-stall operating operating tip outlet total pressure Overall performance overall pressure ratio percent of design Percent of span PRESS RP RATIO IN RATIO RATIO TIP reference MVR stage rotor 20 rotor inlet rotor outlet span from tip stall pressure ratio static pressure stator 16 STREAMLINE SLOPE suction-surface tip radial distortion tip region TOTAL TEMP TOTAL total temperature trailing edge Transonic undistorted sector undistorted-flow WHEEL SPEED RP