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  • 1
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    Overall and blade element performance of a 1.20-pressure-ratio fan stage with rotor blades reset -5 deg (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 51-cm-diam model of a fan stage for a short haul aircraft was tested in a single stage-compressor research facility. The rotor blades were set 5 deg toward the axial direction (opened) from design setting angle. Surveys of the air flow conditions ahead of the rotor, between the rotor and stator, and behind the stator were made over the stable operating range of the stage. At the design speed of 213.3 m/sec and a weight flow of 31.5 kg/sec, the stage pressure ratio and efficiency were 1.195 and 0.88, respectively. The design speed rotor peak efficiency of 0.91 occurred at the same flow rate.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3338 , E-8057
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Effects of four inlet and outlet tip-annulus-area blockage configurations on the performance of an axial-flow fan rotor (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An axial-flow fan rotor was tested with four configurations of tip-annulus-area blockage to speeds as high as 0.8 of design speed. The rotor performance with the four blockage configurations is compared with the unblocked rotor performance and with blockage configurations previously investigated. The blockage configurations enable the rotor to operate in a stable condition, to much lower flows than the unblocked rotor, with no evidence of rotating stall. The blockage configurations were effective in reducing rotor torque and weight flow but were accompanied by reductions in pressure ratio and efficiency.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8131 , E-8466
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Effect of several porous casing treatments on stall limit and on overall performance of an axial flow compressor rotor (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Several geometrically different porous casings were tested with an axial-flow compressor rotor to determine their effects upon the rotor stall-limit line and overall performance. The tests were conducted using both uniform and nonuniform inlet-flow conditions. The rotor performance with the various casing treatments is compared with that obtained with a solid casing. The ability of the various casing treatments to displace the rotor stall-limit line to lower weight flows was observed. Significant stall-margin increases were obtained with several of the porous casings. Peak efficiencies with two of the porous casings were as high as or slightly higher than that obtained with solid casing.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6537 , E-5973
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Aerodynamic performance of a 1.35-pressure-ratio axial-flow fan stage (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The overall blade element performances and the aerodynamic design parameters are presented for a 1.35-pressure-ratio fan stage. The fan stage was designed for a weight flow of 32.7 kilograms per second and a tip speed of 302.8 meters per second. At design speed the stage peak efficiency of 0.879 occurred at a pressure ratio of 1.329 and design flow. Stage stall margin was approximately 14 percent. At design flow rotor efficiency was 0.94 and the pressure ratio was 1.360.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1299 , E-9025
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Performance of a 1.15-pressure-ratio axial-flow fan stage with a blade tip solidity of 0.5 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The overall and blade-element performance of a low-solidity, low-pressure-ratio, low-tip-speed fan stage is presented over the stable operating range at rotative speeds from 90 to 120 percent of design speed. At design speed a stage peak efficiency of 0.836 was obtained at a weight flow of 30.27 kilograms per second and a pressure ratio of 1.111. The pressure ratio was less than design pressure ratio, and the design energy input into the rotor was not achieved. A mismatch of the rotor and stator blade elements resulted due to the lower than design pressure ratio of the rotor.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3052 , E-7433
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Effect of casing treatment of overall performance of axial-flow transonic fan stage with pressure ratio of 1.75 and tip solidity of 1.5 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of a number of casing treatments on the overall performance of a 1.75-pressure-ratio, 423-m/sec-tip-speed fan stage was evaluated. The skewed slot configuration with short-open slots over the midportion of the rotor had a stall margin of 23.5 percent, while the solid casing had a stall margin of 15.0 percent. The skewed slot configuration with long open slots extending ahead of and over portion of rotor displaced the stall line to the lowest flow at all speeds tested. At design speed, the peak efficiency for the long, forward open slots was 1 point less than that for the short midopen slots and 3 points less than that for the solid casing.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3477 , E-8488
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Effects of tip clearance on overall performance of transonic fan stage with and without casing treatment (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The overall performance of a transonic fan stage is presented for various tip clearances, with and without casing treatment. The stage was tested with a solid casing, and with open skewed slots and closed skewed slots in the casing over the rotor blade tips. Four nominal nonrotating rotor blade tip clearances from 0.061 to 0.178 centimeter were used. For all three casings, the pressure ratio and efficiency decreased with increasing tip clearance. The stall margin for a given casing also decreased with increasing clearance. At design speed and a given tip clearance, the highest stall margin was obtained with the open-slot casing, and the lowest stall margin was obtained with the solid casing.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3479 , E-8945
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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