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  • 1
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    Experimental and analytical investigation of fan flow interaction with downstream struts (1985)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An investigation which was designed to provide insight into the fundamental aspects of fan rotor-downstream strut interaction was undertaken. High response, miniature pressure transducers were embedded in the rotor blades of an experimental fan rig. Five downstream struts were placed at several downstream locations in the discharge flow annulus of the single-stage machine. Significant interaction of the rotor blade surface pressures with the flow disturbance produced by the downstream struts was measured. Several numerical procedures for calculating the quasi-steady rotor response due to downstream flow obstructions were developed. A preliminary comparison of experimental and calculated fluctuating blade pressures on the rotor blades shows general agreement between the experimental and calculated values.
    Keywords: AERODYNAMICS
    Type: NASA-CR-175756 , NAS 1.26:175756 , IR-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A study of the application of microwave techniques to the measurement of solid propellant burning rates Progress report, 1 Sep. 1966 - 31 Aug. 1967 (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Microwave techniques for measurement of solid rocket propellant burning rates
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-66627
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Interaction of fan rotor flow with downstream struts (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The detailed unsteady pressure field produced on the rotor blades of an axial-flow fan by interaction with downstream struts was investigated. The experimental arrangement was similar to that found in the fan casings of turbofan aircraft engines. Acoustically significant pressure fluctuations were measured on both thy suction and pressure sides of the rotor blades for several positions of the downstream struts. The level of the observed interaction decreased with increased spacing of the struts behind the rotor. An inviscid flow analysis for the disturbance level is compared with trends of the measured results.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-0682 , American Institute of Aeronautics and Astronautics, Aeroacoustics Conference; Apr 11, 1983 - Apr 13, 1983; Atlanta, GA
    Format: text
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    NASA TECHNICAL REPORTS
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