NOISE DUE TO THE INTERACTION OF BOUNDARY LAYER TURBULENCE WITH A MARINE PROPULSOR OR AN AIRCRAFT COMPRESSOR

The sound generated by the interaction of inlet boundary layer turbulence with a rotating blade row is investigated. To experimentally study this radiated sound, an existing aeroacoustic facility was modified to produce the inflows desired. The rotor was operated in air with different blade space-to-chord ratios, different flow coefficients and different anisotropic, nonhomogeneous turbulent inflows. The inflows ingested are: (1) natural boundary layer on hub and annulus wall, (2) a tripped boundary layer on the hub, and (3) a fully developed boundary layer on the hub. The turbulence intensities and length scales were altered by placing a grid at the inlet. The sound pressure level is found to be directly proportional to the turbulence intensity squared and inversely proportional to the ratio of axial length scale to blade spacing.

  • Supplemental Notes:
    • Master's thesis.
  • Corporate Authors:

    Pennsylvania State University, University Park

    Applied Research Laboratory
    University Park, PA  USA  16802
  • Authors:
    • Moiseev, N
    • Lakshminarayana, B
    • Thompson, D E
  • Publication Date: 1976-10-11

Media Info

  • Pagination: 122 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00166033
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: TM-76-258
  • Contract Numbers: N00017-73-C-1418
  • Files: TRIS
  • Created Date: Sep 20 1977 12:00AM