The relative importance of combustion as a source of noise in a flow regime representative of a subsonic jet engine exhaust was investigated. The combustion noise source characteristics were obtained from pressure and temperature fluctuation measurements in the combustor and exhaust nozzle. The similarity between the fluctuations in this source region and the far field noise were compared. In the jet exhaust velocity range between 450 and 660 ft/sec investigated in detail, the frequencies of dominant pressure and temperature fluctuations in the combustor were also the frequencies of the dominant far field noise. The overall noise levels were 14 to 20 dB higher than from a corresponding clean jet in the same velocity range. Thus it seemed clear that the unsteadiness associated with the combustion process was responsible for the dominant noise in the far field. A simple analysis to predict the far field noise due to the internal pressure fluctuations causing exit plane velocity fluctuations produced trends closely resembling the measured results, but under predicted the far field noise over the spectral range examined. The possible reason for the higher far field noise is direct transmission of acoustic waves through the nozzle, which was not accounted for in the prediction scheme. (Author)

  • Corporate Authors:

    National Aeronautics and Space Administration

    600 Independence Avenue, SW
    Washington, DC  United States  20546
  • Authors:
    • Plett, E G
    • Abdelhamid, A N
    • Harrje, D T
    • Summerfield, M
  • Publication Date: 1976-7

Media Info

  • Pagination: 42 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00145781
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-CR-2704, REPT-1146
  • Contract Numbers: NGR-31-001-241
  • Files: TRIS
  • Created Date: Jan 16 1977 12:00AM