An experimental and theoretical program was conducted to see if entropy noise and vorticity-nozzle interaction noise, as well as direct combustion noise, could be isolated in gas turbine combustor tests. Moreover, a unified correlation, with a rational theoretical basis, was developed for direct noise from combustor rig tests. It was found that (a) vorticity noise was at least as large as combustion noise; (b) entropy noise is minor but is large only at low frequency; (c) all noise sources are coherent with each other over various frequency ranges; (d) with a choked nozzle termination the nose is higher frequency (approximately 2000 Hz) than heretofore believed; (e) some other unexplained noise source contaminated the results at low frequency; and (f) the diffuser used caused additional coherent noise, probably through the vorticity source. A method for accounting for the vorticity and entropy sources in combustor rig tests was indicated. (Author)

  • Corporate Authors:

    University of Georgia, Experiment

    Georgia Experiment Station
    Experiment, GA  United States 

    Federal Aviation Administration

    Systems R&D Service, 800 Independence Avenue, SW
    Washington, DC  United States 
  • Authors:
    • Strahle, W C
    • Muthukrishnan, M
    • Neale, D H
    • Aggarwal, S K
  • Publication Date: 1979-3

Media Info

  • Pagination: 155 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00197645
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: FAA-RD-79-1 Final Rpt.
  • Contract Numbers: DOT-FA77WA-4077
  • Files: NTIS, TRIS, USDOT
  • Created Date: Sep 15 1980 12:00AM