COMBUSTOR CONCEPTS FOR AIRCRAFT GAS TURBINE LOW-POWER EMISSIONS REDUCTION

Several combustor concepts were designed and tested to demonstrate significant reductions in aircraft engine idle pollutant emissions. Each concept used a different approach for pollutant reductions: the hot wall combustor employs a thermal barrier coating and impingement cooled liners; the recuperative cooling combustor preheats the air before entering the combustion chamber; and the catalytic converter combustor is composed of a conventional primary zone followed by a catalytic bed for pollutant cleanup. The designs are discussed in detail and test results are presented for a range of aircraft engine idle conditions. The results indicate that ultralow levels of unburned hydrocarbons and carbon monoxide emissions can be achieved.

  • Supplemental Notes:
    • Conf-Presented at the 14TH Propulsion Conf., Las Vegas, Nev., 25-27 Jul. 1978; CO-Sponsored by the Aiaa and the Soc. Of Automotive Engr.
  • Corporate Authors:

    Department of the Navy

    The Pentagon
    Washington, DC  USA  20350
  • Authors:
    • Mularz, E J
    • Gleason, C C
    • Dodds, W J
  • Publication Date: 1978-7

Media Info

  • Pagination: 20 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00185732
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-TM-78875, AVRADCOM-TR-78-23(PL)
  • Files: TRIS
  • Created Date: Dec 29 1979 12:00AM