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.
- 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.
Department of the NavyThe Pentagon
Washington, DC USA 20350
- Mularz, E J
- Gleason, C C
- Dodds, W J
- Publication Date: 1978-7
- Pagination: 20 p.
- TRT Terms: Air pollution; Air quality; Aircraft; Carbon monoxide; Catalytic converters; Combustion chambers; Engines; Exhaust gases; Gas turbines; Hydrocarbons; Internal combustion engines; Pollutants; Pollution control; Turbine engines
- Uncontrolled Terms: Aircraft engines
- Old TRIS Terms: Hot surfaces; Particle emission
- Subject Areas: Aviation; Vehicles and Equipment;
- 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