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Combustor concepts for aircraft gas turbine low-power emissions reductionThree combustor concepts have been 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 ultra-low levels of unburned hydrocarbons and carbon monoxide emissions can be achieved with this technology.
Document ID
19780059637
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mularz, E. J.
(NASA Lewis Research Center; U.S. Army, Air Mobility Research and Development Laboratory, Cleveland Ohio, United States)
Gleason, C. C.
(NASA Lewis Research Center Cleveland, OH, United States)
Dodds, W. J.
(NASA Lewis Research Center Cleveland; General Electric Co., Evendale, Ohio, United States)
Date Acquired
August 9, 2013
Publication Date
July 1, 1978
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 78-999
Meeting Information
Meeting: Joint Propulsion Conference
Location: Las Vegas, NV
Country: US
Start Date: July 25, 1978
End Date: July 27, 1978
Sponsors: Society of Automotive Engineers, American Institute of Aeronautics and Astronautics
Accession Number
78A43546
Funding Number(s)
CONTRACT_GRANT: NAS3-20580
Distribution Limits
Public
Copyright
Other

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