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Investigation of low NOx staged combustor concept in high-speed civil transport enginesLevels of exhaust emissions due to high temperatures in the main combustor of high-speed civil transport (HSCT) engines during supersonic cruise are predicted. These predictions are based on a new combustor design approach: a rich burn/quick quench/lean burn combustor. A two-stage stirred reactor model is used to calculate the combustion efficiency and exhaust emissions of this novel combustor. A propane-air chemical kinetics model is used to simulate the fuel-rich combustion of jet fuel. Predicted engine exhaust emissions are compared with available experimental test data. The effect of HSCT engine operating conditions on the levels of exhaust emissions is also presented. The work described in this paper is a part of the NASA Lewis Research Center High-Speed Civil Transport Low NO(x) Combustor program.
Document ID
19890059815
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nguyen, Hung Lee
(NASA Lewis Research Center Cleveland, OH, United States)
Bittker, David A.
(NASA Lewis Research Center Cleveland, OH, United States)
Niedzwiecki, Richard W.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1989
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 89-2942
Accession Number
89A47186
Distribution Limits
Public
Copyright
Other

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