Levels 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.
Investigation of Low NOx Staged Combustor Concept in High-Speed Civil Transport Engines
1989
23 pages
Report
No indication
English
Jet & Gas Turbine Engines , Engine Studies, Energy Related , Aircraft , Combustion chambers , Nitrogen oxides , Supersonic speed , Transport aircraft , Turbojet engines , Combustion efficiency , Exhaust emission , Burning rate , Engine design , Fuel combustion , Fuel-air ratio , Inlet pressure , Inlet temperature , Pressure effects , Reaction kinetics