Effect of inlet temperature and pressure on emissions from a premixing gas turbine primary zone combustor, Volume 2740
Gerald Roffe, General Applied Science Laboratories (Westbury, Nassau County, N.Y.), United States. National Aeronautics and Space Administration, Lewis Research Center
U.S. National Aeronautics and Space Administration, 1976 - Technology & Engineering - 43 pages
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315B CO analyzer adiabatic flame temperature adiabatic temperature correlation autoignition occurred Beckman Model 315B bustor calibration curve CALIBRATION OF BECKMAN CARBON MONOXIDE EMISSION COMBUSTION APPARATUS combustion inefficiency combustor entrance temperature COMBUSTOR INLET TEMPERATURE combustor section concentration data points downstream emission levels Equivalence Rati FIGURE equivalence ratio exit flashback fuel injection FUEL ORIFICE DIAMETER FUNCTION OF EQUIVALENCE g/kg gas analysis instrumentation gas turbine heated hydrocarbon analyzer HYDROCARBON EMISSION INDEX ignition delay INDEX WITH ADIABATIC LENCE RATIO levels tested liner mass flow mixer tube mixing duct MONOXIDE EMISSION INDEX N/cm N/cm2 100 Equivalence N0x EMISSION nitrogen NOx EMISSION INDEX operated oxidation ppmC premixing combustor RATIO AND COMBUSTOR reassembly reference velocity Rotameter ing Valve sampling rake separated flow slip joint stagnation pressure storage SUPER-EQUILIBRIUM CARBON MONOXIDE super-equilibrium CO emission supersonic cruise temperature and equivalence TEMPERATURE AT 80 TEST APPARATUS tion total pressure UHC emission upstream VARIATION varied Zero gas