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of present and proposed gas turbine combustors
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0xide 20 RADIAL DISTANCE adiabatic flame temperature aircraft approximately Axial concentration C0 oxidation C3Hg chemical kinetic chemiluminescent cold flow Combustion Institute combustion zone combustor centerline combustor exit concentration and temperature conservation equations constant effect emission index values emission levels Engineering equivalence ratio experimental and predicted flame zone flamefront flowfield gas turbine gas turbine combustors high temperature hydrocarbon increase jet exit jet injector jet stream kinetic main stream inlet mass fraction mechanism mole fraction N0 concentrations N0 emissions N0 formation N0 levels N0 production OICO opposed reacting jet OTOO oxides of nitrogen partial equilibrium predicted N0 premixed present investigation pressure propane oxidation radial location reaction recirculation region recirculation zone residence sampling probe shown in Figure stability limits stirred reactor stream equivalence ratio stream function TABLE D-l Continued temperature distri temperature distributions temperature profiles temperature regions test section thermocouple tion turbulent upstream viscosity Vycor