The design and on-engine testing of a lean-premixed, low-NOx combustor for a simple-cycle, single-shaft, 250-kW gas turbine engine of a pressure ratio of eight are described. A variable-geometry system composed of butterfly air valves was used to control the combustor air split between combustion and dilution. Fuel was staged to a direct-injection pilot burner, and a lean-premixed main burner was fitted to the combustor liner. The NOx emissions with natural gas fueling were found to be less than 20 ppm (at 15 percent O2) at and near full-load conditions with combustion efficiencies greater than 99.8 percent. Emissions data from early high-pressure rig tests of the combustor hardware are also presented.

Issue Section:
Gas Turbines: Combustion and Fuels
Topics:
Combustion chambers, Emissions, Engines, Geometry, Combustion, Cycles, Design, Fuels, Gas turbines, Hardware, High pressure (Physics), Natural gas, Nitrogen oxides, Pressure, Stress, Testing, Valves
1.
Aigner
M.
, and
Muller
G.
,
1993
, “
Second-Generation Low-Emission Combustors for ABB Gas Turbines: Field Measurements With GT11N-EV
,”
ASME JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER
, Vol.
115
, pp.
533
–
536
.
2.
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3.
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4.
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5.
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6.
Smith, K. O., Holsapple, A. C., Mak, H. K., and Watkins, L., 1991, “Development of a Natural Gas Fired, Ultra-Low NOx Can Combustor for 800 kW Gas Turbine,” ASME Paper No. 92-GT-303.
7.
Smith, K. D., 1992, “Engine Testing of a Prototype Low NOx Gas Turbine Combustor,” ASME Paper No. 92-GT-116.
8.
Solt, J. C., and Tuzson, J., 1993, “Status of Low NOx Combustor Development,” ASME Paper No. 93-GT-270.
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