Affiliation:
1. Thermofluid Dynamics Division, National Aerospace Laboratory, Chofu, Tokyo 182, Japan
Abstract
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.
Subject
Mechanical Engineering,Energy Engineering and Power Technology,Aerospace Engineering,Fuel Technology,Nuclear Energy and Engineering
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