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Low-Emissions Gas Turbine Combustor Development for Regional-Class Aircraft

[+] Author Affiliations
J. Zelina

Honeywell Engines and Systems, Phoenix, AZ

P. F. Penko

NASA Glenn Research Center, Cleveland, OH

Paper No. 2000-GT-0100, pp. V002T02A020; 8 pages
doi:10.1115/2000-GT-0100
From:
  • ASME Turbo Expo 2000: Power for Land, Sea, and Air
  • Volume 2: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations
  • Munich, Germany, May 8–11, 2000
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7855-2
  • Copyright © 2000 by ASME

abstract

Sector-rig test results of four combustor configurations for medium-sized, gas-turbine engines are presented. The sector test section consists of a three-injector combustor cross-section, unrolled to a rectangular area, and simulating about a sixty-eight degree section of the combustor. Performance and emissions data are presented for four design-of-experiment (DOE) combinations of 1) air swirlers, 2) fuel injectors, and 3) primary-zone lengths. Emission concentrations from gas sampling are given for NOx, CO, and UHC as a function of inlet temperature, pressure, and overall fuel air ratio. NOx production as a function of inlet temperature, pressure, stoichiometry, and residence time are presented. The trade-off between NOx and CO is given over a range of operating conditions for each sector configuration.

Copyright © 2000 by ASME

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