TS-72 Ultra Low NO_x Gas Turbine Combustion(Session C-7 NO_x Reduction 2)

概要

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Gas turbine radial swirlers with passage fuel injection combustor design techniques, that have demonstrated the potential to achieve ultra low NO_x emissions without premixing are reviewed. Transfer from propane to kerosene operation is demonstrated with no combustion inefficiency problems. It is shown that the radial swirler designs investigated with gaseous fuel can achieve a NO_x emission index of 0.4 with kerosene at 1 bar 600K with a combustion inefficiency of 0.01%. The use of double swirlers is investigated with co and counter swirl and with fuel staged to the upstream swirler in an attempt to extend the stability margin between the weak extinction and the minimum NO_x and CO operating point. The extension of the lean stability was poor and this type of fuel staging is not recommended. To cope with the varying power requirements of aero engines variable geometry combustors are advocated with no film cooling of the primary zone. The addition of film cooling to a radial swirl lean primary zone is shown to result in a major increase in NO_x emissions.
公益社団法人日本ガスタービン学会の論文
1999-11-14