| 摘要 |
A system to facilitate operating within flame-holding margins in a turbine engine, is provided. The system includes at least one swirler segment coupled within the fuel nozzle of the turbine engine, the at least one swirler segment includes at least one vane extending between an inner band (50) and an outer band (40), a design fuel from a fuel source, at least one fuel injection orifice defined in a surface of the at least one vane, the at least one fuel injection orifice designed to optimize turbine performance using the design fuel, a non-design fuel channeled through the at least one fuel injection orifice into a compressed fluid flow to establish a jet penetration height, and an operating window (110) to facilitate reducing the jet penetration height and to facilitate increasing the flame-holding margins.
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