Pilot fuel flow tuning for gas turbine combustors
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United States of America Patent
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Jan 5, 2010
Grant Date -
Jul 12, 2007
app pub date -
Jan 12, 2006
filing date -
Jan 12, 2006
priority date (Note) -
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Abstract
A method and system for controlling combustion in a gas turbine combustor (18) includes adjusting an amount of a premix fuel portion (30) of a pilot fuel (28) provided to a premix burner stage (48) of a pilot (46) of the gas turbine combustor. The amount of the premix fuel portion is adjusted from a preset premix fuel portion amount to an adjusted premix fuel portion amount to achieve a desired first operating condition of the combustor. An amount of a diffusion fuel portion (34) of the pilot fuel provided to a diffusion burner stage (50) of the pilot is then adjusted from a preset diffusion fuel portion amount to an adjusted diffusion fuel portion amount to achieve a desired second operating condition of the combustor.
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