Abstract: A method for gas turbine light-off that utilizes a fixed or secondary fuel line that provides a substantially constant flow of fuel to the combustor primarily upon light-off.

Abstract: Air tubes are circumferentially spaced around the outer liner of an annular combustor for a microturbine engine in proximity to and downstream of a dam extending into the combustion chamber for reducing the emission of NOX. The air tubes are dimensioned so that the length to passage diameter is such that a swirling motion of the air injected into the combustion zone is normal to the center line of the annular combustor.

Abstract: An atomizer for use with a combustor in a gas turbine has a body with a fuel passageway extending through the center of the body. A plurality of channels extends within the body about the passageway centerline, and are oriented along a circumferential angle about the passageway centerline to deliver air at the discharge end of the passageway with an axially whirling motion. The channels are simultaneously oriented along an axial angle about the passageway centerline, thereby directing the flow of air to converge toward the passageway centerline, mix with the fuel, and then at least in part diverge from the passageway centerline. The whirling air intersects with the fuel at the exit of the nozzle to effectively atomize both the air and fuel thereby providing a homogeneous air/fuel mixture to the combustion chamber.