A gas turbine engine, comprising: a compressor for compressing an airflow; a combustor downstream of the compressor; a turbine downstream of the combustor; an RPM sensor for monitoring a rotational speed of the gas turbine engine; and a fuel injection system comprising: a primary fuel line, wherein the primary fuel line includes an atomizer for injecting fuel into the combustor; a secondary fuel line, wherein the secondary fuel line includes a jet for injecting fuel into the combustor; a dual passage injector, wherein each of the primary fuel line and the secondary fuel line terminate within the dual passage injector and inject fuel into the combustor, the dual passage injector including the atomizer of the primary fuel line and the jet of the secondary fuel line; a fuel pump; a fuel supply; a flow divider valve located on the secondary fuel line, wherein the flow divider valve is a solenoid valve having more than one position, and the flow divider valve is used to alter a fuel pressure in the secondary fuel line; a flow meter for monitoring a fuel flow rate; and a control system in electronic communication with the fuel pump, the RPM sensor, the flow meter and the flow divider valve, the control system adapted to operate the flow divider valve in a first fuel delivery mode including a first delta pressure condition between the primary fuel line and the secondary fuel line, the control system adapted to further operate the flow divider valve in a second fuel delivery mode including a second delta pressure condition between the primary fuel line and the secondary fuel line; wherein the control system is adapted to command the flow divider valve to execute a fuel schedule employing the first fuel delivery mode during a transition between steady states and subsequently employing the second fuel delivery mode before the gas turbine engine enters a steady state but during the transition. a compressor for compressing an airflow; a combustor downstream of the compressor; a turbine downstream of the combustor; an RPM sensor for monitoring a rotational speed of the gas turbine engine; and a fuel injection system comprising: a primary fuel line, wherein the primary fuel line includes an atomizer for injecting fuel into the combustor; a secondary fuel line, wherein the secondary fuel line includes a jet for injecting fuel into the combustor; a dual passage injector, wherein each of the primary fuel line and the secondary fuel line terminate within the dual passage injector and inject fuel into the combustor, the dual passage injector including the atomizer of the primary fuel line and the jet of the secondary fuel line; a fuel pump; a fuel supply; a flow divider valve located on the secondary fuel line, wherein the flow divider valve is a solenoid valve having more than one position, and the flow divider valve is used to alter a fuel pressure in the secondary fuel line; a flow meter for monitoring a fuel flow rate; and a control system in electronic communication with the fuel pump, the RPM sensor, the flow meter and the flow divider valve, the control system adapted to operate the flow divider valve in a first fuel delivery mode including a first delta pressure condition between the primary fuel line and the secondary fuel line, the control system adapted to further operate the flow divider valve in a second fuel delivery mode including a second delta pressure condition between the primary fuel line and the secondary fuel line; wherein the control system is adapted to command the flow divider valve to execute a fuel schedule employing the first fuel delivery mode during a transition between steady states and subsequently employing the second fuel delivery mode before the gas turbine engine enters a steady state but during the transition. a primary fuel line, wherein the primary fuel line includes an atomizer for injecting fuel into the combustor; a secondary fuel line, wherein the secondary fuel line includes a jet for injecting fuel into the combustor; a dual passage injector, wherein each of the primary fuel line and the secondary fuel line terminate within the dual passage injector and inject fuel into the combustor, the dual passage injector including the atomizer of the primary fuel line and the jet of the secondary fuel line; a fuel pump; a fuel supply; a flow divider valve located on the secondary fuel line, wherein the flow divider valve is a solenoid valve having more than one position, and the flow divider valve is used to alter a fuel pressure in the secondary fuel line; a flow meter for monitoring a fuel flow rate; and a control system in electronic communication with the fuel pump, the RPM sensor, the flow meter and the flow divider valve, the control system adapted to operate the flow divider valve in a first fuel delivery mode including a first delta pressure condition between the primary fuel line and the secondary fuel line, the control system adapted to further operate the flow divider valve in a second fuel delivery mode including a second delta pressure condition between the primary fuel line and the secondary fuel line; wherein the control system is adapted to command the flow divider valve to execute a fuel schedule employing the first fuel delivery mode during a transition between steady states and subsequently employing the second fuel delivery mode before the gas turbine engine enters a steady state but during the transition.