KRAFTSTOFFEINSPRITZUNG FÜR EINE GESTUFTE GASTURBINENBRENNKAMMER

摘要

In a staged gas turbine combustion engine, each combustion chamber of an annular array of chambers includes at least a pilot and a main combustion stage each having an fuel injection nozzle; the method includes feeding fuel continuously in operation to the pilot stage nozzle and controlling the fuel flow to the main stage nozzle through a pulsing and dosing valve to control the fuel flow delivered to the main stage fuel nozzle.