Abstract: An injection assembly for a combustor of a gas turbine has an outer body provided with inlet passages for comburent air, a conical tubular portion housed inside the outer body and delimiting partly an inner duct and an outer annular duct; a first and a second supply means for supplying a liquid fuel into the inner duct and, respectively, into the outer annular duct; at least one circumferential annular seat formed being carried by one of the tubular portion and the outer body, so as to collect a mass of liquid fuel advancing in the outer annular duct and make uniform the flow of liquid flowing out of the circumferential annular seat.

Abstract: A fuel mixture is fed to a gas turbine combustor by an injection assembly, which has an outer body with combustion-supporting air inlets; a conical tubular portion housed inside the outer body and partly defining an inner conduit and an outer annular conduit; and a first and second feed circuit for feeding liquid fuel to the inner conduit and outer annular conduit respectively; the first circuit having a ring of conduits with respective axes parallel to a generating line of an outer surface of the conical tubular portion.

Abstract: A fuel mixture is fed to a gas turbine combustor by an injection assembly, which has an outer body with combustion-supporting air inlets; a conical tubular portion housed inside the outer body and partly defining an inner conduit and an outer annular conduit; and a first and second feed circuit for feeding liquid fuel to the inner conduit and outer annular conduit respectively; the first circuit having a ring of conduits with respective axes parallel to a generating line of an outer surface of the conical tubular portion.