Injector assembly for a gas turbine and aircraft

An injector assembly for a gas turbine, configured for introducing a gaseous fuel and a liquid fuel and air into a combustion chamber, comprising:

• an injector shaft, and
• an injector main body aligned along an injector longitudinal axis,
• wherein the injector main body comprises:
• a first gas duct arranged centrally on the injector longitudinal axis and including the longitudinal axis, for introducing a flow of the gaseous fuel or a flow of air into the combustion chamber,
• at least one air duct arranged radially around an outside of the first gas duct, and
• a liquid fuel injector arranged radially around the first gas duct for introducing the liquid fuel into the combustion chamber,
• wherein the injector assembly is also configured to introduce the gaseous fuel,
• wherein the injector assembly is configured to adopt two alternative configurations between which the injector assembly can be switched during operation,
• wherein in a first configuration air flows through the first gas duct, as an air injection, and in a second configuration the gaseous fuel flows through the first gas duct as a gas fuel injection;
• wherein the air duct is formed as a second gas duct running radially directly around the first gas duct, wherein an upstream end of the second gas duct is positioned at, or upstream of, an axial position of an upstream end of an air inflow opening at an upstream end of the first gas duct;
• wherein the first gas duct is arranged in a central body extending coaxially to the injector longitudinal axis within the second gas duct;
• at least one gas fuel transfer line connecting a gas fuel supply line and the first gas duct, the at least one gas fuel transfer line extending radially through the second gas duct, and
• further support elements and/or swirl elements extending radially within the second gas duct to hold the central body.