Fuel injector assembly for gas turbine engine

An assembly for a turbine engine, comprising:

• a hydrogen fuel source;
• and
• a fuel injector configured to receive hydrogen fuel from the hydrogen fuel source, the fuel injector including an air passage, a fuel passage and a fuel swirler within the fuel passage;
• the air passage extending axially along an axis within the fuel injector to an air passage outlet, and the air passage configured to direct inner air out of the fuel injector through the air passage outlet;
• the fuel swirler configured to swirl the hydrogen fuel to provide swirled hydrogen fuel;
• the fuel passage extending axially along the axis within the fuel injector to a fuel passage outlet, the fuel passage configured to direct the swirled hydrogen fuel out of the fuel injector through the fuel passage outlet, and the fuel passage radially adjacent and circumscribing the air passage, wherein a downstream end of the fuel swirler is axially spaced from the fuel passage outlet along the axis;
• the air passage configured to direct the inner air out of the fuel injector through the air passage outlet along a first trajectory;
• and
• the fuel passage configured to direct the swirled hydrogen fuel out of the fuel injector through the fuel passage outlet along a second trajectory that is substantially parallel with the first trajectory when viewed in a plane parallel with the axis.