Method of fabricating gas turbine fuel injection
AssigneeGeneral Electric Company
InventorsEly Eskenazi Halila, Michael Anderson
Life of this patent
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Abstract
A combustor for a gas turbine engine including a pilot fuel injection assembly that includes a replaceable heat shield is described. The pilot fuel injection assembly also includes a fuel stem and a mixer divider. The fuel stem includes a first end, a second end, and a body extending therebetween. An alignment slot is defined within a portion of the interface between the fuel stem body and the second end. The mixer divider is attached to the fuel stem second end and the heat shield is removably coupled to the mixer divider with a plurality of transfer tubes.
Claims4
A method for fabricating an integral pilot fuel injector assembly for a gas turbine engine, the pilot fuel injector assembly including a fuel stem, a mixer divider, and a heat shield, the fuel stem comprising a first end, a second end, and a body extending therebetween, said method comprising the steps of:
- attaching a plurality of fuel injectors to the fuel stem to extend radially outward from the fuel stem;
- attaching the mixer divider to the fuel stem second end;
- and
- slidably coupling the heat shield to the mixer divider.
Dependencies are inferred from the claim text.