Apparatus for injecting fuel into gas turbine engines
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.
Claims16
A pilot fuel injection assembly for a gas turbine engine combustor, said pilot fuel injection assembly comprising:
- a fuel stem comprising a first end, a second end, and a body extending therebetween;
- a mixer divider attached to said fuel stem second end and defining a cavity between said fuel stem body and said mixer divider;
- and
- a heat shield slidably coupled to said mixer divider.
A combustor for a gas turbine engine, said combustor comprising a pilot fuel injection assembly configured to deliver fuel to said combustor, said pilot fuel injection assembly comprising a fuel stem, a mixer divider, and a heat shield, said fuel stem comprising a first end, a second end, and a body extending therebetween, said mixer divider attached to said fuel stem second end and defining a cavity between said fuel stem body and said mixer divider, said heat shield slidably coupled to said mixer divider.
Dependencies are inferred from the claim text.