Turbine engine fuel injector with helmholtz resonators

A component for a fuel injector configured to direct a stream of fuel and a separate stream of fuel air mixture to a combustion chamber of a turbine engine, comprising:

• a longitudinal axis;
• a barrel member coupled to the combustion chamber and disposed radially outwards the longitudinal axis, the barrel member including an end face facing the combustion chamber;
• and
• an end cap coupled to the barrel member, wherein the end cap and the end face form an array of Helmholtz resonators, the array of Helmholtz resonators includes a plurality of perforations exposed to the combustion chamber, and each of the plurality of perforations includes a central axis substantially parallel to the longitudinal axis.

A fuel injector configured to deliver a premixed fuel air mixture to a combustor of a gas turbine engine, comprising:

• a central body formed around a common axis and containing a pilot injector, the pilot injector configured to inject a first stream of fuel out of a first axial end into the combustor;
• a barrel housing positioned around the central body to form an annular mixing duct there between, the mixing duct being configured to mix a second stream of fuel and air therein to create the premixed fuel air mixture, and deliver the premixed fuel air mixture to the combustor through the first axial end without mixing with the first stream of fuel;
• a ring-shaped end cap coupled to the barrel housing at the first axial end to form an array of Helmholtz resonators with a hollow cavity between the end cap and the barrel housing, the array of Helmholtz resonators being annularly positioned about the common axis;
• and,
• a plurality of perforations formed in the end cap and arranged in a radial pattern about the common axis, the perforations penetrating through the end cap to fluidly communicate the hollow cavity with the combustor, the perforations each defining an axis that is parallel to the common axis.