Patent attributes
The present disclosure is directed to a fuel nozzle for a gas turbine engine. The fuel nozzle includes a sleeve defining a plurality of radially oriented air inlet ports. The sleeve defines a sleeve outlet at the downstream end of the fuel nozzle and a longitudinally extended annular inner wall inward of the sleeve in the radial direction. The inner wall defines a fluid passage and an inner wall outlet, in which the inner wall outlet is disposed toward the downstream end of the inner wall. At least a portion of the plurality of radially oriented air inlet ports is outward of the inner wall along the radial direction. The fuel nozzle further includes a plurality of fuel injectors surrounding the sleeve, in which the sleeve and each of the fuel injectors are connected to an aft body at the downstream end and a forward body at the upstream end.
