Mini mixing fuel nozzle assembly with mixing sleeve

1. A fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, an upstream end, and a downstream end, the fuel nozzle comprising:

a sleeve defining a plurality of radially oriented air inlet ports, a single sleeve outlet at the downstream end of the fuel nozzle, and an annular inner wall extending radially inward from the sleeve in the radial direction and extending in the longitudinal direction,

wherein the sleeve outlet comprises a first diameter, the inner wall defines a fluid passage therewithin, and an inner wall outlet is disposed at a downstream end of the inner wall,

wherein a first radially oriented air inlet port of the plurality of radially oriented air inlet ports is disposed upstream of the inner wall outlet and a second radially oriented air inlet port of the plurality of radially oriented air inlet ports is disposed downstream of the inner wall outlet,

wherein a radial swirler of the plurality of radially oriented air inlet ports is disposed downstream of the first radially oriented air inlet port and the second radially oriented air inlet port,

wherein the first radially oriented air inlet port, the second radially oriented air inlet port, and the radial swirler are in serial arrangement through the sleeve along the longitudinal direction,

and further wherein the first radially oriented air inlet port and the second radially oriented air inlet port define a radially inward, straight flow perpendicular to a centerline axis of the fuel nozzle; and

a plurality of fuel injectors surrounding the sleeve, each of the plurality of fuel injectors comprising a single annular fuel injector outlet having an inner circumference defining a second diameter, the second diameters being greater than the first diameter of the sleeve outlet,

wherein the sleeve and each of the fuel injectors are connected to an aft body at the downstream end of the fuel nozzle and a forward body at the upstream end of the fuel nozzle, such that the annular fuel injector outlets and the sleeve outlet are at the same location along the longitudinal direction.

2. The fuel nozzle of claim 1 , wherein the sleeve further comprises a plurality of air inlet port walls defining the radial swirler.

3. The fuel nozzle of claim 2 , wherein the inner wall and the sleeve define an air passage therebetween.

4. The fuel nozzle of claim 1 , wherein the sleeve defines a mixing passage extended from the inner wall outlet to the sleeve outlet.

5. The fuel nozzle of claim 1 , wherein the sleeve further defines a sleeve inlet, and wherein the sleeve inlet flows a fuel through the fluid passage.

6. The fuel nozzle of claim 1 , wherein the aft body, the plurality of fuel injectors, and the forward body together define an air supply cavity to feed air to the plurality of fuel injectors and the sleeve.

7. The fuel nozzle of claim 1 , wherein the sleeve is a unitary structure with the forward body and the aft body.

8. The fuel nozzle of claim 1 , wherein the sleeve defines the fluid passage upstream of the inner wall.

9. The fuel nozzle of claim 1 , wherein at least a portion of the inner wall is an inner diameter portion of the sleeve upstream of the first air inlet port.

10. The fuel nozzle of claim 1 , wherein the fuel nozzle is configured to flow only a liquid and/or gaseous fuel through the fluid passage, and wherein the fuel nozzle is configured to flow air through the first air inlet port, the second air inlet port, and the radial swirler to mix with the flow of fuel at a mixing passage downstream of the inner wall outlet.

11. A combustor assembly for a gas turbine engine, the combustor assembly defining a radial direction, a longitudinal direction, an upstream end, and a downstream end, the combustor assembly comprising:

a bulkhead wall extended radially between an upstream end of an inner liner and an upstream end of an outer liner, wherein the inner liner is radially spaced from the outer liner with respect to an engine centerline to define an annular combustion chamber therebetween, and wherein the inner liner and the outer liner extend downstream from the bulkhead wall;

and one or more fuel nozzles extended at least partially through the bulkhead wall, each of the fuel nozzles comprising:

a sleeve defining a plurality of radially oriented air inlet ports, a single sleeve outlet at the downstream end of the fuel nozzle, and an annular inner wall extending inward from the sleeve in the radial direction and extending in the longitudinal direction,

wherein the sleeve outlet comprises a first diameter, the inner wall defines a fluid passage therewithin, and an inner wall outlet disposed at a downstream end of the inner wall,

wherein a first radially oriented air inlet port of the plurality of radially oriented air inlet ports is upstream of the inner wall outlet and a second radially oriented air inlet port of the plurality of radially oriented air inlet ports is disposed downstream of the inner wall outlet,

wherein a radial swirler of the plurality of radially oriented air inlet ports is disposed downstream of the first radially oriented air inlet port and the second radially oriented air inlet port,

wherein the first radially oriented air inlet port, the second radially oriented air inlet port, and the radial swirler are in serial arrangement through the sleeve along the longitudinal direction,

and further wherein the first radially oriented air inlet port and the second radially oriented air inlet port define a radially inward, straight flow perpendicular to a centerline axis of the fuel nozzle;

and a plurality of fuel injectors surrounding the sleeve, each of the plurality of fuel injectors comprising a single annular outlet having an inner circumference defining a second diameter,

the second diameters being greater than the first diameter of the sleeve outlet,

wherein the sleeve and each of the fuel injectors are connected to an aft body at a downstream end of the fuel nozzle and a forward body at an upstream end of the fuel nozzle, such that the annular fuel injector outlets and the sleeve outlet are at the same location along the longitudinal direction.

12. The combustor assembly of claim 11 , wherein the combustor assembly defines a first combustion zone and a second combustion zone, and wherein the first combustion zone is defined in at least a portion of an outer circumference of the annular combustion chamber, and wherein the second combustion zone is defined in at least a portion of a middle circumference of the annular combustion chamber.

13. The combustor assembly of claim 12 , wherein the combustor assembly further defines a third combustion zone defined in at least a portion of an inner circumference of the annular combustion chamber.