Jet swirl air blast fuel injector for gas turbine engine
A fuel injector for a gas turbine engine including an outer sleeve. An upstream end of the outer sleeve defines an inlet opening and a downstream end defines an exit opening, each of which defined within the outer sleeve. The outer sleeve defines a radial opening extended therethrough along the radial direction. At least a portion of the outer sleeve defines a plurality of grooves. The outer sleeve defines a fuel conduit through at least a portion of the outer sleeve outward of the plurality of grooves along the radial direction from the fuel injector centerline. The fuel conduit defines a fuel injection opening inward along the radial direction of the radial opening defined through the outer sleeve. A first member of an arm is coupled to the outer sleeve. A second member of the arm is contoured defining a fuel injection port generally concentric to the fuel injector centerline.
1. A fuel injector for a gas turbine engine, the fuel injector comprising:
an outer sleeve extended along at least partially co-directional to a fuel injector centerline, wherein an upstream end of the outer sleeve defines an inlet opening and a downstream end of the outer sleeve defines an exit opening, wherein each of the inlet opening and the exit opening are defined within the outer sleeve along a radial direction relative to the fuel injector centerline, and further wherein the outer sleeve defines a radial opening extended therethrough relative to the fuel injector centerline along the radial direction, and wherein at least a portion of an inner diameter of the outer sleeve defines a plurality of grooves extended from approximately the inlet opening, and further wherein the outer sleeve defines a fuel conduit through at least a portion of the outer sleeve outward of the plurality of grooves along the radial direction from the fuel injector centerline, and wherein the fuel conduit defines a fuel injection opening inward along the radial direction of the radial opening defined through the outer sleeve;
an arm coupled to the outer sleeve and extended along the radial direction relative to the fuel injector centerline, wherein the arm defines a first member coupled to the outer sleeve and a second member extended along the radial direction and contoured to define a fuel injection port generally concentric to the fuel injector centerline, and wherein the second member defines a fuel passage extended therethrough in fluid communication with the fuel injection port; and further comprising:
a forward wall extended along the radial direction between the outer sleeve and the second member of the arm, wherein the forward wall is generally concentric to the fuel injector centerline, and wherein the forward wall defines a plurality of wall openings therethrough.
2. The fuel injector of claim 1 , wherein the second member of the arm defines a pressure atomizer within the fuel passage.
3. The fuel injector of claim 1 , wherein the outer sleeve defines at least a portion of the inner diameter at the plurality of grooves as decreasing from the inlet opening toward the downstream direction.
4. The fuel injector of claim 1 , wherein the radial opening defined through the outer sleeve is disposed outward along the radial direction of a downstream end of the plurality of grooves.
5. The fuel injector of claim 1 , wherein the radial opening defined through the outer sleeve is extended at least partially along the circumferential direction relative to the fuel injector centerline.
6. The fuel injector of claim 1 , wherein a fuel/oxidizer mixing passage is defined inward of the outer sleeve, and further wherein the fuel/oxidizer mixing passage is defined downstream of the plurality of grooves and upstream of the exit opening.
7. The fuel injector of claim 1 , wherein the fuel conduit is further defined through the first member of the arm.
8. The fuel injector of claim 1 , wherein the radial opening through the outer sleeve is extended at least partially along an axial direction relative to the fuel injector centerline, and wherein the fuel injection opening and a downstream end of the plurality of grooves are each defined inward of the radial opening along the radial direction.
9. The fuel injector of claim 1 , wherein the wall opening is defined through the forward wall extended at least partially in the circumferential direction relative to the fuel injector centerline.
10. A gas turbine engine defining an axial engine centerline, the gas turbine engine comprising:
a combustion section defined generally concentric to the engine centerline, wherein the combustion section comprises a plurality of fuel injectors defines in adjacent circumferential arrangement around the engine centerline, wherein the fuel injector comprises:
an at least partially cylindrical outer sleeve extended along a circumferential direction relative to a fuel injector centerline and at least partially co-directional to the fuel injector centerline, wherein an upstream end of the outer sleeve defines an inlet opening and a downstream end of the outer sleeve defines an exit opening, wherein each of the inlet opening and the exit opening are defined within the outer sleeve along a radial direction relative to the fuel injector centerline, and further wherein the outer sleeve defines a radial opening extended therethrough relative to the fuel injector centerline along the radial direction, and wherein at least a portion of an inner diameter of the outer sleeve defines a plurality of grooves extended from approximately the inlet opening, and further wherein the outer sleeve defines a fuel conduit through at least a portion of the outer sleeve outward of the plurality of grooves along the radial direction from the fuel injector centerline, and wherein the fuel conduit defines a fuel injection opening inward along the radial direction of the radial opening defined through the outer sleeve; and
an arm coupled to the outer sleeve and extended along the radial direction relative to the fuel injector centerline, wherein the arm defines a first member coupled to the outer sleeve and a second member extended along the radial direction and contoured to define a fuel injection port generally concentric to the fuel injector centerline, and wherein the second member defines a fuel passage extended therethrough in fluid communication with the fuel injection port; and wherein the fuel injector further comprises:
a forward wall extended along the radial direction between the outer sleeve and the second member of the arm, wherein the forward wall is generally concentric to the fuel injector centerline, and wherein the forward wall defines a plurality of wall openings therethrough.
11. The gas turbine engine of claim 10 , wherein the second member of the arm of the fuel injector defines a pressure atomizer within the fuel passage.
12. The gas turbine engine of claim 10 , wherein the outer sleeve of the fuel injector defines at least a portion of the inner diameter at the plurality of grooves as decreasing from the inlet opening toward the downstream direction.
13. The gas turbine engine of claim 10 , wherein a fuel/oxidizer mixing passage is defined inward of the outer sleeve, and further wherein the fuel/oxidizer mixing passage is defined downstream of the plurality of grooves and upstream of the exit opening.
14. The gas turbine engine of claim 10 , wherein the radial opening through the outer sleeve of the fuel injector is extended at least partially along an axial direction relative to the fuel injector centerline, and wherein the fuel injection opening and a downstream end of the plurality of grooves are each defined inward of the radial opening along the radial direction.
15. The gas turbine engine of claim 10 , wherein the wall opening is defined through the forward wall of the fuel injector is extended at least partially in the circumferential direction relative to the fuel injector centerline.
16. The gas turbine engine of claim 10 , wherein the combustion section defines a trapped vortex combustor assembly.
17. The gas turbine engine of claim 10 , wherein the plurality of fuel injectors are disposed at least partially in a circumferential direction relative to the engine centerline.
18. The gas turbine engine of claim 10 , wherein the plurality of fuel injectors are disposed at least partially in a radial direction relative to the engine centerline.