Variable swirl fuel nozzle
A fuel injector providing a flow of fuel having a variable swirl and/or variable effective area is disclosed. The fuel injector may have a nozzle defining a mixing chamber having an outlet proximate a centerline of the mixing chamber, a first fuel line in fluid communication with the mixing chamber and a second fuel line in fluid communication with the mixing chamber. The first fuel line may terminate in a tangential fuel inlet positioned tangential to the centerline of the nozzle, while the second fuel line may terminate in a radial fuel inlet positioned radial to the centerline of the nozzle.
1. A fuel injector, comprising:
a nozzle having an outer wall defining a mixing chamber having an outlet proximate a centerline of the nozzle;
a first fuel line in fluid communication with the mixing chamber, the first fuel line terminating in a tangential fuel inlet located in the outer wall; and
a second fuel line in fluid communication with the mixing chamber, the second fuel line terminating in a radial fuel inlet located in the outer wall, the radial fuel inlet being orthogonal to the tangential fuel inlet.
2. The fuel injector of claim 1 , further including a plurality of tangential fuel inlets.
3. The fuel injector of claim 1 , further including a plurality of radial fuel inlets.
4. The fuel injector of claim 1 , further including a valve, the valve controlling a flow of fuel to at least one of the first and second fuel lines.
5. The fuel injector of claim 4 , wherein the valve is a pressure valve having a spring-biased pin and metering slot.
6. The fuel injector of claim 4 , wherein the valve is an electronic valve controlled by a processor.
7. The fuel injector of claim 1 , further including a manifold, the manifold controlling fuel flow to the radial fuel inlet and the tangential fuel inlet.
8. The fuel injector of claim 1 , wherein the nozzle further defines an outlet in fluid communication with the mixing chamber, the outlet being annular in shape.
9. The fuel injector of claim 4 , wherein the valve is located distant and separate from the nozzle.
10. A combustor of a gas turbine engine, comprising:
an outer wall;
an inner wall;
a bulkhead spanning between the inner and outer walls, the outer wall, inner wall and bulkhead defining an annular combustion chamber; and
a fuel injector extending through the bulkhead to the combustor chamber, the fuel injector including a nozzle having an outer nozzle wall defining a mixing chamber, the mixing chamber having an exit proximate a centerline of the nozzle;
a first fuel line in fluid communication with the mixing chamber, the first fuel line terminating in a tangential fuel inlet located in the outer nozzle wall; and
a second fuel line in fluid communication with the mixing chamber, the second fuel line terminating in a radial fuel inlet located in the outer nozzle wall, the radial fuel inlet being orthogonal to the tangential fuel inlet.
11. The combustor of claim 10 , further including a valve, the valve controlling a flow of fuel to at least one of the first fuel line and the second fuel line.
12. The combustor of claim 11 , further including a plurality of tangential fuel inlets and a plurality of radial fuel inlets.
13. A method of supplying fuel to a combustor using a fuel injector comprising:
a fuel nozzle having an outer wall defining a mixing chamber having an outlet proximate a centerline of the fuel nozzle;
a first fuel line in fluid communication with the mixing chamber, the first fuel line terminating in a tangential fuel inlet located in the outer wall; and
a second fuel line in fluid communication with the mixing chamber, the second fuel line terminating in a radial fuel inlet located in the outer wall, the radial fuel inlet being orthogonal to the tangential fuel inlet;
wherein the method comprises:
directing a tangential flow of fuel to the fuel nozzle; directing a radial flow of fuel to the fuel nozzle;
mixing the tangential flow of fuel and the radial flow of fuel in the mixing chamber of the fuel nozzle; and
exiting fuel through the outlet of the fuel nozzle.
14. The method of claim 13 , further comprising reducing the tangential flow of fuel during a low-power engine operation.
15. The method of claim 13 , further comprising increasing the radial flow of fuel during a high-power engine operation.
16. The method of claim 15 , further comprising reducing the tangential flow of fuel during the high-power engine operation.
17. The method of claim 13 , further comprising controlling the radial flow of fuel and the tangential flow of fuel via a valve.
18. The method of claim 17 , further comprising gradually transitioning from the tangential flow of fuel during low-power operation to the radial flow of fuel during high-power operation using the valve.
19. The method of claim 13 , further comprising creating an atomized fuel mist during low-power operations by imparting a swirl to the fuel.
20. The method of claim 13 , further comprising creating an atomized fuel mist during high-power operations by creating a pressure drop in the fuel.