Injector with integrated resonator
The system may include a turbine engine. The turbine engine may include a fuel nozzle. The fuel nozzle may include an air path. The fuel nozzle may also include a fuel path such that the fuel nozzle is in communication with a combustion zone of the turbine engine. Furthermore, the fuel nozzle may include a resonator. The resonator may be disposed in the fuel nozzle directly adjacent to the combustion zone.
1. A system, comprising:
a turbine engine, comprising:
a combustor configured to house one or more fuel nozzles, wherein the combustor comprises a fuel nozzle having a downstream plate, an air path, and a fuel path, wherein the fuel nozzle is in communication with a combustion zone of the turbine engine via the downstream plate of the fuel nozzle; and
a resonator disposed in a chamber in the fuel nozzle directly adjacent to the combustion zone, wherein the chamber is defined by a dividing plate separating the fuel nozzle into a plurality of compartments, the downstream plate, and a cylindrical sidewall coupled to each of the dividing plate and the downstream plate, wherein the resonator comprises a resonator plate coupled to the downstream plate of the fuel nozzle, wherein the resonator plate is separate, distinct, and spaced from each of the dividing plate and the cylindrical sidewall, and separate and distinct from the downstream plate.
2. The system of claim 1 , wherein the resonator is disposed in the air path.
3. The system of claim 1 , wherein the resonator is disposed in a fuel nozzle cavity adjacent the downstream plate of the fuel nozzle as the chamber.
4. The system of claim 3 , wherein the resonator comprises a hollow enclosure defining a resonator chamber, the hollow enclosure comprises a resonator inlet within the fuel nozzle cavity, and the hollow enclosure comprises a resonator outlet along the downstream end of the fuel nozzle.
5. The system of claim 4 , wherein the resonator inlet comprises a radial inlet, an axial inlet, or both, through the hollow enclosure, and the resonator outlet comprises an axial outlet.
6. The system of claim 1 , comprising:
a central fuel cavity in the fuel path, wherein the central fuel cavity concentrically encloses the mixing tubes; and
a central air cavity enclosing both the mixing tubes and the resonator.
7. The system of claim 6 , comprising a central air cavity enclosing both the mixing zone and the resonator as the air compartment.
8. A system, comprising:
a fuel nozzle sized to be utilized in a combustor configured to house one or more fuel nozzles, the fuel nozzle comprising a downstream plate, wherein the fuel nozzle is configured to mount in communication with a combustion zone of a turbine engine via the downstream plate of the fuel nozzle, wherein the fuel nozzle comprises:
a fuel path configured to supply fuel;
an air path configured to supply air; and
a resonator disposed in a chamber in the fuel nozzle directly adjacent to the combustion zone, wherein the chamber is defined by a dividing plate separating the fuel nozzle into a plurality of compartments, the downstream plate, and a cylindrical sidewall coupled to each of the dividing plate and the downstream plate, wherein the resonator comprises a resonator plate coupled to the downstream plate of the fuel nozzle, wherein the resonator plate is separate, distinct, and spaced from each of the dividing plate and the cylindrical sidewall, and separate and distinct from the downstream plate.
9. The system of claim 8 , wherein the resonator plate comprises an upstream plate and a plurality of side plates, wherein the upstream plate is coupled to the side plates to define a resonator chamber.
10. The system of claim 9 , wherein the resonator comprises a tuned resonator, wherein the resonator is tuned to dampen acoustic oscillations generated by a combustion process adjacent to an outer wall of the fuel nozzle based on the length of the upstream plate and the length of the side plates.
11. The system of claim 10 , comprising an air outlet extending through the outer wall of the fuel nozzle and a second air inlet disposed on at least one of the side plates for providing air to the resonator chamber.
12. The system of claim 8 , wherein the resonator comprises a tuned resonator, wherein the resonator is tuned to dampen acoustic oscillations generated by combustion adjacent to an outer wall of the fuel nozzle based on dimensions and number of air inlets and air outlets disposed in a resonator chamber of the resonator.
13. The system of claim 8 , comprising an air inlet and an air outlet disposed in a resonator chamber of the resonator, wherein the air inlet is approximately 0.05 inches in diameter and the air outlet is approximately 0.1 inches in diameter.
14. The system of claim 8 , comprising a plurality of mixing tubes disposed in the fuel path and concentrically disposed about the resonator.
15. The system of claim 14 , comprising a central fuel cavity in the fuel path, wherein the central fuel cavity concentrically encloses the mixing tubes and a central air cavity enclosing both the mixing tubes and the resonator.
16. The system of claim 8 , wherein the fuel nozzle comprises a mixing zone disposed directly adjacent the downstream plate and configured to mix fuel and air to generate a fuel/air mixture.
17. A fuel nozzle, comprising:
a downstream plate;
a fuel path, wherein the fuel nozzle is located in the fuel path, wherein the fuel nozzle is configured to mount in communication with a combustion zone of a turbine engine via the downstream plate of the fuel nozzle;
an air compartment in a downstream portion of the fuel nozzle, wherein the air compartment is circumferentially surrounded by the fuel path, wherein the air compartment is defined by a dividing plate separating the fuel nozzle into a plurality of compartments, the downstream plate, and a cylindrical sidewall coupled to each of the dividing plate and the downstream plate;
an air path configured to supply air to the air compartment; and
a resonator disposed in the air compartment of the fuel nozzle directly adjacent to the combustion zone, wherein the resonator comprises a resonator plate coupled to the downstream plate of the fuel nozzle, wherein the resonator plate is separate, distinct, and spaced from each of the dividing plate and the cylindrical sidewall, and separate and distinct from the downstream plate, wherein the fuel nozzle is sized to be utilized in a combustor configured to house one or more fuel nozzles.
18. The fuel nozzle of claim 17 , wherein the resonator is configured to dampen pressure oscillations between approximately 1000 to 4000 Hz.
19. The fuel nozzle of claim 17 , wherein the resonator comprises a resonator inlet configured to allow air to pass into a cavity within the resonator and a resonator outlet configured to allow air to pass from the cavity within the resonator through the downstream plate of the fuel nozzle.
20. The fuel nozzle of claim 17 , comprising a central fuel cavity in the fuel path, wherein the central fuel cavity concentrically encloses the mixing tubes, wherein the air compartment comprises a central air cavity enclosing both the mixing tubes and the resonator.