In one embodiment, a system includes a turbine engine fuel nozzle having an air path, a fuel path, and a surface along the air path. The fuel path may be directed toward the surface. The turbine engine fuel nozzle also may include a heating element configured to heat the surface.
대표청구항▼
1. A system, comprising: a turbine engine, comprising: a turbine;a combustor;a compressor; anda fuel nozzle disposed in the combustor, wherein the fuel nozzle comprises: an air passage defined by an inner tube and an outer tube; at least one prefilmer disposed in a region of the air passage radially
1. A system, comprising: a turbine engine, comprising: a turbine;a combustor;a compressor; anda fuel nozzle disposed in the combustor, wherein the fuel nozzle comprises: an air passage defined by an inner tube and an outer tube; at least one prefilmer disposed in a region of the air passage radially between the inner tube and the outer tube; and a heat source disposed within the region of the air passage, wherein the prefilmer is configured to control fuel vaporization, coking, or a combination thereof. 2. The system of claim 1, wherein the heat source comprises an active heat control configured to actively control temperature in the fuel to adjust a rate of the fuel vaporization and reduce the coking. 3. The system of claim 1, wherein the heat source comprises an electric heating element or convective heat transfer from another source. 4. The system of claim 1, wherein the heat source is configured to maintain a temperature of the at least one prefilmer to a target value within a range of approximately 700 to 1000 degrees Fahrenheit. 5. The system of claim 1, wherein the fuel nozzle comprises a swirler, and the at least one prefilmer is upstream of the swirler relative to a direction of flow through the fuel nozzle. 6. The system of claim 1, wherein the heat source is coupled to the at least one prefilmer, the at least one prefilmer comprises a cross-sectional shape that is curved, and the at least one prefilmer and the heat source are disposed inside a perforated annulus of a flow conditioner. 7. The system of claim 1, wherein the at least one prefilmer is coupled to a swirler inside the fuel nozzle. 8. The system of claim 7, wherein the heat source is inside an airfoil shaped profile of the at least one prefilmer. 9. The system of claim 7, wherein the heat source comprises a heated air passage through a portion of the at least one prefilmer. 10. A system, comprising: a fuel nozzle comprising: an air passage defined by an inner tube and an outer tube; a fuel prefilmer configured to create a fuel film that sheds fuel in the fuel nozzle; and a heat source configured to control fuel vaporization and coking associated with the fuel prefilmer; wherein the fuel prefilmer and the heat source are disposed within a region of the air passage radially between the inner tube and the outer tube. 11. The system of claim 10, wherein the fuel prefilmer comprises a plurality of annular members located around a circumference of an annulus of the fuel nozzle. 12. The system of claim 11, wherein the plurality of annular members are staggered axially along the annulus. 13. The system of claim 10, wherein the fuel prefilmer is inside the fuel nozzle upstream from a swirler relative to a flow direction through the turbine fuel nozzle. 14. The system of claim 13, comprising a perforated annular flow conditioner disposed about the fuel prefilmer, wherein the fuel prefilmer comprises an annular geometry having a curved cross-section facing a fuel port. 15. The system of claim 10, wherein the fuel prefilmer is coupled to a swirler inside the fuel nozzle. 16. The system of claim 15, wherein the fuel prefilmer comprises an air foil-shaped cross-section. 17. The system of claim 10, wherein the heat source is configured to maintain a temperature of at least greater than approximately 700 degrees Fahrenheit on a surface of the fuel prefilmer. 18. A system, comprising: a turbine engine fuel nozzle, comprising: an air path between an inner wall and an outer wall, wherein the outer wall extends around the inner wall; a fuel path; a prefilmer disposed in a region of the air path spaced between the inner wall and the outer wall, wherein the fuel path is directed toward the prefilmer; and a heat source configured to heat the prefilmer, wherein the heat source is disposed within the region of the air path. 19. The system of claim 18, comprising a controller coupled to the heat source, wherein the controller is configured to adjust the heat source to maintain a temperature of at least greater than approximately 700 degrees Fahrenheit. 20. The system of claim 18, comprising a controller coupled to the heat source, wherein the controller is configured to adjust the heat source to a target temperature to reduce coking and control fuel vaporization.
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이 특허에 인용된 특허 (12)
Graves,Charles B.; DeSalle,Stephanie, Air assist fuel injector for a combustor.
Roffe Gerald A. (3 Markwood La. East Northport NY 11731) Trucco Horacio A. (13 Saddler Ct. Huntington Station NY 11746), Apparatus for the premixed gas phase combustion of liquid fuels.
Pellizzari, Roberto O.; Baron, John; Linna, Jan Roger; Loftus, Peter; Palmer, Peter; Mello, John Paul; Sprague, Stuart Bennett, Fuel injector for an internal combustion engine.
Snyder Timothy S. (Glastonbury CT) Rosfjord Thomas J. (South Windsor CT) McVey John B. (Glastonbury CT) Hu Aaron S. (Hartford CT) Schlein Barry C. (Wethersfield CT), Tangential entry fuel nozzle.
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