초록

A system includes a fuel nozzle for a turbine engine that includes a tapered central body located at an interior base of the fuel nozzle, an air swirler, and a fuel port in the tapered central body, separate from the air swirler.

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1. A system, comprising: a fuel nozzle, comprising: a tubular body portion with an inlet end portion and an outlet end portion;a nozzle base portion having a tapered central body coaxial with the tubular body portion, wherein the nozzle base portion is disposed adjacent the inlet end portion of the

1. A system, comprising: a fuel nozzle, comprising: a tubular body portion with an inlet end portion and an outlet end portion;a nozzle base portion having a tapered central body coaxial with the tubular body portion, wherein the nozzle base portion is disposed adjacent the inlet end portion of the tubular body portion, wherein an annular flow region is disposed between the tubular body portion and the tapered central body, wherein the tapered central body comprises an upstream end portion, a downstream end portion, an outer surface facing outwardly toward an inner surface of the tubular body portion between the upstream and downstream end portions, and a plurality of fuel ports disposed along the outer surface about a longitudinal axis of the fuel nozzle, wherein downstream corresponds to a direction of fluid flow from the inlet end portion toward the outlet end portion of the tubular body portion;a radial air swirler coaxial with the tubular body portion, wherein the radial air swirler extends about the tapered central body, and the radial air swirler is disposed between the tubular body portion and nozzle base portion; anda converging diverging venturi chamber coaxial with and located inside the tubular body portion, wherein the converging diverging venturi chamber has a generally smooth curved surface, the converging diverging venturi chamber comprises a diverging section having a diverging angle and a converging section having a converging angle, the diverging angle does not exceed about 15 degrees along substantially an entire diverging length of the diverging section, the converging angle does not exceed about 30 degrees along substantially an entire converging length of the converging section, an entrance into the converging section is downstream of the radial air swirler, an exit from the diverging section extends toward the outlet end portion of the tubular body portion, and the radial air swirler has a first outer diameter that is less than or substantially equal to a second outer diameter of the inlet end portion of the tubular body portion. 2. The system of claim 1, wherein the tapered central body protrudes from an interior base surface of the fuel nozzle, and the plurality of fuel ports are disposed at an offset from the interior base surface. 3. The system of claim 1, wherein the radial air swirler is configured to swirl an air flow in a radially inward direction toward the plurality of fuel ports on the tapered central body. 4. The system of claim 1, wherein the tapered central body has a generally bell shaped exterior that curves along the outer surface and the downstream end portion, and the generally bell shaped exterior has a curvature that extends in a first direction inwardly toward the longitudinal axis, a second direction after the first direction that extends generally along the longitudinal axis, and a third direction after the second direction that extends inwardly toward the longitudinal axis at the downstream end portion. 5. The system of claim 1, wherein the radial air swirler comprises air slots in a circumferential arrangement along the tubular body portion about the tapered central body. 6. The system of claim 1, wherein the plurality of fuel ports have respective axes oriented crosswise to the longitudinal axis of the fuel nozzle. 7. The system of claim 1, wherein the plurality of fuel ports have respective axes oriented lengthwise along the longitudinal axis of the fuel nozzle. 8. The system of claim 1, wherein the fuel nozzle is configured to inject fuel only downstream from the radial air swirler, and the plurality of fuel ports are disposed downstream from the radial air swirler. 9. The system of claim 1, comprising a combustion chamber having the fuel nozzle. 10. The system of claim 9, comprising a compressor disposed upstream of the combustion chamber in an intake path to the combustor, a turbine disposed downstream of the combustion chamber in an exhaust path from the combustor, or a combination thereof. 11. The system of claim 1, wherein the outer surface of the tapered central body comprises a first curved surface that gradually increases in angle relative to the longitudinal axis in a downstream direction between the upstream and downstream end portions. 12. The system of claim 11, wherein the outer surface of the tapered central body comprises a second curved surface that gradually decreases in angle relative to the longitudinal axis in the downstream direction between the upstream and downstream end portions, and the second curved surface is disposed upstream from the first curved surface. 13. A fuel nozzle for a turbine engine, comprising: tubular body, with an inlet end portion and an outlet end portion;a tapered central body located at an interior base of the fuel nozzle, wherein the interior base is coaxial with and adjacent the inlet end portion of the tubular body, the tapered central body comprises a curved outer surface surrounding a longitudinal axis and facing outwardly toward an inner surface of the tubular body, and at least one fuel port disposed along the curved outer surface;a radial air swirler configured to swirl an air flow in a radially inward direction toward the at least one fuel port on the tapered central body, wherein the radial air swirler is coaxial with and located between the interior base and the inlet end portion of the tubular body, the radial air swirler has a first outer diameter that generally does not exceed a second outer diameter of the inlet end portion of the tubular body, the fuel nozzle is configured to inject fuel only downstream from the radial air swirler, and the at least one fuel port is disposed downstream from the radial air swirler; anda converging diverging venturi chamber coaxial with and located inside the tubular body, wherein an entrance into the converging diverging venturi chamber is downstream of the radial air swirler, an exit from the converging diverging venturi chamber is disposed upstream or adjacent to the outlet end portion of the tubular body, and downstream corresponds to a direction of fluid flow from the inlet end portion toward the outlet end portion of the tubular body. 14. The fuel nozzle of claim 13, wherein the radial air swirler comprises air slots located along the inner surface of the tubular body adjacent to the interior base of the fuel nozzle. 15. The fuel nozzle of claim 13, wherein the curved outer surface of the tapered central body has a bell shaped curve that extends in a first direction inwardly toward the longitudinal axis, a second direction after the first direction that extends generally along the longitudinal axis, and a third direction after the second direction that extends inwardly toward the longitudinal axis at a downstream end portion of the tapered central body. 16. The fuel nozzle of claim 13, wherein the converging diverging venturi chamber has a curved converging portion and a curved diverging portion, wherein the curved converging portion has a converging angle that does not exceed about 30 degrees relative to the longitudinal axis along substantially an entire converging length of the curved converging portion, and the curved diverging portion comprises a diverging angle that does not exceed about 15 degrees relative to the longitudinal axis along substantially an entire diverging length of the curved diverging portion. 17. The fuel nozzle of claim 13, wherein the at least one fuel port is oriented in a radially outward direction relative to the longitudinal axis. 18. The fuel nozzle of claim 13, wherein the at least one fuel port is oriented in an axial direction along the longitudinal axis. 19. The fuel nozzle of claim 13, wherein the converging diverging venturi chamber has a maximum angle that does not exceed about 30 degrees along substantially an entire length of the converging diverging venturi chamber. 20. The fuel nozzle of claim 13, wherein the converging diverging venturi chamber has a diverging portion, a throat, and a converging portion, wherein the diverging portion is angled from an entry region to the throat, the converging portion is angled from the throat to an exit region, and the entry and exit regions have a substantially equal width. 21. A method of operating a turbine engine, comprising: injecting fuel from at least one lateral fuel port in a bell shaped body disposed at a base region of a fuel nozzle, wherein the bell shaped body has a bell shaped exterior surface that curves from an upstream end portion to a downstream end portion in a first direction inwardly toward a longitudinal axis of the fuel nozzle, a second direction after the first direction that extends generally along the longitudinal axis, and a third direction after the second direction that extends inwardly toward the longitudinal axis at the downstream end portion;flowing air through a tubular body from an inlet end portion to an outlet end portion, wherein the tubular body and the bell shaped body extend lengthwise along the longitudinal axis of the fuel nozzle, and the inlet end portion is adjacent the base region;swirling the air, via a radial air swirler, in a cross flow direction with the fuel injected from the at least one lateral fuel port, wherein fuel is injected only downstream from the radial air swirler, the at least one lateral fuel port is disposed downstream from the radial air swirler, the radial air swirler is located between the base region and the inlet end portion of the tubular body, and the radial air swirler has a first outer diameter that is less than or substantially the same as a second outer diameter of the inlet end portion of the tubular body; and flowing the fuel and the air through a converging diverging venturi chamber downstream from the radial air swirler, wherein the converging diverging venturi chamber has a generally smooth curved surface, the converging diverging venturi chamber is disposed between the inlet end portion and the outlet end portion of the tubular body, and downstream corresponds to a direction of fluid flow from the inlet end portion toward the outlet end portion of the tubular body. 22. The method of claim 21, wherein swirling the air comprises injecting air into the fuel nozzle through air inlet vanes of the radial air swirler in directions radially toward but offset from the longitudinal axis of the fuel nozzle. 23. The method of claim 21, comprising reducing fuel mixing stagnation zones and flame holding within an interior of the fuel nozzle at least partially by the bell shaped body. 24. The method of claim 21, wherein the converging diverging venturi chamber has a maximum angle that does not exceed about 30 degrees along substantially an entire length of the converging diverging venturi chamber. 25. A system, comprising: a fuel nozzle, comprising: a base portion having a central body portion extending axially away from the base portion along a longitudinal axis of the fuel nozzle, wherein the central body portion comprises at least one fuel port;an outer tubular portion extending lengthwise along the longitudinal axis of the fuel nozzle, wherein the outer tubular portion comprises a converging diverging venturi chamber between an inlet end portion and an outlet end portion of the outer tubular portion, and the converging diverging venturi chamber is disposed downstream from the central body portion relative to a direction of fluid flow through the fuel nozzle from the inlet end portion to the outlet end portion; anda radial air swirler disposed between the base portion and the inlet end portion of the outer tubular portion, wherein the radial air swirler extends circumferentially around the central body portion, and the radial air swirler has a first outer diameter that is less than or substantially the same as a second outer diameter of the inlet end portion of the outer tubular portion. 26. The system of claim 25, wherein the converging diverging venturi chamber has a maximum angle that does not exceed about 30 degrees along substantially an entire length of the converging diverging venturi chamber. 27. The system of claim 25, wherein the second outer diameter is substantially constant lengthwise along the outer tubular portion. 28. The system of claim 25, wherein the first outer diameter and the second outer diameter are substantially the same as one another. 29. The system of claim 25, comprising a turbine combustor or a turbine engine having the fuel nozzle.