Patent Application
20130086910
The subject matter disclosed herein relates to a fuel nozzle with an improved fuel injection design.
A gas turbine engine combusts a mixture of fuel and air to generate hot combustion gases, which in turn drive one or more turbines. In particular, the hot combustion gases force turbine blades to rotate, thereby driving a shaft to rotate one or more loads, e.g., an electrical generator. The gas turbine engine includes a fuel nozzle to inject fuel and air into a combustor. As appreciated, the fuel air mixture significantly affects engine performance, fuel consumption, and emissions. In particular, non-uniform mixing of fuel and air may increase emissions, e.g., nitrogen oxides (NOx). Also, in some fuel nozzles, fuel may be injected via fuel outlets located on vanes disposed within the fuel nozzle. However, limited space for fuel injection on the vanes may lead to poor flame holding margins and fuel distribution.
Certain embodiments commensurate in scope with the originally claimed invention are summarized below. These embodiments are not intended to limit the scope of the claimed invention, but rather these embodiments are intended only to provide a brief summary of possible forms of the invention. Indeed, the invention may encompass a variety of forms that may be similar to or different from the embodiments set forth below.
In accordance with a first embodiment, a system includes a fuel nozzle. The fuel nozzle includes a hub, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple first fuel outlets disposed on the hub, and multiple swirl vanes disposed in the airflow path downstream from the multiple first fuel outlets.
In accordance with a second embodiment, a system includes a fuel nozzle. The fuel nozzle includes a hub, a shroud disposed about the hub, an airflow path between the hub and the shroud, and a swirl mechanism disposed in the airflow path. The fuel nozzle also includes a first fuel path leading to multiple first fuel outlets directed into the airflow path upstream from the swirl mechanism. The fuel nozzle further includes a second fuel path leading to multiple second fuel outlets directed into the airflow path, wherein the multiple second fuel outlets is downstream from the multiple first fuel outlets, and the first and second fuel paths are configured to supply independently controlled amounts of fuel to the multiple first and second outlets, respectively.
In accordance with a third embodiment, a system includes a fuel nozzle. The fuel nozzle includes a hub, a shroud disposed about the hub, an airflow path between the hub and the shroud, a converging-diverging geometry disposed along the airflow path, multiple first fuel outlets directed into the airflow path along the converging diverging geometry, and multiple second fuel outlets directed into the airflow path at an axial offset distance from the converging-diverging geometry
These and other features, aspects, and advantages of the present invention will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein:
One or more specific embodiments of the present invention will be described below. In an effort to provide a concise description of these embodiments, all features of an actual implementation may not be described in the specification. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions must be made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be appreciated that such a development effort might be complex and time consuming, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure.
When introducing elements of various embodiments of the present invention, the articles “a,” “an,” “the,” and “said” are intended to mean that there are one or more of the elements. The terms “comprising,” “including,” and “having” are intended to be inclusive and mean that there may be additional elements other than the listed elements.
The present disclosure is directed to systems for improving the injection of fuel (e.g., liquid and/or gas) into a fuel nozzle, thereby enhancing fuel wobbe capability (i.e., interchangeability of fuels used), flame holding margin (e.g., reducing the possibility of flame holding), premixing of the fuel (e.g., premixing fuel and air), and control over the fuel-air profile. In particular, embodiments of the present disclosure include a distributed fuel injection circuit that enables injection of fuel (e.g., liquid and/or gas) via fuel outlets disposed on a hub or shroud upstream from fuel outlets located on vanes (e.g., swirl vanes) extending between the hub and the shroud. In certain embodiments, the fuel nozzle includes a common fuel passage that splits fuel flow between the fuel outlets upstream of the vanes and the fuel outlets on the vanes enabling passive control of fuel between the respective fuel outlets. In other embodiments, the fuel nozzle includes separate fuel passages that enable independent fuel flows to fuel outlets upstream of the vanes and the fuel outlets on the vanes enabling active control (e.g., via a controller) of fuel to the respective fuel outlets. The fuel outlets upstream of the vanes may be located on a converging-diverging geometry of the hub. In addition, the fuel outlets upstream of the vanes may be oriented at an angle (e.g., less than 90 degrees relative to an axis of the fuel nozzle) in a downstream direction and/or circumferentially about the axis of the fuel nozzle to induce swirl about the axis. Further, the fuel outlets upstream of the vanes may be spaced circumferentially about the hub and/or include sets of fuel outlets axially offset from one another relative to the axis of the fuel nozzle. By utilizing the distributed fuel injection circuit in the disclosed embodiments, fuel may be injected via the hub and/or shroud upstream of the vanes to enhance the fuel wobbe capability, flame holding margin, premixing of the fuel, and control over the fuel-air profile, while reducing emissions.
Turning now to the drawings and referring first to
The fuel passage 56 includes a common fuel passage 64 that extends through the inner body 38 and leads to a plurality of first fuel outlets 66 disposed on the hub 13 and a plurality of second fuel outlets 68 disposed in the region of the swirl mechanism 11 (e.g., on the plurality of vanes 48). As illustrated, the plurality of first fuel outlets 66 is disposed upstream from the plurality of second fuel outlets 68. The common fuel passage 64 splits a fuel flow between the first fuel outlets 66 and the second fuel outlets 68 as indicated by arrows 70 and 72. Approximately 30 percent or less of the total fuel in the common fuel passage 64 may be diverted to the first fuel outlets 66. For example, approximately 5, 10, 15, 20, 25, or 30 percent, or any other number therebetween of the total fuel in the common fuel passage 64 may be diverted to the first fuel outlets 66. The common fuel passage 64 enables passive control over the injection of fuel via the fuel outlets 66 and 68. The first fuel outlets 66 are disposed on the hub 13 upstream from the swirl mechanism 11 (e.g., vanes 48). In particular, the first fuel outlets 66 are disposed on the converging-diverging geometry 15 of the hub 13 along an airflow path 74. The converging-diverging geometry 15 includes a converging portion 76 that gradually converges toward the shroud 17 in an axial direction 77 and a diverging portion 78 that gradually diverges away from the shroud 17 in the axial direction 77. The diverging portion 78 is disposed downstream of the converging portion 76 in the axial direction 77. In certain embodiments, the first fuel outlets 66 may be disposed on another portion of the hub 13 (e.g., besides the converging-diverging geometry 15) upstream of the swirl mechanism 11. The plurality of second fuel outlets 68 is disposed at an axially offset distance 79 downstream from the converging diverging geometry 15. The first fuel outlets 66 are oriented outward in the radial directions 50 and 52 (i.e. crosswise) relative to the axis 42 of the fuel nozzle 12. In some embodiments, the first fuel outlets 66 may also be distributed on the shroud 17 (see
As mentioned above, the plurality of second fuel outlets 68 is disposed in the region of the swirl mechanism 11 (e.g., on the plurality of vanes 48). Each vane 48 includes one or more fuel outlets 68. In addition, each vane 48 may include a first set 80 of fuel outlets 68 and a second set 82 of fuel outlets 68 axially offset from each other along the axis 42 of the fuel nozzle 12 in the axial (i.e., downstream) direction 77. The number of fuel outlets 68 on each vane 48 may range from 1 to 50, 1 to 10, 4 to 20, or 4 to 10, or any other number. For example, each vane 48 may include one or more fuel outlets 68 (e.g., 1 to 10) on each side. The plurality of vanes 48 is configured to swirl or rotate the air flow, while mixing fuel with air.
Fuel flows into the common fuel passage 64 as indicated by arrows 84. The common fuel passage 64 splits the fuel flow into a first fuel flow 70 to the plurality of first fuel outlets 66 and a second fuel flow 72 to the plurality of second fuel outlets 68. For example, fuel (e.g., gas fuel) flows in the axial direction 77 through the fuel passage 64 until a portion of the fuel exits the first fuel outlets 66 in radial directions 50 and 52 into a first mixing region 86. In particular, the fuel exits the fuel outlets 66 disposed on the hub 13 crosswise to the axis 42 of the fuel nozzle 12. As illustrated, the fuel nozzle 12 include the airflow path (e.g., annular flow path), generally indicated by arrow 74, between the hub 13 and the shroud 17. Air flows in the axial direction 77 into the first mixing region 86. In the first mixing region 86, the fuel from the fuel outlets 66 interacts with the air. The fuel-air mixture 88 flows downstream towards the swirl mechanism 11 (e.g., blades 48) disposed in the airflow path 74. Another portion of the fuel exits the second fuel outlets 68 into a second mixing region 90. The fuel-air mixture 88 flows through the airflow path 74 into the second mixing region 90 surrounding each vane 48. In the mixing region 90 of each vane 48, fuel from the fuel outlets 68 interacts with the fuel-air mixture 88 to form a fuel-air mixture 92. The fuel-air mixture 92 is swirled by the vanes 48 to aid in mixing of the fuel and air for proper combustion, and flows downstream towards an exit 94 of the fuel nozzle 12, as generally indicated by arrows 96.
The injection of fuel upstream of the swirl mechanism 11 enhances the flame holding margins (e.g., reducing the possibility of flame holding) around the vanes 48. In particular, diverting a portion of the fuel for upstream injection enables a reduction in a diameter 98 of the fuel outlets 68 on the vanes 48 enhancing the flame holding margin. For example, the reduction in diameter 98 of the fuel outlet 68 relative to a typical fuel outlet 68 may range from approximately 1 to 99 percent, 10 to 90 percent, 20 to 80 percent, 30 to 70 percent, or 40 to 60 percent, and all subranges therebetween. The reduction in diameter 98 of the fuel outlet 68 may be approximately 5, 10, 15, 20, 25, 30, 35, 40, 45, 50, 55, 60, 65, 70, 75, 80, 85, 90, or 95 percent, or any other number.
In addition to reducing the possibility of flame holding, the improved fuel injection design enhances premixing efficiencies which reduces emissions. In addition, the improved fuel injection design provides fuel injection from both a circumferential direction 54 and radial direction 50 and 52 to provide better control over the overall fuel-air profile of the fuel nozzle 12 and, thus, improve the dynamics and operability of the fuel nozzle 12. Further, the improved fuel injection design enhances wobbe capability and fuel flexibility for the fuel nozzle 12.
As mentioned above, fuel may be injected from fuel outlets 66 located at other locations besides and/or in addition to the hub 13 upstream of the swirl mechanism 11. In addition, the fuel passages to the different fuel outlets 66 and 68 may be separate, enabling active control over the fuel flows.
As mentioned above, the plurality of first fuel outlets 66 are disposed on the hub 13 (e.g., along the converging-diverging geometry 15). Each illustrated fuel outlet 66 may represent one or more fuel outlets 66 circumferentially 54 disposed about the axis 42 of the fuel nozzle 12 (see
As illustrated, the fuel nozzle 12 also includes the plurality of first outlets 66 disposed on the shroud 17. The first outlets 66 are located along a converging-diverging geometry 134. The converging-diverging geometry 134 is similar to the converging-diverging geometry 15. In certain embodiments, the first outlets 66 may be disposed upstream of the swirl mechanism 11 (e.g., vanes 48) on a portion of the shroud 17 different from the converging-diverging geometry 134. The first outlets 66 disposed on the shroud 17 are similar to the first outlets 66 disposed on the hub 13. The plurality of first outlets 66 on the shroud 17 (and converging-diverging geometry 134) may be disposed directly across from the plurality of first outlets 66 on the hub 13 (and converging-diverging geometry 15). In certain embodiments, the plurality of first outlets 66 on the shroud 17 may be axially offset from the plurality of fuel outlets 66 on the hub 13 along the axis 42 of the fuel nozzle 12.
Fuel flows into the fuel path 113 leading to the plurality of first fuel outlets 66 directed into the airflow path 74 upstream from the swirl mechanism 11. In particular, fuel flows into fuel passages 110 and 112 as indicated by arrows 136 and 138, respectively. For example, fuel (e.g., liquid and/or gas fuel) flows in the axial direction 54 through the fuel passages 110 and exits the first fuel outlets 66 in the radial directions 50 and 52 into the first mixing region 86. Also, fuel (e.g., liquid and/or gas fuel) flows through the fuel passages 112 and exits the first fuel outlets 66 in the radial directions 50 and 52 into the first mixing region. In particular, the fuel exits the fuel outlets 66 disposed on the hub 13 and shroud 17 crosswise to the axis 42 of the fuel nozzle 12. For example, the fuel outlets 66 disposed on the hub 13 and shroud 17 are oriented crosswise to one another (e.g., in outward 50 and inward 52 radial directions, respectively) and to axis 42. As illustrated, the fuel nozzle 12 include the airflow path (e.g., annular flow path), generally indicated by arrow 74, between the hub 13 and the shroud 17. Air flows in the axial direction 54 into the first mixing region 86. In the first mixing region 86 the fuel from the fuel outlets 66 interacts with the air. The fuel-air mixture 88 flows downstream towards the swirl mechanism 11 (e.g., blades 48) disposed in the airflow path 74.
As mentioned above, the plurality of second fuel outlets 68 is disposed in a region of the swirl mechanism 11 (e.g., on the swirl vanes 48). Fuel flows into the fuel path 111 leading to the plurality of second fuel outlets 68 directed into the airflow path 74. In particular, fuel flows into fuel passage 56 as indicated by arrows 140, and flows to the fuel outlets 68 on the vanes 48 as indicated by arrows 72. Fuel exits the second fuel outlets 68 into the second mixing region 90. The fuel-air mixture 88 flows through the airflow path 74 into the second mixing region 90 surrounding each vane 48. In the mixing region 90 of each vane 48, fuel from the fuel outlets 68 interacts with the fuel-air mixture 88 to form a fuel-air mixture 90. The fuel-air mixture 90 is swirled by the vanes 48 to aid in mixing of the fuel and air for proper combustion, and flows downstream towards the exit 94 of the fuel nozzle 12, as generally indicated by arrows 96.
The injection of fuel upstream of the swirl mechanism 11 enhances the flame holding margins around the vanes 48. In particular, diverting a portion of the fuel for upstream injections enables a reduction in a diameter 98 of the fuel outlets 68 on the vanes 48 enhancing the flame holding margin. For example, the reduction in diameter 98 of the fuel outlet 68 relative to a typical fuel outlet 68 may range from approximately 1 to 99 percent, 10 to 90 percent, 20 to 80 percent, 30 to 70 percent, or 40 to 60 percent, and all subranges therebetween. The reduction in diameter 98 of the fuel outlet 68 may be approximately 5, 10, 15, 20, 25, 30, 35, 40, 45, 50, 55, 60, 65, 70, 75, 80, 85, 90, or 95 percent, or any other number.
In addition to reducing the possibility of flame holding, the improved fuel injection design improves premixing efficiencies which reduces emissions. In addition, the improved fuel injection design provides fuel injection from both a circumferential direction 54 and radial direction 50 and 52 to provide better control over the overall fuel-air profile of the fuel nozzle 12 and, thus, improves the dynamics and operability of the fuel nozzle 12. In particular, the improved fuel injection design enables a staged mixing of fuel with air. Further, the improved fuel injection design enhances wobbe capability and fuel flexibility for the fuel nozzle 12. In particular, the multiple fuel passages 56, 111, and 113 enable different fuels (e.g., liquid and/or gas fuels) to be employed with the fuel nozzle 12.
As illustrated, each fuel outlet 66 is directed into the airflow path 74. In particular, each fuel outlet 66 is oriented at the angle 130 relative to the axis 42 of the fuel nozzle 12. Specifically, the illustrated fuel outlets 66 are oriented directly perpendicular (e.g., crosswise) in radial direction 50 to the airflow path 74 with each fuel outlet 66 including the angle 130 of 90 degrees relative to the axis 42 of the fuel nozzle 12. Thus, fuel exits the fuel outlets in radial direction 50 crosswise to the airflow path 74 as indicated by arrows 148. Alternatively, the fuel outlets 66 may be oriented at the angle 130 in an upstream (e.g., axial) direction 132 (e.g., third set 128 of the fuel outlets 66) or the downstream (e.g., axial) direction 77 (e.g., first set 124 of the fuel outlets 66) along the airflow path 74 (see
In addition, each fuel outlet 66 may include a diameter 150. The diameter 150 of each fuel outlet 66 may range from approximately 0.5 to 1.8 mm, 0.75 to 1.55 mm, 1 to 1.3 mm, 0.5 to 1.0 mm, 1 to 1.8 mm, 1.3 to 1.8 mm, and all subranges therebetween. For example, the diameter 150 each fuel outlet 66 may be approximately 0.5, 0.6., 0.7, 0.8, 0.9, 1.0, 1.1, 1.2, 1.3, 1.4, 1.5, 1.6, 1.7, or 1.8 mm, or any other number therebetween. The diameter 150 of each fuel outlet 66 may be the same or different at different axial positions. The difference in diameter 150 between fuel outlets 66 may vary by approximately 10 to 200 percent relative to one another. For example, the diameter 150 of the fuel outlets 66 may vary by approximately 10 to 100 percent, 10 to 50 percent, 50 to 100 percent, 100 to 200 percent, 100 to 150 percent, 150 to 200 percent, and all subranges therebetween. For example, the diameter 150 between fuel outlets 66 may vary by approximately 10, 20, 30, 40, 50, 60, 70, 80, 90, 100, 110, 120, 130, 140, 150, 160, 170, 180, 190, or 200 percent, or any other number therebetween.
Besides the converging-diverging geometry 15 mentioned above, one or more fuel outlets 66 may be disposed on different geometries of the hub 13 upstream of the swirl mechanism 11.
Technical effects of the disclosed embodiments include providing systems for improving injection of fuel into the fuel nozzle 12. Fuel outlets 66 located upstream from fuel injection in the region of the swirl mechanism 11 (e.g., vanes 48) enable hub 13 and shroud 17 injection of fuel crosswise to the airflow. The fuel may be distributed between these fuel outlets 66 for cross-flow injection at a variety of angles (e.g., 0 to 90 degrees). The improved design enhances the fuel wobbe capability, flame holding margin, premixing of the fuel, and control over the fuel-air profile, while reducing emissions (e.g., NOx) in the turbine system 10.
This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.
