Patent Application
20160298847
The subject matter disclosed herein relates to gas turbine systems, and more particularly, to a system and method for attenuating resonance.
Gas turbine systems generally include a gas turbine engine having a compressor section, a combustor section, and a turbine section. The combustor section may include one or more combustors (e.g., combustion cans), which receive and combust a fuel with an oxidant (e.g., air) in a combustion chamber of each combustor. As combustion occurs in each combustor, hot combustion gases flow into and drive one or more turbine stages in the turbine section. Unfortunately, gas turbine systems may be susceptible to resonant behavior due to a variety of drivers, such as a resonant frequency of the oxidant, fuel, or other fluids supplied to the combustors. Over time, the resonant frequencies may change in the gas turbine system.
Certain embodiments commensurate in scope with the originally claimed disclosure are summarized below. These embodiments are not intended to limit the scope of the claimed disclosure, but rather these embodiments are intended only to provide a brief summary of possible forms of the disclosure. Indeed, the disclosure may encompass a variety of forms that may be similar to or different from the embodiments set forth below.
In a first embodiment, a system includes a combustor having a combustion chamber and a combustor supply passage configured to supply a fluid flow into the combustion chamber. The system also includes a resonator configured to receive at least a portion of the fluid flow. The resonator comprises a frequency adjuster configured to change an attenuation frequency of the resonator.
In a second embodiment, a system includes a resonator configured to receive at least a portion of a fluid flow being supplied to a combustion chamber of a combustor. The resonator includes a frequency adjuster configured to change an attenuation frequency of the resonator. The system also includes a controller comprising a memory operatively coupled to a processor configured to store data and instructions. The controller is configured to transmit instructions to the frequency adjuster to change the attenuation frequency of the resonator.
In a third embodiment, a method includes adjusting an attenuation frequency of a resonator coupled to a combustor supply passage configured to supply a fluid flow into a combustion chamber of a combustor. The resonator is configured to receive at least a portion of the fluid flow.
These and other features, aspects, and advantages of the present disclosure 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 disclosure 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 disclosure, 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.
Embodiments of the present disclosure are directed toward a system and method for adjusting combustion conditions by adjustably attenuating resonance of a flowing fluid (e.g., fuel, oxidant such as air, steam, inert gas such as nitrogen, combustion gases, or any combination thereof), thereby helping to increase flammability, improve stability of a flame, reduce emissions, and control combustion dynamics. For example, a gas turbine system may include a resonance attenuation system associated with one or more combustors, such as an annular combustor or a plurality of can-annular combustors circumferentially spaced about the rotational axis. The resonance attenuation system may include one or more resonators (e.g., adjustable resonators) associated with each combustor. For example, the resonator may be configured to attenuate or damp resonant frequencies associated with one or more fluid flows (e.g., gas and/or liquid flows), such as fluid flows upstream from, within, or downstream from the combustors. The fluid flows may include supplies of fuel (e.g., liquid and/or gas fuel), oxidant (e.g., oxygen, air, oxygen-rich air, oxygen-reduced air, or any other oxygen-containing mixture), steam, inert gas (e.g., nitrogen), recirculated exhaust gas, or any combination thereof. The fluid flows also may include combustion gases. However, in the following discussion and illustrated embodiments, the resonators are presented in context of oxidant flows (e.g., air flows) upstream, at, or within the combustors. For example, the resonators may be mounted in fluid communication with flows (e.g., oxidant flows) between a liner and flow sleeve of the combustor, through a head end chamber of the combustor, or any combination thereof. The resonators redirect at least a portion of the fluid flow along an attenuation length of the resonator to attenuate resonance frequencies and induce dampening. In certain embodiments, the attenuation length corresponds to a particularly selected frequency.
The resonators may include adjustment mechanisms (e.g., frequency adjusters) configured to adjust one or more parameters of the resonators before, during, and/or after operation of the gas turbine system, thereby tailoring the resonators to resonant frequencies that may change with time and use of the gas turbine system. In certain embodiments, the resonators include quarter wavelength tube (QWT) resonators with an adjustable length. In other embodiments, the resonators may include other types of resonators with adjustments to vary the attenuation frequency of the resonators. For example, the adjustment mechanisms may enable adjustments to the volume (e.g., length) and thus attenuation frequency of the resonators during manufacturing, during operational testing and tuning, during normal operation, during downtime, during servicing or maintenance, or at any other suitable time. For example, the adjustment mechanisms may include manual adjusters and/or powered adjusters, such as automatic or semi-automatic adjusters. The powered adjusters also may be coupled to a control system and a monitoring system, thereby helping to enable automatic adjustments in response to changes in resonant frequencies in the gas turbine system. For example, the adjustment mechanisms may adjust the attenuation lengths based on signals received from sensors monitoring various operating conditions of the combustors. As a result, tuning of the resonators may stabilize emissions, reduce combustion dynamics, and/or stabilize combustion conditions.
With the foregoing in mind,
The combustor 12 may represent a single annular combustor, which extends circumferentially around a rotational axis of the turbine system 10. By further example, the combustor 12 may represent a plurality of combustors (e.g., 2, 3, 4, 5, 6, 7, 8, 9, 10, or more) spaced circumferentially about the rotational axis of the turbine system 10. In certain embodiments, any number of combustors 12 (e.g., 1 to 20 or more) may be provided in the turbine system 10. The resonators 13 of the resonance attenuation system 11 may be coupled to each combustor 12 in a uniform arrangement or a non-uniform arrangement, and the arrangement of resonators 13 may be uniform or non-uniform from one combustor 12 to another. For example, the number, spacing, and attenuation frequency of the resonators 12 may be the same or different from one combustor 12 to another.
The turbine system 10 may use liquid or gaseous fuel, such as natural gas and/or a synthetic gas, to drive the turbine system 10. In the illustrated embodiment, one or more fuel nozzles 16 (e.g., primary fuel nozzles, one or more quaternary injectors or pegs, and/or one or more late lean injectors) intake a supply of fuel 18 (e.g., a liquid fuel supply, a gaseous fuel supply, a liquid/gas mixture fuel supply). Each of the plurality of combustors 12 includes one or more fuel nozzles 16 (e.g., 1, 2, 3, 4, 5, 6, or more). Examples of the fuel 18 include, but are not limited to, hydrocarbon based liquid fuels, such as diesel fuel, jet fuel, gasoline, naphtha, fuel oil, liquefied petroleum gas, and so forth. Moreover, the fuel 18 may include a hydrocarbon based gaseous fuel, such as natural gas, synthetic gas, or the like. In the illustrated embodiment, the turbine system 10 may route the fuel 18 along a fuel path 20 upstream of the fuel nozzles 16. In certain embodiments, the fuel nozzles 16 may include premix fuel nozzles and/or diffusion flame fuel nozzles. For example, the fuel nozzles 16 may premix the fuel 18 with oxidant (e.g., air) to generate a premix flame and/or separately flow the fuel 18 and oxidant into the combustors 12 to generate a diffusion flame.
The fuel 18 combusts with oxidant (e.g., air) in the combustion chamber 17 within each of the combustors 12, thereby creating hot pressurized exhaust gases. The combustors 12 direct the exhaust gases through a turbine or turbine section 22 toward an exhaust outlet 24. The turbine section 22 may include one or more turbine stages (e.g., 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, or more), each having a plurality of turbine blades coupled to a turbine rotor and shaft 26. As the exhaust gases pass through the turbine 22, the gases force the turbine blades to rotate the shaft 26 along a rotational axis of the turbine system 10. As illustrated, the shaft 26 is connected to various components of the turbine system 10, including a compressor or compressor section 28. The compressor section 28 may include one or more compressor stages (e.g., 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, or more), each having a plurality of compressor blades coupled to a compressor rotor and shaft, e.g., shaft 26. As the shaft 26 rotates, the blades within the compressor 28 also rotate, thereby compressing oxidant (e.g., air) from an oxidant intake (e.g., air intake 30) through the compressor 28 and into the fuel nozzles 16 and/or combustors 12. The shaft 26 may also be connected to a load 31, which may be a vehicle or a stationary load, such as an electrical generator in a power plant or a propeller on an aircraft, for example. The load 31 may include any suitable device capable of being powered by the rotational output of the turbine system 10.
In the following discussion, reference may be made to an axial direction or axis 42 (e.g., a longitudinal axis) of the combustor 12, a radial direction or axis 44 that extends radially relative to the axis 42 of the combustor 12, and a circumferential direction or axis 46 that extends circumferentially about the axis 42 of the combustor 12. As discussed in detail below, in certain embodiments, the turbine system 10 includes adjustable resonators 13 (e.g., quarter wavelength tube resonators) positioned on the combustors 12 at various locations, such as indicated by resonators 13A, 13B, 13C, and 13D. For example, the resonators 13 may be coupled to each combustor 12 in fluid communication with a flow path 32 along the combustor 12 (e.g., external to the combustion chamber 17), a head end chamber 33 in the head end section 14, or a combination thereof. For example, the flow path 32 may be in fluid communication with the head end chamber 33 and a compressor discharge chamber from the compressor 28, thereby routing a compressed gas flow (e.g., compressed oxidant such as air) through the flow path 32 along the combustor (e.g., for cooling purposes), through the head end chamber 33, and into the combustion chamber 17 (e.g., through the fuel nozzles 16) for purposes of combustion. In certain embodiments, the fluid flow through the flow path 32 and the head end chamber 33 (e.g., upstream of the fuel nozzles 16) may include or exclude any one or more of an oxidant (e.g., air, oxygen, oxygen-enriched air, oxygen-reduced air, etc.), exhaust gas recirculation (EGR) gas, steam, inert gas (e.g., nitrogen), and/or some amount of fuel (e.g., secondary fuel injection upstream of fuel nozzles 16). In certain embodiments, the flow path 32 may be disposed circumferentially about at least one wall defining a boundary of the combustor 12, such as a first wall 34 (e.g., a combustion liner) disposed circumferentially about the combustion chamber 17 and/or at least a portion of the head end chamber 33. The flow path 32 also may be bounded by a second wall 35 (e.g., a flow sleeve) disposed circumferentially about the first wall 34. The second wall 35 also may be disposed circumferentially about the head end chamber 33 of the head end section 14.
In the illustrated embodiment, the resonators 13 (e.g., 13A, 13B, 13C, and 13D) are coupled to at least one of the walls defining the boundary of the combustor 12. For example, the resonator 13A is coupled to the wall 35 disposed about the head end chamber 33, the resonator 13B is coupled to the wall 35 disposed about the head end chamber 33 and/or flow path 35 at a transition region between the combustor section 15 and the head end section 14, and the resonators 13C and 13D are coupled to the wall 35 disposed the flow path 35, the first wall 34, and the combustion chamber 17 of the combustor section 15. Furthermore, as illustrated in
The turbine system 10 also may have a variety of monitoring and control equipment associated with the resonators 13 of the resonance attenuation system 11. In the illustrated embodiment, the turbine system 10 may include one or more sensors 48 to monitor the combustion process, oxidant flow, fuel flow, turbine speed, compressor feed, combustor temperature, combustion dynamics, acoustic noise, or a variety of other parameters of operation of the turbine system 10. For example, one or more vibration sensors 50 may be positioned on the combustors 12 between the one or more resonators 13. The vibration sensors 50 may detect vibrations within the combustors 12. For example, vibration above a set value level may provide an indication that tuning the resonators 13 may provide improved combustion characteristics. As will be described below, in certain embodiments, the resonators 13 may be adjustable to enable tuning before, during, and/or after operation (e.g., during maintenance) of the gas turbine system 10.
The sensors 48, 50 may be configured to send signals to a controller 52 (e.g., an electronic controller). In the illustrated embodiment, the controller 52 includes a memory 54 and a processor 56. The memory 54 may be a mass storage device, a FLASH memory device, removable memory, or any other non-transitory computer-readable medium (e.g., not only a signal). Additionally and/or alternatively, the instructions may be stored in an additional suitable article of manufacture that includes at least one tangible, non-transitory computer-readable medium that at least collectively stores these instructions or routines in a manner similar to the memory 54 as described above. The controller 52 may be configured to receive signals from the sensors 48, 50 indicative of operating parameters of the gas turbine system 10 (e.g., temperature, pressure, fuel/air ratio, acoustics, vibration). The signals may be evaluated by the processor 56 utilizing instructions stored on the memory 54. Additionally, the controller 52 may send signals to various components of the gas turbine system 10 (e.g., the resonators 13, the air intake 30, the combustor 12, etc.) to adjust operating conditions of the gas turbine system 10 (e.g., including adjustments to the resonators 13) based on the signals received from the sensors 48, 50.
During operation, the resonators 13 are configured to receive a portion of the air flow from the air intake 30 and direct the portion of the air flow into the body of the resonators 13. For example, in the illustrated embodiment, each resonator 13 includes a resonator tube 60 and an adjustment mechanism 62 (e.g., frequency adjuster) to vary a resonator chamber 64 in the tube 60, thereby adjusting an attenuation frequency of the resonator 13. The adjustment mechanism 62 may include a plunger or piston 66 disposed in the tube 60, a drive shaft or rod 68 coupled to the piston 66, and an actuator 70 coupled to the rod 68. Each actuator 70 is in turn coupled to, and controlled by, the controller 52. The tube 60 may be a hollow cylindrical tube defining a cylinder, while the piston 66 may be a cylindrical piston. However, the tube 60 and piston 66 may have other shapes. The piston 66 also may include one or more seals (e.g., annular seal rings) to seal against an inner wall of the tube 60. The actuator 70 is configured to drive movement of the rod 68, which in turn drives movement of the piston 66 in the tube 60. The actuator 70 may include a manual actuator, such as a hand wheel, a crank lever, a tool interface (e.g., a bolt head that interfaces with a wrench), or any other suitable manual actuation feature. The actuator 70 also may include a powered actuator, such as an electric drive or motor, a pneumatic drive, a hydraulic drive, or any combination thereof. The actuator 70 (e.g., manual, powered, or both) may cause rotation and/or axial movement of the rod 68, which in turn causes axial movement of the piston 66 to vary an attenuation length 71 of the resonator chamber 64 within the tube 60 between the piston 66 and an open inner end portion along the wall 35 of the combustor 12.
As illustrated, the attenuation length 71 of the resonator chamber 64 varies from one resonator 13 to another about the circumference 58 of the wall 35 of the combustor 12. The attenuation length 71 of the resonator chamber 64 of each of the resonators 13 is particularly selected to attenuate (e.g., tune) a particular frequency or range of frequencies of the portion of the air flow from the air intake 30. Accordingly, as shown in the illustrated embodiment, the resonators 13 may have different attenuation lengths to attenuate different frequencies. However, in the illustrated embodiment, an overall length and diameter of each tube 60 may be constant (or uniform) among all of the resonators 13, thereby enabling simplified construction of the resonator 13 while still enabling attenuation of different frequencies for the combustor 12. As a result, similar parts may be utilized to manufacture and service the resonators 13. Moreover, the resonators 13 may be utilized over a larger range of frequencies due to their adjustability, thereby increasing their utility as conditions and resonance frequencies change in the gas turbine system 10.
In the illustrated embodiment, the resonator 13 has a body length 76, e.g., a total length of the tube 60, extending from a first axial end 78 (e.g., end opening or face) to a second axial end 80 (e.g., end opening, sealed end, or face) along a resonator longitudinal axis 82. In the illustrated embodiment, the resonator longitudinal axis 82 is perpendicular or substantially perpendicular (e.g., 90 degrees plus or minus 1, 2, 3, 4, 5, 6, 7, 8, 9, or 10 degrees) relative to the longitudinal axis 42 of the combustor 12. However, in other embodiments, the resonator longitudinal axis 82 may be positioned crosswise at an angle (e.g., 10 to 80, 20 to 70, 30 to 60, or 40 to 50 degrees) relative to the longitudinal axis 42. In operation, the first axial end 78 (e.g., end opening) of the tube 60 receives a gas flow 84 (e.g., oxidant such as air, EGR gas, steam, inert gas such as nitrogen, gaseous fuel, fuel/air mixtures, etc.) from a fluid supply directed to the combustor 12 and directs the gas flow 84 into the resonator 13. In certain embodiments, the gas flow 84 excludes combustion gases directly from the combustion chamber 17, but may include any fluid flows directed into the combustion chamber 17 such as through the head end section 14. In other embodiments, the gas flow 84 may include the combustion gases directly from the combustion chamber 17. However, in the illustrated embodiment, the gas flow 84 may include at least a substantial amount (e.g., greater than 50, 60, 70, 80, 90, or 95 percent by volume) oxidant flow from the air intake 30, e.g., after compression by the compressor 28. As mentioned above, the resonator 13 is configured to reduce resonance in the combustion system by attenuating any resonance frequencies in the gas flow 84. In the illustrated embodiment, the frequency at which the resonator 13 attenuates the gas flow 84 is directly related to the attenuation length 71 of the resonator 13. The attenuation length 71 represents the distance that the gas flow 84 may travel through the resonator 13 before being reflected back toward the combustor 12. In other words, the attenuate length 86 is the distance between the first axial end 78 and the piston 66 in the tube 60 of the resonator 13. In certain embodiments, the attenuation length 71 may be varied continuously and/or incrementally (e.g., in incremental steps) between 0 and 100, 5 and 95, 10 and 90, 15 and 85, and 20 and 80 percent of the body length 76. For example, the attenuation length 71 may be varied in incremental steps of approximately 1, 2, 3, 4, 5, 6, 7, 8, 9, or 10 percent of the total body length 76 of the tube 60. As will be described below, the attenuation length 71 of the resonator 13 may be adjusted to enable attenuation over a range of frequencies.
Because it may be desirable to attenuate a range of frequencies in the combustor 12, the adjustment mechanism 62 (e.g., piston 66, rod 68, and actuator 70) is configured to adjust the attenuation length 71 of the resonator 13. In the illustrated embodiment, the adjustment mechanism 62 includes the piston 66, the rod 68, and the actuator 70. For example, the actuator 70 may include a drive or motor (e.g., electric, pneumatic, and/or hydraulic) that drives the rod 68 to change an axial position of the piston 66 along the resonator longitudinal axis 82. As a result, the piston 66 in the tube 60 of the resonator 13 has a different axial position, thereby adjusting the attenuation length 71. In the illustrated embodiment, the piston 66 includes seals 94 (e.g., annular seal rings) configured to fluidly isolate an active section 96 (e.g., resonator chamber 64) from an inactive section 98 (e.g., opposing chamber 99). The active section 96 may receive the gas flow 84, while the inactive section 98 may not receive the gas flow 84 due to blockage provided by the piston 66 and sealing provided by the seals 94.
The adjustment mechanism 62 may adjust the attenuation length 71, and therefore respective volumes of the active section 96 and the inactive section 98, via the actuator 70 driving axial motion of the piston 66 along the resonator longitudinal axis 82. That is, the adjustment mechanism 62 may drive movement of the piston 66 in a first direction 100 radially inward toward the longitudinal axis 42 of the combustor 12 or in a second direction 102 radially outward away from the longitudinal axis 42 of the combustor 12. For example, the actuator 70 may cause axial translation (i.e., axial movement without rotation) of the rod 68, thereby driving axial translation of the piston 66 in the tube 60. By further example, the actuator may cause rotation (with or without axial movement) of the rod 68, thereby driving axial movement of the piston 66 in the tube 60 (e.g., by threading the rod 68 through a threaded receptacle in the piston 66 while the piston 66 is blocked from rotating via an axial guide feature). By further example, the actuator 70 may drive rotation of the piston 66 to engage with corresponding threads, ridges, or gear teeth on an interior surface 104 of the wall 72, thereby causing the piston 66 to threadingly rotate and axially move along the wall 72 to change its axial position. Regardless of the specific configuration of the actuation mechanism 62, the piston 66 moves in the tube 60 to vary the attenuation length 71, thereby adjusting the resonator 13 to attenuate different frequencies without replacing the resonator 13. Moreover, the adjustment mechanism 62 may adjust the attenuation length 71 (e.g., via manual adjustments and/or control by the controller 52) during operation of the gas turbine system 10, thereby reducing system downtimes and enabling real-time or near real-time tuning of the gas turbine system 10.
In the illustrated embodiment, the resonator 13 includes a plate 106 at the first axial end 78. The plate 106 may include perforations 108 (e.g., orifices, openings, slots, etc.) to restrict and/or throttle the gas flow 84 entering the active section 96 of the resonator 13. For example, the plate 106 and the perforations 108 may decrease the cross-sectional area of openings through the first axial end 78, thereby reducing the gas flow 84 entering the active section 96. Moreover, the perforations 108 in the plate 106 enable viscous damping of the gas flow 84 entering the resonator 13 by forcing the gas flow 84 through the perforations 108 before entering the resonator 13, resulting in a loss of energy to the gas flow 84. For example, the pressure of the gas flow 84 may decrease as the gas flow 84 enters the resonator 13 due to the pressure drop across the plate 106.
For example, the gear set 120 may be a rack and pinion gear set, wherein the first gear 122 is a linear gear bar or rack and the second gear 124 is a circular gear or pinion. Accordingly, as the actuator 70 (e.g., a motor or drive 130) drives rotation of the pinion 124, gear teeth 126 of the pinion 124 engage with gear teeth (or threads) 128 of the rack 122 to transfer rotational movement of the pinion 124 into axial movement of the rack 122 and thus the piston 66.
By further example, the gear set 120 may be a worm gear set, wherein the first gear 122 is a worm (e.g., an elongated threaded worm shaft 68) and the second gear 124 is a worm gear. Accordingly, as the actuator 70 (e.g., a motor or drive 130) drives rotation of the worm gear 124, gear teeth 126 of the worm 124 engage with gear teeth (or threads) 128 of the worm 122 to transfer rotational movement of the worm gear 124 into movement of the worm 122 and thus the piston 66. For example, the worm gear 124 may drive rotation of the worm 122, which then rotates threads within a threaded bore in the piston 66 to cause axial movement of the piston 66, or rotates the piston 66 along a threaded interface along the interior surface 104, or another suitable arrangement. By further example, the worm gear 124 may drive axial movement of the worm 122, thereby driving axial movement of the piston 66.
As a result, the piston 66 may be moved in first and second directions 100, 102 in response to actuation of the gear set 120 by the actuator 70 (e.g., drive 130). Similar to the discussion above, the drive 130 may include an electric, pneumatic, and/or hydraulic drive or motor. As shown, the gear 124 may be coupled to the wall 72 of the resonator 13. However, in other embodiments, the gear 124 may include a separate housing coupled to the sidewall 74 of the combustor 12. As described above, the controller 52 may send a signal to the adjustment mechanism 62 instructing the adjustment mechanism 62 to change the attenuation length 71.
As described in detail above, the gas turbine system 10 may include resonators 13 positioned on the combustors 12 to attenuate frequencies in the gas flow 84 traveling through the combustors 12. For example, the resonators 13 may be positioned circumferentially along the circumferential axis 46 of the combustors 12 and/or axially along the axial length 36 of the combustors 12. In certain embodiments, the resonators 13 may be configured to attenuate the frequency of the gas flow 84 related to the attenuation length 71 of the resonators 13. For example, in certain embodiments, the resonators 13 may include the piston 66 configured to separate the resonators 13 into active sections 96 and inactive sections 98. The active sections 96 receive the gas flow 84, and the inactive sections 98 do not. Moreover, the piston 66 is movable along the resonator longitudinal axis 82 to enable adjustment of the attenuation length 71 before, during, and/or after operation of the combustors 12. For example, the resonators 13 may include the adjustment mechanisms 70 configured to drive movement of the piston 66 within the resonators 13, and thereby adjust the attenuation length 71. Furthermore, the adjustment mechanisms 70 may receive instructions from the controller 52 to set a desired attenuation length. Moreover, the attenuation length 71 may be adjusted based on operating parameters received from the sensors 48, 50 distributed throughout the gas turbine system 10. Accordingly, the combustors 12 may be tuned before, during, and/or after operation to stabilize emissions, reduce combustion dynamics, stabilize combustion conditions, or the like.
This written description uses examples to disclose various embodiments of the disclosure, including the best mode, and also to enable any person skilled in the art to practice the disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the disclosure 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.
