Patent Application
20140123650
The present application and the resultant patent relate generally to gas turbine engines and more particularly relate to a micro-mixer nozzle with simplified components for ease of manufacturing, ease of configuration, and overall ease of operation.
Operational efficiency and overall output of a gas turbine engine generally increases as the temperature of the hot combustion gas stream increases. High combustion gas stream temperatures, however, may produce high levels of nitrogen oxides and other types of regulated emissions. A balancing act thus exists between operating a gas turbine engine in an efficient temperature range while also ensuring that the output of nitrogen oxides and other types of regulated emissions remain below mandated levels.
Lower emission levels of nitrogen oxides and the like may be promoted by providing for good mixing of the fuel stream and the air stream prior to combustion. Such premixing tends to reduce combustion temperatures and the output of nitrogen oxides. One method of providing such good mixing is through the use of a micro-mixer combustion nozzle wherein the fuel and the air are mixed in a number of micro-mixer tubes within a plenum before combustion.
Although current micro-mixer nozzle designs provide improved combustion performance, manufacturing such a micro-mixer nozzle may be challenging. As described above, the micro-mixer nozzle generally includes a number of small tubes with a number of small holes therein. Such components may require tight tolerances and hence may be time consuming to manufacture. Moreover, overall flow distribution may be difficult to control therein.
There is such a desire for an improved micro-mixer combustion nozzle design. Such an improved micro-mixer combustion nozzle design may promote good fuel/air mixing while providing ease of manufacturing, configuration, and use with lower cost components and techniques.
The present application and the resultant patent thus provide a micro-mixer combustion nozzle for mixing a flow of fuel and a flow of air in a gas turbine engine. The micro-mixer combustion nozzle may include a fuel plate with a number of fuel plate apertures and a fuel plate passage in communication with the flow of fuel and an air plate with a number of air plate apertures and an air plate passage in communication with the flow of air. The fuel plate passage and the air plate passage may align to mix in part the flow of fuel and the flow of air.
The present application and the resultant patent further provide a method mixing a flow of fuel and a flow of air in a combustion nozzle. The method may include the steps of aligning at least in part one or more gas plate passages on a gas plate with one or more air plate passages on an air plate, flowing the fuel through a number of fuel plate apertures into the one or more gas plate passages, flowing the air into the one or more air plate passages, mixing the flow of fuel and the flow of air, and flowing the fuel-air mixture through a number of air plate apertures.
The present application and the resultant patent further provide a micro-mixer combustion nozzle for mixing a flow of fuel and a flow of air in a gas turbine engine. The micro-mixer combustion nozzle may include a fuel plate with a number of fuel plate apertures and a number of fuel plate passages in communication with the flow of fuel and an air plate with a number of air plate apertures and a number of air plate passages in communication with the flow of air. The fuel plate passages and the air plate passages may align in part to mix the flow of fuel and the flow of air into a fuel-air flow therethrough.
These and other features and improvements of the present application and the resultant patent will become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the several drawings and the appended claims.
Referring now to the drawings, in which like numerals refer to like elements throughout the several views,
The gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels. The gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, N.Y., including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like. The gas turbine engine 10 may have different configurations and may use other types of components. Other types of gas turbine engines also may be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
The combustion nozzle 100 may include a fuel plate 120. The fuel plate 120 may be in communication with the flow of fuel 30. By use of the term “plate,” we are simply referring to the downstream end of the fuel passage. The fuel plate 120 may be combined with many other overall designs. The fuel plate 120 may have as first side 130 and a second side 140. The fuel plate 120 may have as number of fuel plate apertures 150 extending therethrough from the first side 130 to the second side 140. The fuel plate apertures 150 may have any suitable size, shape, or configuration. Fuel apertures 150 of differing sizes and shapes may be used herein together. Any number of the fuel plate apertures 150 may be used herein.
The fuel pate 120 may have a number of fuel plate passages 160 formed therein about the second side 140. The fuel plate passages 160 may be grooved into the second side 140 of the fuel plate 140 or otherwise formed therein. The fuel plate apertures 150 may align with the fuel plate passages 160. In this example, the fuel plate passages 160 take the form of a number of concentric circles 170. The concentric circles 170 may be continuous and/or intermittent. The fuel plate passages 160 may have any suitable size, shape, or configuration. Any number of the fuel plate passages 160 may be used herein. Fuel plate passages 160 of differing sizes and shapes may be used herein together. Other components and other configurations may be used herein.
The combustion nozzle 100 also may include an air plate 180. The air plate 180 may be in communication with the flow of air 20 from the compressor 150 or elsewhere. By use of the term “plate,” we are simply referring to the downstream end of the air passage. The air plate 180 may be combined with many other overall designs. The air plate 180 may surround the fuel plate 120 in whole or in part or the respective positions may be reversed. The air plate 180 may include a first side 190 and a second side 200. The second side 140 of the fuel plate 120 may face the first side 190 of the air plate 180. The air plate 180 may have a number of air plate apertures 210 extending therethrough from the first side 190 to the second side 200. The air plate apertures 210 may have any suitable size, shape, or configuration. Any number of the air plate apertures 210 may be used. The air plate apertures 210 generally may not align directly with the fuel plate apertures 150 (although such may be used) but may be offset therefrom. Moreover, differing numbers of air plate apertures 210 and fuel plate apertures 150 may be used herein. Air plate apertures 210 of differing sizes and shapes may be used herein together.
The air plate 180 also may have a number of air plate passages 220. The air plate passages 220 may have any suitable size, shape, or configuration. Any number of the air plate passages 220 may be used herein. The air plate passages 220 may be formed in the first side 190 of the air plate 180. The air plate passages 220 may be grooved into the first side 190 of the air plate 180 or otherwise formed therein. In this example, a number of linear air plate passages 230 may be used herein. Moreover, one or more circular air plate passage segments 240 also may be used. The air plate apertures 210 may be positioned within the linear air plate passages 230 and the circular air plate passage segments 240 and elsewhere. As is shown, air plate passages 220 of differing size and shape may be used herein together. Other components and other configurations may be used herein.
In use, the flow of fuel 30 extends to the fuel plate 120 and passes through the fuel plate apertures 150 and into the fuel plate passages 160 on the second side 140 thereof The flow of fuel 30 may be accelerated as it passes through the small fuel plate apertures 150. The flow of air 20 extends to the air plate 180 and flows through the air plate passages 220. The intertwining of the fuel plate passages 160 and the air plate passages 220 forms a kind of a mixing tube 250 to promote good fuel-air mixing therein in combination with the accelerated flow of fuel 30. A fuel-air mixture 260 thus exits the air plate apertures 210 for combustion in the combustion zone 60. Other components and other configurations also may be used herein.
The size, shape, and configuration of the various apertures and passages may be varied herein. For example,
Varying the size of the air plate apertures 210 may be used to control flame quenching for the fuel-air mixture 260 passing therethrough. The size of the fuel plate passages 160 and the air plate passages 220 may be varied to control the pressure drop therethrough. Overall tuning of the combustion nozzle 100 also may be provided by altering the sizes and shape of the plates 120, 180, the apertures 150, 210, and the passages 160, 220. The respective apertures 150, 210 and the passages 160, 220 also may be clocked for fine tuning. The respective positions of the fuel plates 220 and the air plate 180 also may be reversed. Different types of fillers may be added to the air passages 220 to maintain the quenching capability to control flame holding. Such fillers may be a catalyst to enhance the chemical reaction therein while inhibiting flame holding. Moreover, layers of the air plates 180 may be used to maintain a quenching distance and increase the flow area of the passages 220. Other components and other configurations may be used herein.
The combustion nozzle 100 described herein thus may provide for ease of manufacture in that the components may be substantially modular. Moreover, the combustion nozzle 100 may be easy to reconfigure. These manufacturing benefits are combined with a number of operation advantages including a very high flame holding limit, low emissions, a short flame for fast combustion, and a lower pressure drop. Specifically, the combustion nozzle 100 provides enhanced control of air and fuel distribution.
It should be apparent that the foregoing relates only to certain embodiments of the present application and the resultant patent. Numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof.
