| Counterflow injection mechanism having coaxial fuel-air passages -> Monitor Keywords |
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Counterflow injection mechanism having coaxial fuel-air passagesRelated Patent Categories: Power Plants, Combustion Products Used As Motive Fluid, ProcessCounterflow injection mechanism having coaxial fuel-air passages description/claimsThe Patent Description & Claims data below is from USPTO Patent Application 20070151251, Counterflow injection mechanism having coaxial fuel-air passages. Brief Patent Description - Full Patent Description - Patent Application Claims
BACKGROUND [0001] This section is intended to introduce the reader to various aspects of art that may be related to aspects of the present invention, which are described and/or claimed below. This discussion is believed to be helpful in providing the reader with background information to facilitate a better understanding of the various aspects of the present invention. Accordingly, it should be understood that these statements are to be read in this light, and not as admissions of prior art. [0002] Combustion engines, such as gas turbine engines, produce a variety of pollutant emissions. For example, pollutant emissions generally include carbon oxides (COx), nitrogen oxides (NOx), sulfur oxides (SOx), and particulate matter (PM). These pollutant emissions are highly regulated in the United States and elsewhere. NOx emissions from a gas turbine engine can be reduced by premixing fuel and air. Unfortunately, premixing can result in unstable flames that are difficult to anchor, and the best premixed systems today cannot reach the NOx emission targets. Another approach is selective catalytic reduction (SCR) of NOx through ammonia injection. Unfortunately, the SCR approach is relatively expensive. [0003] Accordingly, an improved technique is needed to reduce pollutant emissions, such as NOx emissions, from a gas turbine combustor. BRIEF DESCRIPTION [0004] Certain aspects commensurate in scope with the originally claimed invention are set forth below. It should be understood that these aspects are presented merely to provide the reader with a brief summary of certain forms the invention might take and that these aspects are not intended to limit the scope of the invention. Indeed, the invention may encompass a variety of aspects that may not be set forth below. [0005] In accordance with certain embodiments, a system includes a fuel-air injection mechanism having coaxial fuel and air passages leading to fuel and air injection openings. The fuel and air injection openings are configured to reside at an off-axis position of a gas turbine combustor, and the fuel and air injection openings are configured to orient in an injection direction not aligned with a flow direction through the gas turbine combustor to a turbine. [0006] In accordance with other embodiments, a system includes a gas turbine combustor having a combustion liner with a generally lengthwise flow axis extending from a stagnation zone to a turbine nozzle. The gas turbine combustor also includes a counterflow fuel-air injector disposed in the combustion liner at one or more intermediate positions between the stagnation zone and the turbine nozzle. The counterflow fuel-air injector includes coaxial fuel and air passages extending to fuel and air injection openings not aligned with a flow direction from the stagnation zone to the turbine nozzle. [0007] In accordance with further embodiments, a method includes coaxially flowing fuel and air to a counterflow fuel-air injector oriented in a generally counterflow direction relative to a generally lengthwise flow axis from a stagnation zone to a turbine nozzle of a gas turbine combustor. [0008] Various refinements of the features noted above exist in relation to the various aspects of the present invention. Further features may also be incorporated in these various aspects as well. These refinements and additional features may exist individually or in any combination. For instance, various features discussed below in relation to one or more of the illustrated embodiments may be incorporated into any of the above-described aspects of the present invention alone or in any combination. Again, the brief summary presented above is intended only to familiarize the reader with certain aspects and contexts of the present invention without limitation to the claimed subject matter. DRAWINGS [0009] 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: [0010] FIG. 1 is a block diagram of an exemplary system having a gas turbine engine coupled to a load in accordance with certain embodiments of the present technique; [0011] FIG. 2 is a lengthwise diagrammatical view of an exemplary combustor of the gas turbine engine as illustrated in FIG. 1, further illustrating a counterflow injection mechanism having a plurality of fuel-air injection lobes arranged circumferentially along a solid inner casing of the combustor in accordance with certain embodiments of the present technique; [0012] FIG. 3 is a crosswise diagrammatical view of an embodiment of the combustor as illustrated in FIG. 2, further illustrating the plurality of fuel-air injection lobes disposed at multiple radial positions along the circumference of the solid inner casing; [0013] FIG. 4 is a lengthwise diagrammatical view of an alternative embodiment of the combustor as illustrated in FIGS. 1 and 2, further illustrating a counterflow injection mechanism having a radial array of flush fuel-air injection regions arranged circumferentially along a solid inner casing of the combustor; [0014] FIG. 5 is a lengthwise diagrammatical view of an alternative embodiment of the combustor as illustrated in FIGS. 1 and 2, further illustrating a counterflow injection mechanism having a radial array of inwardly cantilevered fuel-air injection members arranged circumferentially along a solid inner casing of the combustor, wherein each of the inwardly cantilevered fuel-air injection members has a plurality of coaxial fuel-air ports oriented generally lengthwise and counterflow relative to a lengthwise flow axis of the combustor; [0015] FIG. 6 is a crosswise diagrammatical view of an embodiment of the combustor as illustrated in FIG. 5, further illustrating the radial array of inwardly cantilevered fuel-air injection members disposed at multiple radial positions along the circumference of the solid inner casing; [0016] FIG. 7 is a cross-sectional view of an embodiment of one of the inwardly cantilevered fuel-air injection members as illustrated in FIG. 5, further illustrating coaxial flow of fuel and air in a direction generally lengthwise and counterflow relative to a lengthwise flow axis of the combustor; [0017] FIG. 8 is a lengthwise diagrammatical view of an alternative embodiment of the combustor as illustrated in FIG. 5, wherein each of the inwardly cantilevered fuel-air injection members further includes a plurality of coaxial fuel-air port oriented generally crosswise and counterflow relative to the lengthwise flow axis of the combustor; [0018] FIG. 9 is a crosswise diagrammatical view of an embodiment of the combustor as illustrated in FIG. 8, further illustrating the radial array of inwardly cantilevered fuel-air injection members disposed at multiple radial positions along the circumference of the solid inner casing; [0019] FIG. 10 is a cross-sectional view of an embodiment of one of the inwardly cantilevered fuel-air injection members as illustrated in FIG. 8, further illustrating coaxial flow of fuel and air in a direction generally lengthwise and counterflow relative to a lengthwise flow axis of the combustor and, also, illustrating coaxial flow of fuel and air in two opposite directions generally crosswise and counterflow relative to the lengthwise flow axis of the combustor; [0020] FIG. 11 is a lengthwise diagrammatical view of another embodiment of the combustor as illustrated in FIG. 1, further illustrating a counterflow injection mechanism having a single inwardly cantilevered fuel-air injection member disposed on a solid inner casing of the combustor at or near a turbine nozzle, wherein the inwardly cantilevered fuel-air injection member has a plurality of coaxial fuel-air ports oriented generally lengthwise and counterflow relative to a lengthwise flow axis of the combustor; [0021] FIG. 12 is a diagram of an exemplary fuel-air injector having coaxial fuel and air flows in the same lengthwise or axial direction in accordance with certain embodiments of the present technique; Continue reading about Counterflow injection mechanism having coaxial fuel-air passages... Full patent description for Counterflow injection mechanism having coaxial fuel-air passages Brief Patent Description - Full Patent Description - Patent Application Claims Click on the above for other options relating to this Counterflow injection mechanism having coaxial fuel-air passages patent application. ###  How KEYWORD MONITOR works... a FREE service from FreshPatents1. Sign up (takes 30 seconds). 2. Fill in the keywords to be monitored. 3. Each week you receive an email with patent applications related to your keywords. Start now! - Receive info on patent apps like Counterflow injection mechanism having coaxial fuel-air passages or other areas of interest. ### Previous Patent Application: Heat shield Next Patent Application: Gas turbine combustor having counterflow injection mechanism Industry Class: Power plants ### FreshPatents.com Support Thank you for viewing the Counterflow injection mechanism having coaxial fuel-air passages patent info. 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