• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The present invention provides an injection system (50) for mixed fuel with carrier gas, for example an oxidizing or inert gas, on a surface of a turbine guide device (54) between a combustion chamber and a turbine stage. For this purpose, a mixing chamber (70) let into the turbine guide device (54) encloses a mixing zone (52), into which a first (60) and a second (62) outlet open. A first injection channel delivers carrier gas through the first outlet (60), at least one second injection channel delivers fuel through the second outlet (62). Alternatively, the first outlet (60) is oriented opposite to the second outlet (62), or the at least one second injection channel is arranged within the first injection channel.
    公开号:CH710507B1
    申请号:CH01789/15
    申请日:2015-12-08
    公开日:2020-06-30
    发明作者:Kevin Widener Stanley；Berkley Davis Lewis Jr；Thomas Foster Gregory；Marie Graham Kaitlin；Venkataraman Krishnakumar
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    BACKGROUND OF THE INVENTION
    The disclosure relates generally to fuel and gas injection systems. More particularly, the disclosure relates to injection systems for introducing fuel and a carrier gas into components of a power generation system. The components can e.g. Combustion chambers or afterburner, such as those used in gas turbine systems or other types of turbomachinery.
    Turbine systems (also known as turbomachinery) can use energy e.g. generate for electrical generators. A working fluid, such as hot gas or steam, can flow over sets of turbine blades connected to a rotor of the turbine system. The force of the working fluid on the blades causes the blades (and the connected body of the rotor) to rotate. In many cases, the rotor body is mechanically connected to the drive shaft of a dynamoelectric machine, such as an electrical generator. In this sense, initiating rotation of the turbine system rotor can also drive the drive shaft in the electrical generator and an electrical current to produce a certain output.
    To generate the working fluid in a combustion-based turbomachine, a fuel or reactant can burn in the presence of air to generate a hot gas stream for the transfer of work, i.e., to drive the blades of the turbine system. Some combustors use the auto-ignition principle to burn the fuel in the presence of air in the combustor. Autoignition refers to the mixing of fuel and air in a high temperature reaction chamber, where fuel and air can burn within the chamber without the need for a flame to activate the reaction. In conventional systems, the fuel is added to a flow of air from a turbomachine in a mixing duct that is spaced a predetermined distance from the chamber. Fuel and air can mix in the mixing channel before reaching the chamber where the auto-ignition combustion reactions take place.
    BRIEF DESCRIPTION OF THE INVENTION
    The present disclosure relates generally to fuel and gas injection systems. In particular, injection systems in accordance with the present disclosure provide systems for mixing fuel, air, and / or inert gases in different ways and to generate different amounts of residence times, both for mixing before oxygen and fuel combustion and for complete reactions before the mixture leaves the combustion chamber.
    The invention claimed in accordance with the present disclosure provides, on the one hand, an injection system, comprising: a mixing zone, which is embedded in a surface of a turbine guide device and is positioned between a first outlet and a second outlet, the turbine guide device being a combustion chamber of a power generation system from a turbine stage of the power generation system, wherein the first outlet is oriented substantially opposite to the second outlet; a first injection port for delivering a carrier gas to the mixing zone through the first outlet; a second injection port for delivering fuel to the mixing zone through a second outlet; wherein the carrier gas and the fuel mix within the mixing zone after leaving the first injection channel and the second injection channel.
    [0006] In any embodiment of the injection system, it may be advantageous that the injection system further include: an outlet passage that extends through the mixing chamber between the mixing zone and an exterior of the mixing chamber.
    In any exemplary embodiment of the injection system, it may be advantageous that the contour of the outlet passage prevents fluid communication from a burned gas outside the turbine guide into the mixing chamber.
    In any embodiment of the injection system, it may be advantageous for the combustion chamber to have an afterburner of the power generation system and for the surface of the turbine baffle to be exposed to a flow of fluid through the afterburner, the power generation system having a gas turbine system.
    In any embodiment of the injection system, it may be advantageous that the first injection channel and / or the second injection channel is formed from a thermally conductive material, so that a respective fluid in the first injection channel or the second injection channel heat from the surface of the turbine guide absorbed.
    In any embodiment of the injection system, it may be advantageous that the injection system also includes a manifold that is embedded in the turbine baffle, the manifold being in fluid communication with the first injection channel and a plurality of carrier gas supply channels.
    [0011] The invention claimed herein, according to the present disclosure, otherwise provides an injection system, comprising: at least a first injection channel for delivering fuel to a surface of a turbine guide through a first outlet, the turbine guide being a combustion chamber of a power generation system from a turbine stage of the power generation system separates; a second injection channel for supplying a carrier gas to the surface of the turbine guide device through a second outlet, the at least one first injection channel being arranged within the second injection channel; and at least one barrier arranged between the second injection channel and the at least one first injection channel, the at least one barrier separating the fuel in the at least one first injection channel from the carrier gas of the second injection channel.
    In any embodiment of the injection system, it can be advantageous that the at least one second injection channel has a plurality of second injection channels and each of the plurality of second injection channels is arranged within the first injection channel.
    [0013] In any embodiment of the injection system, it may be advantageous for the at least one barrier to have a plurality of barriers, each of the plurality of barriers being arranged between the first injection channel and a respective one of the plurality of second injection channels, and each of the plurality of barriers separates the fuel from each of the plurality of second injection channels from the carrier gas of the first injection channel.
    In any embodiment of the injection system, it may be advantageous that the first injection channel is formed from a thermally conductive material, so that a respective fluid in the first injection channel or the second injection channel heat from the surface of the turbine guide device through the thermally conductive material absorbed.
    BRIEF DESCRIPTION OF THE DRAWINGS
    [0015] These and other features of this invention will be more readily understood from the following detailed description of the various aspects of the invention, taken in conjunction with the accompanying drawings, which illustrate various embodiments of the invention, in which:
    Figure 1 is a schematic view of a gas turbine system having an afterburner.
    Figures 2-4 are partial perspective views of an injection system for fuel and carrier gas according to an embodiment of the present disclosure.
    Figures 5-6 are partial perspective views of another fuel and carrier gas injection system according to another embodiment of the present disclosure.
    Figures 7-8 are partial perspective views of yet another fuel and gas injection system according to another embodiment of the present disclosure.
    Figure 9 is a cross-sectional view of a turbine baffle between a combustor and a turbine section in accordance with embodiments of the present disclosure.
    [0021] It is noted that the drawings of the invention are not necessarily to scale. The drawings are intended to illustrate only typical aspects of the invention and should therefore not be considered to limit the scope of the invention. In the drawings, like numbers represent like elements within the drawings.
    DETAILED DESCRIPTION OF THE INVENTION
    [0022] As discussed herein, aspects of the invention generally relate to injection systems for a carrier gas and a combustible fuel in a power generation system. In an exemplary embodiment, injection systems in accordance with the present disclosure may inject fuel and carrier gas into a reaction chamber of the gas turbine system. One type of reaction chamber in a gas turbine system may include an afterburner reaction chamber. The present disclosure describes various injection systems for injecting the fuel and carrier gas, which may be positioned at one or more specific locations on the turbine baffle that separates a reaction chamber from a turbine stage. The use of different relative positions and orientations of a first outlet for one medium and a second outlet for another medium can enable different types of post-injection mixture within the injection system and / or the reaction chamber.
    Terms related to space, such as "inside", "outside", "below", "below", "lower", "above", "upper", "inlet", "outlet", and the like can used herein to simplify the description to describe an element or feature relationship to another element or to other elements or another feature or features, as illustrated in the figures. Terms related to space may be intended to encompass different orientations of the device in use or operation in addition to the orientation illustrated in the figures. For example, if a device is turned over in the figures, elements described as “below” or “below” other elements or features would then be “above” the other elements or features aligned. Therefore, the term "under" can include both an orientation above and below it. The facility may also be oriented differently (rotated 90 degrees or with other orientations) and the descriptions used herein relating to the space interpreted accordingly.
    Referring to Figure 1, a conventional power generation system 10 is shown in the form of a turbo machine. Embodiments of the present disclosure can be adapted for use with the power generation system 10 and / or can be integrated into components thereof. Power generation system 10 is shown by way of example as a combustion-based turbomachine arrangement, although embodiments of the present disclosure may also be adapted for use with other types of combustion systems where applicable. In the embodiment of combustion-based turbomachines, a combustion chamber 12, which is connected to a fuel supply 14, is typically arranged between a compressor 16 and a high-pressure (HP) gas turbine 18 of the energy generation system 10. The fuel supply 14 may be fluidly connected to or otherwise in the form of one or more fuel nozzles connected to the combustion chamber 12. In one embodiment, the fuel supply 14 may be fluidly connected to a group of fuel nozzles arranged circumferentially around the combustion chamber 12 and / or other combustion chambers of the energy generation system 10. The compressor 16 and the HP gas turbine 18 can be mechanically connected to one another by means of a rotatable shaft 20. To increase power output and / or efficiency, power generation system 10 may also include an afterburner 22 and a low pressure (LP) gas turbine 24 in fluid communication with the fluid output from HP gas turbine 18.
    Air 26 flows in succession through the compressor 16, the combustion chamber 12, the HP gas turbine 18, the afterburner 22 and the LP gas turbine 24. The compression provided by the compressor 16 can also increase the temperature of the air 26. Fuel supply 14 may supply fuel to combustor 12 and afterburner 22 which burns in the presence of air 26 to produce a hot gas stream. The hot gas stream from the combustor 12 can enter the HP gas turbine 18 to transfer mechanical energy to the rotatable shaft 20, e.g. by rotating a group of turbine blades, providing power back to the compressor 16 and / or any loads (not illustrated) mechanically coupled to the rotatable shaft 20. Likewise, the fuel provided by the fuel supply 14 to the afterburner 22 may burn in the presence of excess air supplied by the gas turbine 18 to produce a hot gas flow for the LP gas turbine 24 that will add additional mechanical energy to the rotatable one Can transmit wave, for example by rotating turbine blades within the LP gas turbine 24. Power generation system 10 may be one of several individual turbomachinery controlled by the same operator and / or may be part of a larger power generation system.
    An injection system 50 according to the invention is shown by way of example in FIG. 2. The injection system 50 includes a mixing zone 52 that is embedded within the surface of a turbine guide 54. The turbine guide 54 may be a combustor (e.g., combustor 12 (Figure 1) or afterburner 22 (Figure 1)) from a turbine blade (e.g., HP turbine 18 (Figure 1) or LP turbine 26 (Figure 1)) of a system such as of the power generation system 10 (Figure 1) separate. In the example of a gas turbine system, the turbine guide device 54 can separate the afterburner 22 from the LP turbine 24 of the energy generation system 10. Here, the turbine guide 54 may be exposed to a flow of fluid through the afterburner 22.
    [0027] The mixing zone 52 is arranged between a first outlet 60 and a second outlet 62. The first outlet 60 may be in the form of one or more holes, openings, channels, nozzles, etc. for directing a carrier gas (e.g., an oxygen-containing combustible gas or an inert gas) into the mixing zone 52 in a first injection channel 64. The carrier gas directed to the mixing zone 52 from the first outlet 60 may be excess cooling air directed from a compressor (e.g. compressor 16 (Figure 1)) or may be provided by an independent supply of air or other gas e.g. is arranged outside the power generation system 10. The second outlet 62 may be in the form of one or more holes, openings, channels, nozzles, etc. to direct a fuel in the second injection channel 66 into the mixing zone 52. The fuel directed to the mixing zone 52 through the second outlet 62 can be supplied, for example, from a fuel supply (FIG. 1) or other sources that receive and / or dispense fuel in the initial state. The carrier gas can be an oxidizing gas, e.g. Air; it can be an inert gas or it can be a mixture of any chemical composition suitable for the purposes of improving the mixing and reacting of a fuel and controlling the residence time of the fuel both before and after ignition. In any event, the fuel and carrier gas supplied to the mixing zone 52 may mix together therein to become a reactive gas mixture 68.
    In order to increase the mixing of the fuel and the gas in the mixing zone 52, the first outlet 60 and the second outlet 62 are oriented essentially “opposite” to one another. In the most general sense, “opposite” includes all orientations in which at least some fuel and at least some carrier gas from the first outlet 60 and the second outlet 62 collide with one another within the mixing zone 52 before they leave the mixing zone 52 as a reactive gas mixture 68. In one embodiment, the first outlet 60 and the second outlet 62 may be directly opposite along a certain linear direction, i.e. with opposite or substantially opposite orientations (ie within an error range of approximately 5 degrees), so that the angular orientation of the first outlet 60 and the second outlet 62 with respect to a horizontal axis (eg axis “X” from FIG. 2) is approximately 180 Differentiate degrees. The opposite orientation of the first outlet 60 to the second outlet 62 can be improved by forming a recess or recess in the surface of the turbine guide 54 and placing the first and second outlets 60, 62 within that recess. In another embodiment, the first or second outlet 60, 62 may be aligned with the flow of the other from the first or second outlet 60, 62, e.g. with a fluid flow vector component in the same direction as the other outlet along one axis and with another vector component in a different direction from the other outlet along another axis. For example, the first or second outlet 60, 62 may be oriented in a direction substantially perpendicular to the surface of the turbine guide 54, while the other outlet may be oriented at an angle from the surface of the turbine guide 54 that extends from the other outlet by an angular difference of less than about 45 degrees. In the exemplary embodiment according to FIG. 2, the first outlet 60 and 62 are essentially opposite to one another and conduct fluid with a positive “Y” direction vector component, but with “X” direction vector components in opposite directions and face one another. Any number of possible relative orientations between the first outlet 60 and the second outlet 62 are provided in embodiments of the present disclosure, as long as at least a portion of the carrier gas exiting the first outlet 60 with at least a portion of the fuel exiting the second outlet 62 leaves, collides and / or mixes during operation.
    3, an injection system 50 is shown, which contains additional components. Injection system 50 may include a mixing chamber 70 that is embedded within the surface of turbine guide 54 to enclose mixing zone 52 therein. The mixing chamber 70 also has an outlet passage 72 that extends through the mixing chamber 70 between the mixing zone 52 and an outer region of the mixing chamber. The mixing chamber 70, together with the substantially opposite orientations of the first outlet 60 and the second outlet 62, may determine the degree of contact between the carrier gas and the fuel from the first and second injection channels 64, 66 before leaving the mixing zone 52 through the outlet passage 72 increase. Here, the first and second outlets 60, 62 are aligned with opposite "X" directional vector components and arranged in different Y-Z planes (i.e., arranged at different coordinates along the "X" axis). In this case, the first and second outlets 60, 62 direct fluid flows of carrier gas and fuel into the mixing zone 52 that are substantially in a clockwise or counterclockwise direction within the mixing chamber 70 prior to combination therein and pass through the outlet passage 72 stream.
    As also shown in Figure 3, the outlet passage 72 may be contoured with a particular geometry to allow fluid communication in one direction while preventing fluid communication in the other direction. For example, the passage 72 may be substantially frusto-conical, with a cross-section of the outlet passage 72 that is larger at one end than at the opposite end. The outlet passage 72 may additionally or alternatively be made to have other geometries, e.g. a labyrinth shape, a conical shape, etc. In any event, the fluid flow rate of carrier gas and fuel within the mixing zone 52 to the outlet passage 72 may be significantly greater than the fluid flow rate of substances outside the mixing chamber 70 (e.g., inside the reaction chamber) into the outlet passage 72. Therefore, certain contours of the exhaust passage 72 may prevent fluid communication of burned gases from outside the turbine baffle 54 from entering the mixing zone 52 through the exhaust passage 72. In other embodiments where there is little risk of burned gases entering the mixing zone 52, the outlet passage may have any other desired geometry, e.g. cylindrical, a parallelepiped shaped passage with a rectangular cross section, etc.
    The injection system 50 can be used for other functions in addition to providing a mixed reactive gas for a component of the energy generation system 10 (Figure 1). For example, injection system 50 may provide cooling for turbine guide 54. In one embodiment, one or both of the first and second injection channels 64, 66 may be made of a thermally conductive material. For example, thermally conductive materials can include metal compounds such as alloys, thermally conductive plastics and / or organic materials, conductive ceramic materials, etc. In any event, the material compositions of the first and second injection channels 64, 66 with conductive properties may allow a respective fluid (e.g., carrier gas or fuel) in the first and second injection channels 64, 66 to absorb heat from the surface of the turbine baffle 54. In this case, the heat transferred to the turbine guide 54 during a combustion reaction may be partially dissipated by transferring it to the carrier gas or fuel in the first and / or second injection passages 64, 66 by the degree of damage the turbine guide 54 to reduce.
    4, an injection system 50 is shown as it is coupled and / or included with additional components of the turbine guide device 54. Here, the second injection channel 64 can be in fluid communication with a distributor 74 for collecting carrier gas from a plurality of carrier gas supply channels 76. Carrier gas supply channels 76 may each be in fluid communication with a single source of carrier gas or different sources of carrier gas. As shown in FIG. 4, the distributor 74 can be formed from a plurality of layers with holes, openings, passages, etc., the various layers being fluidly connected to a first injection channel 64. At least one of the various layers in manifold 74 may include one of the plurality of carrier gas supply channels 76 that is connected to a source of carrier gas. Manifold 74 may combine carrier gas from multiple sources to provide to first injection port 64. As shown in FIG. 4, the second injection channel 66 can extend through the distributor 74, so that the second injection channel 66 is fluidly isolated from the carrier gas in the distributor 74. With this arrangement, where the first injection channel 66 is formed from a thermally conductive material, the manifold 74 can cool a larger surface area of the turbine baffle 54 than that occupied by the mixing zone 52 and the fuel in the second injection channel 66 can also remove heat from of turbine guide 54 to provide additional cooling.
    Turning now to FIG. 5, another injection system 100 according to the invention is shown. The injection system 100 can have a first outlet 160 for supplying carrier gas and at least a second outlet 162 for supplying a fuel to a surface of the turbine guide device 154. A first injection passage 164 may provide cooling air (as a carrier gas) to the surface of the turbine baffle 154 through the first outlet 160. At least one second injection passage 166 may deliver fuel to the surface of turbine guide 154 through second outlet 162. In addition, the second injection channel 166 may be positioned within the first injection channel 164. A barrier 168 can be positioned between the first injection channel 164 and the second injection channel or the second injection channels 166. The barrier 168 can separate the carrier gas in the first injection channel 164 from the fuel of the second injection channel 166. As indicated elsewhere herein, turbine guide 154 may be a combustor (e.g., combustor 12 (FIG. 1) or afterburner 122 (FIG. 1)) from a turbine stage (e.g., HP turbine 18 (FIG. 1) or LP turbine 26 (Figure 1)) of a system such as a power generation system 10 (Figure 1). In an exemplary embodiment, the turbine baffle 154 may separate the afterburner 22 from the LP turbine 24 of a power generation system 10 in the form of a gas turbine system and may be exposed to a flow of fluid through the afterburner 22.
    The injection system 100 can also have a mixing chamber 170, which is arranged within the surface of the turbine guide device 154. Mixing chamber 170 may also have an outlet passage 172 disposed above first and second outlets 160, 162 to provide fluid communication between the interior and exterior of mixing chamber 170. The mixing chamber 170 may provide an area for mixing between the carrier gas and the fuel that exits the first and second injection channels 164, 166 through the first and second outlets 160, 162, respectively. The outlet passage 172 can be directly aligned and / or arranged coaxially with the first and / or second outlet 160, 162, as shown in FIG. 5. Alternatively, the outlet passage 172 may be aligned with another axis from the first and / or second outlet 160, 162. In yet another embodiment, the outlet duct 162 may be in the form of multiple outlet ducts 162 that extend through the mixing chamber 170.
    [0035] Embodiments of the injection system 100 may have different relative positions of the first injection port 164 and the second injection port 166 with respect to other components disposed therebetween or otherwise included, where applicable. For example, the second injection channel 166 may be disposed within the first injection channel 164. As shown in Figure 5, the first and second outlets 160, 162 may have a coaxial arrangement with a barrier 168, which may be in the form of a substantially circular divider between the two outlets. The barrier 168 can form part of the first and / or second injection channel 164, 166 or can be a completely different structure. The first injection channel 164 may split or branch within the turbine baffle 154 and may be formed from a thermally conductive material, e.g. one of the thermally conductive materials discussed elsewhere herein with respect to the first injection port 64 (Figure 2-Figure 4). Where the first injection channel 164 is formed from a thermally conductive material, the carrier gas in the first injection channel 164 can be collected from multiple sources that are in fluid communication with the first injection channel 164 so that the carrier gas passes heat from a larger surface area of the turbine baffle 154 can absorb its thermally conductive composition. The second injection passage 166 may extend substantially perpendicular to the turbine guide 154 relative to the surface thereof to connect the second outlet 162 to a particular fuel source. The second injection channel 166 can also be formed from thermally conductive material. The use of thermally conductive material in the composition of the second injection channel 166 and / or the barrier 168 may allow the heat to be transferred through the barrier 168 between the fuel in the second injection channel 166 and the carrier gas in the first injection channel 164.
    6, an injection system 200 with a different arrangement of the first and second injection channels 264, 266 is shown. The injection system 200 can have a plurality of second injection channels 266, each of which can be arranged within the first injection channel 264. Here, some second injection channels 266 cannot be arranged coaxially with the first injection channel 264 and can be arranged evenly or unevenly distributed over the cross-sectional area of the first injection channel 264. Some second outlets 262 may direct fuel over the surface of turbine baffle 254 where the fuel may mix with cooling air (as a carrier gas) supplied from first injection port 264 to the surface of turbine baffle 254 via first outlet 260. A plurality of barriers 268 may be disposed between the first injection channel 264 and one of the plurality of second injection channels 266 to separate the carrier gas within the first injection channel 264 from the fuel in the second injection channels 266. The number and size of second injection channels 266 within the first injection channel 264 may vary based on the intended application, reaction conditions, etc., both the amount of mixing between the fuel and the air after injection, the level of additional through the injection system 200 control combustion and other reaction properties provided. Although the mixing chamber 170 (FIG. 5) and the outlet passage 172 (FIG. 5) have been omitted from FIG. 6 by way of example, it will be understood that these components can also be used with or without accompanying modifications in embodiments where multiple second injection channels 266 are used.
    Another injection system 300 is shown in FIG. 7. Injection system 300 may include an array of injection channels that are particularly suitable, e.g. for situations where long delays before the post-injection mixing of oxygen and fuel are desired. As shown in FIG. 7, the injection system 300 may have at least one first outlet 360 that is fluidly connected to a corresponding first injection channel 364 for delivering either fuel or air to a surface of the turbine guide 354. Likewise, at least a second outlet 362 can provide a fluid connection between a surface of a turbine guide 354 and at least a second injection channel 366. The second outlet 362 and the second injection channel 366 may provide fluid to the surface of the turbine guide 354 that is different from what is provided by the first outlet 360 and the second injection channel 364. For example, where the first injection channel 364 provides carrier gas to the turbine nozzle 354, the second injection channel 366 can provide fuel to the surface of the turbine nozzle 354. The first injection channel 362 may be in fluid communication with a supply of carrier gas (e.g., cooling air) from a compressor of a power generation system or, in an alternative embodiment, may be fluidly connected to a particular source of carrier gas, e.g. is arranged inside or outside the energy generation system 10 (FIG. 1).
    The first and second outlets 360, 362 may have different sizes with respect to each other and, in some embodiments, may be about the same area size to provide substantially equal flows of fluid to the surface of the turbine baffle 354. The injection system 300 may have at least two second injection channels 366, which are arranged adjacent to the first injection channel 364, such that the first and second injection channels 364, 366 and the first and second outlets 360, 362 have an alternating linear sequence of outlets across the surface of the Form turbine guide 354. The alternating linear order can prevent two first outlets 360 and / or two second outlets 362 from being positioned adjacent to one another and causing mixing of an amount of fuel or air with a disproportionately large or small amount of the other medium. The exemplary embodiment shown in FIG. 7 and described herein is a generalized form of the injection system 200 and other embodiments with different shapes that include the alternating linear arrangement of first and second outlets 360, 362 and / or first and second injection channels 364, 366 are described and considered herein. Each first outlet 360 and second outlet 362 may be substantially coplanar with one another (eg, within the same XY plane as shown in FIG. 7) to produce a certain type and amount of mixture between fuel and carrier gas after both media Leave turbine guide 354 through their respective outlets.
    The alternating order of the first and second outlets 360, 362 can form a certain type of shape or pattern. For example, as shown in Figure 7, the plurality of first and second outlets 360, 362 and / or first and second injection channels 364, 366 have a linear, row-like pattern. The pattern can be effective in particular for certain areas of the turbine guide 354. For example, a flow of fluid across the turbine baffle 354 may have a direction of movement substantially parallel to the direction of the series alternating pattern of first and second injection channels 364, 366 and / or first and second outlets 360, 362. The first and second outlets 360, 362 can be arranged on a “front edge” or a “rear edge” of the turbine guide device 354. A leading edge generally refers to an edge of the turbine baffle 354 through which fluid flows from a reaction chamber, and a rear edge generally refers to an edge of the turbine baffle 354 through which fluid flows and which is located in front of a turbine stage of a power generation system. Examples of front and rear edges of a turbine baffle 354 are discussed elsewhere herein.
    8, an injection system 400 with a different arrangement of components is shown. Injection system 400 may include a group of second outlets 462 that are substantially circular around at least one outlet 460. This particular pattern can maintain the alternating linear sequence of first and second outlets 460, 462, e.g. from a second outlet 462 to a first outlet 460 and to a further second outlet 462 positioned on an opposite side from the substantially annular arrangement. Although the type of outlet may vary along a certain linear direction, the second outlets 462 may be in a substantially circular pattern with the first outlet located at or near the center of the injection system 400. The first and second outlets 460, 462 can be fluidly connected to the first and second injection channels 464, 466.
    As shown in Figure 8, the injection system 400 may have a mixing chamber 470 which forms a mixing zone therein. The mixing zone may generally include a space within the mixing chamber 470 above the surface of the turbine nozzle 454. Carrier gas and fuel from the first and second outlets 460, 462 with the alternating arrangement may mix in the mixing zone (i.e., within the mixing chamber 470). The mixture of carrier gas and fuel can flow away from the surface of the turbine baffle 454 through an outlet passage 472 that extends through the mixing chamber 470. Adding the mixing chamber 470 and outlet passage 472 to create a mixing zone above the alternate first and second outlets 460, 462 can increase the amount that carrier gas and fuel can mix before they enter a reaction zone and are burned.
    Referring to Figure 9 is a cross section of a turbine guide 554 with various possible positions for injection systems 50 (Figures 2-4), 100 (Figure 5), 200 (Figure 6), 300 (Figure 7), 400 (Figure 8) shown. Although turbine guide 554 is shown as an example in Figure 9, other types of turbine guides as discussed herein, e.g. turbine guide 54 (Figures 2-4), turbine guide 154 (Figure 5), turbine guide 254 (Figure 6), turbine guide 354 (Figure 7) and / or turbine guide 454 (Figure 8) where applicable be used. The locations on the turbine guide device 554 identified in FIG. 9 and explained here are given as an example and are not intended to restrict possible locations for a specific injection system. The placement of an injection system or systems 50, 100, 200, 300, 400 may vary depending on the intended use and type of power generation system by using the injection system or systems. The turbine guide 554 can be used between the afterburner 22 and the LP (low pressure) turbine 24 of a particular power generation system.
    As shown in the cross-sectional view in the X-Y plane in FIG. 9, the turbine guide device 554 can be arranged downstream of the afterburner 22 and upstream of the LP turbine 24 and between an inner side wall 506 and an outer side wall 508. Corresponding fluid flows F can pass the turbine guide device 554 while they are moving from the afterburner 22 to the LP turbine 24. The injection system (s) 50, 100, 200, 300, 400 may be located at locations exposed to the fluid flow F, such as the leading edge 510 or the trailing edge 512, which because of their location relative to the flow of the fluid F from the reaction chamber 502 to the turbine stage 504 are so called. Additionally or alternatively, an injection system or injection systems 50, 100, 200, 300, 400 can be arranged on or near the pressure side 514 and / or the suction side 516 of the turbine guide device 554. The pressure side 514 and the suction side 516 can be identified as such based on the positive or negative resultant pressures flowing adjacent to their positions. Turbine guide 554 may include a single embodiment of injection system 50, 100, 200, 300, 400, or may include multiple embodiments of injection system (s) 50, 100, 200, 300, 400 as described herein and as described for different ones technical applications is desired or necessary.
    The apparatus of the present disclosure is not limited to any particular gas turbine, internal combustion engine, power generation system, or other system, and can be used with other power generation systems and / or systems (e.g., combined gas and steam systems, simple systems, nuclear reactors, etc.) be used. In addition, the device of the present invention may be used with other systems not described herein that may benefit from the increased operating range, efficiency, life, and reliability of the device described herein. In addition, the various injection systems can be used together on a single control device or on / with different control devices in different sections of a single power generation system. Any number of different embodiments may be added or shared where desired, and the embodiments described herein by way of example are not intended to be mutually exclusive to each other.
    [0045] Embodiments of the present disclosure may have several technical and commercial advantages. For example, embodiments of injection systems disclosed herein may use existing afterburner technologies by allowing a greater proportion of the total gas turbine flow to be injected through the turbine guide than other injection systems, thereby improving efficiency. The arrangement and size of injection systems added to a turbine nozzle according to embodiments of the present disclosure can also be varied to change the amount of fuel and carrier gas injected by the turbine nozzle to different amounts of delay between times of injection and reaction (eg by auto-ignition) between the injected fuel and the carrier gas. The use of separate carrier gas injection channels and outlets may also allow injection systems of the present disclosure to use carrier gas from a particular source rather than extract carrier gas from a compressor component of a power generation system.
    The terminology used herein is for the purpose of describing certain embodiments only and is not intended to limit the disclosure. As used herein, the singular forms "a", "an" and "the / that" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It is also understood that the terms "have" and / or "have" when used in the specification indicate the presence of the features, numbers, steps, commands, elements and / or components specified, but not the presence or that Exclude adding one or more other features, numbers, steps, commands, elements, components and / or groups thereof.
    The written description uses embodiments to disclose the invention, including the preferred embodiment, and to enable any person skilled in the art to practice the invention, including the manufacture and use of any devices or systems. 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 wording of the claims, or if they have equivalent structural elements with non-substantial differences from the wording of the claims.
    REFERENCE SIGN LIST
    [0048]<tb> Power generation system <SEP> 10<tb> combustion chamber <SEP> 12<tb> Fuel supply <SEP> 14<tb> compressor <SEP> 16<tb> gas turbine <SEP> 18<tb> rotatable shaft <SEP> 20<tb> Afterburner <SEP> 22<tb> Low pressure (LP) gas turbine <SEP> 24<tb> air <SEP> 26<tb> Injection system <SEP> 50, 100, 200, 300, 400<tb> Mixing zone <SEP> 52<tb> Turbine guidance device <SEP> 54, 154, 254, 354, 454, 554<tb> first outlet <SEP> 60, 160, 260, 360, 460<tb> second outlet <SEP> 62, 162, 262, 362, 462<tb> second injection channels <SEP> 66, 166, 266, 366, 464<tb> Mixing chamber <SEP> 70, 170, 470<tb> outlet passage <SEP> 72, 172, 472<tb> distributor <SEP> 74<tb> Gas supply channels <SEP> 76<tb> first injection channel <SEP> 64, 164, 264, 364, 466<tb> Barrier <SEP> 168, 268<tb> Reaction chamber <SEP> 502<tb> turbine stage <SEP> 504<tb> front edge <SEP> 510<tb> trailing edge <SEP> 512<tb> Print page <SEP> 514<tb> suction side <SEP> 516
    权利要求:
    Claims (10)
    [1]
    1.Injection system (50, 100, 200, 300, 400) comprising:a mixing zone (52) which is arranged on a surface of a turbine guide device (54, 154, 254, 354, 454, 554) and between a first outlet (60, 160, 260, 360) and a second outlet (62, 162, 262 , 362, 462), the turbine guide device (54, 154, 254, 354, 454, 554) separating a combustion chamber (12) of an energy generation system (10) from a turbine stage (504) of the energy generation system (10), the first Outlet 60, 160, 260, 360) is oriented substantially opposite to the second outlet (62, 162, 262, 362, 462);a first injection channel (164, 264, 364) for delivering a carrier gas to the mixing zone (52) through the first outlet (60, 160, 260, 360); anda second injection port (166, 266, 366) for delivering fuel to the mixing zone (52) through the second outlet (62, 162, 262, 362, 462);wherein the carrier gas and the fuel mix within the mixing zone (52) after leaving the first injection channel (164, 264, 364) and the second injection channel (166, 266, 366);a mixing chamber (70, 170, 470) which is embedded in the surface of the turbine guide device (54, 154, 254, 354, 454, 554) and encloses the mixing zone (52) therein.
    [2]
    2. The injection system (50, 100, 200, 300, 400) according to claim 1, further comprising:an outlet passage (72, 172, 472) extending through the mixing chamber (70, 170, 470) between the mixing zone (52) and the exterior of the mixing chamber (70, 170, 470).
    [3]
    3. The injection system (50, 100, 200, 300, 400) of claim 2, wherein a contour of the outlet passage (72, 172, 472) fluid communication of burned gas outside the turbine guide (54, 154, 254, 354, 454, 554 ) in the mixing chamber (70, 170, 470) prevented.
    [4]
    4. Injection system (50, 100, 200, 300, 400) according to one of the preceding claims, wherein the combustion chamber (12) has an afterburner (22) of the energy generation system (10) and the surface of the turbine guide device (54, 154, 254, 354 , 454, 554) is exposed to a flow of fluid through the afterburner (22), the energy generation system (10) having a gas turbine system (18).
    [5]
    5. Injection system (50, 100, 200, 300, 400) according to one of the preceding claims, wherein the first injection channel (164, 264, 364) and / or the second injection channel (166, 266, 366) consists of a thermally conductive material such that a respective fluid in the first injection channel (164, 264, 364) or the second injection channel (166, 266, 366) absorbs heat from the surface of the turbine guide device (54, 154, 254, 354, 454, 554).
    [6]
    6. Injection system (50, 100, 200, 300, 400) according to one of the preceding claims, further comprising a distributor (74) which is embedded in the turbine guide device (54, 154, 254, 354, 454, 554), the Distributor (74) is in fluid communication with the first injection channel (164, 264, 364) and a plurality of carrier gas supply channels (76).
    [7]
    7.Injection system (50, 100, 200, 300, 400) comprising:at least a first injection channel (164, 264, 364) for supplying carrier gas to a surface of a turbine guide device (54, 154, 254, 354, 454, 554) through a first outlet (60, 160, 260, 360), the turbine guide device (54, 154, 254, 354, 454, 554) separates a combustion chamber (12) of an energy generation system (10) from a turbine stage (504) of the energy generation system (10);at least a second injection port (166, 266, 366) for delivering fuel to the surface of the turbine baffle (54, 154, 254, 354, 454, 554) through a second outlet (62, 162, 262, 362, 462), wherein the at least one second injection channel (166, 266, 366) is arranged within the first injection channel (164, 264, 364);wherein at least one barrier (168, 268) is provided between the first injection channel (164, 264, 364) and the at least second injection channel (166, 266, 366), the at least one barrier (168, 268) containing the carrier gas in the at least one separates a first injection channel (164, 264, 364) from the fuel of the second injection channel (166, 266, 366);a mixing chamber (70, 170, 470) which is arranged in the surface of the turbine guide device (54, 154, 254, 354, 454, 554), the carrier gas and the fuel within the mixing chamber (70, 170, 470) mixing after leaving the first injection channel (164, 264, 364) and the second injection channel (166, 266, 366).
    [8]
    The injection system (50, 100, 200, 300, 400) of claim 7, wherein the at least one barrier (168, 268) comprises a plurality of barriers (168, 268), each of the plurality of barriers (168, 268 ) is disposed between the first injection channel (164, 264, 364) and a respective one of an equal plurality of second injection channels (66, 166, 266, 366) and wherein each of the plurality of barriers (168, 268) the fuel of each from the second injection channels (166, 266, 366) from the carrier gas of the first injection channel (164, 264, 364, 362).
    [9]
    9. Injection system (50, 100, 200, 300, 400) according to one of the preceding claims, wherein the carrier gas is an oxidizing gas, in particular air or an oxygen-containing combustible gas.
    [10]
    10. Injection system (50, 100, 200, 300, 400) according to one of claims 1 to 8, wherein the carrier gas is an inert gas.
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    同族专利:
    公开号 | 公开日
    DE102015120832A1|2016-06-16|
    US10107498B2|2018-10-23|
    US20160169524A1|2016-06-16|
    CN205641000U|2016-10-12|
    CH710507A2|2016-06-15|
    JP2016128740A|2016-07-14|
    JP6721323B2|2020-07-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4438625A|1978-10-26|1984-03-27|Rice Ivan G|Reheat gas turbine combined with steam turbine|
    US4735052A|1985-09-30|1988-04-05|Kabushiki Kaisha Toshiba|Gas turbine apparatus|
    US5309709A|1992-06-25|1994-05-10|Solar Turbines Incorporated|Low emission combustion system for a gas turbine engine|
    CH687269A5|1993-04-08|1996-10-31|Abb Management Ag|Gas turbine group.|
    US6079197A|1998-01-02|2000-06-27|Siemens Westinghouse Power Corporation|High temperature compression and reheat gas turbine cycle and related method|
    GB2346177B|1999-02-01|2003-03-19|Alstom Gas Turbines Ltd|Gas turbine engine|
    US6691519B2|2000-02-18|2004-02-17|Siemens Westinghouse Power Corporation|Adaptable modular gas turbine power plant|
    DE10035676A1|2000-07-21|2002-02-07|Siemens Ag|Gas turbine and method for operating a gas turbine|
    GB2373299B|2001-03-12|2004-10-27|Alstom Power Nv|Re-fired gas turbine engine|
    DE50109870D1|2001-03-26|2006-06-29|Siemens Ag|gas turbine|
    FR2826055B1|2001-06-14|2003-12-19|Snecma Moteurs|VARIABLE CYCLE PROPULSION DEVICE WITH COMPRESSED AIR TAKE-OFF FOR SUPERSONIC AIRCRAFT|
    US6619026B2|2001-08-27|2003-09-16|Siemens Westinghouse Power Corporation|Reheat combustor for gas combustion turbine|
    JP3960166B2|2001-08-29|2007-08-15|株式会社日立製作所|Gas turbine combustor and operation method of gas turbine combustor|
    GB2390150A|2002-06-26|2003-12-31|Alstom|Reheat combustion system for a gas turbine including an accoustic screen|
    US6796130B2|2002-11-07|2004-09-28|Siemens Westinghouse Power Corporation|Integrated combustor and nozzle for a gas turbine combustion system|
    DE10336432A1|2003-08-08|2005-03-10|Alstom Technology Ltd Baden|Gas turbine and associated cooling process|
    US7966822B2|2005-06-30|2011-06-28|General Electric Company|Reverse-flow gas turbine combustion system|
    US7716931B2|2006-03-01|2010-05-18|General Electric Company|Method and apparatus for assembling gas turbine engine|
    JP5204756B2|2006-03-31|2013-06-05|アルストムテクノロジーリミテッド|Fuel lance used in gas turbine equipment and method for operating the fuel lance|
    EP1847684A1|2006-04-21|2007-10-24|Siemens Aktiengesellschaft|Turbine blade|
    EP1847696A1|2006-04-21|2007-10-24|Siemens Aktiengesellschaft|Component for a secondary combustion system in a gas turbine and corresponding gas turbine.|
    US7784261B2|2006-05-25|2010-08-31|Siemens Energy, Inc.|Combined cycle power plant|
    US7603863B2|2006-06-05|2009-10-20|General Electric Company|Secondary fuel injection from stage one nozzle|
    US20080134685A1|2006-12-07|2008-06-12|Ronald Scott Bunker|Gas turbine guide vanes with tandem airfoils and fuel injection and method of use|
    US7886545B2|2007-04-27|2011-02-15|General Electric Company|Methods and systems to facilitate reducing NOx emissions in combustion systems|
    US20090064654A1|2007-09-11|2009-03-12|General Electric Company|Turbine engine with modulated combustion and reheat chambers|
    US8443608B2|2008-02-26|2013-05-21|Delavan Inc|Feed arm for a multiple circuit fuel injector|
    EP2116767B1|2008-05-09|2015-11-18|Alstom Technology Ltd|Burner with lance|
    EP2116768B1|2008-05-09|2016-07-27|Alstom Technology Ltd|Burner|
    EP2116766B1|2008-05-09|2016-01-27|Alstom Technology Ltd|Burner with fuel lance|
    US20090301054A1|2008-06-04|2009-12-10|Simpson Stanley F|Turbine system having exhaust gas recirculation and reheat|
    US8220271B2|2008-09-30|2012-07-17|Alstom Technology Ltd.|Fuel lance for a gas turbine engine including outer helical grooves|
    US8511059B2|2008-09-30|2013-08-20|Alstom Technology Ltd.|Methods of reducing emissions for a sequential combustion gas turbine and combustor for a gas turbine|
    ES2400247T3|2008-12-19|2013-04-08|Alstom Technology Ltd|Burner of a gas turbine that has a special lance configuration|
    US8112216B2|2009-01-07|2012-02-07|General Electric Company|Late lean injection with adjustable air splits|
    EP2208934A1|2009-01-15|2010-07-21|ALSTOM Technology Ltd|Burner of a gas turbine for a reactive fuel air mixture|
    EP2211109A1|2009-01-23|2010-07-28|Alstom Technology Ltd|Burner of a gas turbine and method for mixing a fuel with a gaseous flow|
    EP2230455B1|2009-03-16|2012-04-18|Alstom Technology Ltd|Burner for a gas turbine and method for locally cooling a hot gases flow passing through a burner|
    EP2287456A1|2009-08-17|2011-02-23|Alstom Technology Ltd|Gas turbine and method for operating a gas turbine|
    EP2295864B1|2009-08-31|2012-11-14|Alstom Technology Ltd|Combustion device of a gas turbine|
    WO2011054739A2|2009-11-07|2011-05-12|Alstom Technology Ltd|Reheat burner injection system|
    EP2496884B1|2009-11-07|2016-12-28|General Electric Technology GmbH|Reheat burner injection system|
    WO2011054757A2|2009-11-07|2011-05-12|Alstom Technology Ltd|Reheat burner injection system with fuel lances|
    EP2362147B1|2010-02-22|2012-12-26|Alstom Technology Ltd|Combustion device for a gas turbine|
    EP2388520B1|2010-05-20|2016-10-26|General Electric Technology GmbH|Lance of a gas turbine burner|
    EP2400216B1|2010-06-23|2014-12-24|Alstom Technology Ltd|Lance of a Reheat Burner|
    RU2531110C2|2010-06-29|2014-10-20|Дженерал Электрик Компани|Gas-turbine unit and unit with injector vanes |
    US8225591B2|2010-08-02|2012-07-24|General Electric Company|Apparatus and filtering systems relating to combustors in combustion turbine engines|
    EP2420731B1|2010-08-16|2014-03-05|Alstom Technology Ltd|Reheat burner|
    US8322121B1|2011-01-05|2012-12-04|Marcell Roland J|Electric trimmer attachment for lawn tractors|
    US8322141B2|2011-01-14|2012-12-04|General Electric Company|Power generation system including afirst turbine stage structurally incorporating a combustor|
    EP2522912B1|2011-05-11|2019-03-27|Ansaldo Energia Switzerland AG|Flow straightener and mixer|
    US8966910B2|2011-06-21|2015-03-03|General Electric Company|Methods and systems for cooling a transition nozzle|
    US9366432B2|2012-05-17|2016-06-14|Capstone Turbine Corporation|Multistaged lean prevaporizing premixing fuel injector|
    US9482434B2|2013-03-15|2016-11-01|General Electric Company|Methods relating to downstream fuel and air injection in gas turbines|US10139111B2|2014-03-28|2018-11-27|Siemens Energy, Inc.|Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine|
    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2019-05-31| NV| New agent|Representative=s name: FREIGUTPARTNERS IP LAW FIRM DR. ROLF DITTMANN, CH |
    2021-07-30| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/567,753|US10107498B2|2014-12-11|2014-12-11|Injection systems for fuel and gas|
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