• 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 a fuel nozzle (100) for a gas turbine that uses a primary fuel and a secondary fuel. The fuel nozzle (100) includes a number of primary fuel injection ports (170) for the primary fuel, a water passage (220), a number of secondary fuel injection ports (280) and a secondary fuel evaporation system for atomizing the secondary fuel.
    公开号:CH710377B1
    申请号:CH01596/15
    申请日:2015-11-03
    公开日:2020-09-30
    发明作者:David Myers Geoffrey；Yurievich Gerasimov Alexey；Igorevna Vyazemskaya Natalya；Shershnyov Borys；Subbota Andrey；Valeev Almaz
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    TECHNICAL AREA
    The present invention relates to a fuel nozzle with an integrated liquid evaporator to reduce the total water consumption and to improve thermal efficiency.
    BACKGROUND OF THE INVENTION
    The operating efficiency and total power output of a gas turbine generally increase as the temperature of the hot combustion gas stream increases. However, high combustion gas stream temperatures can produce higher levels of nitrogen oxides (NOx). Such emissions may be subject to both federal and state laws in the United States and may be subject to similar rules abroad. There is therefore a balancing act between the benefits of operating the gas turbine in an efficient high temperature range while also ensuring that the output of nitrogen oxides and other types of regulated emissions remain well below the prescribed levels. In addition, varying load levels, varying environmental conditions, and other types of operating parameters can also have a significant impact on overall gas turbine efficiency and emissions.
    Several types of known gas turbine designs, such as those using dry low NOx combustors (DLN), pre-mix the fuel flow and air flow upstream of a reaction or combustion zone by means of a number of premixed fuel nozzles to reduce the NOx emissions to reduce. Such a premix tends to reduce the peak flame temperatures and consequently the NOx emissions.
    For fuel flexibility and energy system availability, gas turbines with low emissions are often equipped with a system for injecting a liquid fuel as secondary or fallback fuel in addition to the gas premixers. The liquid fuel injectors can be inserted through the center of the gas premixer. Because the liquid fuel cannot evaporate and mix sufficiently with the air prior to combustion, large amounts of water can be injected into the combustion zone to reduce flame temperatures and the resulting NOx emissions. A significant and expensive volume of water may therefore be required when working with such a liquid fuel. In addition, water injection can lower overall gas turbine efficiency.
    Therefore, there is a need for an improved fuel nozzle. Such a fuel nozzle can receive a secondary fuel such as liquid fuel with reduced total water consumption while maintaining gas turbine thermal efficiency and power generation.
    SUMMARY OF THE INVENTION
    The present invention therefore provides a fuel nozzle as described in claim 1.
    In any embodiment of the fuel nozzle, it can be advantageous that the fuel nozzle also comprises a plurality of swirl guide surfaces, the plurality of primary fuel injection openings being arranged thereon.
    In any embodiment of the fuel nozzle, it can be advantageous if the plurality of swirl guide surfaces are arranged in a premixing chamber.
    In any embodiment of the fuel nozzle, it can be advantageous if the primary fuel comprises a flow of natural gas.
    In any embodiment of the fuel nozzle, it may be advantageous if the water passage comprises a pilot liquid fuel passage.
    In any embodiment of the fuel nozzle, it may be advantageous if the pilot liquid fuel passage extends to a pilot tip.
    In any embodiment of the fuel nozzle, it can be advantageous that the pilot tip comprises a pilot swirl generator arranged around it.
    In any embodiment of the fuel nozzle, it may be advantageous that it includes a secondary fuel passage in communication with the plurality of secondary fuel injection ports.
    In any embodiment of the fuel nozzle, it can be advantageous that the secondary fuel comprises a flow of liquid fuel.
    In any embodiment of the fuel nozzle, it may be advantageous that the secondary fuel vaporizer system comprises an atomizer.
    In any embodiment of the fuel nozzle, it may be advantageous that the atomizer comprises an atomizer swirl generator.
    In any embodiment of the fuel nozzle, it may be advantageous for the atomizer swirler to include a neck and a flange.
    In any embodiment of the fuel nozzle, it may be advantageous for the atomizer swirler to include a plurality of slots therein.
    In any embodiment of the fuel nozzle, it may be advantageous that the atomizer comprises a jacket with an opening therein.
    These and other features and improvements of the present application and the resulting patent will become better understood by those of ordinary skill in the art after reviewing the following detailed description when taken in conjunction with the several drawings and the appended claims.
    BRIEF DESCRIPTION OF THE DRAWINGS
    Fig. 1 is a schematic illustration of a gas turbine showing a compressor, a combustor, a turbine and a load.
    FIG. 2 is a schematic illustration of a combustor that may be used with the gas turbine of FIG. 1.
    Figure 3 is a cross-sectional view of a fuel nozzle as may be described herein.
    FIG. 4 is a partial cross-sectional view of a pilot fuel tip that can be used with the premix nozzle of FIG.
    FIG. 5 is a cross-sectional view of a liquid fuel injector that may be used with the premix nozzle of FIG.
    DETAILED DESCRIPTION
    Referring to the drawings, in which like reference characters refer to like elements throughout the several views, FIG. 1 shows a schematic view of a gas turbine 10 as may be used herein. The gas turbine 10 can have a compressor 15. The compressor 15 compresses an incoming flow of air 20. The compressor 15 delivers the compressed flow of air 20 to a combustion chamber 25. The combustion chamber 25 mixes the compressed flow of air 20 with a pressurized flow of fuel 30 and ignites the mixture, to create a flow of combustion gases 35. Although only a single combustor 25 is shown, the gas turbine 10 may include any number of combustors 25 arranged in a circumferential arrangement or otherwise. The flow of combustion gases 35 is in turn provided to a turbine 40. The flow of combustion gases 35 drives the turbine 40 to produce mechanical work. The mechanical work generated in the turbine 40 drives the compressor 15 through a shaft 45 and an external load 50 such as an electric generator or the like.
    The gas turbine 10 may use natural gas, liquid fuels, various types of synthesis gas, and / or other types of fuels and mixtures thereof. The gas turbine 10 may be any of a number of different gas turbines available by the General Electric Company of Schenectady, New York, including, but not limited to, such as a Series 7 or a Series 9 heavy gas turbine and the like. The gas turbine 10 can have different configurations and use other types of components. Other types of gas turbines can also be used herein. Multiple gas turbines, other types of gas turbines, and other types of power generation facilities can be used together herein.
    FIG. 2 shows a schematic representation of an exemplary combustor 25 that can be used with the gas turbine 10 described above or the like. The combustor 25 may extend around the turbine 40 from an end cover 52 at a head end to a transition piece 54 at a rear end. A number of fuel nozzles 56 may be disposed around the end cover 52. A shroud 58 can extend from the fuel nozzles 56 to the transition piece 54 and can define a combustion zone 60 therein. The casing 58 can be surrounded by a flow sleeve 62. The jacket 58 and the flow sleeve 62 may form a flow path 64 therebetween for the flow of air 20 from the compressor 15 or the like. An outer housing 66 can partially enclose the flow sleeve 62. Any number of combustion chambers 25 may be used herein, in a circumferential arrangement or the like. As described above, the flow of air 20 and the flow of fuel 30 in the combustor 25 can be ignited to create the flow of combustion gases 35. The combustion chamber 25 described herein is for purposes of example only. Combustors with other types of components and other configurations can also be used herein.
    3-5 show an example of a fuel nozzle 100 as may be described herein. The fuel nozzle 100 can be used with the combustor 25 and the like. The combustor 25 may employ any number of fuel nozzles 100 in any configuration.
    In general terms, the fuel nozzle 100 can have an outer ring cover 110. The outer ring cover 110 may extend from an air inlet at an upstream end thereof and may terminate around the combustion zone 60 at a downstream end thereof. The outer ring cover 110 may surround an inner ring wall or core 130. The core 130 may extend from a gas fuel nozzle flange 140 at an upstream end thereof and may terminate upstream of the end of the outer ring cover 110. The outer ring cover 110 and the core 130 can form a premixing chamber 150 therebetween. The premix chamber 150 may be in communication with a flow of air 20 from the compressor 15 or elsewhere. A number of swirl guide surfaces 160 can also extend from the core 130 to or around the outer ring cover 110. The swirl baffles 160 can have any suitable size, shape, or configuration. A number of primary fuel injection ports 170 may be arranged around the swirl baffles 160. The fuel injection ports 170 may be in communication with a flow of fuel 30. The swirl guide surfaces 160 with the primary fuel injection openings 170 therefore provide a mixture of fuel / air and a premixed flame stabilization. In this example, the fuel flow 30 may be a flow of natural gas. Other types of fuels can be used herein. The flow of air 20 and the flow of fuel 30 may begin to mix within the premixing chamber 150 downstream of the swirl baffles 160 and to flow into the combustion zone 60. Other components and other configurations can be used herein.
    The fuel nozzle 100 may also include a number of concentric tubes that define separate annular passages for the flow of different types of fluids. The concentric tubes can be of any suitable size, shape, or configuration. A gas passage 180 for flow of a primary fuel, such as natural gas, may extend from the gas fuel nozzle flange 140 to the primary fuel injection ports 170 around the swirl baffles 160. A pilot air passage 190 may extend from a pilot air inlet 200 through the core 130 to a downstream pilot tip 210. Likewise, a pilot liquid fuel passage 220 may extend from a pilot liquid fuel inlet 230 to a pilot tip 210. As shown in FIG. 4, the pilot tip 210 may have a pilot swirler 240 therein. The pilot swirler 240 can provide good mixing of the flow of pilot air through the pilot air passage 190 and the flow of pilot liquid fuel through the pilot liquid fuel passage 220. The pilot swirler 240 can also provide thermal protection for the pilot tip 210 during the combustion of gas, improved atomization of the pilot fuel, and flame stabilization. The pilot liquid fuel passage 220 can also be used for flows of other types of fluids. For example, a flow of water and / or other types of fluids could be used herein. Other passages can also be used herein. Other components and other configurations can also be used herein.
    [0032] The fuel nozzle 100 can also include a liquid fuel system 250. The liquid fuel system 250 may provide a flow of a secondary fuel such as a distillate, biodiesel, ethanol, and the like. The liquid fuel system 250 may include a liquid fuel passageway 260. The liquid fuel passage 260 may extend from a premix liquid fuel inlet 270 to a number of premix fuel injectors 280. In this embodiment, six (6) of the premix fuel injectors 280 are shown, although any number may be used herein. The premix fuel injectors 280 can be oriented in a single plane, as shown, and / or the injectors 280 can be in a staggered arrangement.
    [0033] Each of the premix fuel injectors 280 may include a liquid fuel atomizer 290. As shown in FIG. 5, each liquid fuel atomizer 290 can have an inner swirl generator 300 arranged within an outer shell 310. The inner swirl generator 300 can have a lower neck 320 which leads to an upper flange 330. A number of slots 340 may be located in the top flange 330. The slots 340 can be angled. Any number of slots 340 can be used. The flow of premixed liquid fuel can thus pass through the premixed liquid fuel passages 260. The top shell 310 may have a narrow opening 350 therein. The premixed liquid fuel can be accelerated and atomized as it flows through the slots 340 of the upper flange 340 of the inner swirler 300. The flow can then be accelerated again as it passes through the narrow opening 350 and into the premixers 150 to be mixed with the flow of air 20 therein. The premixed liquid fuel injectors 280 may be mounted around the core 130 downstream of the swirl baffles 160 to prevent the aerodynamics of the entire fuel nozzle 100 from being compromised or the serviceability and / or emissions compliance by perturbing the gas fuel / air mixture profile when operating with a Gas fuel is affected.
    In use, fuel nozzle 100 mixes a flow of fuel 30, such as natural gas, through gas passageway 180 and fuel injection ports 170 of swirl surfaces 160 with a flow of air 20 from compressor 50 or elsewhere through air inlet 120. The flows A swirl can be applied downstream of the swirl guide surfaces 160 and mixed within the premixing chamber 150 within the combustion zone 60 before ignition. Likewise, a flow of pilot liquid fuel at ignition speed can be used to start the turbine with liquid fuel, to accelerate to full shaft speed and for operating conditions with low partial loads. The pilot liquid fuel can be direct fuel injection, diffusion flame. Alternatively, a flow of water or other types of fluids may pass through the pilot liquid fuel passage 220 or elsewhere. The water flow can provide additional emissions control as needed when operating on a liquid fuel.
    The fuel nozzle 100 also provides the liquid fuel system 250 with the liquid fuel atomizer 290 to enhance the ability to vaporize a liquid fuel and to mix the liquid fuel vapor with the flow of air 20. The fuel nozzle 100 thus provides a two stage fluid system that includes injection at the pilot tip 210 or via the premixed liquid fuel injectors 280 for robust ignition, acceleration to no-load, full-speed, and part-load operating conditions. In addition, the premixed liquid fuel injectors 280 can be used under load when emissions compliance may be required.
    The fuel nozzle 100 can also reduce overall water consumption while improving gas thermal efficiency. The liquid fuel atomizer 290 may atomize the flow to reduce peak fuel / air ratios and temperatures in the downstream combustion zone 60. This reduction can reduce the need for water injection. In particular, vaporizing the liquid fuel via the liquid fuel atomizer 290 can reduce the overall requirement for water while remaining within emission parameters when operating on a gas fuel. In addition, overall maintenance costs can be reduced by avoiding the need for excess water injection and eliminating the cost of water. The overall water system can therefore be reduced in size and complexity. Additional costs can be reduced by using the pilot liquid fuel passage 220 for both the flow of the pilot fuel and the flow of the water as needed. The pilot water injection would be used when it is necessary to reduce further NOx emissions. In addition, the pilot water injection can e.g. used to achieve a 25 ppm limit rather than a typically higher control limit.
    In particular, the pilots can be used to make an ignitable spray at ignition rate when starting with oil and switching from gas to liquid during the output fuel switch. The pilots are dimensioned so that the gas turbine can only be operated by the pilots when the “rotating reserve” (minimum possible load) is in use. Emissions regulations generally do not require compliance below about 50% of full load. As soon as higher loads are reached and when the combustion chamber inlet conditions (pressure and temperature) are high enough that the premix flame is stable, the pilot oil circuits can be switched off and flushed with water to ensure that all of the oil is removed. This flushing prevents thermal breakdown of the remaining oil and clogging of the nozzles, which would otherwise affect reliability. If the local regulations are such that additional NOx suppression by means of water injection is required, this much smaller amount of water can be injected directly via the pilot circuits. If there is a problem with the turbine or the grid under these circumstances that a full load suppression (loss of hundreds of megawatts of power when the generator breaker is opened) there is no time to turn off the water and turn the pilots back on because the gas turbine arrives at full speed in a range of seconds in no-load conditions. The fuel flow rate must be reduced quickly to avoid overspeeding the shaft and the combustion system should still remain ignited to allow rapid recovery and reloading. The procedure would be to relieve pressure on the central main fluid circuit. The pilot water would also be switched off for relief.
    REFERENCE LIST
    10 gas turbine 15 compressor 20 air 25 combustion chamber 30 fuel 35 combustion gases 40 turbine 45 shaft 50 load 52 end cover 54 transition piece 56 fuel nozzles 58 casing 60 combustion zone 62 flow sleeve 64 flow path 66 housing 100 fuel nozzle 110 ring cover 120 air inlet 130 core 140 nozzle flange 150 premixing chamber 160 Swirl baffles 170 Primary fuel injection orifices 180 Gas passage 190 Air passage 200 Air inlet 210 Pilot tip 220 Liquid fuel passage 230 Liquid fuel inlet 240 Pilot swirl generator 250 Liquid fuel evaporation system 260 Liquid fuel passage 270 Premixed liquid fuel inlet 280 Premixed fuel injectors 340 Outer Flange generator 310 330 Orifice 350
    权利要求:
    Claims (8)
    [1]
    A fuel nozzle (100) for a gas turbine (10) which is configured to use a primary fuel and a secondary fuel, comprising:a plurality of primary fuel injection ports (170) for the primary fuel;a water passage;a plurality of secondary fuel injection ports; anda secondary fuel evaporation system (290) for atomizing the secondary fuel.
    [2]
    2. The fuel nozzle (100) according to claim 1, further comprising a plurality of swirl guide surfaces (160) with the plurality of primary fuel injection openings (170) arranged thereon.
    [3]
    3. Fuel nozzle (100) according to claim 2, wherein the plurality of swirl guide surfaces (160) is arranged in a premixing chamber (150).
    [4]
    4. The fuel nozzle (100) according to any one of the preceding claims, wherein the water passage comprises a pilot liquid fuel passage (220).
    [5]
    The fuel nozzle (100) of claim 4, wherein the pilot liquid fuel passage (220) extends towards a pilot tip (210).
    [6]
    6. The fuel nozzle (100) of claim 5, wherein the pilot tip (210) comprises a pilot swirler (240) disposed around it.
    [7]
    7. The fuel nozzle (100) according to any one of the preceding claims, further comprising a secondary fuel passage (260) in communication with the plurality of secondary fuel injection ports.
    [8]
    8. The fuel nozzle (100) according to any one of the preceding claims, wherein the secondary fuel vaporizer system comprises an atomizer (290) and wherein the atomizer (290) comprises an atomizer swirl generator (300) and / or wherein the atomizer (290) has an outer jacket (310) an opening (350) disposed therein.
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    同族专利:
    公开号 | 公开日
    JP2016095128A|2016-05-26|
    US9964043B2|2018-05-08|
    CH710377A2|2016-05-13|
    CN105698175B|2020-01-07|
    CN105698175A|2016-06-22|
    US20160169110A1|2016-06-16|
    DE102015118761A1|2016-05-12|
    JP6840458B2|2021-03-10|
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    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 |
    2019-07-15| AZW| Rejection (application)|
    2020-05-29| AEN| Modification of the scope of the patent|Free format text: :DIE PATENTANMELDUNG WURDE AUFGRUND DES WEITERBEHANDLUNGSANTRAGS VOM 3.9.2019 REAKTIVIERT. |
    2021-06-30| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/537,973|US9964043B2|2014-11-11|2014-11-11|Premixing nozzle with integral liquid evaporator|
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