CN103307635A - 用于将工作流体供应到燃烧器的系统 - Google Patents
用于将工作流体供应到燃烧器的系统 Download PDFInfo
- Publication number
- CN103307635A CN103307635A CN2013100782023A CN201310078202A CN103307635A CN 103307635 A CN103307635 A CN 103307635A CN 2013100782023 A CN2013100782023 A CN 2013100782023A CN 201310078202 A CN201310078202 A CN 201310078202A CN 103307635 A CN103307635 A CN 103307635A
- Authority
- CN
- China
- Prior art keywords
- liner
- pipe
- combustion chamber
- working fluid
- flowing sleeve
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000012530 fluid Substances 0.000 title claims abstract description 61
- 238000002485 combustion reaction Methods 0.000 claims abstract description 58
- 239000000446 fuel Substances 0.000 claims description 32
- 230000001154 acute effect Effects 0.000 claims description 12
- 239000007789 gas Substances 0.000 description 24
- 238000002347 injection Methods 0.000 description 16
- 239000007924 injection Substances 0.000 description 16
- 230000006835 compression Effects 0.000 description 15
- 238000007906 compression Methods 0.000 description 15
- 239000003638 chemical reducing agent Substances 0.000 description 14
- 239000000203 mixture Substances 0.000 description 14
- 239000000567 combustion gas Substances 0.000 description 7
- 238000000034 method Methods 0.000 description 5
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- 230000003321 amplification Effects 0.000 description 3
- 238000003199 nucleic acid amplification method Methods 0.000 description 3
- ATUOYWHBWRKTHZ-UHFFFAOYSA-N Propane Chemical compound CCC ATUOYWHBWRKTHZ-UHFFFAOYSA-N 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 239000003949 liquefied natural gas Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 1
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000001934 delay Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000005012 migration Effects 0.000 description 1
- 238000013508 migration Methods 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000001294 propane Substances 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000009834 vaporization Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/045—Air inlet arrangements using pipes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
- F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
- F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
- F23C6/047—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure with fuel supply in stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Of Fluid Fuel (AREA)
- Gas Burners (AREA)
Abstract
本发明提供一种用于将工作流体供应到燃烧器的系统。该系统包括燃烧室、周向地围绕燃烧室的至少一部分的内衬、以及周向地围绕内衬的至少一部分的流动套管。管提供工作流体通过流动套管和内衬流动到燃烧室中的流体连通，并且管在流动套管和内衬之间成螺旋形。
Description
技术领域
本发明总体上涉及一种用于将工作流体供应到燃烧器的系统。在特定实施例中，本发明可以通过围绕燃烧室周向布置的延迟贫喷射器将贫燃料-空气混合物供应到燃烧室。
背景技术
燃烧器通常在工业和发电操作中用于点燃燃料以产生具有高温和高压的燃烧气体。例如，燃气涡轮机典型地包括一个或多个燃烧器以生成动力或推力。用于生成电力的典型燃气涡轮机包括在前面的轴流式压缩器、围绕中间的一个或多个燃烧器和在后面的涡轮机。环境空气可以供应到压缩器，并且压缩器中的旋转桨叶和固定叶逐渐将动能施加到工作流体（空气）以产生处于高能状态的压缩工作流体。压缩工作流体离开压缩器并且流入燃烧室中，在燃烧室中压缩工作流体与燃料混合并且点燃以生成具有高温和高压的燃烧气体。燃烧气体在涡轮机中膨胀以产生功。例如，燃烧气体在涡轮机中的膨胀可以旋转连接到发电机的轴以产生电力。
各种设计和操作参数影响燃烧器的设计和操作。例如，更高的燃烧气体温度大体上改善燃烧器的热力学效率。然而，更高的燃烧气体温度也促进回烧（flashback）或火焰保持状况，其中燃烧火焰朝着正由燃料喷嘴供应的燃料迁移，可能在较短时间内导致燃料喷嘴的严重损坏。另外，更高的燃烧气体温度大体上增加了双原子氮的分解率，增加氮氧化物（NOX）的产生。相反地，与燃料流量减小和/或部分负荷操作（调低）关联的更低的燃烧气体温度大体上减小了燃烧气体的化学反应速率，增加了一氧化碳和未燃烃的产生。
在特定燃烧器设计中，一个或多个延迟贫(late lean)喷射器或管可以围绕燃料喷嘴的下游的燃烧室周向地布置。离开压缩器的压缩工作流体的一部分可以流动通过管以与燃料混合，从而产生贫燃料-空气混合物。然后贫燃料-空气混合物可以由管喷射到燃烧室中，导致升高燃烧气体温度并且增加燃烧器的热力学效率的额外燃烧。
延迟贫喷射器有效地增加燃烧气体温度而不引起NOX的产生的相应增加。然而，提供贫燃料-空气混合物的延迟喷射的管典型地具有大致恒定的横截面，在延迟贫喷射器周围产生易受局部火焰保持影响的状况。另外，管大体上垂直于燃烧室中的燃烧气体的流动定位。因此，延迟贫喷射器可以产生将热燃烧气体再循环回到燃烧室的表面的大旋涡，产生高热梯度并且缩短硬件寿命。所以，一种用于将工作流体供应到燃烧器的改进系统将是有用的，其减小火焰保持和/或旋涡脱落的状况。
发明内容
下面，本发明的方面和优点将在以下描述中进行阐述，或者可以从该描述显而易见，或者可以通过本发明的实施而获悉。
本发明的一个实施例是一种用于将工作流体供应到燃烧器的系统。该系统包括燃烧室、周向地围绕燃烧室的至少一部分的内衬、以及周向地围绕内衬的至少一部分的流动套管。管提供工作流体通过流动套管和内衬流动到燃烧室中的流体连通，并且管在流动套管和内衬之间成螺旋形。
本发明的另一个实施例是一种用于将工作流体供应到燃烧器的系统，该系统包括燃烧室、周向地围绕燃烧室的至少一部分的内衬、以及周向地围绕内衬的至少一部分的流动套管。管提供通过流动套管和内衬进入燃烧室中的流体连通，并且管包括成第一锐角与内衬相交的第一侧、成第二角与内衬相交且与第一侧相对的第二侧，并且第一锐角小于第二角。
本发明也可以包括一种用于将工作流体供应到燃烧器的系统，该系统包括燃烧室、周向地围绕燃烧室的至少一部分的内衬、以及周向地围绕内衬的至少一部分的流动套管。管提供工作流体通过流动套管和内衬流动到燃烧室中的流体连通。管包括具有纵轴线的卵形横截面，并且当管穿过内衬时，卵形横截面的纵轴线相对于燃烧室的纵轴线成角。
当阅览说明书时，本领域的普通技术人员将更好地领会这样的实施例的特征和方面等。
附图说明
在包括对附图的参考的说明书的剩余部分中更详细地阐述了包括对于本领域的技术人员来说是本发明的最佳模式的本发明的完整和允许公开，其中：
图1是示例性燃气涡轮机的简化侧视横截面图；
图2是根据本发明的第一实施例的图1中所示的燃烧器的一部分的简化侧视透视图；
图3是图2中所示的延迟贫喷射器的放大侧视透视图；
图4是图2中所示的延迟贫喷射器的放大侧视横截面图；以及
图5是从燃烧室的内部看到的图2中所示的延迟贫喷射器的平面图。
具体实施方式
现在将详细地参考本发明的呈现的实施例，所述实施例的一个或多个例子在附图中示出。详细描述使用数字和字母标记来表示附图中的特征。附图和描述中的相似或类似标记用于表示本发明的相似或类似部件。当在本文中使用时，术语“第一”、“第二”和“第三”可以可互换地使用以将一个部件与另一个区分开并且不旨在表示单独部件的位置或重要性。另外，术语“上游”和“下游”表示流体路径中的部件的相对位置。例如，如果流体从部件A流动到部件B，则部件A在部件B的上游。相反地，如果部件B接收来自部件A的流体流，则部件B在部件A的下游。
每个例子作为本发明的解释而不是作为本发明的限制而被提供。实际上，本领域的技术人员将显而易见可以在本发明中进行修改和变化而不脱离本发明的范围或精神。例如，作为一个实施例的一部分示出或描述的特征可以用于另一个实施例以产生又一个实施例。因此，本发明旨在涵盖属于附带的权利要求及其等效物的范围内的这样的修改和变型。
本发明的各实施例包括一种用于将工作流体供应到燃烧器的系统。所述系统大体上包括一个或多个延迟贫喷射器，所述延迟贫喷射器围绕燃烧室周向地布置以将燃料和工作流体的贫混合物喷射到燃烧室中。在特定实施例中，延迟贫喷射器可以具有各种几何轮廓以增强贫混合物喷射到燃烧室中而不增加火焰保持和/或旋涡脱落。例如，延迟贫喷射器可以包括螺旋形轮廓、锥形的横截面和/或卵形横截面。尽管为了举例说明大体上在包含到燃气涡轮机中的燃烧器的背景下描述了本发明的示例性实施例，但是本领域的普通技术人员将容易领会本发明的实施例可以应用于任何燃烧器并且不限于燃气涡轮机燃烧器，除非在权利要求中具体地叙述。
图1提供包含本发明的一个实施例的示例性燃气涡轮机10的简化横截面图。如图所示，燃气涡轮机10可以包括在前面的压缩器12、围绕中间径向布置的一个或多个燃烧器14以及在后面的涡轮机16。压缩器12和涡轮机16典型地共用连接到发电机20以产生电力的公共转子18。
压缩器12可以是轴流式压缩器，其中工作流体22（例如环境空气）进入压缩器12并且穿过固定叶24和旋转桨叶26的交替级。当固定叶24和旋转桨叶26加速并且重定向工作流体22以产生压缩工作流体22的连续流时，压缩器壳体28包含工作流体22。压缩工作流体22的大部分通过压缩器排气增压室30流动到燃烧器14。
燃烧器14可以是本领域中已知的任何类型的燃烧器。例如，如图1中所示，燃烧器壳体32可以周向地围绕燃烧器14的一些或全部以包含从压缩器12流出的压缩工作流体22。一个或多个燃料喷嘴34可以径向地布置在端盖36中以将燃料供应到在燃料喷嘴34的下游的燃烧室38。可能的燃料例如包括高炉煤气、焦炉煤气、天然气、汽化液化天然气（LNG）、氢和丙烷中的一种或多种。压缩工作流体22在到达端盖36并且反向以流动通过燃料喷嘴34与燃料混合之前可以从压缩器排气增压室30沿着燃烧室38的外部流动。燃料和压缩工作流体22的混合物流动到燃烧室38中，在燃烧室中它点燃以生成具有高温和高压的燃烧气体。燃烧气体通过过渡件40流动到涡轮机16。
涡轮机16可以包括定子42和旋转叶片44的交替级。定子42的第一级将燃烧气体重定向并且集中到旋转叶片44的第一级上。当燃烧气体经过旋转叶片44的第一级时，燃烧气体膨胀，导致旋转叶片44和转子18旋转。燃烧气体然后流动到定子42的下一级，该级将燃烧气体重定向到旋转叶片44的下一级，并且对于后续级该过程重复。
图2提供根据本发明的第一实施例的图1中所示的燃烧器14的一部分的简化透视图。如图所示，燃烧器14可以包括周向地围绕燃烧室38的至少一部分的内衬46，并且流动套管48可以周向地围绕内衬46以限定围绕内衬46的环形通道50。以该方式，来自压缩器排气增压室30的压缩工作流体22在反向以流动通过燃料喷嘴34（图1中所示）并且进入燃烧室38之前可以沿着内衬46的外部流动通过环形通道50以将对流冷却提供给内衬46。
燃烧器14还可以包括多个延迟贫喷射器或管60，延迟贫喷射器或管60可以使燃料和压缩工作流体22延迟贫喷射到燃烧室38中。管60可以围绕在燃料喷嘴34的下游的燃烧室38、内衬46和流动套管48周向地布置以提供压缩工作流体22通过流动套管48和内衬46流动到燃烧室38中的流体连通。如图2中所示，流动套管48可以包括内部燃料通道62，并且每个管60可以包括围绕管60周向布置的一个或多个燃料口64。以该方式，燃料通道62可以提供燃料通过燃料口64流动到管60中的流体连通。管60可以接收与供应到燃料喷嘴34相同或不同的燃料，并且在将混合物喷射到燃烧室38中之前或期间混合燃料和压缩工作流体22的一部分。以该方式，管60可以供应用于额外燃烧的燃料和压缩工作流体22的贫混合物以升高燃烧器14的温度，并且因此提高效率。
图3-5提供管60的放大透视图、横截面图和平面图以示出可以存在于在本发明的范围内的管60的各种实施例中的各种特征和特征的组合。例如，图3提供图2中所示的管60的放大透视图以在一个特定实施例中更清楚地示出在流动套管48和内衬46之间的管60的形状和曲率。如图3中所示，管60可以包括具有纵轴线72的椭圆形或卵形横截面70。另外，管60的纵轴线72可以在流动套管48和内衬46之间完全或部分地成螺旋形。螺旋的量将根据特定实施例而变化。例如，取决于流动套管48和内衬46之间的距离、特定管60的内部体积、纵轴线72的长度和/或其它设计考虑，纵轴线72可以在特定实施例中旋转达到80度或以上。可以预料椭圆形和螺旋的组合将减小流动通过管60的压缩工作流体22的压力损失和/或增强贫燃料-工作流体混合物和燃烧气体的混合。
图4提供图2中所示的管60的放大侧视横截面图以示出管60可以包括穿过内衬46的锥形的端部74。例如，锥形的端部74可以在内衬46的交点处使管的横截面积减小2-50%或以上以加速流体喷射到燃烧室38中并且减小靠近管60的火焰保持和/或回烧的发生率。在特定实施例中，锥形的端部74可以是对称的或不对称的。例如，如图4中所示，锥形的端部74可以包括成第一锐角78与内衬46相交的第一侧76、成第二角82与所述内衬46相交且与第一侧76相对的第二侧80。为了一致并且根据惯例，在第一侧76和第二侧80分别与内衬46的交点处从管60的外部测量第一锐角78和第二角82。取决于特定实施例，第一锐角78例如可以为2-25度，并且第一锐角78可以小于第二角82。在锥形的端部74处产生的不对称性不仅可以加速流体喷射到燃烧室38中，而且它也可以减小由喷射流体产生的靠近内衬46的热燃烧气体的旋涡脱落和相关再循环。
图5从燃烧室38的内部提供图2中所示的管60的平面图。如图所示，当管60穿过内衬46时，卵形横截面70的纵轴线72可以相对于燃烧室38的纵轴线84成角。因此，特别当与图3中所示的螺旋特征和/或图4中所示的锥形的端部74组合时，喷射的贫燃料-工作流体混合物可以进一步穿入燃烧室38中以增强燃烧气体和喷射流体之间的混合。
本领域的普通技术人员从本文中的教导将容易领会图2中所示的管60可以仅仅包括在图3-5中更详细描述和示出的特征中的一个或一个以上特征，并且本发明的实施例不限于这样的特征的任何组合，除非在权利要求中具体地叙述。另外，关于图1-5所示和所述的特定实施例也可以提供将工作流体22供应到燃烧器14的方法。该方法可以包括使来自压缩器12的工作流体22流动通过燃烧室38，并且使工作流体22的一部分转向或流动通过围绕燃烧室38周向布置的管60。在特定实施例中，该方法还可以包括在喷射到燃烧室38中之前螺旋运动和/或加速管60内部的工作流体22的转向部分。本文中所述的管60的各种特征因此可以减小导致靠近管60的火焰保持的状况，减小靠近管60的旋涡脱落和再循环区域，和/或增强燃烧室38的内部的流体穿透和混合以强化NOX的减少。
该书面描述使用例子来公开包括最佳模式的本发明，并且也使本领域的任何技术人员能够实施本发明，包括制造和使用任何装置或系统并且执行任何包含的方法。本发明的专利范围由权利要求限定，并且可以包括本领域的技术人员想到的其它例子。这样的其它例子旨在属于权利要求的范围内，只要它们包括与权利要求的文字语言没有区别的结构元件，或者只要它们包括与权利要求的文字语言无实质区别的等效结构元件。
Claims (20)
1.一种用于将工作流体供应到燃烧器的系统，所述系统包括：
a.燃烧室；
b.内衬，所述内衬周向地围绕所述燃烧室的至少一部分；
c.流动套管，所述流动套管周向地围绕所述内衬的至少一部分；以及
d.管，所述管提供工作流体通过所述流动套管和所述内衬流动到所述燃烧室中的流体连通，其中所述管在所述流动套管和所述内衬之间成螺旋形。
2.根据权利要求1所述的系统，其中所述管包括穿过所述内衬的锥形的端部。
3.根据权利要求2所述的系统，其中所述锥形的端部是不对称的。
4.根据权利要求2所述的系统，其中所述锥形的端部包括与所述内衬相交成第一锐角的第一侧、与所述内衬相交成第二角且与所述第一侧相对的第二侧，并且所述第一锐角小于所述第二角。
5.根据权利要求1所述的系统，其中所述管包括具有纵轴线的卵形横截面。
6.根据权利要求5所述的系统，其中当所述管穿过所述内衬时，所述卵形横截面的所述纵轴线相对于所述燃烧室的纵轴线成角度。
7.根据权利要求1所述的系统，其中所述管包括穿过所述内衬的锥形的端部和具有纵轴线的卵形横截面。
8.根据权利要求1所述的系统，其中所述系统还包括围绕所述管周向布置的多个燃料口。
9.根据权利要求1所述的系统，其中所述系统还包括在所述流动套管的内部与所述管流体连通的燃料通道。
10.一种用于将工作流体供应到燃烧器的系统，所述系统包括：
a.燃烧室；
b.内衬，所述内衬周向地围绕所述燃烧室的至少一部分；
c.流动套管，所述流动套管周向地围绕所述内衬的至少一部分；以及
d.管，所述管提供通过所述流动套管和所述内衬进入所述燃烧室中的流体连通，其中所述管包括与所述内衬相交成第一锐角的第一侧、与所述内衬相交成第二角且与所述第一侧相对的第二侧，并且所述第一锐角小于所述第二角。
11.根据权利要求10所述的系统，其中所述管在所述流动套管和所述内衬之间成螺旋形。
12.根据权利要求10所述的系统，其中所述管包括具有纵轴线的卵形横截面。
13.根据权利要求12所述的系统，其中当所述管穿过所述内衬时，所述卵形横截面的所述纵轴线相对于所述燃烧室的纵轴线成角度。
14.根据权利要求10所述的系统，其中所述管包括在所述流动套管和所述内衬之间成螺旋形的具有纵轴线的卵形横截面。
15.根据权利要求10所述的系统，其中所述系统还包括围绕所述管周向布置的多个燃料口。
16.根据权利要求10所述的系统，其中所述系统还包括在所述流动套管的内部与所述管流体连通的燃料通道。
17.一种用于将工作流体供应到燃烧器的系统，所述系统包括：
a.燃烧室；
b.内衬，所述内衬周向地围绕所述燃烧室的至少一部分；
c.流动套管，所述流动套管周向地围绕所述内衬的至少一部分；以及
d.管，所述管提供工作流体通过所述流动套管和所述内衬流动到所述燃烧室中的流体连通，其中所述管包括具有纵轴线的卵形横截面，并且当所述管穿过所述内衬时，所述卵形横截面的所述纵轴线相对于所述燃烧室的纵轴线成角度。
18.根据权利要求17所述的系统，其中所述管在所述流动套管和所述内衬之间成螺旋形。
19.根据权利要求17所述的系统，其中所述管包括穿过所述内衬的锥形的端部。
20.根据权利要求19所述的系统，其中所述锥形的端部包括与所述内衬相交成第一锐角的第一侧、与所述内衬相交成第二角且与所述第一侧相对的第二侧，并且所述第一锐角小于所述第二角。
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/417405 | 2012-03-12 | ||
| US13/417,405 US9097424B2 (en) | 2012-03-12 | 2012-03-12 | System for supplying a fuel and working fluid mixture to a combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103307635A true CN103307635A (zh) | 2013-09-18 |
| CN103307635B CN103307635B (zh) | 2016-10-19 |
Family
ID=47827028
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310078202.3A Active CN103307635B (zh) | 2012-03-12 | 2013-03-12 | 用于将工作流体供应到燃烧器的系统 |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US9097424B2 (zh) |
| EP (2) | EP2639507B1 (zh) |
| JP (1) | JP6122315B2 (zh) |
| CN (1) | CN103307635B (zh) |
| RU (1) | RU2013110456A (zh) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018000799A1 (zh) * | 2016-06-27 | 2018-01-04 | 杨航 | 一种动力装置 |
Families Citing this family (87)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101981272B (zh) | 2008-03-28 | 2014-06-11 | 埃克森美孚上游研究公司 | 低排放发电和烃采收系统及方法 |
| CN104098070B (zh) | 2008-03-28 | 2016-04-13 | 埃克森美孚上游研究公司 | 低排放发电和烃采收系统及方法 |
| SG195533A1 (en) | 2008-10-14 | 2013-12-30 | Exxonmobil Upstream Res Co | Methods and systems for controlling the products of combustion |
| EA023673B1 (ru) | 2009-11-12 | 2016-06-30 | Эксонмобил Апстрим Рисерч Компани | Система и способ для низкоэмиссионного производства электроэнергии и извлечения углеводородов |
| PL2588727T3 (pl) | 2010-07-02 | 2019-05-31 | Exxonmobil Upstream Res Co | Spalanie stechiometryczne z recyrkulacją gazów spalinowych i chłodnicą bezpośredniego kontaktu |
| JP5913305B2 (ja) | 2010-07-02 | 2016-04-27 | エクソンモービル アップストリーム リサーチ カンパニー | 低エミッション発電システム及び方法 |
| BR112012031153A2 (pt) | 2010-07-02 | 2016-11-08 | Exxonmobil Upstream Res Co | sistemas e métodos de geração de energia de triplo-ciclo de baixa emissão |
| JP5906555B2 (ja) | 2010-07-02 | 2016-04-20 | エクソンモービル アップストリーム リサーチ カンパニー | 排ガス再循環方式によるリッチエアの化学量論的燃焼 |
| TWI563165B (en) | 2011-03-22 | 2016-12-21 | Exxonmobil Upstream Res Co | Power generation system and method for generating power |
| TWI563166B (en) | 2011-03-22 | 2016-12-21 | Exxonmobil Upstream Res Co | Integrated generation systems and methods for generating power |
| TWI564474B (zh) | 2011-03-22 | 2017-01-01 | 艾克頌美孚上游研究公司 | 於渦輪系統中控制化學計量燃燒的整合系統和使用彼之產生動力的方法 |
| TWI593872B (zh) | 2011-03-22 | 2017-08-01 | 艾克頌美孚上游研究公司 | 整合系統及產生動力之方法 |
| CN103917826B (zh) * | 2011-11-17 | 2016-08-24 | 通用电气公司 | 涡轮机燃烧器组件和操作涡轮机的方法 |
| CN104428490B (zh) | 2011-12-20 | 2018-06-05 | 埃克森美孚上游研究公司 | 提高的煤层甲烷生产 |
| US9353682B2 (en) | 2012-04-12 | 2016-05-31 | General Electric Company | Methods, systems and apparatus relating to combustion turbine power plants with exhaust gas recirculation |
| US9784185B2 (en) | 2012-04-26 | 2017-10-10 | General Electric Company | System and method for cooling a gas turbine with an exhaust gas provided by the gas turbine |
| US10273880B2 (en) | 2012-04-26 | 2019-04-30 | General Electric Company | System and method of recirculating exhaust gas for use in a plurality of flow paths in a gas turbine engine |
| US9310078B2 (en) * | 2012-10-31 | 2016-04-12 | General Electric Company | Fuel injection assemblies in combustion turbine engines |
| US9574496B2 (en) | 2012-12-28 | 2017-02-21 | General Electric Company | System and method for a turbine combustor |
| US9869279B2 (en) | 2012-11-02 | 2018-01-16 | General Electric Company | System and method for a multi-wall turbine combustor |
| US9611756B2 (en) | 2012-11-02 | 2017-04-04 | General Electric Company | System and method for protecting components in a gas turbine engine with exhaust gas recirculation |
| US9599070B2 (en) | 2012-11-02 | 2017-03-21 | General Electric Company | System and method for oxidant compression in a stoichiometric exhaust gas recirculation gas turbine system |
| US9708977B2 (en) | 2012-12-28 | 2017-07-18 | General Electric Company | System and method for reheat in gas turbine with exhaust gas recirculation |
| US10161312B2 (en) | 2012-11-02 | 2018-12-25 | General Electric Company | System and method for diffusion combustion with fuel-diluent mixing in a stoichiometric exhaust gas recirculation gas turbine system |
| US10215412B2 (en) | 2012-11-02 | 2019-02-26 | General Electric Company | System and method for load control with diffusion combustion in a stoichiometric exhaust gas recirculation gas turbine system |
| US9803865B2 (en) | 2012-12-28 | 2017-10-31 | General Electric Company | System and method for a turbine combustor |
| US10107495B2 (en) | 2012-11-02 | 2018-10-23 | General Electric Company | Gas turbine combustor control system for stoichiometric combustion in the presence of a diluent |
| US9631815B2 (en) | 2012-12-28 | 2017-04-25 | General Electric Company | System and method for a turbine combustor |
| US10208677B2 (en) | 2012-12-31 | 2019-02-19 | General Electric Company | Gas turbine load control system |
| US9581081B2 (en) | 2013-01-13 | 2017-02-28 | General Electric Company | System and method for protecting components in a gas turbine engine with exhaust gas recirculation |
| US9512759B2 (en) | 2013-02-06 | 2016-12-06 | General Electric Company | System and method for catalyst heat utilization for gas turbine with exhaust gas recirculation |
| TW201502356A (zh) | 2013-02-21 | 2015-01-16 | Exxonmobil Upstream Res Co | 氣渦輪機排氣中氧之減少 |
| US9938861B2 (en) | 2013-02-21 | 2018-04-10 | Exxonmobil Upstream Research Company | Fuel combusting method |
| RU2637609C2 (ru) | 2013-02-28 | 2017-12-05 | Эксонмобил Апстрим Рисерч Компани | Система и способ для камеры сгорания турбины |
| TW201500635A (zh) | 2013-03-08 | 2015-01-01 | Exxonmobil Upstream Res Co | 處理廢氣以供用於提高油回收 |
| US9784182B2 (en) | 2013-03-08 | 2017-10-10 | Exxonmobil Upstream Research Company | Power generation and methane recovery from methane hydrates |
| US20140250945A1 (en) | 2013-03-08 | 2014-09-11 | Richard A. Huntington | Carbon Dioxide Recovery |
| US9618261B2 (en) | 2013-03-08 | 2017-04-11 | Exxonmobil Upstream Research Company | Power generation and LNG production |
| US9617914B2 (en) | 2013-06-28 | 2017-04-11 | General Electric Company | Systems and methods for monitoring gas turbine systems having exhaust gas recirculation |
| US9835089B2 (en) | 2013-06-28 | 2017-12-05 | General Electric Company | System and method for a fuel nozzle |
| US9631542B2 (en) | 2013-06-28 | 2017-04-25 | General Electric Company | System and method for exhausting combustion gases from gas turbine engines |
| TWI654368B (zh) | 2013-06-28 | 2019-03-21 | 美商艾克頌美孚上游研究公司 | 用於控制在廢氣再循環氣渦輪機系統中的廢氣流之系統、方法與媒體 |
| US9903588B2 (en) | 2013-07-30 | 2018-02-27 | General Electric Company | System and method for barrier in passage of combustor of gas turbine engine with exhaust gas recirculation |
| US9587510B2 (en) | 2013-07-30 | 2017-03-07 | General Electric Company | System and method for a gas turbine engine sensor |
| US9951658B2 (en) | 2013-07-31 | 2018-04-24 | General Electric Company | System and method for an oxidant heating system |
| US20150052905A1 (en) * | 2013-08-20 | 2015-02-26 | General Electric Company | Pulse Width Modulation for Control of Late Lean Liquid Injection Velocity |
| WO2015030927A1 (en) * | 2013-08-30 | 2015-03-05 | United Technologies Corporation | Contoured dilution passages for a gas turbine engine combustor |
| EP3066387B1 (en) * | 2013-11-04 | 2019-10-02 | United Technologies Corporation | Assembly for a turbine engine with acombustor comprising a quench air aperture |
| US10030588B2 (en) | 2013-12-04 | 2018-07-24 | General Electric Company | Gas turbine combustor diagnostic system and method |
| US9752458B2 (en) | 2013-12-04 | 2017-09-05 | General Electric Company | System and method for a gas turbine engine |
| US10227920B2 (en) | 2014-01-15 | 2019-03-12 | General Electric Company | Gas turbine oxidant separation system |
| US9915200B2 (en) | 2014-01-21 | 2018-03-13 | General Electric Company | System and method for controlling the combustion process in a gas turbine operating with exhaust gas recirculation |
| US9863267B2 (en) | 2014-01-21 | 2018-01-09 | General Electric Company | System and method of control for a gas turbine engine |
| EP3102887B1 (en) * | 2014-01-24 | 2023-11-15 | RTX Corporation | Axial staged combustor with restricted main fuel injector |
| US10079564B2 (en) | 2014-01-27 | 2018-09-18 | General Electric Company | System and method for a stoichiometric exhaust gas recirculation gas turbine system |
| US10139111B2 (en) * | 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 |
| US10047633B2 (en) | 2014-05-16 | 2018-08-14 | General Electric Company | Bearing housing |
| US9885290B2 (en) | 2014-06-30 | 2018-02-06 | General Electric Company | Erosion suppression system and method in an exhaust gas recirculation gas turbine system |
| US10655542B2 (en) | 2014-06-30 | 2020-05-19 | General Electric Company | Method and system for startup of gas turbine system drive trains with exhaust gas recirculation |
| US10060359B2 (en) | 2014-06-30 | 2018-08-28 | General Electric Company | Method and system for combustion control for gas turbine system with exhaust gas recirculation |
| US9851107B2 (en) * | 2014-07-18 | 2017-12-26 | Ansaldo Energia Ip Uk Limited | Axially staged gas turbine combustor with interstage premixer |
| US20160047317A1 (en) * | 2014-08-14 | 2016-02-18 | General Electric Company | Fuel injector assemblies in combustion turbine engines |
| US9819292B2 (en) | 2014-12-31 | 2017-11-14 | General Electric Company | Systems and methods to respond to grid overfrequency events for a stoichiometric exhaust recirculation gas turbine |
| US9869247B2 (en) | 2014-12-31 | 2018-01-16 | General Electric Company | Systems and methods of estimating a combustion equivalence ratio in a gas turbine with exhaust gas recirculation |
| US10788212B2 (en) | 2015-01-12 | 2020-09-29 | General Electric Company | System and method for an oxidant passageway in a gas turbine system with exhaust gas recirculation |
| US10132498B2 (en) * | 2015-01-20 | 2018-11-20 | United Technologies Corporation | Thermal barrier coating of a combustor dilution hole |
| US10094566B2 (en) | 2015-02-04 | 2018-10-09 | General Electric Company | Systems and methods for high volumetric oxidant flow in gas turbine engine with exhaust gas recirculation |
| US10253690B2 (en) | 2015-02-04 | 2019-04-09 | General Electric Company | Turbine system with exhaust gas recirculation, separation and extraction |
| US10316746B2 (en) | 2015-02-04 | 2019-06-11 | General Electric Company | Turbine system with exhaust gas recirculation, separation and extraction |
| US10267270B2 (en) | 2015-02-06 | 2019-04-23 | General Electric Company | Systems and methods for carbon black production with a gas turbine engine having exhaust gas recirculation |
| US10145269B2 (en) | 2015-03-04 | 2018-12-04 | General Electric Company | System and method for cooling discharge flow |
| US10480792B2 (en) | 2015-03-06 | 2019-11-19 | General Electric Company | Fuel staging in a gas turbine engine |
| US9976487B2 (en) * | 2015-12-22 | 2018-05-22 | General Electric Company | Staged fuel and air injection in combustion systems of gas turbines |
| US20170260866A1 (en) * | 2016-03-10 | 2017-09-14 | Siemens Energy, Inc. | Ducting arrangement in a combustion system of a gas turbine engine |
| US11181273B2 (en) | 2016-09-27 | 2021-11-23 | Siemens Energy Global GmbH & Co. KG | Fuel oil axial stage combustion for improved turbine combustor performance |
| US11149952B2 (en) | 2016-12-07 | 2021-10-19 | Raytheon Technologies Corporation | Main mixer in an axial staged combustor for a gas turbine engine |
| US20180283695A1 (en) * | 2017-04-03 | 2018-10-04 | United Technologies Corporation | Combustion panel grommet |
| US20180340689A1 (en) * | 2017-05-25 | 2018-11-29 | General Electric Company | Low Profile Axially Staged Fuel Injector |
| US10816203B2 (en) * | 2017-12-11 | 2020-10-27 | General Electric Company | Thimble assemblies for introducing a cross-flow into a secondary combustion zone |
| US11137144B2 (en) | 2017-12-11 | 2021-10-05 | General Electric Company | Axial fuel staging system for gas turbine combustors |
| US11187415B2 (en) * | 2017-12-11 | 2021-11-30 | General Electric Company | Fuel injection assemblies for axial fuel staging in gas turbine combustors |
| GB201902693D0 (en) * | 2019-02-28 | 2019-04-17 | Rolls Royce Plc | Combustion liner and gas turbine engine comprising a combustion liner |
| US11933223B2 (en) * | 2019-04-18 | 2024-03-19 | Rtx Corporation | Integrated additive fuel injectors for attritable engines |
| KR102138013B1 (ko) * | 2019-05-30 | 2020-07-27 | 두산중공업 주식회사 | 축방향 연료 스테이징 시스템을 갖는 연소기 및 이를 포함하는 가스터빈 |
| US11371709B2 (en) | 2020-06-30 | 2022-06-28 | General Electric Company | Combustor air flow path |
| US11920790B2 (en) | 2021-11-03 | 2024-03-05 | General Electric Company | Wavy annular dilution slots for lower emissions |
| CN216617683U (zh) * | 2022-02-16 | 2022-05-27 | 烟台杰瑞石油装备技术有限公司 | 涡轮发动机进气冷却系统以及涡轮发动机设备 |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3303645A (en) * | 1963-04-30 | 1967-02-14 | Hitachi Ltd | Ultra-high temperature burners |
| US4955191A (en) * | 1987-10-27 | 1990-09-11 | Kabushiki Kaisha Toshiba | Combustor for gas turbine |
| US20020189260A1 (en) * | 2001-06-19 | 2002-12-19 | Snecma Moteurs | Gas turbine combustion chambers |
| US20100018209A1 (en) * | 2008-07-28 | 2010-01-28 | Siemens Power Generation, Inc. | Integral flow sleeve and fuel injector assembly |
| CN101839177A (zh) * | 2009-01-07 | 2010-09-22 | 通用电气公司 | 延迟贫油喷射的燃料分级构造 |
| US20110056206A1 (en) * | 2009-09-08 | 2011-03-10 | Wiebe David J | Fuel Injector for Use in a Gas Turbine Engine |
Family Cites Families (65)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2922279A (en) | 1956-02-02 | 1960-01-26 | Power Jets Res & Dev Ltd | Combustion apparatus and ignitor employing vaporized fuel |
| US3826078A (en) * | 1971-12-15 | 1974-07-30 | Phillips Petroleum Co | Combustion process with selective heating of combustion and quench air |
| FR2221621B1 (zh) | 1973-03-13 | 1976-09-10 | Snecma | |
| US4045956A (en) | 1974-12-18 | 1977-09-06 | United Technologies Corporation | Low emission combustion chamber |
| US4040252A (en) | 1976-01-30 | 1977-08-09 | United Technologies Corporation | Catalytic premixing combustor |
| US4112676A (en) | 1977-04-05 | 1978-09-12 | Westinghouse Electric Corp. | Hybrid combustor with staged injection of pre-mixed fuel |
| US4301657A (en) * | 1978-05-04 | 1981-11-24 | Caterpillar Tractor Co. | Gas turbine combustion chamber |
| US4253301A (en) | 1978-10-13 | 1981-03-03 | General Electric Company | Fuel injection staged sectoral combustor for burning low-BTU fuel gas |
| US4288980A (en) | 1979-06-20 | 1981-09-15 | Brown Boveri Turbomachinery, Inc. | Combustor for use with gas turbines |
| US4687436A (en) * | 1986-08-05 | 1987-08-18 | Tadao Shigeta | Gasified fuel combustion apparatus |
| US4928481A (en) * | 1988-07-13 | 1990-05-29 | Prutech Ii | Staged low NOx premix gas turbine combustor |
| JPH0684817B2 (ja) | 1988-08-08 | 1994-10-26 | 株式会社日立製作所 | ガスタービン燃焼器及びその運転方法 |
| US4926630A (en) * | 1988-12-12 | 1990-05-22 | Sundstrand Corporation | Jet air cooled turbine shroud for improved swirl cooling and mixing |
| US5749219A (en) | 1989-11-30 | 1998-05-12 | United Technologies Corporation | Combustor with first and second zones |
| US5099644A (en) | 1990-04-04 | 1992-03-31 | General Electric Company | Lean staged combustion assembly |
| EP0540167A1 (en) | 1991-09-27 | 1993-05-05 | General Electric Company | A fuel staged premixed dry low NOx combustor |
| FR2689567B1 (fr) | 1992-04-01 | 1994-05-27 | Snecma | Injecteur de carburant pour chambre de post-combustion d'une turbomachine. |
| US5687572A (en) * | 1992-11-02 | 1997-11-18 | Alliedsignal Inc. | Thin wall combustor with backside impingement cooling |
| JP3335713B2 (ja) | 1993-06-28 | 2002-10-21 | 株式会社東芝 | ガスタービン燃焼器 |
| US5613357A (en) * | 1993-07-07 | 1997-03-25 | Mowill; R. Jan | Star-shaped single stage low emission combustor system |
| JP2950720B2 (ja) * | 1994-02-24 | 1999-09-20 | 株式会社東芝 | ガスタービン燃焼装置およびその燃焼制御方法 |
| AU681271B2 (en) | 1994-06-07 | 1997-08-21 | Westinghouse Electric Corporation | Method and apparatus for sequentially staged combustion using a catalyst |
| US5974781A (en) | 1995-12-26 | 1999-11-02 | General Electric Company | Hybrid can-annular combustor for axial staging in low NOx combustors |
| US6047550A (en) | 1996-05-02 | 2000-04-11 | General Electric Co. | Premixing dry low NOx emissions combustor with lean direct injection of gas fuel |
| US6070406A (en) | 1996-11-26 | 2000-06-06 | Alliedsignal, Inc. | Combustor dilution bypass system |
| US5966926A (en) * | 1997-05-28 | 1999-10-19 | Capstone Turbine Corporation | Liquid fuel injector purge system |
| US6925809B2 (en) | 1999-02-26 | 2005-08-09 | R. Jan Mowill | Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities |
| GB9911871D0 (en) * | 1999-05-22 | 1999-07-21 | Rolls Royce Plc | A gas turbine engine and a method of controlling a gas turbine engine |
| US6253538B1 (en) | 1999-09-27 | 2001-07-03 | Pratt & Whitney Canada Corp. | Variable premix-lean burn combustor |
| DE10214574A1 (de) * | 2002-04-02 | 2003-10-16 | Rolls Royce Deutschland | Brennkammer für ein Luftstrahltriebwerk mit Sekundärluftzuführung |
| GB0219461D0 (en) | 2002-08-21 | 2002-09-25 | Rolls Royce Plc | Fuel injection arrangement |
| WO2004035187A2 (en) | 2002-10-15 | 2004-04-29 | Vast Power Systems, Inc. | Method and apparatus for mixing fluids |
| US6868676B1 (en) | 2002-12-20 | 2005-03-22 | General Electric Company | Turbine containing system and an injector therefor |
| US6935116B2 (en) | 2003-04-28 | 2005-08-30 | Power Systems Mfg., Llc | Flamesheet combustor |
| GB0319329D0 (en) | 2003-08-16 | 2003-09-17 | Rolls Royce Plc | Variable geometry combustor |
| GB0323255D0 (en) | 2003-10-04 | 2003-11-05 | Rolls Royce Plc | Method and system for controlling fuel supply in a combustion turbine engine |
| US7425127B2 (en) | 2004-06-10 | 2008-09-16 | Georgia Tech Research Corporation | Stagnation point reverse flow combustor |
| WO2005124231A2 (en) | 2004-06-11 | 2005-12-29 | Vast Power Systems, Inc. | Low emissions combustion apparatus and method |
| JP2006138566A (ja) | 2004-11-15 | 2006-06-01 | Hitachi Ltd | ガスタービン燃焼器及びその液体燃料噴射ノズル |
| US7237384B2 (en) | 2005-01-26 | 2007-07-03 | Peter Stuttaford | Counter swirl shear mixer |
| US7137256B1 (en) | 2005-02-28 | 2006-11-21 | Peter Stuttaford | Method of operating a combustion system for increased turndown capability |
| US7966822B2 (en) | 2005-06-30 | 2011-06-28 | General Electric Company | Reverse-flow gas turbine combustion system |
| US7878000B2 (en) | 2005-12-20 | 2011-02-01 | General Electric Company | Pilot fuel injector for mixer assembly of a high pressure gas turbine engine |
| US7665309B2 (en) | 2007-09-14 | 2010-02-23 | Siemens Energy, Inc. | Secondary fuel delivery system |
| US8387398B2 (en) | 2007-09-14 | 2013-03-05 | Siemens Energy, Inc. | Apparatus and method for controlling the secondary injection of fuel |
| US8528340B2 (en) | 2008-07-28 | 2013-09-10 | Siemens Energy, Inc. | Turbine engine flow sleeve |
| US20110146226A1 (en) * | 2008-12-31 | 2011-06-23 | Frontline Aerospace, Inc. | Recuperator for gas turbine engines |
| US8112216B2 (en) | 2009-01-07 | 2012-02-07 | General Electric Company | Late lean injection with adjustable air splits |
| EP2206964A3 (en) | 2009-01-07 | 2012-05-02 | General Electric Company | Late lean injection fuel injector configurations |
| US20100223930A1 (en) * | 2009-03-06 | 2010-09-09 | General Electric Company | Injection device for a turbomachine |
| US8689559B2 (en) | 2009-03-30 | 2014-04-08 | General Electric Company | Secondary combustion system for reducing the level of emissions generated by a turbomachine |
| US8991192B2 (en) | 2009-09-24 | 2015-03-31 | Siemens Energy, Inc. | Fuel nozzle assembly for use as structural support for a duct structure in a combustor of a gas turbine engine |
| US20110131998A1 (en) | 2009-12-08 | 2011-06-09 | Vaibhav Nadkarni | Fuel injection in secondary fuel nozzle |
| US8381532B2 (en) | 2010-01-27 | 2013-02-26 | General Electric Company | Bled diffuser fed secondary combustion system for gas turbines |
| US8769955B2 (en) | 2010-06-02 | 2014-07-08 | Siemens Energy, Inc. | Self-regulating fuel staging port for turbine combustor |
| US8601820B2 (en) * | 2011-06-06 | 2013-12-10 | General Electric Company | Integrated late lean injection on a combustion liner and late lean injection sleeve assembly |
| US8919125B2 (en) | 2011-07-06 | 2014-12-30 | General Electric Company | Apparatus and systems relating to fuel injectors and fuel passages in gas turbine engines |
| US9010120B2 (en) * | 2011-08-05 | 2015-04-21 | General Electric Company | Assemblies and apparatus related to integrating late lean injection into combustion turbine engines |
| US9303872B2 (en) * | 2011-09-15 | 2016-04-05 | General Electric Company | Fuel injector |
| US9010082B2 (en) * | 2012-01-03 | 2015-04-21 | General Electric Company | Turbine engine and method for flowing air in a turbine engine |
| US9170024B2 (en) | 2012-01-06 | 2015-10-27 | General Electric Company | System and method for supplying a working fluid to a combustor |
| US9284888B2 (en) * | 2012-04-25 | 2016-03-15 | General Electric Company | System for supplying fuel to late-lean fuel injectors of a combustor |
| US9200808B2 (en) * | 2012-04-27 | 2015-12-01 | General Electric Company | System for supplying fuel to a late-lean fuel injector of a combustor |
| US8479518B1 (en) * | 2012-07-11 | 2013-07-09 | General Electric Company | System for supplying a working fluid to a combustor |
| US20140174090A1 (en) * | 2012-12-21 | 2014-06-26 | General Electric Company | System for supplying fuel to a combustor |
-
2012
- 2012-03-12 US US13/417,405 patent/US9097424B2/en active Active
-
2013
- 2013-03-06 EP EP13157973.2A patent/EP2639507B1/en active Active
- 2013-03-06 EP EP19157309.6A patent/EP3514455A1/en not_active Withdrawn
- 2013-03-07 JP JP2013044911A patent/JP6122315B2/ja active Active
- 2013-03-11 RU RU2013110456/06A patent/RU2013110456A/ru not_active Application Discontinuation
- 2013-03-12 CN CN201310078202.3A patent/CN103307635B/zh active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3303645A (en) * | 1963-04-30 | 1967-02-14 | Hitachi Ltd | Ultra-high temperature burners |
| US4955191A (en) * | 1987-10-27 | 1990-09-11 | Kabushiki Kaisha Toshiba | Combustor for gas turbine |
| US20020189260A1 (en) * | 2001-06-19 | 2002-12-19 | Snecma Moteurs | Gas turbine combustion chambers |
| US20100018209A1 (en) * | 2008-07-28 | 2010-01-28 | Siemens Power Generation, Inc. | Integral flow sleeve and fuel injector assembly |
| CN101839177A (zh) * | 2009-01-07 | 2010-09-22 | 通用电气公司 | 延迟贫油喷射的燃料分级构造 |
| US20110056206A1 (en) * | 2009-09-08 | 2011-03-10 | Wiebe David J | Fuel Injector for Use in a Gas Turbine Engine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018000799A1 (zh) * | 2016-06-27 | 2018-01-04 | 杨航 | 一种动力装置 |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2013110456A (ru) | 2014-09-20 |
| EP2639507A3 (en) | 2015-10-21 |
| EP2639507A2 (en) | 2013-09-18 |
| JP6122315B2 (ja) | 2017-04-26 |
| EP2639507B1 (en) | 2019-09-04 |
| US20130232980A1 (en) | 2013-09-12 |
| US9097424B2 (en) | 2015-08-04 |
| JP2013190198A (ja) | 2013-09-26 |
| CN103307635B (zh) | 2016-10-19 |
| EP3514455A1 (en) | 2019-07-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103307635A (zh) | 用于将工作流体供应到燃烧器的系统 | |
| US9284888B2 (en) | System for supplying fuel to late-lean fuel injectors of a combustor | |
| US9151500B2 (en) | System for supplying a fuel and a working fluid through a liner to a combustion chamber | |
| US9200808B2 (en) | System for supplying fuel to a late-lean fuel injector of a combustor | |
| US8904798B2 (en) | Combustor | |
| JP5411468B2 (ja) | タービンエンジン燃料送給装置及びシステム | |
| US20120282558A1 (en) | Combustor nozzle and method for supplying fuel to a combustor | |
| CN101153558A (zh) | 预混设备、包括预混设备的燃气涡轮机及使用方法 | |
| US20120058437A1 (en) | Apparatus and method for mixing fuel in a gas turbine nozzle | |
| US8745986B2 (en) | System and method of supplying fuel to a gas turbine | |
| US20130283802A1 (en) | Combustor | |
| JP2015513060A (ja) | 燃焼器ノズルおよび燃焼器に燃料を供給する方法 | |
| JP2011141112A (ja) | 燃料を供給するための装置及び方法 | |
| US20130086920A1 (en) | Combustor and method for supplying flow to a combustor | |
| EP2685163B1 (en) | Premix burner of the multi-cone type for a gas turbine | |
| US20200063964A1 (en) | Premix fuel nozzle for a gas turbine and combustor | |
| CN105247285A (zh) | 用于低氮氧化物预混气体燃烧器的燃烧的方法 | |
| CN103939944A (zh) | 一种用于化学回热循环的双瓣旋流式双燃料喷嘴 | |
| JP2012137228A (ja) | ガスタービン燃焼器 |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240103 Address after: Swiss Baden Patentee after: GENERAL ELECTRIC CO. LTD. Address before: New York State, USA Patentee before: General Electric Co. |
|
| TR01 | Transfer of patent right |