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公开(公告)号：JP2014048040A
公开(公告)日：2014-03-17
申请号：JP2013181240
申请日：2013-09-02
Inventor： FRANKLIN MARIE GENIN , MARCEL RIEKER , BETTINA PAIKERT
CPC classification number: F23D14/02 , F23C2900/07002 , F23D14/62 , F23D17/002 , F23D2900/14021 , F23R3/286
Abstract: PROBLEM TO BE SOLVED: To provide a smooth transition of flow limiting contours from a swirl generator into a mixing zone.SOLUTION: There is provided a premix burner for operating a heat generator, the burner at least having the swirl generator, a mixing section disposed downstream of the swirl generator and a transition piece for transferring the swirl flow from the swirl generator into the mixing section. The transition piece comprises an inlet connected to the swirl generator, an outlet connected to a mixing tube, and a continuing flow limiting interior contour between the inlet and the outlet. A least in an inlet section, the interior contour is curved radially inwards towards the inner diameter of the mixing tube, and at the outlet, the interior contour is flush with an interior flow limiting contour of the mixing tube.
Abstract translation: 要解决的问题：提供流动限制轮廓从涡流发生器到混合区域的平滑过渡。解决方案：提供一种用于操作发热体的预混合燃烧器，至少具有涡流发生器的燃烧器，设置的混合部分 在涡流发生器的下游，以及用于将来自涡流发生器的涡流传递到混合部分的过渡件。 过渡件包括连接到涡流发生器的入口，连接到混合管的出口以及在入口和出口之间的连续流动限制内部轮廓。 至少在入口部分中，内部轮廓朝向混合管的内径径向向内弯曲，并且在出口处，内部轮廓与混合管的内部流动限制轮廓齐平。
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72.发明专利Method for mixing dilution air in sequential combustion system of gas turbine 有权用于混合气体涡轮机顺序燃烧系统中的稀释空气的方法
公开(公告)号：JP2014044045A
公开(公告)日：2014-03-13
申请号：JP2013174435
申请日：2013-08-26
Inventor： MIRKO RUBEN BOTHIEN
CPC classification number: F23R3/28 , F23R3/06 , F23R3/12 , F23R3/26 , F23R2900/00013 , F23R2900/03341 , Y02E20/14
Abstract: PROBLEM TO BE SOLVED: To provide a method of improving mixing of dilution air and hot combustion products of a first stage combustor by injecting dilution air with a swirl.SOLUTION: The hot gases of the first combustor are admitted to at least one intermediate turbine or directly or indirectly to at least one second combustor. The hot gases of the second combustor are admitted to a further turbine or directly or indirectly to an energy recovery. At least one combustor is operated under a caloric combustion path having a cylindrical architecture. At least one dilution air injection is introduced into the first combustor. A swirl flow caused by the dilution air injection is directed against or in the direction of the original swirl flow inside of the first combustor.
Abstract translation: 要解决的问题：提供一种通过喷射具有漩涡的稀释空气来改善稀释空气和第一级燃烧器的热燃烧产物的混合的方法。解决方案：第一燃烧器的热气体被允许进入至少一个中间涡轮机或 直接或间接地连接到至少一个第二燃烧器。 第二燃烧器的热气体被允许进一步涡轮机，或直接或间接地进入能量回收。 在具有圆柱形结构的热量燃烧路径下操作至少一个燃烧器。 至少一次稀释空气注入被引入到第一燃烧器中。 由稀释空气喷射引起的涡旋流被引向第一燃烧器内部的原始涡流的方向或者朝向第一燃烧器内部的原始涡流的方向。
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73.发明专利Method for mixing dilution air in sequential combustion system of gas turbine 有权用于混合气体涡轮机顺序燃烧系统中的稀释空气的方法
公开(公告)号：JP2014044044A
公开(公告)日：2014-03-13
申请号：JP2013174433
申请日：2013-08-26
Inventor： EROGLU ADNAM , EWALD FREITAG
IPC: F23R3/42 , F02C3/14 , F02C7/18 , F02C7/22 , F02C7/228 , F23R3/16 , F23R3/20 , F23R3/28 , F23R3/30 , F23R3/34 , F23R3/46
CPC classification number: F23R3/34 , F02C7/22 , F02C7/228 , F23R3/06 , F23R3/20 , F23R3/346 , F23R3/42 , F23R2900/00014 , F23R2900/03042 , F23R2900/03341 , Y02E20/14
Abstract: PROBLEM TO BE SOLVED: To provide a method for mixing a dilution air with a hot main flow in a sequential combustion system of a gas turbine (100).SOLUTION: The gas turbine essentially comprises: at least one compressor; and a first combustor which is connected downstream from the compressor. The hot gases of the first combustor are supplied to at least one intermediate turbine or directly or indirectly to at least one second combustor. The hot gases of the second combustor are supplied to a further turbine or directly or indirectly to an energy recovery. First combustor liner (104) cooling air is injected coaxially with second combustor liner (105) cooling air, accompanied with a sufficient excess pressure margin with respect to the second combustor liner cooling air.
Abstract translation: 要解决的问题：提供一种在燃气轮机（100）的顺序燃烧系统中混合稀释空气与热主流的方法。解决方案：燃气轮机基本上包括：至少一个压缩机; 以及连接在压缩机下游的第一燃烧器。 第一燃烧器的热气体被供应到至少一个中间涡轮机，或者直接或间接地供给至少一个第二燃烧器。 将第二燃烧器的热气体供应到另外的涡轮机，或者直接或间接地供应到能量回收。 第一燃烧器衬套（104）冷却空气与第二燃烧器衬套（105）同轴地喷射冷却空气，伴随着相对于第二燃烧器衬套冷却空气的足够的过大的压力裕度。
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公开(公告)号：JP2014020373A
公开(公告)日：2014-02-03
申请号：JP2013145178
申请日：2013-07-11
Inventor： ADRIEN FRANZ STUDERUS , ULRICH ROBERT STEIGER , JAKOBY RALF , WAELCHLI RENE
CPC classification number: F02C9/18 , F02C3/00 , F02C3/04 , F02C7/18 , F02C7/26 , F04D27/0207 , F04D27/0292 , F05D2260/232 , F05D2270/101 , Y02T50/675
Abstract: PROBLEM TO BE SOLVED: To provide a surging control method for a gas turbine capable of operating a gas turbine at improved efficiency while actively preventing surging of a compressor.SOLUTION: A gas turbine engine surging controlling method includes steps of: providing a gas turbine engine 10 including a compressor 20, a combustor 30 positioned on a downstream side of the compressor 20 and having a high temperature gas passage, and a turbine 40 positioned on a downstream side of the combustor 30 and having a high temperature gas passage; monitoring the gas turbine engine 10 relating to potential surging conditions; controlling a blow-off flow from the compressor 20 for the control purpose of avoiding the surging conditions based on the monitoring; and directing the blow-off flow to at least one of the plural high pressure gas passages, and bypassing at least a part of the combustor.
Abstract translation: 要解决的问题：提供一种能够以更高的效率运行燃气轮机的燃气轮机的喘振控制方法，同时主动地防止压缩机的喘振。解决方案：一种燃气涡轮发动机起动控制方法，包括以下步骤：提供燃气涡轮发动机 10包括压缩机20，位于压缩机20的下游侧并具有高温气体通道的燃烧器30和位于燃烧器30的下游侧并具有高温气体通道的涡轮40; 监测与可能的浪涌状况有关的燃气涡轮发动机10; 控制来自压缩机20的排出流，用于基于监测避免浪涌状况的控制; 并且将排出流引导到多个高压气体通道中的至少一个，并绕过燃烧器的至少一部分。
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公开(公告)号：JP2014016151A
公开(公告)日：2014-01-30
申请号：JP2013144798
申请日：2013-07-10
Inventor： FERNANDO BIAGIOLI , NARESH ALURI , MADHAVAN NARASIMHAN POYYAPAKKAM , JAN CERNY
Abstract: PROBLEM TO BE SOLVED: To provide an axial swirler for a gas turbine burner, which allows creation of an optimal exit flow velocity profile for increased combustion stability.SOLUTION: In order to achieve a controlled distribution of an exit flow velocity profile and/or a fuel equivalence ratio in the radial direction, a trailing edge 22, 35 is discontinuous with the trailing edge 22, 35 having a discontinuity 27 at a predetermined radius (R); at an inner radius (R), an exit flow angle (α), i.e. the angle between the tangent to the camber line of a vane 19, 19b, 33a, 33b and a swirler axis, is between 0° and 30°; and the exit flow angle (α) from the inner radius (R) is increasing to a value of between 30° and 60° at the predetermined radius (R), and the angle (α) from this predetermined radius (R) is decreasing to a value of between 10° and 40° at an outer radius (R).
Abstract translation: 要解决的问题：提供一种用于燃气轮机燃烧器的轴向旋流器，其允许创建用于提高燃烧稳定性的最佳出口流速分布。解决方案：为了实现出口流速分布和/或 燃料当量比在径向方向上，后缘22,35与后缘22,35不连续，后缘具有预定半径（R）的不连续部分27; 在内半径（R）处，出口流角（α），即叶片19,19b，33a，33b和旋流器轴线的弯度线的切线之间的角度在0°和30°之间; 并且从规定的半径（R）开始，内径（R）的出口流量角（α）增加到30°〜60°之间，从该规定的半径（R）的角度（α）减小 在外径（R）为10°至40°之间的值。
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Patent Agency Ranking
公开(公告)号：JP2014016150A
公开(公告)日：2014-01-30
申请号：JP2013144638
申请日：2013-07-10
Inventor： ENNIO PASQUALOTTO , PIRMIN SEASEL , HELLAT JAAN
CPC classification number: F23R3/286 , F23C5/06 , F23C7/002 , F23C2900/07002
Abstract: PROBLEM TO BE SOLVED: To provide a combustor array that combines wide-range axial variance of a burner with a minimum influence of a leakage air flow on an oxidation process by flames.SOLUTION: There is provided a combustor array 30 especially for gas turbine that includes a combustion chamber 22 having a front panel 23 and a multi-cone type pre-mixing burner 21, the pre-mixing burner 21 being coupled to the front panel 23 through thin and long mixing zones 24, 26 by sealed slide joints 24, 26, and 32 in an axially movable configuration. The sealed slide joints 24, 26, and 32 are arranged upstream from the mixing zones 24, 26.
Abstract translation: 要解决的问题：提供一种燃烧器阵列，其将燃烧器的宽范围轴向变化与火焰对氧化过程的泄漏空气流的影响最小化。解决方案：提供了一种特别用于燃气轮机的燃烧器阵列30， 包括具有前面板23和多锥型预混合燃烧器21的燃烧室22，预混合燃烧器21通过密封的滑动接头24通过薄且长的混合区24,26联接到前面板23， 26和32可轴向移动。 密封的滑动接头24,26和32布置在混合区24,26的上游。
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公开(公告)号：JP2014016146A
公开(公告)日：2014-01-30
申请号：JP2013143565
申请日：2013-07-09
Inventor： FRANKLIN MARIE GENIN , NARESH ALURI , JAN CERNY , EROGLU ADNAM , ENNIO PASQUALOTTO
CPC classification number: F02C7/22 , F02C3/14 , F02C6/003 , F23C6/047 , F23C2201/301 , F23C2201/40 , F23C2900/07002 , F23M20/005 , F23R3/286 , F23R3/346 , F23R3/46 , F23R2900/00014 , F23R2900/03341
Abstract: PROBLEM TO BE SOLVED: To enable operation with reduced CO emissions.SOLUTION: A gas turbine combustion system includes a gas turbine. The gas turbine includes: at least one compressor; at least one combustion chamber for generating working gas, which is connected to receive compressed air from the compressor; and at least one turbine connected to receive working gas from the combustion chamber. The combustion chamber consists of a single can-combustor or comprises a plurality of individual or interdependent can-combustors arranged in an annular can-architecture. The can-combustor has at least one premixed burner. The ignition of a mixture starts at the premixed burner outlet and the flame is stabilized in the region of the premixed burner outlet by means of a backflow zone. The can-combustor comprises a plurality of premixed burners arranged uniformly or is divided in at least two groups within the can-combustor.
Abstract translation: 要解决的问题：使CO 2排放减少的操作。解决方案：燃气轮机燃烧系统包括燃气轮机。 燃气轮机包括：至少一个压缩机; 用于产生工作气体的至少一个燃烧室，其被连接以从压缩机接收压缩空气; 以及至少一个涡轮连接以从燃烧室接收工作气体。 燃烧室由单个罐式燃烧器组成，或包括多个单独的或相互依赖的罐式燃烧器，它们以环形罐结构布置。 罐式燃烧器具有至少一个预混燃烧器。 混合物的点燃从预混燃烧器出口开始，并且通过回流区在火焰稳定在预混燃烧器出口的区域。 罐式燃烧器包括均匀排列的多个预混燃烧器，或者在罐式燃烧器内分成至少两组。
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78.发明专利Diffuser for exhaust section of gas turbine, and gas turbine with such diffuser 有权用于气体涡轮排气部分的发泡机，以及具有这种发动机的气体涡轮
公开(公告)号：JP2014009693A
公开(公告)日：2014-01-20
申请号：JP2013136455
申请日：2013-06-28
Inventor： EDUARD BRUEHWILLER
CPC classification number: F01D25/30 , F02C7/24 , F02K1/04 , F02K1/80 , F02K1/822 , F05D2230/642 , Y02T50/675
Abstract: PROBLEM TO BE SOLVED: To provide a diffuser which combines a smooth inner surface with safe compensation of different thermal expansions during transient conditions of a gas turbine.SOLUTION: Each of liner segments 29, 30 is fixed in the lateral direction at one fixing point 35. Each of liner segments 29, 30 is supported at a plurality of distributed points outside the fixing point 35 by means of supporting elements 26a, 26b, 31a, 31b, which are confined to a space between a conical liner 15, 15a, 15b and the support structure 17, 17a, 17b and allow a lateral thermal expansion of the liner segments 29, 30.
Abstract translation: 要解决的问题：提供一种在燃气轮机的瞬态条件下将平滑内表面与不同热膨胀的安全补偿相结合的扩散器。解决方案：每个衬垫段29,30在一个固定点35处沿横向固定 每个衬垫段29,30通过支撑元件26a，26b，31a，31b支撑在固定点35外部的多个分布点上，支撑元件26a，26b，31a，31b限定在锥形衬垫15,15a，15b和15b之间的空间中 支撑结构17,17a，17b，并且允许衬垫段29,30的横向热膨胀。
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公开(公告)号：JP2014001735A
公开(公告)日：2014-01-09
申请号：JP2013127715
申请日：2013-06-18
Inventor： CHRISTOPH PFOSTER , MOKULYS THOMAS , MICHAEL SELL , HANS-LUDWIG BOXHEIMER , GAFNER SILVIA , BEATE GRZONDZIEL
IPC: F01D25/30
Abstract: PROBLEM TO BE SOLVED: To further optimize existing diffuser designs and thus increase efficiency of turbo-machines, particularly low pressure modules or turbines of a steam driven power plant.SOLUTION: A diffuser 12 has an outer wall 121 extending to a diffuser lip 124 forming a diffuser outlet 123, and is continued to last stages 101, 111 of a turbine. The outer wall 121 has several subsequent straight wall parts at an angle to each other followed by a curved wall part. The curved section is arranged between a straight portion 3 and the diffuser lip 124, and has a perpendicular cross section forming a secondary curve 21.
Abstract translation: 要解决的问题：进一步优化现有的扩散器设计，从而提高涡轮机，特别是蒸汽驱动发电厂的低压模块或涡轮机的效率。解决方案：扩散器12具有延伸到形成的扩散器唇缘124的外壁121 扩散器出口123，并且继续到涡轮机的最后阶段101,111。 外壁121具有彼此成一定角度的几个随后的直壁部分，随后是弯曲的壁部分。 弯曲部分布置在直线部分3和扩散器唇缘124之间，并且具有形成次级曲线21的垂直横截面。
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公开(公告)号：JP2013245684A
公开(公告)日：2013-12-09
申请号：JP2013109769
申请日：2013-05-24
Inventor： HERZOG MAURUS , RAY SUMAN
Abstract: PROBLEM TO BE SOLVED: To provide a plant configured to minimize an amount of wet steam supplied to downstream steam turbines while minimizing reheat equipment requirements.SOLUTION: A steam Rankine cycle plant 10 includes: a higher-pressure steam turbine 20 having an outlet 22 for exhausting exhaust steam; a reheater 35 fluidly connected to the higher-pressure steam turbine 20; a lower-pressure steam turbine 25 having an inlet 27 fluidly connected to the reheater 35; and a bypass fluidly connected to the outlet 22 and the inlet 27 to bypass the reheater. The higher-pressure steam turbine 20 has an intermediate stage. The reheater 35 is fluidly connected to the intermediate stage, allows extraction steam to be extracted from the intermediate stage, and directs the extraction steam to the reheater 35.
Abstract translation: 要解决的问题：提供一种被配置为使提供给下游蒸汽轮机的湿蒸汽的量最小化的设备，同时最小化再热设备要求。解决方案：蒸汽兰金循环设备10包括：具有出口22的高压蒸汽轮机20， 废气排气; 流体连接到高压蒸汽轮机20的再热器35; 具有流体连接到再热器35的入口27的低压蒸汽轮机25; 以及流体连接到出口22和入口27以绕过再热器的旁路。 高压汽轮机20具有中间级。 再热器35流体地连接到中间阶段，允许从中间阶段提取提取蒸汽，并将提取蒸汽引导到再热器35。
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