-
公开(公告)号：US08266883B2
公开(公告)日：2012-09-18
申请号：US13217646
申请日：2011-08-25
申请人： Noémie Dion Ouellet , Daniel David Snook , Lisa Anne Wichmann , Samuel David Draper , Scott Allen Rittenhouse
发明人： Noémie Dion Ouellet , Daniel David Snook , Lisa Anne Wichmann , Samuel David Draper , Scott Allen Rittenhouse
CPC分类号： F02C7/277 , F01D13/02 , F01D19/00 , F02C3/36 , F02C7/18 , F02C9/52 , F05D2220/76 , F05D2260/85 , F05D2270/061 , F05D2270/082 , Y02T50/675 , Y02T50/677
摘要： Ambient air is compressed into a compressed ambient gas flow and delivered to a turbine combustor. At least one of an exhaust port, a bypass conduit, or an extraction conduit is opened to vent the power plant. A turbine shaft is rotated at an ignition speed and a fuel stream is delivered to the turbine combustor for mixing with the compressed ambient gas flow to form a combustible mixture. The combustible mixture is burned and forms a recirculated gas flow that drives the turbine. The recirculated gas flow is recirculated using the recirculation loop. The turbine is operated at a target operating speed and then reaches substantially stoichiometric combustion. At least a portion of the recirculated gas flow is extracted using an extraction conduit that is fluidly connected to the turbine compressor.
摘要翻译： 环境空气被压缩成压缩的环境气流并输送到涡轮机燃烧器。 打开排气口，旁通管道或抽取管道中的至少一个以排放发电厂。 涡轮轴以点火速度旋转，并且燃料流被输送到涡轮机燃烧器以与压缩的环境气流混合以形成可燃混合物。 可燃混合物被燃烧并形成驱动涡轮机的再循环气流。 再循环气体循环使用再循环回路。 涡轮机以目标操作速度运行，然后达到基本上化学计量的燃烧。 使用流体连接到涡轮压缩机的抽出管道提取至少一部分再循环的气流。
-
公开(公告)号：US20120023958A1
公开(公告)日：2012-02-02
申请号：US13217630
申请日：2011-08-25
IPC分类号： F02C9/50
CPC分类号： F02C3/34 , F01D13/02 , F02C1/08 , F02C6/08 , Y02T50/676
摘要： Ambient air is compressed into a compressed ambient gas flow with a main air compressor. The compressed ambient gas flow having a compressed ambient gas flow rate is delivered to a turbine combustor and mixed with a fuel stream having a fuel stream flow rate and a portion of a recirculated low oxygen content gas flow to form a combustible mixture. The combustible mixture is burned and forms the recirculated low oxygen content gas flow that drives a turbine. A portion of the recirculated low oxygen content gas flow is recirculated from the turbine to the turbine compressor using a recirculation loop. The compressed ambient gas flow rate and the fuel stream flow rate are adjusted to achieve substantially stoichiometric combustion. An excess portion, if any, of the compressed ambient gas flow is vented. A portion of the recirculated low oxygen content gas flow is extracted using an extraction conduit.
摘要翻译： 环境空气用主空气压缩机压缩成压缩的环境气流。 具有压缩环境气体流速的压缩环境气体流被传送到涡轮机燃烧器并与具有燃料流量和再循环的低氧含量气体流的一部分的燃料流混合以形成可燃混合物。 可燃混合物燃烧并形成驱动涡轮机的再循环低氧含量气体流。 再循环的低氧含量气体流的一部分使用循环回路从涡轮再循环到涡轮压缩机。 压缩的环境气体流速和燃料流量被调节以实现基本上化学计量的燃烧。 压缩的环境气体流的过剩部分（如果有的话）被排出。 使用提取管道提取一部分再循环的低氧含量气体流。
-
公开(公告)号：US20100000219A1
公开(公告)日：2010-01-07
申请号：US12166689
申请日：2008-07-02
IPC分类号： F02K1/36
CPC分类号： F02C6/08 , F05D2260/601
摘要： A system and method for supplying cooling air to the turbine section of a gas turbine. The system may include a compressed air supply, an ambient air supply, and an ejector for entraining the ambient air supply with the compressed air supply to form a cooling air supply. In a gas turbine including a compressor section and a turbine section, the method may include extracting compressed air from the compressor section, entraining ambient air with the compressed air to form cooling air, and directing the cooling air to the turbine section.
摘要翻译： 一种用于向燃气轮机的涡轮部供应冷却空气的系统和方法。 该系统可以包括压缩空气源，环境空气源和用于将环境空气供应与压缩空气供应夹带以形成冷却空气源的喷射器。 在包括压缩机部分和涡轮机部分的燃气涡轮机中，该方法可以包括从压缩机部分提取压缩空气，将空气与压缩空气一起夹带以形成冷却空气，并将冷却空气引导到涡轮部分。
-
14.发明申请公开(公告)号：US20130160456A1
公开(公告)日：2013-06-27
申请号：US13334879
申请日：2011-12-22
IPC分类号： F02C7/00
摘要： A system for controlling oxygen emissions from a gas turbine includes a combustor, a plenum downstream from the combustor, and a turbine downstream from the plenum that produces an exhaust. A compressor downstream from the turbine receives the exhaust and produces a compressed exhaust. A compressed exhaust plenum downstream from the compressor provides fluid communication to the combustor and the plenum. A method for controlling oxygen emissions from a gas turbine includes flowing an exhaust from a turbine and increasing the pressure of the exhaust to produce a compressed exhaust. The method further includes flowing a first portion of the compressed exhaust to an inlet of a combustor and flowing a second portion of the compressed exhaust to a plenum between the turbine and the combustor.
摘要翻译： 用于控制来自燃气涡轮机的氧气排放的系统包括燃烧器，来自燃烧器下游的增压室以及产生排气的气室下游的涡轮机。 涡轮机下游的压缩机接收排气并产生压缩排气。 压缩机下游的压缩排气室提供与燃烧器和增压室的流体连通。 用于控制来自燃气轮机的氧气排放的方法包括使来自涡轮机的排气流动并且增加排气的压力以产生压缩排气。 该方法还包括将压缩排气的第一部分流动到燃烧器的入口并将压缩排气的第二部分流动到涡轮和燃烧器之间的集气室。
-
公开(公告)号：US08266913B2
公开(公告)日：2012-09-18
申请号：US13217686
申请日：2011-08-25
IPC分类号： F02C1/00
CPC分类号： F02C3/34 , F01D13/02 , F02C6/00 , F05D2240/40
摘要： A power plant arrangement and method of operation are provided. The power plant arrangement comprises at lease one main air compressor and one or more gas turbine assemblies. Each assembly comprises a turbine combustor for mixing a portion of a compressed ambient gas flow with a portion of a recirculated low oxygen content gas flow and a fuel stream, and burning the combustible mixture to form the recirculated low oxygen content flow. The assembly further comprises a turbine compressor, fluidly connected to the turbine combustor, and connected to a turbine shaft that is arranged to be driven by rotation of a turbine. The assembly also comprises a recirculation loop for recirculating at least a portion of the recirculated low oxygen content gas flow from the turbine to the turbine compressor.
摘要翻译： 提供了电厂布置和操作方法。 发电厂布置包括至少一个主空气压缩机和一个或多个燃气轮机组件。 每个组件包括涡轮机燃烧器，用于将压缩的环境气体流的一部分与再循环的低氧含量气体流和燃料流的一部分混合，并燃烧可燃混合物以形成再循环的低氧含量流。 该组件还包括流体连接到涡轮机燃烧器并连接到涡轮机轴的涡轮压缩机，涡轮机轴被布置成通过涡轮机的旋转而被驱动。 组件还包括再循环回路，用于将来自涡轮机的再循环的低氧含量气体流的至少一部分再循环到涡轮压缩机。
-
公开(公告)号：US20120023966A1
公开(公告)日：2012-02-02
申请号：US13217646
申请日：2011-08-25
申请人： Noémie Dion Ouellet , Daniel David Snook , Lisa Anne Wichmann , Samuel David Draper , Scott Allen Rittenhouse
发明人： Noémie Dion Ouellet , Daniel David Snook , Lisa Anne Wichmann , Samuel David Draper , Scott Allen Rittenhouse
IPC分类号： F02C7/26
CPC分类号： F02C7/277 , F01D13/02 , F01D19/00 , F02C3/36 , F02C7/18 , F02C9/52 , F05D2220/76 , F05D2260/85 , F05D2270/061 , F05D2270/082 , Y02T50/675 , Y02T50/677
摘要： Ambient air is compressed into a compressed ambient gas flow and delivered to a turbine combustor. At least one of an exhaust port, a bypass conduit, or an extraction conduit is opened to vent the power plant. A turbine shaft is rotated at an ignition speed and a fuel stream is delivered to the turbine combustor for mixing with the compressed ambient gas flow to form a combustible mixture. The combustible mixture is burned and forms a recirculated gas flow that drives the turbine. The recirculated gas flow is recirculated using the recirculation loop. The turbine is operated at a target operating speed and then reaches substantially stoichiometric combustion. At least a portion of the recirculated gas flow is extracted using an extraction conduit that is fluidly connected to the turbine compressor.
摘要翻译： 环境空气被压缩成压缩的环境气流并输送到涡轮机燃烧器。 打开排气口，旁通管道或抽取管道中的至少一个以排放发电厂。 涡轮轴以点火速度旋转，并且燃料流被输送到涡轮机燃烧器以与压缩的环境气流混合以形成可燃混合物。 可燃混合物被燃烧并形成驱动涡轮机的再循环气流。 再循环气体循环使用再循环回路。 涡轮机以目标操作速度运行，然后达到基本上化学计量的燃烧。 使用流体连接到涡轮压缩机的抽出管道提取至少一部分再循环的气流。
-
公开(公告)号：US08096757B2
公开(公告)日：2012-01-17
申请号：US12348106
申请日：2009-01-02
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F05D2240/122 , F05D2260/941 , Y10T29/49323
摘要： A gas turbine engine nozzle is described. The gas turbine engine nozzle includes at least one nozzle vane having a first end and a second end. The first end is coupled to an inner sidewall and the second end is coupled to an outer sidewall. The gas turbine engine nozzle also includes at least one stress relief pocket defined within at least one of the inner sidewall and the outer sidewall proximate to the at least one nozzle vane. The at least one stress relief pocket is configured to reduce stress on the proximate nozzle vane.
摘要翻译： 描述燃气涡轮发动机喷嘴。 燃气涡轮发动机喷嘴包括具有第一端和第二端的至少一个喷嘴叶片。 第一端联接到内侧壁，并且第二端联接到外侧壁。 燃气涡轮发动机喷嘴还包括至少一个限定在内侧壁和靠近至少一个喷嘴叶片的外侧壁中的至少一个内的应力消除凹坑。 所述至少一个应力释放腔被构造成减小邻近喷嘴叶片上的应力。
-
公开(公告)号：US20090324415A1
公开(公告)日：2009-12-31
申请号：US12138580
申请日：2008-06-13
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2220/3212 , F05D2250/74 , F05D2260/202
摘要： An article of manufacture includes an object having an airfoil core shape. The airfoil core shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1 where X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil core shape.
摘要翻译： 制品包括具有翼型芯形状的物体。 翼型芯形状具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓，其中X和Y是以英寸为单位的距离，当通过平滑连续的弧连接时，每一个定义翼型轮廓部分 距离Z以英寸为单位。 在Z距离处的轮廓部分彼此平滑地连接以形成完整的翼型芯形状。
-
公开(公告)号：US06893216B2
公开(公告)日：2005-05-17
申请号：US10620365
申请日：2003-07-17
CPC分类号： F01D5/225 , F05D2250/70
摘要： A turbine bucket includes a bucket airfoil having a tip shroud with leading and trailing edges defining leading and trailing edge profiles substantially in accordance with Cartesian coordinate values of X and Y at points 12-20 and 1-11, respectively, set forth in Table I. The X and Y values are distances in inches which, when respective points 12-20 and 1-11 are connected by smooth, continuing arcs, define the leading and trailing edge tip shroud profiles. An airfoil profile at 95% span is defined by Cartesian coordinate values of X, Y and Z in Table II having the same X, Y origin along the radial Z axis as the origin of Table I. The profiled leading and trailing edges of the tip shroud relative to the airfoil profile afford optimum tip shroud mass distribution which maximizes creep life of the bucket. Stage efficiency is also improved by providing a tip shroud covering the airfoil throat.
摘要翻译： 涡轮机桶包括具有尖端护罩的铲斗翼型件，其前缘和后缘基本上根据表I中所示的点12-20和1-11处的X和Y的笛卡尔坐标值来定义前缘和后缘轮廓 X和Y值是以英寸为单位的距离，当各个点12-20和1-11通过平滑连续的弧连接时，可以定义前缘和后缘尖端护罩轮廓。 95％跨度的翼型轮廓由表II中的X，Y和Z的笛卡尔坐标值定义为具有相同的X，Y原点沿着径向Z轴作为表I的原点。尖端的成型前缘和后缘 相对于翼型轮廓的护罩提供最佳的尖端护罩质量分布，其最大化铲斗的蠕变寿命。 通过提供覆盖翼型喉部的尖端护罩也提高了阶段效率。
-
公开(公告)号：US08690530B2
公开(公告)日：2014-04-08
申请号：US13169415
申请日：2011-06-27
IPC分类号： F01D9/02
CPC分类号： F01D5/147 , F01D9/041 , F01D25/246
摘要： A system for supporting a nozzle assembly includes a first member connected to a stationary component and a second member extending from the first member radially through at least a portion of the nozzle assembly. A distal end of the second member is radially displaced from the first member and configured to contact the nozzle assembly. A method for supporting a nozzle assembly includes connecting a first member to a stationary component and extending a second member from the first member radially through at least a portion of the nozzle assembly. The method further includes contacting a distal end of the second member to the nozzle assembly, wherein the distal end is radially displaced from the first member.
摘要翻译： 用于支撑喷嘴组件的系统包括连接到静止部件的第一部件和从第一部件径向延伸穿过喷嘴组件的至少一部分的第二部件。 第二构件的远端从第一构件径向偏移并且构造成接触喷嘴组件。 用于支撑喷嘴组件的方法包括将第一构件连接到固定部件并且将第二构件从第一构件径向延伸穿过喷嘴组件的至少一部分。 所述方法还包括将所述第二构件的远端接合到所述喷嘴组件，其中所述远端从所述第一构件径向移位。
-
-
-
-
-
-
-
-
-
搜索结果
28 条记录 (耗时 0.021 秒)
