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公开(公告)号：US20100172748A1
公开(公告)日：2010-07-08
申请号：US12348106
申请日：2009-01-02
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。
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公开(公告)号：US08057169B2
公开(公告)日：2011-11-15
申请号：US12138580
申请日：2008-06-13
IPC分类号： F03B3/12
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。
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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。
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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。
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公开(公告)号：US20120328413A1
公开(公告)日：2012-12-27
申请号：US13169415
申请日：2011-06-27
IPC分类号： F03B11/00
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。 该方法还包括将第二构件的远端接合到喷嘴组件，其中远端从第一构件径向移位。
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6.发明申请APPARATUS AND METHOD FOR CONTROLLING OXYGEN EMISSIONS FROM A GAS TURBINE 审中-公开用于控制来自气体涡轮机的氧气排放的装置和方法公开(公告)号：US20120180493A1
公开(公告)日：2012-07-19
申请号：US13005930
申请日：2011-01-13
CPC分类号： F02C7/185 , F01D5/081 , F01D5/085 , F01D25/12 , F02C3/34 , F02C6/18 , F05D2260/232 , F05D2270/08 , Y02E20/16
摘要： A combined cycle power plant includes a first compressor that produces a compressed working fluid and a turbine downstream of the first compressor. The turbine includes stationary components and rotating components and produces an exhaust. A heat exchanger downstream of the turbine receives the exhaust from the turbine, and a second compressor downstream of the heat exchanger and upstream of the turbine receives the exhaust from the heat exchanger and provides a flow of exhaust to the turbine. A method for reducing oxygen emissions from a gas turbine includes flowing an exhaust from a turbine to a heat exchanger and removing heat from the exhaust. The method further includes increasing the pressure of the exhaust to produce a pressurized exhaust and flowing the pressurized exhaust back to the turbine to remove heat from the turbine.
摘要翻译： 联合循环发电厂包括产生压缩工作流体的第一压缩机和第一压缩机下游的涡轮机。 涡轮机包括固定部件和旋转部件并产生排气。 在涡轮下游的热交换器接收来自涡轮机的排气，并且在热交换器下游的第二压缩机和涡轮的上游接收来自热交换器的排气并且向涡轮机提供排气流。 一种用于减少来自燃气轮机的氧气排放的方法包括将排气从涡轮机流动到热交换器并从排气口排出热量。 该方法还包括增加排气的压力以产生加压排气并使加压排气回流到涡轮机以从涡轮机移除热量。
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公开(公告)号：US09115595B2
公开(公告)日：2015-08-25
申请号：US13442155
申请日：2012-04-09
申请人： Daniel David Snook
发明人： Daniel David Snook
IPC分类号： F01D11/24
CPC分类号： F01D11/24 , F05D2260/201 , F05D2260/213
摘要： A system adapted for clearance control for a gas turbine including an outer turbine casing, an inner turbine casing and a plenum defined between the inner and outer turbine casings is disclosed. The clearance control system may include an impingement box disposed within the plenum. The impingement box may define a plurality of impingement holes. In addition, the clearance control system may include a first conduit in flow communication with the interior of the impingement box and a second conduit in flow communication with the plenum at a location exterior to the impingement box.
摘要翻译： 公开了一种用于燃气轮机的间隙控制的系统，包括外涡轮机壳体，内涡轮机壳体和限定在内涡轮机壳体和外涡轮机壳体之间的气室。 间隙控制系统可以包括设置在增压室内的冲击箱。 冲击箱可以限定多个冲击孔。 此外，间隙控制系统可以包括与冲击箱的内部流动连通的第一管道和在冲击箱外部的位置处与集气室流动连通的第二管道。
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8.发明申请公开(公告)号：US20120214605A1
公开(公告)日：2012-08-23
申请号：US13031287
申请日：2011-02-21
IPC分类号： F16F15/133
CPC分类号： F02C7/36 , F01D15/10 , F05D2260/96 , F16F15/1215 , F16F15/16
摘要： The present application and the resultant patent provide a gas turbine engine generator system. The gas turbine engine generator system may include a turbine, a generator, and a shaft. The turbine drives the generator via the shaft. A torsional damping coupling may be positioned about the shaft so as to limit the transmission of torque to the turbine during a generator based fault event.
摘要翻译： 本申请和所得专利提供了一种燃气涡轮发动机发电机系统。 燃气涡轮发动机发电机系统可以包括涡轮机，发电机和轴。 涡轮通过轴驱动发电机。 可以围绕轴定位扭转阻尼联轴器，以便在基于发电机的故障事件期间限制到涡轮机的转矩传递。
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公开(公告)号：US20120023959A1
公开(公告)日：2012-02-02
申请号：US13217686
申请日：2011-08-25
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。
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10.发明授权Blade/disk dovetail backcut for blade/disk stress reduction (9FA+e, stage 1) 失效刀片/圆盘燕尾刀刀片/盘片压力降低（9FA + e，阶段1）公开(公告)号：US07419362B2
公开(公告)日：2008-09-02
申请号：US11476109
申请日：2006-06-28
申请人： Daniel David Snook
发明人： Daniel David Snook
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F05D2230/10 , F05D2250/70 , F05D2260/941
摘要： Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.
摘要翻译： 可以转向燃气轮机盘上的叶片负载路径以提供显着的盘疲劳寿命益处。 多个燃气轮机叶片可附接到燃气涡轮盘，其中每个燃气轮机叶片包括可接合在燃气涡轮盘中的相应形状的燕尾槽中的叶片燕尾榫。 为了减少燃气轮机盘应力，根据叶片和/或盘几何形状来定义最佳材料去除面积，以最大化燃气轮机盘上的应力减小，燃气轮机叶片的使用寿命和维持或改进之间的平衡 燃气轮机叶片的机械性能。 从材料去除区域去除材料会最大化平衡。
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