公开(公告)号：US20120214605A1

公开(公告)日：2012-08-23

申请号：US13031287

申请日：2011-02-21

Applicant: Daniel David Snook ,  Klaus Werner Sommerlatte

Inventor： Daniel David Snook ,  Klaus Werner Sommerlatte

IPC: F16F15/133

CPC classification number: F02C7/36 ,  F01D15/10 ,  F05D2260/96 ,  F16F15/1215 ,  F16F15/16

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20120023959A1

公开(公告)日：2012-02-02

申请号：US13217686

申请日：2011-08-25

Applicant: Daniel David Snook ,  Lisa Anne Wichmann ,  Samuel David Draper ,  Noémie Dion Ouellet

Inventor： Daniel David Snook ,  Lisa Anne Wichmann ,  Samuel David Draper ,  Noémie Dion Ouellet

IPC: F02C9/00 ,  F02C7/08

CPC classification number: F02C3/34 ,  F01D13/02 ,  F02C6/00 ,  F05D2240/40

Abstract: 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.

Abstract translation: 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：US20100172748A1

公开(公告)日：2010-07-08

申请号：US12348106

申请日：2009-01-02

Applicant: Daniel David Snook ,  Edward Durell Benjamin

Inventor： Daniel David Snook ,  Edward Durell Benjamin

IPC: F01D9/02 ,  B23P11/00

CPC classification number: F01D9/02 ,  F05D2240/122 ,  F05D2260/941 ,  Y10T29/49323

Abstract: 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.

Abstract translation: 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：US07419362B2

公开(公告)日：2008-09-02

申请号：US11476109

申请日：2006-06-28

Applicant: Daniel David Snook

Inventor： Daniel David Snook

IPC: F01D5/30

CPC classification number: F01D5/3007 ,  F05D2230/10 ,  F05D2250/70 ,  F05D2260/941

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US08690530B2

公开(公告)日：2014-04-08

申请号：US13169415

申请日：2011-06-27

Applicant: Daniel David Snook ,  Leissner Ferdinand Poth, III

Inventor： Daniel David Snook ,  Leissner Ferdinand Poth, III

IPC: F01D9/02

CPC classification number: F01D5/147 ,  F01D9/041 ,  F01D25/246

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20130266418A1

公开(公告)日：2013-10-10

申请号：US13442155

申请日：2012-04-09

Applicant: Daniel David Snook

Inventor： Daniel David Snook

IPC: F04D27/00

CPC classification number: F01D11/24 ,  F05D2260/201 ,  F05D2260/213

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20120023963A1

公开(公告)日：2012-02-02

申请号：US13217713

申请日：2011-08-25

Applicant: Lisa Anne Wichmann ,  Daniel David Snook ,  Noémie Dion Ouellet ,  Scott Allen Rittenhouse

Inventor： Lisa Anne Wichmann ,  Daniel David Snook ,  Noémie Dion Ouellet ,  Scott Allen Rittenhouse

IPC: F02C9/54 ,  F02C9/20 ,  F02C9/26 ,  F02C9/00

CPC classification number: F02C9/42 ,  F02C3/34 ,  F02C9/18

Abstract: At least one main air compressor makes a compressed ambient gas flow. The compressed ambient gas flow is delivered to both master and slave turbine combustors at a pressure that is greater than or substantially equal to an output pressure delivered to each turbine combustor from each turbine compressor as at least a first portion of a recirculated gas flow. A fuel stream is delivered to each turbine combustor, and combustible mixtures are formed and burned, forming the recirculated gas flows. A master and slave turbine power are produced, and each is substantially equal to at least a power required to rotate each turbine compressor. At least a portion of the recirculated gas flow is recirculated through recirculation loops. At least a second portion of the recirculated gas flow bypasses the combustors or an excess portion of each recirculated gas flow is vented or both.

Abstract translation: 至少一个主要空气压缩机使压缩的环境气体流动。 压缩的环境气体流以大于或基本上等于从每个涡轮压缩机作为再循环气流的至少第一部分输送到每个涡轮机燃烧器的输出压力的压力被输送到主涡轮燃烧器和从属涡轮机燃烧器。 燃料流被输送到每个涡轮机燃烧器，并且形成并燃烧可燃混合物，形成再循环的气体流。 制造主和从属涡轮机功率，并且每个主要和从属涡轮机功率基本上等于旋转每个涡轮压缩机所需的至少一个功率。 再循环气体的至少一部分通过再循环回路再循环。 再循环气体流的至少第二部分绕过燃烧器，或者每个再循环气体流的多余部分被排出或两者。

公开(公告)号：US20120023962A1

公开(公告)日：2012-02-02

申请号：US13217658

申请日：2011-08-25

Applicant: Lisa Anne Wichmann ,  Daniel David Snook ,  Samuel David Draper ,  Noémie Dion Ouellet ,  Scott Allen Rittenhouse

Inventor： Lisa Anne Wichmann ,  Daniel David Snook ,  Samuel David Draper ,  Noémie Dion Ouellet ,  Scott Allen Rittenhouse

IPC: F02C9/00

CPC classification number: F02C6/06 ,  F02C3/34 ,  F02C9/18 ,  F05D2260/85 ,  F05D2270/301

Abstract: At least one main air compressor makes a compressed ambient gas flow. The compressed ambient gas flow is delivered to a turbine combustor at a pressure that is greater than or substantially equal to an output pressure delivered to the turbine combustor from a turbine compressor as at least a first portion of a recirculated gas flow. A fuel stream is delivered to the turbine combustor, and a combustible mixture is formed and burned, forming the recirculated gas flow. A turbine power is produced that is substantially equal to at least a power required to rotate the turbine compressor. At least a portion of the recirculated gas flow is recirculated through a recirculation loop. An excess portion of the recirculated gas flow is vented or a portion of the recirculated gas flow bypasses the turbine combustor or both.

Abstract translation: 至少一个主要空气压缩机使压缩的环境气体流动。 压缩的环境气体流以大于或基本上等于从涡轮压缩机作为再循环气流的至少第一部分输送到涡轮机燃烧器的输出压力的压力被输送到涡轮机燃烧器。 燃料流被输送到涡轮机燃烧器，并且形成并燃烧可燃混合物，形成再循环气体流。 产生的涡轮功率基本上等于至少旋转涡轮压缩机所需的功率。 再循环气流的至少一部分通过循环回路再循环。 再循环气流的一部分被排出，或者再循环气流的一部分绕过涡轮机燃烧室或两者。

公开(公告)号：US08057169B2

公开(公告)日：2011-11-15

申请号：US12138580

申请日：2008-06-13

Applicant: Edward Durell Benjamin, Jr. ,  David John Humanchuk ,  Daniel David Snook

Inventor： Edward Durell Benjamin, Jr. ,  David John Humanchuk ,  Daniel David Snook

IPC: F03B3/12

CPC classification number: F01D5/141 ,  F05D2220/3212 ,  F05D2250/74 ,  F05D2260/202

Abstract: 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.

Abstract translation: 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：US07476083B2

公开(公告)日：2009-01-13

申请号：US11476095

申请日：2006-06-28

Applicant: Daniel David Snook ,  John Herbert Dimmick, III ,  Rachel Jane Obermeyer ,  Ariel Caesar Prepena Jacala ,  Robert Craig Akin

Inventor： Daniel David Snook ,  John Herbert Dimmick, III ,  Rachel Jane Obermeyer ,  Ariel Caesar Prepena Jacala ,  Robert Craig Akin

IPC: F01D5/30

CPC classification number: F01D5/30 ,  F05D2230/10

Abstract: 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.

Abstract translation: 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。