公开(公告)号：US09500085B2

公开(公告)日：2016-11-22

申请号：US13555434

申请日：2012-07-23

申请人： Paul Kendall Smith ,  Sylvain Pierre ,  Dennis Scott Holloway

发明人： Paul Kendall Smith ,  Sylvain Pierre ,  Dennis Scott Holloway

IPC分类号： F04D29/44 ,  F04D29/54 ,  F04D27/02 ,  F04D29/02 ,  F01D5/14

CPC分类号： F01D5/142 ,  F05D2220/321 ,  F05D2220/3216 ,  Y02T50/673

摘要： A method for enhancing one or more performance parameters of a gas turbine having at least one row of clocked airfoils may generally include choosing a first, a second and a third row of airfoils where the third row is clocked relative to the first row. An unsteady computational fluid dynamics model may be used to determine at least one wake parameter of a working fluid flowing from the second row of the airfoils to the third row of the airfoils. At least one design parameter of the airfoils of the second row may be modified, and the unsteady computational fluid dynamics model may then be used to determine the effect of the airfoil design parameter modification on the at least one wake parameter. The effect on the wake parameter may be compared to a predetermined target range.

摘要翻译： 一种用于增强具有至少一排时钟翼型的燃气轮机的一个或多个性能参数的方法通常可以包括选择第一排，第二排和第三排翼型件，其中第三排相对于第一排计时。 可以使用不稳定的计算流体动力学模型来确定从翼型的第二排流到翼型的第三排的工作流体的至少一个尾流参数。 可以修改第二排的翼型件的至少一个设计参数，然后可以使用不稳定的计算流体动力学模型来确定翼型设计参数修改对至少一个尾流参数的影响。 可以将对唤醒参数的影响与预定目标范围进行比较。

公开(公告)号：US09291061B2

公开(公告)日：2016-03-22

申请号：US13447134

申请日：2012-04-13

申请人： Rohit Chouhan ,  Sylvain Pierre ,  Gunnar Leif Siden ,  Santhosh Kumar Vijayan ,  Joseph Anthony Cotroneo

发明人： Rohit Chouhan ,  Sylvain Pierre ,  Gunnar Leif Siden ,  Santhosh Kumar Vijayan ,  Joseph Anthony Cotroneo

IPC分类号： F01D5/20 ,  F01D11/08 ,  F01D5/22

CPC分类号： F01D5/225 ,  F01D11/08 ,  F05D2250/312

摘要： Embodiments of the present disclosure include a turbomachine having a turbomachine blade and a stationary structural component. The turbomachine blade includes a tip shroud having a leading edge portion where the leading edge portion has a first surface. The stationary structural component is disposed about the turbomachine blade and includes a corresponding portion corresponding to the leading edge portion of the tip shroud, where the corresponding portion has a second surface, where the first surface and the second surface have generally parallel contours.

摘要翻译： 本公开的实施例包括具有涡轮机叶片和固定结构部件的涡轮机。 涡轮机叶片包括具有前缘部分的前端部分，其中前缘部分具有第一表面。 固定结构部件围绕涡轮机叶片设置并且包括对应于尖端护罩的前缘部分的对应部分，其中对应部分具有第二表面，其中第一表面和第二表面具有大致平行的轮廓。

公开(公告)号：US08777490B2

公开(公告)日：2014-07-15

申请号：US13703642

申请日：2011-06-29

申请人： David Cazaux ,  Sylvain Pierre Votie

发明人： David Cazaux ,  Sylvain Pierre Votie

IPC分类号： F16C27/00

CPC分类号： F16C27/04 ,  F16C19/54 ,  F16C27/045 ,  F16C2360/23 ,  F16F15/023 ,  F16F15/0237

摘要： An architecture making it possible to provide sufficient absorption of shocks for a power shaft while maintaining rigidity at front bearings so as to not compromise meshing of power teeth of a drive pinion. A compressible dynamic shock absorption is provided in alignment with a downstream shock absorber of an additional meshing. An assembly for dynamically absorbing shocks for a power shaft includes upstream and downstream bearings including power rollers mounted on two casings and flanking a speed-reducing teeth meshing. The downstream bearing is coupled to at least one additional roller bearing associated with a compressible shock absorber to form a downstream shock absorber axially offset relative to the upstream bearing opposite the teeth meshing. Both downstream bearings are connectable by a flexible frame mounted on the common casing. The architecture can be used for power-transmission shafts, for example supercritical shafts in turbine engines.

摘要翻译： 一种架构，使得能够为动力轴提供足够的冲击吸收，同时保持前轴承的刚度，从而不损害驱动小齿轮的动力齿的啮合。 提供可压缩的动态冲击吸收，与附加啮合的下游减震器对准。 用于动力吸收动力轴的冲击的组件包括上游和下游轴承，包括安装在两个壳体上的动力辊并且侧向减速齿啮合。 下游轴承联接到与可压缩减震器相关联的至少一个附加的滚子轴承，以形成相对于与齿啮合相对的上游轴承轴向偏移的下游减震器。 两个下游轴承可以通过安装在公共壳体上的柔性框架连接。 该结构可用于动力传动轴，例如涡轮发动机中的超临界轴。

公开(公告)号：US20130189106A1

公开(公告)日：2013-07-25

申请号：US13355436

申请日：2012-01-20

申请人： Rohit Chouhan ,  Sumeet Soni ,  Paul Kendall Smith ,  Srinivasa Govardhan Jayana ,  Sylvain Pierre ,  Harish Bommanakatte ,  Santhosh Kumar Vijayan ,  Spencer Aaron Kareff

发明人： Rohit Chouhan ,  Sumeet Soni ,  Paul Kendall Smith ,  Srinivasa Govardhan Jayana ,  Sylvain Pierre ,  Harish Bommanakatte ,  Santhosh Kumar Vijayan ,  Spencer Aaron Kareff

IPC分类号： F01D5/22

CPC分类号： F01D5/225 ,  F01D5/141 ,  F01D5/20 ,  F01D11/02 ,  F05D2220/31 ,  F05D2220/32 ,  F05D2240/307 ,  F05D2250/20 ,  F05D2250/73 ,  Y02T50/671 ,  Y02T50/673

摘要： Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

公开(公告)号：US20130108444A1

公开(公告)日：2013-05-02

申请号：US13284010

申请日：2011-10-28

申请人： Alexander Stein ,  Bradley Taylor Boyer ,  Sylvain Pierre

发明人： Alexander Stein ,  Bradley Taylor Boyer ,  Sylvain Pierre

IPC分类号： F01D5/18

CPC分类号： F01D5/20

摘要： A turbine blade includes an airfoil portion including a suction side having a suction side contour, a pressure side having a pressure side contour, a leading edge, a trailing edge and a tip portion, and a squeeler pocket formed in the tip portion. The squeeler pocket includes a first side wall and a second side wall. The first side wall includes a first internal surface having a first substantially continuous curvilinear profile and the second side wall includes a second internal surface having a second substantially continuous curvilinear profile. A bleed passage extends from the squeeler pocket towards the trailing edge. The first and second side walls are configured to deliver a substantially unobstructed fluid flow from the squeeler pocket to the bleed passage and limit the fluid flow spillage onto one of the pressure side and the suction side.

摘要翻译： 涡轮叶片包括具有吸力侧轮廓的吸力侧的翼型部，具有压力侧轮廓的压力侧，前缘，后缘和前端部，以及形成在前端部的脚踝袋。 脚尖袋包括第一侧壁和第二侧壁。 第一侧壁包括具有第一基本上连续的曲线轮廓的第一内表面，并且第二侧壁包括具有第二基本连续曲线轮廓的第二内表面。 排出通道从吱吱声口袋向后缘延伸。 第一和第二侧壁构造成将基本上无障碍的流体流从脚er器袋输送到排放通道，并将流体流量溢出限制在压力侧和吸力侧之一上。

公开(公告)号：US20110052387A1

公开(公告)日：2011-03-03

申请号：US12551741

申请日：2009-09-01

申请人： Andrew Ray Kneeland ,  Andres Jose Garcia-Crespo ,  Bradley T. Boyer ,  Thomas William Vandeputte ,  Sylvain Pierre

发明人： Andrew Ray Kneeland ,  Andres Jose Garcia-Crespo ,  Bradley T. Boyer ,  Thomas William Vandeputte ,  Sylvain Pierre

IPC分类号： F01D9/02 ,  F01D5/14

CPC分类号： F01D5/141 ,  F01D5/142 ,  F01D5/143 ,  F01D11/02

摘要： Turbine blade assemblies of a turbine include airfoils that are mounted on bases. The leading and/or trailing edges of the bases are provided with curved portions. Likewise, curved portions may be provided on leading and/or trailing edges of the angle wings of a turbine blade assembly. Also, curved portions may be provided on the leading and/or trailing edges of nozzle assemblies of a turbine.

摘要翻译： 涡轮机的涡轮叶片组件包括安装在基座上的翼型件。 基部的前缘和/或后缘设有弯曲部分。 类似地，弯曲部分可以设置在涡轮叶片组件的角翼的前缘和/或后缘。 此外，弯曲部分可以设置在涡轮机的喷嘴组件的前缘和/或后缘。

公开(公告)号：US20090193785A1

公开(公告)日：2009-08-06

申请号：US12023343

申请日：2008-01-31

申请人： Gunnar L. Siden ,  Sal A. Leone ,  John E. Sholes ,  Victor G. Hatman ,  Douglas C. Hofer ,  Thomas W. Vandeputte ,  Sylvain Pierre

发明人： Gunnar L. Siden ,  Sal A. Leone ,  John E. Sholes ,  Victor G. Hatman ,  Douglas C. Hofer ,  Thomas W. Vandeputte ,  Sylvain Pierre

IPC分类号： F02C6/06

CPC分类号： F02C6/00 ,  F01D15/10 ,  F02C3/10 ,  F02C3/107 ,  F02C6/18

摘要： A power generating turbine system that includes: a turbine that includes three sections, a high-pressure turbine section, a mid-pressure turbine section, and a low-pressure turbine section that each reside on a separate shaft; 2) an axial compressor that compresses a flow of air that is then mixed with a fuel and combusted in a combustor such that the resulting flow of hot gas is directed through the turbine, the axial compressor comprising a high-pressure compressor section and a low-pressure compressor section; 3) a two-pole generator; 4) a four-pole generator; 5) a first shaft that couples the high-pressure turbine section to the high-pressure compressor section such that, in operation, the high-pressure turbine section drives the high-pressure compressor section; 6) a second shaft that couples the mid-pressure turbine section to the high-pressure compressor section and the two-pole generator such that, in operation, the mid-pressure turbine section drives the high-pressure compressor section and two-pole generator; and 7) a third shaft that couples the low-pressure turbine section to the four-pole generator such that in operation the low-pressure turbine section drives the four-pole generator.

摘要翻译： 一种发电涡轮机系统，其包括：涡轮机，其包括三个部分，高压涡轮部分，中压涡轮部分和低压涡轮部分，每个部分驻留在单独的轴上; 2）一种轴向压缩机，其压缩与燃料混合并在燃烧器中燃烧的空气流，使得所产生的热气流引导通过涡轮机，轴向压缩机包括高压压缩机部分和低压 压缩机部分; 3）双极发电机; 4）四极发生器; 5）将高压涡轮部分连接到高压压缩机部分的第一轴，使得在操作中，高压涡轮部分驱动高压压缩机部分; 6）将中压涡轮部分连接到高压压缩机部分和两极发生器的第二轴，使得在运行中，中压涡轮部分驱动高压压缩机部分和两极发生器 ; 以及7）第三轴，其将所述低压涡轮机部分联接到所述四极发电机，使得在运行中所述低压涡轮部分驱动所述四极发电机。

公开(公告)号：US08944678B2

公开(公告)日：2015-02-03

申请号：US13107207

申请日：2011-05-13

申请人： Zachary John Snider ,  Sylvain Pierre ,  Kurt Kramer Schleif

发明人： Zachary John Snider ,  Sylvain Pierre ,  Kurt Kramer Schleif

IPC分类号： G01K3/00 ,  G01K7/00 ,  G01K1/00 ,  G01K13/02 ,  G01K1/12 ,  G01L19/14 ,  G01L23/26

CPC分类号： G01K13/02 ,  G01K1/12 ,  G01K2205/04 ,  G01L19/149 ,  G01L23/26

摘要： An instrumentation rake assembly comprises a rake tower capped at an immersed end and mated to a lead carrier at a base end. The rake tower comprises a curved wall oriented along a longitudinal axis and supporting a plurality of probe holders. The curved wall has an inner surface defining an internal passage for carrying instrumentation from the probe holders to the lead carrier. In another aspect, an instrumentation rake assembly comprises a plurality of rake towers, each having a base end and an immersed end, and each rake tower being coupled at its immersed end to one or more other rake towers.

摘要翻译： 仪表耙组件包括在浸入端处封盖的耙塔，并在基端处与引线架配合。 耙塔包括沿着纵向轴线定向并支撑多个探针支架的弯曲壁。 弯曲的壁具有限定内部通道的内表面，用于将探测器保持器的仪器传送到引线架。 在另一方面，仪表耙组件包括多个耙塔，每个耙塔具有基端和浸入端，并且每个耙塔在其浸入端连接到一个或多个其它耙塔。

公开(公告)号：US20130089284A1

公开(公告)日：2013-04-11

申请号：US13703642

申请日：2011-06-29

申请人： David Cazaux ,  Sylvain Pierre Votie

发明人： David Cazaux ,  Sylvain Pierre Votie

IPC分类号： F16C27/04 ,  F16F15/023

CPC分类号： F16C27/04 ,  F16C19/54 ,  F16C27/045 ,  F16C2360/23 ,  F16F15/023 ,  F16F15/0237

摘要： An architecture making it possible to provide sufficient absorption of shocks for a power shaft while maintaining rigidity at front bearings so as to not compromise meshing of power teeth of a drive pinion. A compressible dynamic shock absorption is provided in alignment with a downstream shock absorber of an additional meshing. An assembly for dynamically absorbing shocks for a power shaft includes upstream and downstream bearings including power rollers mounted on two casings and flanking a speed-reducing teeth meshing. The downstream bearing is coupled to at least one additional roller bearing associated with a compressible shock absorber to form a downstream shock absorber axially offset relative to the upstream bearing opposite the teeth meshing. Both downstream bearings are connectable by a flexible frame mounted on the common casing. The architecture can be used for power-transmission shafts, for example supercritical shafts in turbine engines.

摘要翻译： 一种架构，使得能够为动力轴提供足够的冲击吸收，同时保持前轴承的刚度，从而不损害驱动小齿轮的动力齿的啮合。 提供可压缩的动态冲击吸收，与附加啮合的下游减震器对准。 用于动力吸收动力轴的冲击的组件包括上游和下游轴承，包括安装在两个壳体上的动力辊并且侧向减速齿啮合。 下游轴承联接到与可压缩减震器相关联的至少一个附加的滚子轴承，以形成相对于与齿啮合相对的上游轴承轴向偏移的下游减震器。 两个下游轴承可以通过安装在公共壳体上的柔性框架连接。 该结构可用于动力传动轴，例如涡轮发动机中的超临界轴。

公开(公告)号：US20090193784A1

公开(公告)日：2009-08-06

申请号：US12023319

申请日：2008-01-31

申请人： Gunnar L. Siden ,  Sal A. Leone ,  John E. Sholes ,  Victor G. Hatman ,  Douglas C. Hofer ,  Thomas W. Vandeputte ,  Sylvain Pierre

发明人： Gunnar L. Siden ,  Sal A. Leone ,  John E. Sholes ,  Victor G. Hatman ,  Douglas C. Hofer ,  Thomas W. Vandeputte ,  Sylvain Pierre

IPC分类号： F02C6/04

CPC分类号： F01D15/10 ,  F02C3/10 ,  F02C3/107 ,  F02C6/00 ,  F02C6/18

摘要： A power generating turbine system that may include: 1) a turbine that includes two sections, a high-pressure turbine section and a low-pressure turbine section that each reside on a separate shaft; 2) an axial compressor that compresses a flow of air that is then mixed with a fuel and combusted in a combustor such that the resulting flow of hot gas is directed through the turbine; 3) a two-pole generator; 4) a four-pole generator; 5) a first shaft that couples the high-pressure turbine section to the axial compressor and the two-pole generator such that, in operation, the high-pressure turbine section drives the axial compressor and the two-pole generator; and 6) a second shaft that couples the low-pressure turbine section to the four-pole generator such that, in operation, the low-pressure turbine section drives the four-pole generator.

摘要翻译： 一种发电涡轮机系统，其可以包括：1）包括两个部分的涡轮机，每个部分都存在于单独的轴上的高压涡轮部分和低压涡轮部分; 2）轴向压缩机，其压缩然后与燃料混合并在燃烧器中燃烧的空气流，使得所产生的热气流引导通过涡轮机; 3）双极发电机; 4）四极发生器; 5）将高压涡轮部分连接到轴向压缩机和双极发生器的第一轴，使得在操作中，高压涡轮部分驱动轴向压缩机和两极发电机; 以及6）第二轴，其将所述低压涡轮部分连接到所述四极发电机，使得在操作中所述低压涡轮部分驱动所述四极发电机。