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11. 发明授权

US07628588B2 Coated bucket damper pin 失效
标题翻译：涂层斗风挡销
公开(公告)号：US07628588B2
公开(公告)日：2009-12-08
申请号：US11902252
申请日：2007-09-20
申请人： Gary Michael Itzel , Ariel Caesar-Prepena Jacala , Doyle C. Lewis , Kathleen B. Morey , David V. Bucci , Ganjiang Feng
发明人： Gary Michael Itzel , Ariel Caesar-Prepena Jacala , Doyle C. Lewis , Kathleen B. Morey , David V. Bucci , Ganjiang Feng
IPC分类号： F01D5/10
CPC分类号： F01D5/22 , F01D5/26 , F05D2230/311 , F05D2230/312 , F05D2230/90 , F05D2250/141 , F05D2300/611 , Y10S416/50 , Y10T29/4932
摘要： A damper pin for a turbine bucket includes an elongated main body portion of substantially uniform cross-sectional shape having opposite ends, one only of said opposite ends coated with a corrosion and oxidation-resistant coating.
摘要翻译：用于涡轮机叶片的阻尼器销包括具有相对端部的基本均匀横截面形状的细长主体部分，仅一个所述相对端部涂覆有耐腐蚀和抗氧化涂层。

12. 发明授权

US06386827B2 Nozzle airfoil having movable nozzle ribs 失效
标题翻译：具有可动喷嘴肋的喷嘴翼型
公开(公告)号：US06386827B2
公开(公告)日：2002-05-14
申请号：US09898470
申请日：2001-07-05
申请人： Yufeng Phillip Yu , Gary Michael Itzel
发明人： Yufeng Phillip Yu , Gary Michael Itzel
IPC分类号： F01D904
CPC分类号： F01D5/147 , F01D5/18 , F01D9/02 , F05D2230/21 , F05D2230/23 , F05D2230/642 , F05D2240/128
摘要： A nozzle vane or airfoil structure is provided in which the nozzle ribs are connected to the side walls of the vane or airfoil in such a way that the ribs provide the requisite mechanical support between the concave side and convex side of the airfoil but are not locked in the radial direction of the assembly, longitudinally of the airfoil. The ribs may be bi-cast onto a preformed airfoil side wall structure or fastened to the airfoil by an interlocking slide connection and/or welding. By attaching the nozzle ribs to the nozzle airfoil metal in such a way that allows play longitudinally of the airfoil, the temperature difference induced radial thermal stresses at the nozzle airfoil/rib joint area are reduced while maintaining proper mechanical support of the nozzle side walls.
摘要翻译：提供喷嘴叶片或翼型结构，其中喷嘴肋与叶片或翼型件的侧壁连接，使得肋在翼型的凹侧和凸面之间提供必要的机械支撑，但不被锁定在组件的径向方向上，翼型的纵向。肋条可以双面铸造到预成型的翼型件侧壁结构上，或通过互锁的滑动连接和/或焊接固定到翼型件上。通过以这样的方式将喷嘴肋连接到喷嘴翼型金属上，使其能够在翼型的纵向上发挥作用，在保持喷嘴侧壁的适当的机械支撑的同时，减小喷嘴翼型/肋接合区域处的温度差引起的径向热应力。

13. 发明授权

US09447691B2 Bucket assembly treating apparatus and method for treating bucket assembly 有权
标题翻译：铲斗总成处理装置及方法
公开(公告)号：US09447691B2
公开(公告)日：2016-09-20
申请号：US13214583
申请日：2011-08-22
申请人： Aaron Ezekiel Smith , Gary Michael Itzel , Scott Edmond Ellis
发明人： Aaron Ezekiel Smith , Gary Michael Itzel , Scott Edmond Ellis
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/81
摘要： A bucket assembly and a method for treating a bucket assembly are disclosed. The bucket assembly includes a platform, the platform defining a platform cooling circuit, and an airfoil extending generally radially outward from the platform, the airfoil defining an airfoil cooling circuit. The bucket assembly additionally includes a lower body portion extending generally radially inward from the platform, the lower body portion defining a root and a cooling passage extending from the root, the cooling passage in fluid communication with the airfoil cooling circuit. The bucket assembly further includes a transfer passage defined between and in fluid communication with the airfoil cooling circuit and the platform cooling circuit such that a cooling medium may flow from the airfoil cooling circuit through the transfer passage to the platform cooling circuit.
摘要翻译：公开了一种用于处理铲斗组件的铲斗组件和方法。铲斗组件包括平台，限定平台冷却回路的平台和从平台大致径向向外延伸的翼型件，翼型件限定翼型冷却回路。铲斗组件还包括从平台大致径向向内延伸的下主体部分，下主体部分限定根部和从根部延伸的冷却通道，冷却通道与翼型件冷却回路流体连通。铲斗组件还包括一个传导通道，其限定在翼型件冷却回路和平台冷却回路之间并与其流体连通，使得冷却介质可以从翼型冷却回路通过传送通道流到平台冷却回路。

14. 发明授权

US08632297B2 Turbine airfoil and method for cooling a turbine airfoil 有权
标题翻译：涡轮机翼和用于冷却涡轮机翼型的方法
公开(公告)号：US08632297B2
公开(公告)日：2014-01-21
申请号：US12893506
申请日：2010-09-29
申请人： Jaime Javier Maldonado , Gary Michael Itzel
发明人： Jaime Javier Maldonado , Gary Michael Itzel
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/143 , F01D5/186 , F01D5/288 , F05D2230/90 , F05D2240/304 , F05D2250/11 , F05D2250/132 , F05D2300/611
摘要： According to one aspect of the invention, a turbine includes a first sidewall, an airfoil positioned between the first sidewall and a second sidewall and a first passage in the airfoil proximate a high temperature region, the first passage configured to receive a cooling fluid, wherein the high temperature region is near an interface of the first sidewall and a trailing edge of the airfoil. The turbine further includes a first diffuser in fluid communication with the first passage, the first diffuser configured to direct the cooling fluid to form a film on a surface of the first sidewall.
摘要翻译：根据本发明的一个方面，涡轮机包括第一侧壁，位于第一侧壁和第二侧壁之间的翼型件以及靠近高温区域的翼型件中的第一通道，第一通道构造成接纳冷却流体，其中高温区域靠近翼型件的第一侧壁和后缘的界面。涡轮机还包括与第一通道流体连通的第一扩散器，第一扩散器构造成引导冷却流体在第一侧壁的表面上形成膜。

15. 发明授权

US08523527B2 Apparatus for cooling a platform of a turbine component 有权
标题翻译：用于冷却涡轮机部件的平台的装置
公开(公告)号：US08523527B2
公开(公告)日：2013-09-03
申请号：US12721040
申请日：2010-03-10
申请人： Benjamin Paul Lacy , Gary Michael Itzel , Bin Wei
发明人： Benjamin Paul Lacy , Gary Michael Itzel , Bin Wei
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2230/11 , F05D2230/12 , F05D2240/81 , F05D2250/184 , F05D2250/71 , F05D2250/713 , F05D2260/22141 , Y02T50/67 , Y02T50/676
摘要： The present subject matter discloses a turbine component including a platform and an airfoil extending radially upward from the platform. A plurality of curved cooling passages may be defined in the platform. Each of the curved cooling passages may have at least one end disposed at an exterior surface of the platform. Additionally, each of the cooling passages may be configured to direct a cooling medium through the platform.
摘要翻译：本主题公开了一种涡轮机部件，包括平台和从平台径向向上延伸的翼型件。可以在平台中限定多个弯曲的冷却通道。每个弯曲的冷却通道可以具有设置在平台的外表面的至少一个端部。此外，每个冷却通道可构造成引导冷却介质通过平台。

16. 发明授权

US08434999B2 Bimetallic spline seal 有权
标题翻译：双金属花键密封
公开(公告)号：US08434999B2
公开(公告)日：2013-05-07
申请号：US12731186
申请日：2010-03-25
申请人： Sergio Daniel Marques Amaral , Gary Michael Itzel , Xiuzhang James Zhang
发明人： Sergio Daniel Marques Amaral , Gary Michael Itzel , Xiuzhang James Zhang
IPC分类号： F01D11/00
CPC分类号： F16J15/0887 , F01D11/005 , F05D2300/50212
摘要： A spline seal for a hot gas path component is provided. The spline seal may include a first metal layer and a second metal layer. The first metal layer may have a first volumetric thermal expansion coefficient. The second metal layer may be disposed adjacent the first metal layer and have a second volumetric thermal expansion coefficient. The second volumetric thermal expansion coefficient may be higher than the first volumetric thermal expansion coefficient. When the spline seal is exposed to a heat source, the first and second metal layers may deform to provide a seal between the hot gas path component and an adjacent hot gas path component.
摘要翻译：提供了用于热气路径部件的花键密封。花键密封件可以包括第一金属层和第二金属层。第一金属层可以具有第一体积热膨胀系数。第二金属层可以邻近第一金属层设置并具有第二体积热膨胀系数。第二体积热膨胀系数可以高于第一体积热膨胀系数。当花键密封件暴露于热源时，第一和第二金属层可以变形以在热气体路径部件和相邻的热气体通道部件之间提供密封。

17. 发明授权

US08376706B2 Turbine airfoil concave cooling passage using dual-swirl flow mechanism and method 有权
标题翻译：涡轮翼型凹形冷却通道采用双旋流动机构及方法
公开(公告)号：US08376706B2
公开(公告)日：2013-02-19
申请号：US11863744
申请日：2007-09-28
申请人： Ronald Scott Bunker , Gary Michael Itzel
发明人： Ronald Scott Bunker , Gary Michael Itzel
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/121 , F05D2240/303 , F05D2250/314 , F05D2250/33 , F05D2250/70 , F05D2260/205 , F05D2260/2212 , F05D2260/22141 , F05D2260/2322
摘要： A turbine airfoil includes a leading edge having a concave cooling flow passage. An apex of the concave cooling flow passage divides the flow passage into adjacent regions. The turbine airfoil includes a first plurality of turbulators disposed in one of the adjacent regions, and a second plurality of turbulators disposed in the other of the adjacent regions. The first and second pluralities of turbulators are positioned relative to one another to divert cooling flow in opposing swirl streams that recombine along the apex and to effect a desired heat transfer and pressure loss.
摘要翻译：涡轮机翼片包括具有凹形冷却流道的前缘。凹形冷却流道的顶点将流动通道分成相邻的区域。涡轮机翼片包括设置在相邻区域之一中的第一多个湍流器和设置在相邻区域中的另一个中的第二多个湍流器。第一和第二多个紊流器相对于彼此定位，以使沿着顶点重新组合的相反旋流中的冷却流转向并实现所需的传热和压力损失。

18. 发明申请

US20120317987A1 HOT GAS PATH COMPONENT 有权
标题翻译：热气道组件
公开(公告)号：US20120317987A1
公开(公告)日：2012-12-20
申请号：US13164113
申请日：2011-06-20
申请人： Gary Michael Itzel , Dipankar Pal
发明人： Gary Michael Itzel , Dipankar Pal
IPC分类号： F23R3/42 , B22D46/00 , F28F1/00
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/202 , F05D2260/22141
摘要： A hot gas path component is provided and includes a body having a surface and being formed to define a cavity, the cavity employing coolant flow through a pin-fin bank with coolant discharge through film-cooling holes defined on the surface, the pin-fin bank including first and second pluralities of pin-fins, the first plurality of pin-fins and the second plurality of pin-fins each being aligned with a determined flow streamline, and any two pin-fins of the first and second pluralities of pin-fins being separated from one another by a gap as a function of a film-cooling hole dimension.
摘要翻译：提供了一种热气体通道部件，其包括具有表面并形成为限定空腔的本体，所述腔体采用冷却剂流过穿过翅片组的销翅片组，其中冷却剂通过限定在表面上的薄膜冷却孔排出，其包括第一和第二多个销翅片，所述第一多个销翅片和所述第二多个销翅片各自与确定的流线路对准，并且所述第一和第二多个针脚翅片的任何两个销翅片，翅片通过作为膜冷却孔尺寸的函数的间隙彼此分离。

19. 发明申请

US20120114480A1 SYSTEM AND METHOD FOR COOLING A TURBINE BUCKET 失效
标题翻译：用于冷却涡轮机的系统和方法
公开(公告)号：US20120114480A1
公开(公告)日：2012-05-10
申请号：US12939576
申请日：2010-11-04
申请人： Sergio Daniel Marques Amaral , Gary Michael Itzel , Xiuzhang James Zhang , Camilo Andres Sampayo
发明人： Sergio Daniel Marques Amaral , Gary Michael Itzel , Xiuzhang James Zhang , Camilo Andres Sampayo
IPC分类号： F01D5/18
CPC分类号： F01D5/081 , F01D5/22 , F01D25/12 , F05D2240/57 , F05D2260/96
摘要： A turbine bucket includes an airfoil, a platform adjacent to the airfoil, and a shank adjacent to the platform. The shank defines a shank cavity, and a divider in the shank cavity creates a pressure differential across the shank cavity. A method for cooling a turbine bucket includes directing a fluid to a forward shank cavity and creating a pressure differential between the forward shank cavity and an aft shank cavity.
摘要翻译：涡轮机桶包括翼型件，与翼型件相邻的平台以及与该平台相邻的柄部。柄部限定了柄腔，并且柄腔中的分隔件在柄腔中形成压差。一种用于冷却涡轮机铲斗的方法包括将流体引导到前柄腔，并在前柄腔和后柄腔之间产生压力差。

20. 发明授权

US07811054B2 Shroud configuration having sloped seal 失效
标题翻译：护罩配置具有倾斜密封
公开(公告)号：US07811054B2
公开(公告)日：2010-10-12
申请号：US11806140
申请日：2007-05-30
申请人： John Alan Eastman , Gary Michael Itzel , Charles Malinowski , Victor Morgan , David Richard Johns , Bryan Lewis
发明人： John Alan Eastman , Gary Michael Itzel , Charles Malinowski , Victor Morgan , David Richard Johns , Bryan Lewis
IPC分类号： F01D25/24
CPC分类号： F01D11/08 , F05D2240/11 , F05D2250/192 , F05D2250/70
摘要： A stator shroud segment is provided that includes an outer shroud having a leading edge groove and a trailing edge groove; and a plurality of inner shrouds each having a leading edge hook and a trailing edge hook, the leading and trailing hooks of each of the inner shrouds being respectively engaged with the leading and trailing edge grooves of the outer shroud so as to axially and radially lock the inner shrouds to the outer shrouds. At least one of the trailing edge hook of the inner shroud and the trailing edge groove of the outer shroud includes a sloped surface disposed at an angle to an axial direction of the rotor and to a radial direction of the rotor and facing the other of the inner and outer shrouds whereby a radial inward force on the inner shroud is transformed into a force in axial and radial directions to force the inner shroud to tightly seal a radial gap between the inner and outer shrouds.
摘要翻译：提供了一种定子护罩段，其包括具有前缘槽和后缘槽的外护罩; 以及多个内护罩，每个内护罩具有前缘钩和后缘钩，每个内护罩的前钩和尾钩分别与外护罩的前缘和后缘槽啮合，从而轴向和径向锁定内护罩到外护罩。内护罩的后缘钩和外护罩的后缘槽中的至少一个包括倾斜表面，该倾斜表面设置成与转子的轴向方向成一定角度并且与转子的径向方向相对，内部和外部护罩，由此内部护罩上的径向向内的力在轴向和径向方向上被转换成力，以迫使内部护罩紧密地密封内部和外部护罩之间的径向间隙。

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