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1. 发明申请

US20060252308A1 Hazard boundary termination box 审中-公开
标题翻译：危险边界终端盒
公开(公告)号：US20060252308A1
公开(公告)日：2006-11-09
申请号：US11122570
申请日：2005-05-05
申请人： Jasbir Bhatia , Maurice Jenkins
发明人： Jasbir Bhatia , Maurice Jenkins
IPC分类号： H01R13/73
CPC分类号： H01R13/748 , H01R13/5202
摘要： A termination box, for maintaining an electrical connection across a boundary, can include a terminal block comprising a heat-resistant, non-conducive material having a first surface and a second surface. The first surface can include electrical terminals thereon connected to electrically conductive linkages passing through the terminal block and connecting to electrical terminals on the second surface of the terminal block. The termination box can also include a first cover and a second cover each having a cable conduit passing therethrough for receiving an electrical cable from the respective side of the boundary.
摘要翻译：用于维持跨越边界的电连接的终端盒可以包括端子块，其包括具有第一表面和第二表面的耐热非导电材料。第一表面可以包括其上连接到通过端子块的导电连接件并且连接到端子块的第二表面上的电端子的电端子。终端盒还可以包括第一盖和第二盖，每个盖具有穿过其中的电缆导管，用于从边界的相应侧接收电缆。

2. 发明申请

US20060093484A1 Cooling system for a platform of a turbine blade 有权
标题翻译：涡轮叶片平台的冷却系统
公开(公告)号：US20060093484A1
公开(公告)日：2006-05-04
申请号：US10981290
申请日：2004-11-04
申请人： George Liang
发明人： George Liang
IPC分类号： F01D11/00
CPC分类号： F01D5/18 , F05D2240/81
摘要： A turbine blade for a turbine engine having a platform cooling system formed from one or more platform cooling channels extending from an inner cooling cavity in a root of a turbine blade to an outer surface of a platform on the turbine blade. The platform cooling channels may be positioned in ribs protruding from a bottom surface of the platform. The ribs act as fins during operation of a turbine engine in which the turbine blade is installed by increasing surface area of the platform and thereby increasing convection on the bottom surface.
摘要翻译：一种用于涡轮发动机的涡轮机叶片，其具有由一个或多个平台冷却通道形成的平台冷却系统，所述平台冷却通道从涡轮叶片的根部内的内部冷却腔延伸到涡轮叶片上的平台的外表面。平台冷却通道可以定位在从平台的底表面突出的肋中。在涡轮发动机的操作期间，肋条作为翅片起作用，其中通过增加平台的表面积从而增加底面上的对流来安装涡轮叶片。

3. 发明申请

US20060251521A1 Method of repairing a threaded generator rotor blower assembly 有权
标题翻译：修理螺旋发电机转子鼓风机组件的方法
公开(公告)号：US20060251521A1
公开(公告)日：2006-11-09
申请号：US11122569
申请日：2005-05-05
申请人： Gabriel Hernandez , Jeffrey Mallat
发明人： Gabriel Hernandez , Jeffrey Mallat
IPC分类号： F01D5/30
CPC分类号： F01D5/005 , B23P6/005 , F01D5/3023 , F04D29/322 , F04D29/34
摘要： A method of repairing a generator blower hub assembly (12) and rotor blade (10) removed from the generator blower hub assembly (12) where the rotor blade (10) has fatigued material in threads of a threaded blade root (14). The method may include removing (32) at least a portion of the fatigued material to form the blade root (14) to a first or new diameter. Threads may be formed (36) on the diameter of the blade root (14) using a roll forming process. A collar (20) may be secured within a threaded hole (16) formed in the generator blower hub assembly (12) where the collar (20) includes internal threads (35) for receiving the threads formed on the diameter of the blade root (14), which may be threaded into the collar (20). Collar (20) may be fabricated of steel alloy and include relief groove (40) for improving the fatigue resistance of the threaded blade root (14) when reassembled into the generator blower hub assembly (12).
摘要翻译：一种修理从发电机鼓风机毂组件（12）移除的发电机鼓风机毂组件（12）和转子叶片（10）的方法，其中转子叶片（10）具有螺纹叶片根部（14）的螺纹中的疲劳材料。该方法可以包括移除（32）至少一部分疲劳材料以形成叶片根部（14）至第一或新的直径。螺纹可以使用辊成型工艺在叶片根部（14）的直径上形成（36）。轴环（20）可以固定在形成在发电机鼓风机毂组件（12）中的螺纹孔（16）内，其中轴环（20）包括内螺纹（35），用于接收形成在叶片根部的直径上的螺纹 14），其可以拧入轴环（20）中。轴环（20）可以由钢合金制成，并且包括用于在重新组装到发电机鼓风机毂组件（12）中时改善螺纹叶片根部（14）的抗疲劳性的释放槽（40）。

4. 发明申请

US20060182971A1 Tabbed ceramic article for improved interlaminar strength 有权
标题翻译：用于提高层间强度的标签陶瓷制品
公开(公告)号：US20060182971A1
公开(公告)日：2006-08-17
申请号：US11059221
申请日：2005-02-16
申请人： Gary Merrill , Jay Morrison
发明人： Gary Merrill , Jay Morrison
IPC分类号： B32B17/10
CPC分类号： C04B35/80 , B32B18/00 , C04B2237/32 , C04B2237/38 , C04B2237/64 , Y10T428/24289 , Y10T428/249928 , Y10T428/31
摘要： A ceramic article having improved interlaminar strength and a method of forming the article. The article may be a ceramic matrix composite article. The methods of forming the articles increase the interlaminar strength of the article by forming indentations in the article during processing. The indentations may be tabs that are formed such that they provide one or more beneficial features for ceramic articles, such as CMC articles and hybrid structures. The tabs may be any of a variety of shapes, orientations, spacings, and combinations. In an alternative embodiment, the indentations are formed by pulling one or more fibers from one side of the ceramic layer to the other side. The articles have increased surface area, which helps to increase the bonding strength between the ceramic layer and any thermal barrier coating layer and/or ceramic core in the ceramic article.
摘要翻译：具有改善的层间强度的陶瓷制品和形成该制品的方法。该制品可以是陶瓷基复合制品。形成制品的方法通过在加工过程中在制品中形成凹痕来增加制品的层间强度。压痕可以是形成为使得它们为陶瓷制品（例如CMC制品和混合结构）提供一个或多个有益特征的凸片。翼片可以是各种形状，取向，间距和组合中的任何一个。在替代实施例中，通过将一个或多个纤维从陶瓷层的一侧拉到另一侧而形成凹口。制品具有增加的表面积，这有助于增加陶瓷制品中陶瓷层和任何热障涂层和/或陶瓷芯之间的结合强度。

5. 发明申请

US20060185345A1 Cooled transition duct for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的冷却过渡管道
公开(公告)号：US20060185345A1
公开(公告)日：2006-08-24
申请号：US11062970
申请日：2005-02-22
申请人： Jody Wilson , Raymond Nordlund , Adam Weaver
发明人： Jody Wilson , Raymond Nordlund , Adam Weaver
IPC分类号： F23R3/42
CPC分类号： F01D25/12 , F01D9/023 , F05D2250/312 , F05D2260/20
摘要： A transition duct (30) for a gas turbine engine (2) having improved cooling and reduced stress levels. The transition duct may be formed of two panels ((36, 38) joined together with welds (40) disposed remote from the bent corner regions (34) of the panels. Cooling channels (32) extending longitudinally in the direction of flow of the hot combustion gas carried by the duct are formed within each panel, including the corner regions. Because the entire annular width (W) of the transition duct is cooled, the gap (G) separating adjacent ducts around the inlet to the turbine (4) may be reduced when compared to prior art designs. Two-panel construction with welds remote from the corner regions is facilitated by maintaining the minimum bend radius in the corners (R2) and in the direction of flow (R4) to be greater than in prior art designs.
摘要翻译：一种用于具有改进的冷却和降低的应力水平的燃气涡轮发动机（2）的过渡管道（30）。过渡管道可以由两个面板（（36,38）形成，所述两个面板（36,38）与远离所述面板的弯曲拐角区域（34）设置的焊缝（40）连接在一起。冷却通道（32）由于过渡管道的整个环形宽度（W）被冷却，所以在每个面板内形成由管道承载的热燃烧气体，包括拐角区域，使围绕涡轮机（4）的入口周围的相邻管道的间隙（G）与现有技术的设计相比可以减少。通过保持拐角（R SUB 2＆lt; 2＆gt;）和流动方向上的最小弯曲半径（R 2> 2 < R 4）比现有技术的设计中要大。

6. 发明申请

US20060174625A1 Can-annular turbine combustors comprising swirler assembly and base plate arrangements, and combinations 有权
标题翻译：包括旋流器组件和底板装置的罐式涡轮机燃烧器以及组合
公开(公告)号：US20060174625A1
公开(公告)日：2006-08-10
申请号：US11051799
申请日：2005-02-04
申请人： Rajeev Ohri
发明人： Rajeev Ohri
IPC分类号： F23R3/14
CPC分类号： F23R3/14 , F23R3/286 , F23R3/343 , F23R2900/00005
摘要： A gas turbine combustor (10) comprises a main swirler assembly (400) comprising an annulus casting (410) itself comprising a modified downstream end (418) fitted into an reversed-edge base plate (450) that comprises an opening (453) defined by a lip (452) oriented upstream. The lip (452) comprises an upstream surface (457), an outboard surface (458) and an inboard surface (459). In certain embodiments the modified downstream end (418) has a shape to fit against the upstream surface (457) and the outboard surface (458) so as to increase the natural frequency of the main swirler assembly (400) to above the natural frequency of the combustion in the gas turbine combustor (10).
摘要翻译：燃气涡轮机燃烧器（10）包括主旋流器组件（400），主旋流器组件（400）包括环形铸件（410），其包括装配到反向边缘基板（450）中的改进的下游端（418），所述改进的下游端（418）包括限定的开口（453）通过面向上游的唇缘（452）。唇缘（452）包括上游表面（457），外侧表面（458）和内侧表面（459）。在某些实施例中，改进的下游端（418）具有适合抵靠上游表面（457）和外侧表面（458）的形状，以便将主旋流器组件（400）的固有频率增加到高于固有频率燃气轮机燃烧器（10）中的燃烧。

7. 发明申请

US20060153678A1 Cooling system with internal flow guide within a turbine blade of a turbine engine 有权
标题翻译：具有在涡轮发动机的涡轮叶片内的内部流动引导件的冷却系统
公开(公告)号：US20060153678A1
公开(公告)日：2006-07-13
申请号：US11031793
申请日：2005-01-07
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/22141 , F05D2260/607
摘要： A turbine blade for a turbine engine having a cooling system in the turbine blade formed from at least one cooling channel. The cooling channel may be a serpentine cooling channel with a flow guide extending from a first turn to a second turn of the cooling channel and formed from a first turn section, a second turn section, and a body coupling the first and second turn sections together. The flow guide substantially eliminates separation of cooling fluid flow in the tip region of the cooling channel, thereby increasing heat transfer. In at least one embodiment, the flow guide extends from a first turn in the cooling channel proximate to the blade tip to a second turn proximate to a root of the blade.
摘要翻译：一种用于涡轮发动机的涡轮叶片，其具有由至少一个冷却通道形成的涡轮叶片中的冷却系统。冷却通道可以是蛇形冷却通道，其具有从冷却通道的第一匝延伸到第二匝的流动引导件，并且由第一匝部分，第二匝部分和将第一和第二匝部分联接在一起的主体。流动引导件基本上消除了在冷却通道的尖端区域中的冷却流体流动的分离，从而增加了热传递。在至少一个实施例中，流动引导件从靠近叶片尖端的冷却通道中的第一匝延伸到接近叶片根部的第二匝。

8. 发明申请

US20060171808A1 Vortex dissipation device for a cooling system within a turbine blade of a turbine engine 有权
标题翻译：用于涡轮发动机的涡轮叶片内的冷却系统的涡流耗散装置
公开(公告)号：US20060171808A1
公开(公告)日：2006-08-03
申请号：US11049238
申请日：2005-02-02
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F05D2240/127 , F05D2260/2212
摘要： A turbine blade for a turbine engine having a cooling system in the turbine blade formed from at least one cooling channel. The cooling system may include one or more protrusions positioned in the cooling channel and including one or more vortex breakers along the length of the protrusion. The vortex breakers disrupt vortices formed downstream of the protrusions to increase heat transfer enhancement effect of the protrusions. The cooling channels of the cooling system may include a plurality of protrusions whose configuration is based upon the cooling requirements of the blade in which the cooling system is installed.
摘要翻译：一种用于涡轮发动机的涡轮叶片，其具有由至少一个冷却通道形成的涡轮叶片中的冷却系统。冷却系统可以包括位于冷却通道中的一个或多个突起，并且包括沿着突出部的长度的一个或多个涡流破坏器。涡流破碎器破坏在突起下游形成的涡流，以增加突起的传热增强效果。冷却系统的冷却通道可以包括多个突起，其构造基于其中安装冷却系统的叶片的冷却要求。

9. 发明申请

US20060162314A1 Cooling system for a transition bracket of a transition in a turbine engine 有权
标题翻译：用于涡轮发动机过渡的过渡支架的冷却系统
公开(公告)号：US20060162314A1
公开(公告)日：2006-07-27
申请号：US11044766
申请日：2005-01-27
申请人： Bradley Youngblood
发明人： Bradley Youngblood
IPC分类号： F23R3/42
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/20
摘要： A heat shield for a transition of a turbine engine for coupling a transition component of a turbine engine to a turbine vane assembly to direct combustor exhaust gases from the transition into the turbine vane assembly. The heat shield may be capable of reducing the temperature differential across a transition bracket extending from a transition component, thereby reducing the likelihood of premature failure of the bracket or the transition, or both. The heat shield may reduce the temperature differential by insulating the transition bracket and transition bracket rib from cooling gases. The heat shield may be formed from a tubular elongated body having first and second end attachments configured to attach the elongated heat shield body to the transition.
摘要翻译：一种用于涡轮发动机过渡的隔热罩，用于将涡轮发动机的过渡部件耦合到涡轮叶片组件，以将燃烧器废气引导到从涡轮机叶片组件的过渡部分。隔热罩可能能够降低从过渡部件延伸的过渡托架上的温差，从而降低托架过渡或过渡的过早或两者的可能性。隔热罩可以通过将过渡支架和过渡支架肋条与冷却气体隔离来降低温差。隔热罩可以由管状细长体形成，其具有构造成将细长的热屏蔽体附接到过渡部的第一和第二端附件。

10. 发明申请

US20060120874A1 Stacked lamellate assembly 有权
标题翻译：堆叠层状组件
公开(公告)号：US20060120874A1
公开(公告)日：2006-06-08
申请号：US11031797
申请日：2005-01-07
申请人： Michael Burke , Jay Morrison , Steven Vance , Daniel Thompson , Vijay Parthasarathy , Gary Merrill , Douglas Keller
发明人： Michael Burke , Jay Morrison , Steven Vance , Daniel Thompson , Vijay Parthasarathy , Gary Merrill , Douglas Keller
IPC分类号： F04D29/38
CPC分类号： F01D5/147 , F01D5/284 , F04D29/388 , F05D2230/23 , F05D2300/601 , F05D2300/603 , F05D2300/614
摘要： A stacked ceramic matrix composite lamellate assembly (10) including shear force bearing structures (48) for resisting relative sliding movement between adjacent lamellae. The shear force bearing structures may take the form of a cross-lamellar stitch (50), a shear pin (62), a warp (90) in the lamellae, a tongue (104) and groove (98) structure, or an inter-lamellar sealing member (112), in various embodiments. Each shear force bearing structure secures a subset of the lamellae, with at least one lamella being common between adjacent subsets in order to secure the entire assembly.
摘要翻译：一种层叠的陶瓷基复合材料层状组件（10），其包括用于抵抗相邻薄片之间的相对滑动运动的剪切力轴承结构（48）。剪切力承载结构可以采取跨层状缝合（50），剪切销（62），薄片中的经线（90），舌状物（104）和凹槽（98）结构的形式， - 绝缘密封件（112）。每个剪切力轴承结构确保薄片的一个子集，其中至少一个薄片在相邻子集之间是共同的，以便固定整个组件。

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