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1. 发明申请

US20060139221A1 Multi piece puzzle-lock antenna using flex film radiator 失效
公开(公告)号：US20060139221A1
公开(公告)日：2006-06-29
申请号：US11358230
申请日：2006-02-21
申请人： Thomas Murray , Ying Song , Cheryl Mayer , Brian Potter
发明人： Thomas Murray , Ying Song , Cheryl Mayer , Brian Potter
IPC分类号： H01Q1/24
CPC分类号： H01Q1/242 , H01Q1/38 , H01Q9/40 , H01Q9/42
摘要： The present invention provides a flexible film antenna. The flexible film antenna includes a radiating element comprising a conductive trace on a flexible film. Flexible film is mounted on a core. The core comprises at least two parts that are releasably coupled together in snap or sliding relation. A feed post extends out a base of the core to connect to a power feed. Finally, a protective housing can be molded over the antenna.

2. 发明申请

US20050088350A1 Multi piece puzzle-lock antenna using flex film radiator 失效
标题翻译：多功能拼图锁天线采用柔性薄膜散热器
公开(公告)号：US20050088350A1
公开(公告)日：2005-04-28
申请号：US10939738
申请日：2004-09-13
申请人： Thomas Murry , Ying Song , Cheryl Mayer , Brian Potter
发明人： Thomas Murry , Ying Song , Cheryl Mayer , Brian Potter
IPC分类号： H01Q1/24 , H01Q1/38 , H01Q9/40 , H01Q9/42
CPC分类号： H01Q1/242 , H01Q1/38 , H01Q9/40 , H01Q9/42
摘要： The present invention provides a flexible film antenna. The flexible film antenna includes a radiating element comprising a conductive trace on a flexible film. Flexible film is mounted on a core. The core comprises at least two parts that are releasably coupled together in snap or sliding relation. A feed post extends out a base of the core to connect to a power feed. Finally, a protective housing can be molded over the antenna.
摘要翻译：本发明提供一种柔性薄膜天线。柔性膜天线包括在柔性膜上包括导电迹线的辐射元件。柔性膜安装在芯上。芯部包括至少两个部件，其以卡扣或滑动关系可释放地联接在一起。进料柱延伸出芯的基部以连接到电源。最后，可以在天线上模制保护壳体。

3. 发明申请

US20050260078A1 Laminated turbomachine airfoil with jacket and method of making the airfoil 有权
标题翻译：具有夹套的层压涡轮机翼型和制造翼型的方法
公开(公告)号：US20050260078A1
公开(公告)日：2005-11-24
申请号：US11061313
申请日：2005-02-18
申请人： Brian Potter , Brad Carter , John Ryznic
发明人： Brian Potter , Brad Carter , John Ryznic
IPC分类号： F01D5/28 , F01D5/30 , B63H1/20
CPC分类号： F01D5/282 , F01D5/3007 , F01D5/3092
摘要： An improvement for a turbomachinery blade having an airfoil portion, a neck portion, and a root portion, the neck portion extending from the root portion, and the airfoil portion extending from the neck portion, and the root portion being tear-drop shaped, includes a jacket attached to the root portion and extending along a portion of the neck portion. Additionally, a process of forming a turbomachinery blade includes steps of providing a laminate of a material; providing a blade insert; wrapping the laminate around to insert to form a blade having a root portion, a neck portion extending from the root portion, and an airfoil portion extending from the neck portion; and providing for a jacket secured around the root portion and a portion of the neck portion extending from the root portion, the jacket having such shape as to prevent delamination of the laminates at a critical point due to centrifugal force acting on the blade.
摘要翻译：具有翼型部分，颈部和根部的涡轮机叶片的改进，颈部从根部延伸，并且从颈部延伸的翼型部分和泪滴形状的根部包括护套，其附接到根部并且沿着颈部的一部分延伸。此外，形成涡轮机械刀片的方法包括提供材料层压体的步骤; 提供刀片插入件; 缠绕层压体以插入以形成具有根部部分的叶片，从根部延伸的颈部部分和从颈部部分延伸的翼型部分; 并且提供固定在根部周围的护套和从根部延伸的颈部的一部分，护套具有这样的形状，以防止由于作用在刀片上的离心力在临界点处层压体的分层。

4. 发明授权

US4733354A Method and apparatus for automated medical diagnosis using decision tree analysis 失效
标题翻译：使用决策树分析的自动医学诊断方法和装置
公开(公告)号：US4733354A
公开(公告)日：1988-03-22
申请号：US674130
申请日：1984-11-23
申请人： Brian Potter , Michael C. Potter
发明人： Brian Potter , Michael C. Potter
IPC分类号： G06F19/00
CPC分类号： G06F19/324 , G06F19/345 , G06F19/3487 , Y10S128/924 , Y10S706/924
摘要： An interactive method for performing a differential medical diagnosis utilizing a programmed computer system and a stored data base. In one particular embodiment, the method is for making a dermatopathological diagnosis based on operator selections from data files sequentially presented from the broadest scope to the narrowest scope. The data base is stored in a forwardly and backwardly linked hierarchical array of data files. If the data base were graphically arranged according to the linkages, it would appear in the form of a decision tree having a plurality of levels, each level encompassing the entire subject matter of dermatopathology. Each data file in the data base corresponds to a node of the decision tree and the records in the data file correspond to the branches.
摘要翻译：一种用于使用编程的计算机系统和存储的数据库执行差分医疗诊断的交互方法。在一个具体实施例中，该方法用于基于从最宽范围到最窄范围顺序呈现的数据文件的操作员选择进行皮肤病理学诊断。数据库存储在数据文件的前向和后向链接的分层数组中。如果数据库根据链接图形排列，则它将以具有多个级别的决策树的形式出现，每个级别包含皮肤病理学的整个主题。数据库中的每个数据文件对应于决策树的一个节点，数据文件中的记录对应于分支。

5. 发明授权

US07300255B2 Laminated turbomachine airfoil with jacket and method of making the airfoil 有权
标题翻译：具有夹套的层压涡轮机翼型和制造翼型的方法
公开(公告)号：US07300255B2
公开(公告)日：2007-11-27
申请号：US11061313
申请日：2005-02-18
申请人： Brian Potter , Brad Carter , John Ryznic
发明人： Brian Potter , Brad Carter , John Ryznic
IPC分类号： F01D5/30 , F01D5/12
CPC分类号： F01D5/282 , F01D5/3007 , F01D5/3092
摘要： An improvement for a turbomachinery blade having an airfoil portion, a neck portion, and a root portion, the neck portion extending from the root portion, and the airfoil portion extending from the neck portion, and the root portion being tear-drop shaped, includes a jacket attached to the root portion and extending along a portion of the neck portion. Additionally, a process of forming a turbomachinery blade includes steps of providing a laminate of a material; providing a blade insert; wrapping the laminate around to insert to form a blade having a root portion, a neck portion extending from the root portion, and an airfoil portion extending from the neck portion; and providing for a jacket secured around the root portion and a portion of the neck portion extending from the root portion, the jacket having such shape as to prevent delamination of the laminates at a critical point due to centrifugal force acting on the blade.
摘要翻译：具有翼型部分，颈部和根部的涡轮机叶片的改进，颈部从根部延伸，并且从颈部延伸的翼型部分和泪滴形状的根部包括护套，其附接到根部并且沿着颈部的一部分延伸。此外，形成涡轮机械刀片的方法包括提供材料层压体的步骤; 提供刀片插入件; 缠绕层压体以插入以形成具有根部部分的叶片，从根部延伸的颈部部分和从颈部部分延伸的翼型部分; 并且提供固定在根部周围的护套和从根部延伸的颈部的一部分，护套具有这样的形状，以防止由于作用在刀片上的离心力在临界点处层压体的分层。

6. 发明授权

US06929453B2 Locking spacer assembly for slotted turbine component 失效
标题翻译：用于开槽涡轮机部件的锁定间隔件组件
公开(公告)号：US06929453B2
公开(公告)日：2005-08-16
申请号：US10733737
申请日：2003-12-11
申请人： Edwin L. Kite , Brian Potter , Paul Matheny
发明人： Edwin L. Kite , Brian Potter , Paul Matheny
IPC分类号： F01D5/30 , F01D5/32
CPC分类号： F01D5/32 , F01D5/3038
摘要： Aspects according to the invention relate to a locking spacer assembly for a slotted turbine engine component. In one embodiment, aspects of the invention can be used in connection with the assembly and disassembly of a disc hosting a row of airfoils as can be found in the compressor or turbine section of a turbine engine. The spacer according to the invention is a multi-part assembly. In one embodiment, the spacer includes at least three sub-components: first and second end supports and a filler. The inner and outer faces of each of these components can have various features to facilitate engagement of the assembly and distribution of centrifugal loads in operation. These parts can be held together by a retainer, which can be received in a cutout provided in the end supports and the filler.
摘要翻译：根据本发明的方面涉及一种用于开槽涡轮发动机部件的锁定间隔件组件。在一个实施例中，本发明的各方面可以用于组装和拆卸承载一排翼型件的盘，如可以在涡轮发动机的压缩机或涡轮机部分中发现的那样。根据本发明的间隔件是多部件组件。在一个实施例中，间隔件包括至少三个子部件：第一和第二端部支撑件和填料。这些部件中的每一个的内表面和外表面可以具有各种特征，以便于操作中离合负载的组装和分配的接合。这些部件可以通过保持器保持在一起，该保持器可以容纳在设置在端部支撑件和填料中的切口中。

7. 发明申请

US20050129522A1 LOCKING SPACER ASSEMBLY FOR SLOTTED TURBINE COMPONENT 失效
标题翻译：用于油压涡轮机组件的闭锁间隔装置
公开(公告)号：US20050129522A1
公开(公告)日：2005-06-16
申请号：US10733737
申请日：2003-12-11
申请人： Edwin Kite , Brian Potter , Paul Matheny
发明人： Edwin Kite , Brian Potter , Paul Matheny
IPC分类号： F01D5/30
CPC分类号： F01D5/32 , F01D5/3038
摘要： Aspects according to the invention relate to a locking spacer assembly for a slotted turbine engine component. In one embodiment, aspects of the invention can be used in connection with the assembly and disassembly of a disc hosting a row of airfoils as can be found in the compressor or turbine section of a turbine engine. The spacer according to the invention is a multi-part assembly. In one embodiment, the spacer includes at least three sub-components: first and second end supports and a filler. The inner and outer faces of each of these components can have various features to facilitate engagement of the assembly and distribution of centrifugal loads in operation. These parts can be held together by a retainer, which can be received in a cutout provided in the end supports and the filler.
摘要翻译：根据本发明的方面涉及一种用于开槽涡轮发动机部件的锁定间隔件组件。在一个实施例中，本发明的各方面可以用于组装和拆卸承载一排翼型件的盘，如可以在涡轮发动机的压缩机或涡轮机部分中发现的那样。根据本发明的间隔件是多部件组件。在一个实施例中，间隔件包括至少三个子部件：第一和第二端部支撑件和填料。这些部件中的每一个的内表面和外表面可以具有各种特征，以便于操作中离合负载的组装和分配的接合。这些部件可以通过保持器保持在一起，该保持器可以容纳在设置在端部支撑件和填料中的切口中。

8. 发明授权

US07931443B1 High twist composite blade 失效
标题翻译：高扭复合叶片
公开(公告)号：US07931443B1
公开(公告)日：2011-04-26
申请号：US11827055
申请日：2007-07-10
申请人： Brian Potter , Alfred P. Matheny
发明人： Brian Potter , Alfred P. Matheny
IPC分类号： F01D5/26
CPC分类号： F01D5/26 , F01D5/282 , F05D2260/96 , Y10S416/50
摘要： A turbomachine with a row of blades in which the blades are structured such that the blades can untwist at higher rotational speeds in order to provide optimal aerodynamics at different rotational speeds. Each blade is formed with a thin slot between the pressure side wall and the suction side wall so that stresses from centrifugal forces occurring during high rotations will not pass from adjacent walls and allow for the blade to untwist more than a solid blade. Each blade is formed from a fiber laminated composite material with the fibers oriented at different directions to form different stiffness in each direction so that a desired untwist can occur based upon a given blade mass and rotational speed. A thin sheet of a slippery material can be placed within the thin slot and between the adjacent airfoil walls to allow slippage between the adjacent walls and to promote damping for the blade.
摘要翻译：具有一排叶片的涡轮机，其中叶片被构造成使得叶片能够以更高的旋转速度解开，以便在不同的转速下提供最佳的空气动力学。每个叶片在压力侧壁和吸力侧壁之间形成有薄的狭槽，使得在高转速期间产生的离心力的应力将不会从相邻的壁通过，并且允许刀片比固体刀片解捻更多。每个叶片由纤维层压复合材料形成，其中纤维在不同方向上定向，以在每个方向上形成不同的刚度，使得基于给定的叶片质量和转速可以发生所需的解捻。可以在薄槽内和相邻的翼型件壁之间放置薄的滑动材料，以允许相邻壁之间滑动并促进叶片的阻尼。

9. 发明授权

US07435055B2 Locking spacer assembly for a turbine engine 有权
标题翻译：用于涡轮发动机的锁定间隔件组件
公开(公告)号：US07435055B2
公开(公告)日：2008-10-14
申请号：US11093162
申请日：2005-03-29
申请人： Christian M. Hansen , Alfred P. Matheny , Brian Potter
发明人： Christian M. Hansen , Alfred P. Matheny , Brian Potter
IPC分类号： F01D5/32
CPC分类号： F01D5/32 , F01D5/3038
摘要： A locking spacer assembly for filling a void between adjacent components in a turbine engine. In at least one embodiment, the locking spacer assembly may be configured to be inserted between adjacent turbine blades in a disc groove in a turbine blade stage assembly. The locking spacer assembly may be formed from fore and aft end supports and a locking device having fore and aft angled surfaces for urging the fore and aft end supports into lateral recesses in the disc groove. The locking spacer assembly may also include a mid spacer positioned between the fore and aft end supports. A retainer may be attached to the locking device to draw the fore and aft angled surfaces of the locking device into contact with the fore and aft support surfaces and urge the first and second end supports into lateral recesses in the disc groove.
摘要翻译：一种用于填充涡轮发动机中的相邻部件之间的空隙的锁定间隔件组件。在至少一个实施例中，锁定间隔件组件可构造成在涡轮叶片级组件中的盘槽中插入相邻的涡轮叶片之间。锁定间隔件组件可以由前端支撑件和后端支撑件形成，并且锁定装置具有前后成角度的表面，用于将前端支撑件和后端支撑件推进到盘槽中的横向凹槽中。锁定间隔件组件还可以包括位于前端支撑件和后端支架之间的中间间隔件。保持器可以附接到锁定装置以拉动锁定装置的前后角度的表面与前后支撑表面接触并且将第一和第二端部支撑件推动到盘槽中的侧向凹部中。

10. 发明授权

US07399159B2 Detachable leading edge for airfoils 失效
标题翻译：可拆卸的翼型前缘
公开(公告)号：US07399159B2
公开(公告)日：2008-07-15
申请号：US10876081
申请日：2004-06-24
申请人： Paul Matheny , Brad Carter , Brian Potter
发明人： Paul Matheny , Brad Carter , Brian Potter
IPC分类号： F01D5/28
CPC分类号： F01D5/147 , F01D5/16 , F04D29/324 , F05D2240/303 , Y02T50/672 , Y02T50/673
摘要： The airfoil of fan/compressor and turbine rotors is constructed to include a leading edge that is detachable. The leading edge includes an airfoil section and an attachment that is adapted to fit into a complementary groove formed in the rotor disk. The detachable leading edge is efficacious in integrated bladed rotor (IBR or BLISK) designs because damage to the leading edge can be fixed by either removing the leading edge and repairing it or replacing it without having to disturb the remaining portion of the IBR.
摘要翻译：风扇/压缩机和涡轮转子的翼型被构造成包括可拆卸的前缘。前缘包括翼型部分和适于装配到形成在转子盘中的互补槽的附件。可拆卸的前缘在集成叶片转子（IBR或BLISK）设计中是有效的，因为前缘的损坏可以通过去除前缘并进行修复或更换，而不必干扰IBR的剩余部分来固定。

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