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    • 2. 发明授权
    • Patient support brake system
    • 患者支持制动系统
    • US08196237B2
    • 2012-06-12
    • US12470155
    • 2009-05-21
    • Cory HerbstJohn ZerbelEugene L. Keller, IIIMike BrubakerDouglas Keller
    • Cory HerbstJohn ZerbelEugene L. Keller, IIIMike BrubakerDouglas Keller
    • A61G1/02
    • F16D63/006A61G7/05
    • A movable patient support includes a frame, a patient support surface supported at the frame, a base supporting the frame and having a plurality of bearing assemblies for moving the base along a floor surface. The support also includes a brake, a brake actuator for actuating the brake of at least one bearing assembly, and a brake bar coupled to the brake actuator. The brake bar is movable between a non-braking position and a braking position wherein the actuator causes the brake to move to its braking position. Further, the brake bar extends between the head end and the foot end of the frame and further has a portion extending outwardly from the brake actuator to at least close proximity to the bearing footprint defined by the bearing assemblies but within the frame footprint to thereby provide relatively easy access to the brake bar to an attendant standing adjacent one of the longitudinal sides of the frame.
    • 可移动的患者支撑件包括框架,支撑在框架处的患者支撑表面,支撑框架的底座,并具有用于沿着地板表面移动基座的多个轴承组件。 支撑件还包括制动器,用于致动至少一个轴承组件的制动器的制动致动器以及联接到制动致动器的制动杆。 制动杆可在非制动位置和制动位置之间移动,其中致动器使制动器移动到其制动位置。 此外,制动杆在框架的头端和脚端之间延伸,并且还具有从制动致动器向外延伸的部分,至少靠近由轴承组件限定的轴承盖板,但是在框架占用空间内,从而提供 相对容易地接近制动杆到靠近框架的一个纵向侧面的服务员。
    • 8. 发明申请
    • CMC turbine shroud ring segment and fabrication method
    • CMC涡轮护罩环段及制造方法
    • US20070160466A1
    • 2007-07-12
    • US11330597
    • 2006-01-12
    • Douglas Keller
    • Douglas Keller
    • F04D29/08B28B3/00F03B11/00
    • F01D9/00F05D2230/30F05D2240/11F05D2300/603
    • Fabricating a refractory component for a gas turbine engine, such as a turbine shroud ring segment, by arranging refractory fiber tows (24) in a flaired tubular geometry (20) comprising a stem portion (21) and a funnel-shaped portion (22); impregnating the refractory fibers (24) with a ceramic matrix to form a flaired tube (20) of ceramic composite matrix material; at least partially filling the funnel-shaped portion (22) with a ceramic core (30) extending beyond the end of the funnel-shaped portion to provide a working gas containment surface (31); curing the flaired tube (20) and the ceramic core (30) together; cutting the funnel-shaped portion (22) to provide rectangular edges (27); and providing an attachment mechanism (34, 36, 38, 40) on the stem portion (21) for attaching the component to a surrounding support structure. Additional tows (24) may be introduced at intermediate stages to maintain a desired fabric density.
    • 通过将耐火纤维丝束(24)布置在包括杆部分(21)和漏斗形部分(22)的带花式管状几何形状(20)中来制造用于燃气涡轮发动机(例如涡轮机护罩环段)的耐火构件, ; 用陶瓷基体浸渍耐火纤维(24)以形成陶瓷复合基质材料的带托管(20); 至少部分地用延伸超过所述漏斗形部分的端部的陶瓷芯(30)填充所述漏斗形部分(22)以提供工作气体容纳表面(31); 将所述带托管(20)和所述陶瓷芯(30)一起固化; 切割漏斗形部分(22)以提供矩形边缘(27); 以及在所述杆部分(21)上设置用于将所述部件附接到周围支撑结构的附接机构(34,36,38,40)。 可以在中间阶段引入额外的丝束(24)以保持所需的织物密度。
    • 9. 发明申请
    • Ring seal attachment system
    • 环形密封附件系统
    • US20060292001A1
    • 2006-12-28
    • US11165367
    • 2005-06-23
    • Douglas KellerDavid Radonovich
    • Douglas KellerDavid Radonovich
    • F04D29/08
    • F01D11/025F01D11/08Y02T50/672
    • Aspects of the invention relate to a system for attaching a ring seal to a vane carrier in a turbine engine such that the ring seal can radially expand and contract at least partially independently of the vane carrier. The system can also be configured to substantially restrict axial and/or circumferential movement of the ring seal. In one embodiment, the ring seal can include a plurality of radial slots circumferentially spaced about the ring seal. A pin can extend substantially through each of the slots and into operative engagement with isolation rings, which are connected to the vane carrier. In another embodiment, the ring seal and the isolation rings can include a series of axially-extending protrusions extending substantially circumferentially about each component. The protrusions on the ring seal can substantially matingly engage the protrusions on the isolation rings. The protrusions can be configured as a Hirth coupling.
    • 本发明的方面涉及一种用于将环形密封件附接到涡轮发动机中的叶片载体的系统,使得环形密封件可以至少部分地独立于叶片载体径向地膨胀和收缩。 该系统还可以构造成基本上限制环形密封件的轴向和/或周向运动。 在一个实施例中,环形密封件可以包括围绕环形密封件周向间隔开的多个径向槽。 销可以基本上延伸穿过每个槽,并且与连接到叶片承载件的隔离环可操作地接合。 在另一个实施例中,环形密封件和隔离环可以包括一系列沿着每个部件大致周向延伸的轴向延伸的突出部。 环形密封件上的突起可以基本配合地接合隔离环上的突起。 突起可以配置为Hirth耦合。
    • 10. 发明申请
    • Method for operating a gas turbine
    • 操作燃气轮机的方法
    • US20050150229A1
    • 2005-07-14
    • US10754195
    • 2004-01-09
    • Joan BaerWalter LasterDouglas Keller
    • Joan BaerWalter LasterDouglas Keller
    • F02C7/12
    • F02C7/12Y02E20/16
    • A gas turbine includes a compressor, a combustor, a turbine, and a flow path diverting an excess portion of the compressed air produced by the compressor around the turbine. The flow path conducts the excess portion into a turbine exhaust gas flow producing a cooled exhaust gas. A method of operating the gas turbine includes opening an inlet guide vane of the compressor to allow the compressor to produce an increased volume of compressed air. The increased volume exceeds a volume of compressed air needed to support combustion. An excess portion of the compressed air is directed into the exhaust gas to produce a cooled exhaust. In a combined cycle power plant, the cooled exhaust from the gas turbine may be used to warm a steam turbine portion to a desired temperature while allowing operation of the gas turbine at a power level that produces exhaust gas at a temperature higher than the desired temperature.
    • 燃气轮机包括压缩机,燃烧器,涡轮机以及将由压缩机产生的压缩空气的多余部分转向涡轮机的流路。 流路将过剩部分导入产生冷却废气的涡轮排气流中。 操作燃气涡轮机的方法包括打开压缩机的入口引导叶片,以允许压缩机产生增加的压缩空气体积。 体积增加超过支持燃烧所需的压缩空气体积。 压缩空气的多余部分被引导到废气中以产生冷却的排气。 在联合循环发电厂中,来自燃气涡轮机的冷却的排气可以用于将汽轮机部分加热到期望的温度,同时允许燃气轮机在高于期望温度的温度下产生废气的功率水平 。