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19 条记录 (耗时 0.019 秒)

    Process for production of Helicobacter pylori bacterioferritin
    5.
    发明授权
    Process for production of Helicobacter pylori bacterioferritin 失效
    生产幽门螺杆菌细菌铁蛋白的方法

    公开(公告)号：US07901907B2

    公开(公告)日：2011-03-08

    申请号：US11510509

    申请日：2006-08-25

    申请人： William Byrne ,  Dermot P. Kelleher ,  Henry Windle ,  Ross McManus

    发明人： William Byrne ,  Dermot P. Kelleher ,  Henry Windle ,  Ross McManus

    IPC分类号： C12P21/06

    CPC分类号： C07K14/205 ,  A61K39/00

    摘要： A nucleic acid sequence encoding all or part of an 18-19 kDa Helicobater pylori protein is described to which immunoreactivity is detected in H. pylori negative individuals. A process for the production of a recombinant form of this protein and its use, particularly as a vaccine to provide immunological protection against H. pylori infection are also described.

    摘要翻译： 描述编码18-19kDa幽门螺旋杆菌蛋白的全部或部分的核酸序列，其在幽门螺杆菌阴性个体中检测到免疫反应性。 还描述了生产该蛋白质的重组形式的方法及其用途，特别是作为提供免疫保护以免幽门螺旋杆菌感染的疫苗。

    System for reducing combustor dynamics
    6.
    发明申请
    System for reducing combustor dynamics 审中-公开
    减少燃烧室动力学的系统

    公开(公告)号：US20080245337A1

    公开(公告)日：2008-10-09

    申请号：US11732143

    申请日：2007-04-03

    申请人： Ramarao V. Bandaru ,  Kwanwoo Kim ,  Shiva Srinivasan ,  William Byrne

    发明人： Ramarao V. Bandaru ,  Kwanwoo Kim ,  Shiva Srinivasan ,  William Byrne

    IPC分类号： F02C7/12

    CPC分类号： F23R3/46 ,  F23M20/005 ,  F23R3/04 ,  F23R3/283 ,  F23R2900/00014 ,  F23R2900/03044

    摘要： A system for dampening combustor dynamics within a turbomachine. The system may include at least one resonator installed adjacent a head-end region of a combustion can. The at least one resonator may include a first side having a plurality of holes forming a cold side hole pattern; a second side having a plurality of holes forming a hot side hole pattern; and a cavity substantially defined by the first side and the hot side. The cold side hole pattern may be oriented such that each of the plurality of holes in the cold side hole pattern allows for a jet of a cooling air to substantially impinge a second side facing surface; and wherein the hot side hole pattern is oriented such that each of the plurality of holes in the hot side hole pattern allows for a jet of a working fluid to substantially impinges a first side facing surface.

    摘要翻译： 一种用于抑制涡轮机内燃烧室动力学的系统。 该系统可以包括邻近燃烧罐的前端区域安装的至少一个谐振器。 所述至少一个谐振器可以包括具有形成冷侧孔图案的多个孔的第一侧面; 具有形成热侧孔图案的多个孔的第二侧; 以及基本上由第一侧和热侧限定的空腔。 冷侧孔图案可以被定向成使得冷侧孔图案中的多个孔中的每一个允许冷却空气的射流基本上撞击第二侧面; 并且其中所述热侧孔图案被定向成使得所述热侧孔图案中的所述多个孔中的每一个允许工作流体的射流基本上撞击第一面对面。

    Integrated late lean injection on a combustion liner and late lean injection sleeve assembly
    8.
    发明授权
    Integrated late lean injection on a combustion liner and late lean injection sleeve assembly 有权
    在燃烧衬套和后期精密注射套筒组件上集成后期精馏

    公开(公告)号：US08601820B2

    公开(公告)日：2013-12-10

    申请号：US13153944

    申请日：2011-06-06

    申请人： William Byrne ,  Patrick Benedict Melton ,  David William Cihlar ,  Lucas Stoia

    发明人： William Byrne ,  Patrick Benedict Melton ,  David William Cihlar ,  Lucas Stoia

    IPC分类号： F02C3/00 ,  F02C7/22 ,  F02C1/04 ,  F02C7/224

    CPC分类号： F23R3/346 ,  F23R3/06 ,  F23R3/283 ,  F23R3/286

    摘要： A late lean injection sleeve assembly allows the injection of fuel at the aft end of a gas turbine liner, before the transition piece, into the combustion gases downstream of a turbine combustor's fuel nozzles. The late lean injection enables fuel injection downstream of the fuel nozzles to create a secondary/tertiary (with quaternary injection upstream of the fuel nozzles) combustion zone while reducing/eliminating the risk of fuel leaking into the combustor discharge case. The fuel is delivered by the flow sleeve into one or more nozzles that mix the fuel with CDC air before injecting it into the combustor's liner.

    摘要翻译： 后期的稀薄注射套筒组件允许将燃料涡轮机衬套的后端处的燃料喷射到涡轮机燃烧器的燃料喷嘴下游的燃烧气体中。 后期的稀薄喷射使得燃料喷嘴下游的燃料喷射能够在减少/消除燃料泄漏到燃烧器排出壳体中的风险的同时产生二级/三级（在燃料喷嘴的上游具有四级注入）燃烧区域。 燃料由流动套管输送到一个或多个喷嘴中，该喷嘴将燃料与CDC空气混合，然后将其注入到燃烧器的衬套内。

    System for embedding programming language content in XML
    9.
    发明申请
    System for embedding programming language content in XML 有权
    用于在XML中嵌入编程语言内容的系统

    公开(公告)号：US20070116202A1

    公开(公告)日：2007-05-24

    申请号：US11511211

    申请日：2006-08-29

    申请人： William Byrne ,  Mitsuru Oshima ,  Michael Achenbach ,  Beth Bottos ,  Dai Zhu

    发明人： William Byrne ,  Mitsuru Oshima ,  Michael Achenbach ,  Beth Bottos ,  Dai Zhu

    IPC分类号： H04M11/00

    CPC分类号： H04M3/4938 ,  G06F9/45512

    摘要： A method for providing an interactive voice response service is provided. The method uses a VoiceXML interpreter in cooperation with a voice/audio application. The voice/audio application uses scripts coded in VoiceXML with embedded Java Server Pages (JSP). The use of VoiceXML along with JSP allows the present invention to provide an implementation that minimizes interaction between the voice/audio application and the VoiceXML server.

    摘要翻译： 提供了一种用于提供交互式语音响应服务的方法。 该方法与语音/音频应用程序协作使用VoiceXML解释器。 语音/音频应用程序使用带有嵌入式Java服务器页面（JSP）的VoiceXML编码脚本。 与JSP一起使用VoiceXML允许本发明提供使语音/音频应用和VoiceXML服务器之间的交互最小化的实现。

    METHOD AND APPARATUS FOR COOLING COMBUSTOR LINER AND TRANSITION PIECE OF A GAS TURBINE
    10.
    发明申请
    METHOD AND APPARATUS FOR COOLING COMBUSTOR LINER AND TRANSITION PIECE OF A GAS TURBINE 有权
    用于冷却燃气轮机和气体涡轮机过渡部件的方法和装置

    公开(公告)号：US20050268613A1

    公开(公告)日：2005-12-08

    申请号：US10709886

    申请日：2004-06-03

    申请人： John Intile ,  James West ,  William Byrne

    发明人： John Intile ,  James West ,  William Byrne

    IPC分类号： F23R3/06 ,  F02C7/12 ,  F02C7/18 ,  F23R3/00 ,  F23R3/30 ,  F23R3/42

    CPC分类号： F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  F23R2900/03044

    摘要： A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of circular ring turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an outer surface thereof; a first flow sleeve surrounding the combustor liner with a first flow annulus therebetween including a plurality of axial channels (C) extending over a portion of an aft end portion of the liner parallel to each other, the cross-sectional area of each channel either constant or varying along the length of the channel, the first flow sleeve having a plurality of rows of cooling holes formed about a circumference of the first flow sleeve for directing cooling air from the compressor discharge into the first flow annulus; a transition piece connected to the combustor liner and adapted to carry hot combustion gases to a stage of the turbine; a second flow sleeve surrounding the transition piece a second plurality of rows of cooling apertures for directing cooling air into a second flow annulus between the second flow sleeve and the transition piece; wherein the first plurality of cooling holes and second plurality of cooling apertures are each configured with an effective area to distribute less than 50% of compressor discharge air to the first flow sleeve and mix with cooling air from the second flow annulus.

    摘要翻译： 用于冷却燃烧器衬套和燃气轮机的过渡件的方法和设备包括具有多个圆环形湍流器的燃烧器衬套，所述多个环形湍流器沿着限定燃烧器衬套的长度并位于其外表面上的长度轴向排列; 环绕燃烧器衬套的第一流动套筒包括在衬套的后端部分的一部分上彼此平行延伸的多个轴向通道（C），每个通道的横截面面积是恒定的 或沿着所述通道的长度变化，所述第一流动套筒具有围绕所述第一流动套筒的圆周形成的多排冷却孔，用于将来自所述压缩机排出口的冷却空气引导到所述第一流动环空中; 连接到所述燃烧器衬套并适于将热燃烧气体运送到所述涡轮机的级的过渡件; 围绕所述过渡件的第二流动套筒，用于将冷却空气引导到所述第二流动套筒和所述过渡件之间的第二流动环空中的第二多排冷却孔; 其中所述第一多个冷却孔和第二多个冷却孔分别配置有有效区域以将小于50％的压缩机排出空气分配到所述第一流动套筒并与来自所述第二流动环的冷却空气混合。