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    Heat exchanger tube with enhanced heat transfer co-efficient and related method
    2.
    发明申请
    Heat exchanger tube with enhanced heat transfer co-efficient and related method 审中-公开
    具有增强换热效率和相关方法的换热器管

    公开(公告)号：US20080078534A1

    公开(公告)日：2008-04-03

    申请号：US11540689

    申请日：2006-10-02

    申请人： Ronald S. Bunker ,  Giuseppe Malcaus

    发明人： Ronald S. Bunker ,  Giuseppe Malcaus

    IPC分类号： F28F1/40

    CPC分类号： F28F1/40

    摘要： A method of enhancing the heat transfer coefficient of a tube flowing a fluid in the tube in heat exchange relation with a second fluid external to the tube includes forming a patterned array of grooves on the interior surface of the tube. Each tube has a depth-to-width ratio of 0.10 to 0.30, and the grooves may be formed by mechanical pressing, pulsed ECM or electrodischarge processes.

    摘要翻译： 增加管中流体与管中的第二流体的热交换关系的管的传热系数的方法包括在管的内表面上形成图案化的凹槽阵列。 每个管的深度与宽度之比为0.10至0.30，并且凹槽可以通过机械压制，脉冲ECM或电放电过程形成。

    Turbine airfoil with double shell outer wall
    3.
    发明授权
    Turbine airfoil with double shell outer wall 失效
    涡轮机翼与双壳外墙

    公开(公告)号：US5328331A

    公开(公告)日：1994-07-12

    申请号：US82114

    申请日：1993-06-28

    申请人： Ronald S. Bunker ,  Thomas T. Wallace

    发明人： Ronald S. Bunker ,  Thomas T. Wallace

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  F05D2240/10 ,  F05D2260/201 ,  F05D2260/2212

    摘要： A coolable airfoil for use in gas turbine engine component such as a turbine blade or vane is provided with an integrally formed double shell outer wall surrounding at least one radially extending cavity. The inner and the outer shells are integrally formed of the same material together with tying elements which space apart the shells and mechanically and thermally tie the shells together. The present invention contemplates tying elements including pedestals, rods, and/or continuous or intermittent ribs. Impingement cooling means for the outer shell, in the form of impingement cooling holes, is provided on the inner shell to direct the coolant in impingement jet arrays against the outer shell, thereby, cooling the outer shell.

    摘要翻译： 用于燃气涡轮发动机部件如涡轮叶片或叶片的可冷却翼型设置有围绕至少一个径向延伸腔的整体形成的双壳外壁。 内壳和外壳由相同的材料一起形成，并与隔离空间的捆绑元件一体地形成，并将壳体机械地和热结合在一起。 本发明考虑了包括基座，杆和/或连续或间歇肋的元件的捆扎。 在内壳上设置用于外壳形式的冲击冷却孔的冲击冷却装置，以将冲击喷射阵列中的冷却剂引导到外壳上，由此冷却外壳。

    Heat exchanger tube with enhanced heat transfer co-efficient and related method
    4.
    发明申请
    Heat exchanger tube with enhanced heat transfer co-efficient and related method 审中-公开
    具有增强换热效率和相关方法的换热器管

    公开(公告)号：US20080078535A1

    公开(公告)日：2008-04-03

    申请号：US11541682

    申请日：2006-10-03

    申请人： Ronald S. Bunker ,  Wayne C. Hasz ,  Mohamed A. Ali ,  Giuseppe Malcaus

    发明人： Ronald S. Bunker ,  Wayne C. Hasz ,  Mohamed A. Ali ,  Giuseppe Malcaus

    IPC分类号： F28F13/02

    CPC分类号： F28F13/185 ,  Y10T29/49377

    摘要： A method of enhancing the heat transfer coefficient of a tube flowing a fluid in the tube in heat exchange relation with a second fluid external to the tube includes applying metal particles to an interior surface of the tube to thereby create an increased wetted area for interaction with fluid flowing through the tube; wherein the particles are applied by: providing an applicator head including an electric arc and at least one metal wire; displacing the head along the interior of the tube; feeding the wire into the electric arc as the head is displaced along the interior of the tube; melting the wire to form molten metal particles; and applying the molten metal particles about and along the length of the interior wall surface of the tube as the head is displaced along the interior of the tube.

    摘要翻译： 一种提高管中的流体与管外部的第二流体的热交换关系的传热系数的方法包括将金属颗粒施加到管的内表面，从而产生增加的润湿面积，以与 流经管的流体; 其中所述颗粒通过以下方式施加：提供包括电弧的施用头和至少一个金属丝; 头部沿着管的内部移位; 当头沿着管的内部移动时，将电线馈入电弧; 熔化金属丝以形成熔融金属颗粒; 以及当所述头沿所述管的内部移位时，围绕并沿着所述管的内壁表面的长度施加所述熔融金属颗粒。

    Method of modifying cooled turbine components
    5.
    发明授权
    Method of modifying cooled turbine components 失效
    改进冷却涡轮机组件的方法

    公开(公告)号：US06427327B1

    公开(公告)日：2002-08-06

    申请号：US09726004

    申请日：2000-11-29

    申请人： Ronald S. Bunker

    发明人： Ronald S. Bunker

    IPC分类号： B23P1500

    CPC分类号： F01D9/02 ,  B23P2700/06 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2240/81 ,  Y10T29/49318 ,  Y10T29/49336 ,  Y10T29/49341 ,  Y10T29/49716

    摘要： The cooling scheme of a gas turbine engine component is modified to improve local cooling without redesigning the investment casting. The modification includes forming at least one channel in the component such that the channel is in fluid communication with a cooling medium source associated with the component. The channel is then partially filled with a removable material, and the removable material is covered with a patch material so as to completely fill the channel. Lastly, the removable material is removed from the channel so as to create an internal cooling passage in the component that is in fluid communication with the cooling medium source.

    摘要翻译： 修改燃气涡轮发动机部件的冷却方案以改进局部冷却，而不必重新设计熔模铸造。 修改包括在部件中形成至少一个通道，使得通道与与部件相关联的冷却介质源流体连通。 然后将通道部分地填充有可移除的材料，并且可移除的材料用补片材料覆盖以便完全填充通道。 最后，可移除的材料从通道中移除，以便在与冷却介质源流体连通的部件中产生内部冷却通道。

    METHODS AND SYSTEM FOR REDUCING PRESSURE LOSSES IN GAS TURBINE ENGINES
    7.
    发明申请
    METHODS AND SYSTEM FOR REDUCING PRESSURE LOSSES IN GAS TURBINE ENGINES 审中-公开
    用于降低气体涡轮发动机压力损失的方法和系统

    公开(公告)号：US20090145132A1

    公开(公告)日：2009-06-11

    申请号：US11952165

    申请日：2007-12-07

    申请人： David M. Johnson ,  Ronald S. Bunker ,  Kenneth N. Whaling

    发明人： David M. Johnson ,  Ronald S. Bunker ,  Kenneth N. Whaling

    IPC分类号： F02C1/00

    CPC分类号： F23R3/002

    摘要： A method of assembling a combustor assembly is provided, wherein the method includes providing a combustor liner having a centerline axis and defining a combustion chamber therein, and coupling an annular flowsleeve radially outward from the combustor liner such that an annular flow path is defined substantially circumferentially between the flowsleeve and the combustor finer. The method also includes orienting the flowsleeve such that a plurality of inlets formed within the flowsleeve are positioned to inject cooling air in a substantially axial direction into the annular flow path to facilitate cooling the combustor finer.

    摘要翻译： 提供了一种组装燃烧器组件的方法，其中所述方法包括提供具有中心线轴线并且在其中限定燃烧室的燃烧器衬套，并且将环形流动叶片从燃烧器衬套径向向外耦合，使得环形流动路径基本上周向地限定 在流动和燃烧器之间更细。 该方法还包括使流动方向定向，使得形成在流动中的多个入口被定位成将大致轴向的冷却空气注入到环形流动路径中，以便于冷却燃烧器更细。

    Closed-circuit air cooled turbine
    8.
    发明授权
    Closed-circuit air cooled turbine 失效
    闭路风冷涡轮机

    公开(公告)号：US5611197A

    公开(公告)日：1997-03-18

    申请号：US551870

    申请日：1995-10-23

    申请人： Ronald S. Bunker

    发明人： Ronald S. Bunker

    IPC分类号： F02C7/18 ,  F02C7/224

    CPC分类号： F02C7/224 ,  F02C7/185 ,  Y02T50/675

    摘要： A gas turbine engine includes a compressor, combustor, and turbine, and a cooling air closed-circuit having an extraction line from the compressor to a hot turbine component such as vanes, blades, or shrouds, and a return line to the compressor. The extraction line may be joined to any suitable compressor stage for extracting air at a suitable pressure for flow to the turbine, with the return line being joined to any suitable injection stage of the compressor having a lower pressure than the extraction stage for driving the cooling air through the closed-circuit. The compressor itself therefore drives the closed-circuit and is self regulated.

    摘要翻译： 燃气涡轮发动机包括压缩机，燃烧器和涡轮机，以及具有从压缩机到诸如叶片，叶片或护罩的热涡轮机部件以及到压缩机的返回管线的抽吸管线的冷却空气闭合回路。 抽吸管线可以连接到任何合适的压缩机级，用于以适当的压力抽出空气以流到涡轮机，其中返回管线被连接到压缩机的任何合适的喷射级，其压力低于用于驱动冷却的提取级 空气通过闭路。 因此，压缩机本身会驱动闭路并自动调节。