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11. 发明授权

US08016552B2 Stator—rotor assemblies having surface features for enhanced containment of gas flow, and related processes 有权
标题翻译：具有表面特征的定子 - 转子组件用于增强气流的容纳以及相关过程
公开(公告)号：US08016552B2
公开(公告)日：2011-09-13
申请号：US11541336
申请日：2006-09-29
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
IPC分类号： F01D11/02 , F04D29/32
CPC分类号： F01D11/001
摘要： A stator-rotor assembly which includes at least one interface region between the stator and rotor is described. At least one stator or rotor surface in the interface region includes a pattern of concavities. The concavities restrict gas flow through a gap between the stator and the rotor. Various turbomachines which can contain such a stator-rotor assembly are also described. The disclosure also discusses methods to restrict gas flow through gaps in a stator-rotor assembly, utilizing the concavities.
摘要翻译：描述了包括定子和转子之间的至少一个界面区域的定子 - 转子组件。界面区域中的至少一个定子或转子表面包括凹凸图案。凹槽限制气流通过定子和转子之间的间隙。还描述了可以容纳这种定子 - 转子组件的各种涡轮机。本公开还讨论了利用凹面来限制通过定子 - 转子组件中的间隙的气流的方法。

12. 发明申请

US20110164653A1 THERMAL INSPECTION SYSTEM AND METHOD INCORPORATING EXTERNAL FLOW 审中-公开
标题翻译：热检查系统和外部流量的方法
公开(公告)号：US20110164653A1
公开(公告)日：2011-07-07
申请号：US12683638
申请日：2010-01-07
申请人： Jason Randolph Allen , Ronald Scott Bunker , Jared Michael Crosby
发明人： Jason Randolph Allen , Ronald Scott Bunker , Jared Michael Crosby
IPC分类号： G01N25/20
CPC分类号： G01N25/72
摘要： A thermal inspection method is disclosed. The inspection method includes disposing a component in a wind tunnel configured to create a predetermined Mach number distribution for an external surface of the component. A gas is supplied at a known temperature T into the wind tunnel to create an external flow of gas over the external surface of the component in accordance with the predetermined Mach number distribution. The inspection method further includes directly or indirectly measuring one or more external surface temperatures of the component to generate an external surface temperature distribution for the external surface of the component and using the external surface temperature distribution to perform a quality control inspection of the component. A thermal inspection system is also provided.
摘要翻译：公开了一种热检查方法。所述检查方法包括将组件设置在风洞中，所述风洞被配置为为所述部件的外表面创建预定的马赫数分布。在已知温度T下将气体供应到风洞中，以根据预定的马赫数分布在部件的外表面上产生气体的外部气流。检查方法还包括直接或间接地测量部件的一个或多个外表面温度以产生组件的外表面的外表面温度分布，并且使用外表面温度分布来执行部件的质量控制检查。还提供热检查系统。

13. 发明申请

US20110030375A1 AERODYNAMIC PYLON FUEL INJECTOR SYSTEM FOR COMBUSTORS 有权
标题翻译：燃气轮机燃油喷射系统
公开(公告)号：US20110030375A1
公开(公告)日：2011-02-10
申请号：US12535313
申请日：2009-08-04
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
IPC分类号： F02C7/22
CPC分类号： F23R3/286 , F23D14/64 , F23R3/20 , F23R2900/03341
摘要： A combustor system includes a pylon fuel injection system coupled to a combustion chamber and configured to inject fuel to the combustion chamber. The pylon fuel injection system includes a plurality of radial elements, each radial element having a plurality of first Coanda type fuel injection slots. A plurality of transverse elements are provided to each radial element. Each transverse element includes a plurality of second Coanda type fuel injection slots.
摘要翻译：燃烧器系统包括连接到燃烧室并构造成将燃料喷射到燃烧室的塔式燃料喷射系统。塔式燃料喷射系统包括多个径向元件，每个径向元件具有多个第一柯恩达型燃料喷射槽。多个横向元件设置在每个径向元件上。每个横向元件包括多个第二柯恩达型燃料喷射槽。

14. 发明申请

US20100205972A1 ONE-PIECE CAN COMBUSTOR WITH HEAT TRANSFER SURFACE ENHACEMENTS 审中-公开
标题翻译：一体式可加热传热表面加强型
公开(公告)号：US20100205972A1
公开(公告)日：2010-08-19
申请号：US12372246
申请日：2009-02-17
申请人： Ronald James Chila , Ronald Scott Bunker , Kevin Weston McMahan , Jonathan Dwight Berry
发明人： Ronald James Chila , Ronald Scott Bunker , Kevin Weston McMahan , Jonathan Dwight Berry
IPC分类号： F02C7/12
CPC分类号： F23R3/005 , F23R3/002
摘要： A method, system, and apparatus is provided for transferring heat from a can combustor associated with a gas turbine by providing a one-piece can combustor body having surface features that facilitate the transfer of heat away from the can combustor body, and by directing air flow to the surface features so that heat from the can combustor body is transferred from the surface features to the air flow.
摘要翻译：提供了一种方法，系统和装置，用于通过提供具有便于将热量从罐式燃烧器主体传递的表面特征的一体式罐式燃烧器主体，以及通过引导空气流到表面特征，使得来自罐式燃烧器主体的热量从表面特征传递到气流。

15. 发明申请

US20090297336A1 ONLINE SYSTEMS AND METHODS FOR THERMAL INSPECTION OF PARTS 审中-公开
标题翻译：在线检测零件的系统和方法
公开(公告)号：US20090297336A1
公开(公告)日：2009-12-03
申请号：US11842219
申请日：2007-08-21
申请人： Jason Randolph Allen , Ronald Scott Bunker
发明人： Jason Randolph Allen , Ronald Scott Bunker
IPC分类号： F01D25/00 , G01F1/68
CPC分类号： G01F1/68 , F05B2260/80
摘要： A thermal inspection method is provided. The method includes measuring a transient thermal response of a cooled part installed in a turbine engine, wherein the transient thermal response results from operation of the turbine engine. The method also includes using the transient thermal response to determine one or more of a flow rate of a fluid flowing through one or more film cooling holes in the cooled part during operation of the turbine engine, at least one heat transfer coefficient for one or more internal passages in the cooled part, and a combined thermal response for the cooled part. The method further includes comparing at least one of the flow rate, the at least one heat transfer coefficient, and the combined thermal response of at least a portion of the cooled part to at least one baseline value to determine whether a thermal performance of the cooled part is satisfactory.
摘要翻译：提供了热检测方法。该方法包括测量安装在涡轮发动机中的冷却部件的瞬态热响应，其中瞬态热响应来自涡轮发动机的操作。该方法还包括使用瞬态热响应来确定在涡轮发动机运行期间流过冷却部分中的一个或多个膜冷却孔的流体的流速中的一个或多个，至少一个或多个传热系数冷却部分的内部通道，以及冷却部件的组合热响应。该方法还包括将至少一个热传递系数和至少一部分冷却部件的组合热响应中的至少一个比较至至少一个基准值，以确定冷却的部分令人满意

16. 发明申请

US20090277803A1 METHOD AND TOOL FOR FORMING NON-CIRCULAR HOLES USING A SELECTIVELY COATED ELECTRODE 有权
标题翻译：使用选择性涂层电极形成非圆形孔的方法和工具
公开(公告)号：US20090277803A1
公开(公告)日：2009-11-12
申请号：US12118791
申请日：2008-05-12
申请人： Bin Wei , Ronald Scott Bunker
发明人： Bin Wei , Ronald Scott Bunker
IPC分类号： B23H9/14 , B23H3/00 , B23H11/00
CPC分类号： B23H3/00 , B23H3/04 , B23H3/06 , B23H9/00 , B23H9/14 , C25F3/00
摘要： An electrochemical machining process for forming a non-circular hole from a substantially circular hole within a workpiece using an electrode. The electrode is made of an electrically conductive material and has insulated areas in which the electrically conductive material is coated with an insulating material, and exposed areas of metal or conductive material. The insulated areas and exposed areas extending in rows substantially along a longitudinal axis of the electrode. The electrode is first positioned in a substantially circular hole. An electric current is then applied to the electrode to electrochemically remove a predetermined amount of material from the substantially circular hole to form a non-circular hole. A variety of different non-circular shapes are achievable using the process.
摘要翻译：一种用于使用电极从工件内的大致圆形孔形成非圆形孔的电化学加工过程。电极由导电材料制成，并且具有绝缘区域，其中导电材料涂覆有绝缘材料，以及暴露的金属或导电材料区域。绝缘区域和暴露区域基本沿着电极的纵向轴线延伸。首先将电极定位在大致圆形的孔中。然后将电流施加到电极，以从大致圆形的孔电化学去除预定量的材料以形成非圆形孔。使用该过程可以实现各种不同的非圆形形状。

17. 发明授权

US07493767B2 Method and apparatus for cooling combustor liner and transition piece of a gas turbine 有权
标题翻译：一种用于冷却燃气轮机的燃烧器衬套和过渡件的方法和装置
公开(公告)号：US07493767B2
公开(公告)日：2009-02-24
申请号：US10907866
申请日：2005-04-19
申请人： Ronald Scott Bunker , Jeremy Clyde Bailey , Stanley Kevin Widener , Thomas Edward Johnson , John C Intile
发明人： Ronald Scott Bunker , Jeremy Clyde Bailey , Stanley Kevin Widener , Thomas Edward Johnson , John C Intile
IPC分类号： F02C1/00 , F02G3/00
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 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, 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：一种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湍流器的燃烧器衬套，该多个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; 围绕所述燃烧器衬套的第一流动套筒，其间具有第一流动环空，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，用于将冷却空气从所述压缩机排出口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。

18. 发明申请

US20090016402A1 SYSTEM AND METHOD FOR THERMAL INSPECTION OF PARTS 有权
标题翻译：用于部件热检查的系统和方法
公开(公告)号：US20090016402A1
公开(公告)日：2009-01-15
申请号：US11775502
申请日：2007-07-10
申请人： Ronald Scott Bunker , Jason Randolph Allen
发明人： Ronald Scott Bunker , Jason Randolph Allen
IPC分类号： G01N25/72
CPC分类号： G01N25/72
摘要： A method of thermal inspection of a part having at least one internal cavity is provided. The method includes flowing a fluid through the at least one internal cavity. The method also includes measuring a temperature at one or more locations on the part over time. The method further includes calculating at least one of a first and a second derivative of the temperature with respect to time. The method also includes comparing at least one of the first or the second derivative to one or more baseline values to determine if the part meets a desired specification.
摘要翻译：提供了具有至少一个内部空腔的部件的热检查方法。该方法包括使流体流过至少一个内腔。该方法还包括随时间测量该部件上的一个或多个位置处的温度。该方法还包括相对于时间计算温度的第一和第二导数中的至少一个。该方法还包括将第一或第二导数中的至少一个与一个或多个基线值进行比较，以确定该部分是否满足期望的规范。

19. 发明授权

US07373778B2 Combustor cooling with angled segmented surfaces 有权
标题翻译：燃烧器冷却具有成角度的分段表面
公开(公告)号：US07373778B2
公开(公告)日：2008-05-20
申请号：US10711131
申请日：2004-08-26
申请人： Ronald Scott Bunker , Jeremy Clyde Bailey , Stanley Kevin Widener , Thomas Edward Johnson
发明人： Ronald Scott Bunker , Jeremy Clyde Bailey , Stanley Kevin Widener , Thomas Edward Johnson
IPC分类号： F02C1/00
CPC分类号： F02C7/12 , F01D25/12 , F01D25/14 , F02C7/18 , F05D2240/35 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , F23R3/005
摘要： A combustor liner for a gas turbine includes a body having a plurality of angled strips on an outside surface of the combustor liner. The plurality of angled strips are arranged in an array about the outside surface. A space is disposed between each of said plurality of angled strips so as to create vortices in a cooling air flowing in a longitudinal direction across said outside surface of said combustor liner. A method of fabricating a combustor liner includes forming a plurality of angled strips on an outside surface of the combustor liner and arranged in an array about the outside surface, each of the angled strips is disposed so as to be spaced apart to create vortices in a cooling air flowing across the outside surface of the combustor liner.
摘要翻译：用于燃气轮机的燃烧器衬套包括在燃烧器衬套的外表面上具有多个成角度的条带的主体。多个成角度的条带围绕外表面布置成阵列。在所述多个成角度的条带中的每一个之间设置一个空间，以便在穿过所述燃烧器衬套的所述外表面沿纵向方向流动的冷却空气中产生涡流。一种制造燃烧器衬套的方法包括在燃烧器衬套的外表面上形成多个成角度的带，并围绕外表面排列成阵列，每个成角度的带被设置为间隔开以形成涡流流过燃烧器衬套的外表面的冷却空气。

20. 发明授权

US07328580B2 Chevron film cooled wall 有权
标题翻译：雪佛龙薄膜冷却墙
公开(公告)号：US07328580B2
公开(公告)日：2008-02-12
申请号：US10874900
申请日：2004-06-23
申请人： Ching-Pang Lee , Steven Robert Brassfield , Ronald Scott Bunker
发明人： Ching-Pang Lee , Steven Robert Brassfield , Ronald Scott Bunker
IPC分类号： F23R3/42
CPC分类号： B23K26/384
摘要： A wall in a gas turbine engine includes inner and outer surfaces having a row of compound chevron film cooling holes extending therethrough. The chevron holes diverge both longitudinally and laterally between an inlet at the wall inner surface and a chevron outlet at the wall outer surface.
摘要翻译：燃气涡轮发动机中的壁包括内表面和外表面，其具有穿过其延伸的一排复合人字形薄膜冷却孔。人字形孔在壁内表面的入口和壁外表面的人字形出口之间纵向和横向分开。

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