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公开(公告)号：US20130156600A1
公开(公告)日：2013-06-20
申请号：US13326540
申请日：2011-12-15
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/20 , F01D5/288 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A component includes a substrate having an outer surface, an inner surface and a tip. The inner surface defines at least one hollow, interior space. The outer surface defines one or more grooves, where each groove extends at least partially along the outer surface of the substrate and has a base. The component further includes a coating disposed over at least a portion of the outer surface of the substrate. The coating includes at least a structural coating that extends over the groove(s), such that the groove(s) and the structural coating together define one or more channels for cooling the component. The tip comprises a tip cap enclosing the hollow, interior space(s), and a tip rim disposed at a radially outer end of the substrate. The tip rim at least partially defines at least one discharge channel in fluid communication with at least one cooling channel.
摘要翻译： 组件包括具有外表面，内表面和尖端的基底。 内表面限定至少一个中空的内部空间。 外表面限定一个或多个凹槽，其中每个凹槽至少部分地沿衬底的外表面延伸并且具有基部。 该部件还包括设置在基板的外表面的至少一部分上的涂层。 该涂层包括至少一个在凹槽上延伸的结构涂层，使得凹槽和结构涂层一起限定一个或多个通道以冷却部件。 尖端包括封闭中空的内部空间的尖端盖和设置在基底的径向外端的尖端边缘。 尖端边缘至少部分地限定与至少一个冷却通道流体连通的至少一个排放通道。
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22.发明授权Turbine airfoil concave cooling passage using dual-swirl flow mechanism and method 有权涡轮翼型凹形冷却通道采用双旋流动机构及方法公开(公告)号：US08376706B2
公开(公告)日：2013-02-19
申请号：US11863744
申请日：2007-09-28
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/121 , F05D2240/303 , F05D2250/314 , F05D2250/33 , F05D2250/70 , F05D2260/205 , F05D2260/2212 , F05D2260/22141 , F05D2260/2322
摘要： A turbine airfoil includes a leading edge having a concave cooling flow passage. An apex of the concave cooling flow passage divides the flow passage into adjacent regions. The turbine airfoil includes a first plurality of turbulators disposed in one of the adjacent regions, and a second plurality of turbulators disposed in the other of the adjacent regions. The first and second pluralities of turbulators are positioned relative to one another to divert cooling flow in opposing swirl streams that recombine along the apex and to effect a desired heat transfer and pressure loss.
摘要翻译： 涡轮机翼片包括具有凹形冷却流道的前缘。 凹形冷却流道的顶点将流动通道分成相邻的区域。 涡轮机翼片包括设置在相邻区域之一中的第一多个湍流器和设置在相邻区域中的另一个中的第二多个湍流器。 第一和第二多个紊流器相对于彼此定位，以使沿着顶点重新组合的相反旋流中的冷却流转向并实现所需的传热和压力损失。
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23.发明申请公开(公告)号：US20120148769A1
公开(公告)日：2012-06-14
申请号：US12966101
申请日：2010-12-13
CPC分类号： F01D5/187 , B23P15/04 , B23P2700/13 , C23C4/01 , C23C4/02 , C23C14/0005 , C23C24/04 , F01D5/186 , F05D2230/31 , F05D2230/313 , F05D2230/90 , F05D2250/12 , F05D2250/13 , Y02T50/67 , Y02T50/672 , Y02T50/676 , Y02T50/6765 , Y10T428/13
摘要： A method of fabricating a component is provided. The fabrication method includes depositing a first layer of a structural coating on an outer surface of a substrate. The substrate has at least one hollow interior space. The fabrication method further includes machining the substrate through the first layer of the structural coating, to define one or more openings in the first layer of the structural coating and to form respective one or more grooves in the outer surface of the substrate. Each groove has a respective base and extends at least partially along the surface of the substrate. The fabrication method further includes depositing a second layer of the structural coating over the first layer of the structural coating and over the groove(s), such that the groove(s) and the second layer of the structural coating together define one or more channels for cooling the component. A component is also disclosed.
摘要翻译： 提供了一种制造组件的方法。 制造方法包括在基板的外表面上沉积第一层结构涂层。 衬底具有至少一个中空的内部空间。 制造方法还包括通过结构涂层的第一层加工衬底，以在结构涂层的第一层中限定一个或多个开口，并在衬底的外表面中形成相应的一个或多个凹槽。 每个凹槽具有相应的基部并且至少部分地沿着基底的表面延伸。 该制造方法还包括将结构涂层的第二层沉积在结构涂层的第一层上并在该沟槽之上，使得该沟槽和该结构涂层的第二层一起限定一个或多个通道 用于冷却组件。 还公开了一种组件。
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公开(公告)号：US20120114868A1
公开(公告)日：2012-05-10
申请号：US12943563
申请日：2010-11-10
IPC分类号： B05D5/00 , B05D3/02 , B05D3/00 , B05D1/18 , C25F3/00 , B05D1/00 , C23C16/44 , C23C16/50 , C23C4/12 , B05D3/12 , B05D1/04
CPC分类号： B23P15/04 , B23P2700/13 , F01D5/187 , F01D5/288 , F05D2230/10 , F05D2230/31 , F05D2260/202 , F05D2260/204 , F23M5/08 , F23R2900/03041 , Y02T50/67 , Y02T50/672 , Y02T50/676 , Y02T50/6765
摘要： A method of fabricating a component is provided. The method includes depositing a fugitive coating on a surface of a substrate, where the substrate has at least one hollow interior space. The method further includes machining the substrate through the fugitive coating to form one or more grooves in the surface of the substrate. Each of the one or more grooves has a base and extends at least partially along the surface of the substrate. The method further includes forming one or more access holes through the base of a respective one of the one or more grooves to connect the respective groove in fluid communication with the respective hollow interior space. The method further includes filling the one or more grooves with a filler, removing the fugitive coating, disposing a coating over at least a portion of the surface of the substrate, and removing the filler from the one or more grooves, such that the one or more grooves and the coating together define a number of channels for cooling the component.
摘要翻译： 提供了一种制造组件的方法。 该方法包括在衬底的表面上沉积短片，其中衬底具有至少一个中空的内部空间。 该方法还包括通过短暂涂层来加工衬底以在衬底的表面中形成一个或多个凹槽。 所述一个或多个凹槽中的每一个具有基部并至少部分地沿着所述基底的表面延伸。 该方法还包括通过一个或多个凹槽中的相应一个凹槽的基部形成一个或多个访问孔，以将相应的沟槽与相应的中空内部空间流体连通。 该方法还包括用填充物填充一个或多个凹槽，去除短暂涂层，在基底的表面的至少一部分上设置涂层，以及从一个或多个凹槽中移除填料，使得一个或多个凹槽 更多的凹槽和涂层一起限定了用于冷却部件的多个通道。
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25.发明授权Stator—rotor assemblies having surface features for enhanced containment of gas flow, and related processes 有权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
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。
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公开(公告)号：US20110164653A1
公开(公告)日：2011-07-07
申请号：US12683638
申请日：2010-01-07
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。
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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。
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公开(公告)号：US20100205972A1
公开(公告)日：2010-08-19
申请号：US12372246
申请日：2009-02-17
IPC分类号： F02C7/12
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。
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公开(公告)号：US20090297336A1
公开(公告)日：2009-12-03
申请号：US11842219
申请日：2007-08-21
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
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30.发明申请METHOD AND TOOL FOR FORMING NON-CIRCULAR HOLES USING A SELECTIVELY COATED ELECTRODE 有权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
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。
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