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1. 发明申请

US20150132117A1 GAS TURBINE ENGINE DUCTING ARRANGEMENT HAVING DISCRETE INSERT 审中-公开
标题翻译：具有分离插件的气体涡轮发动机排气装置
公开(公告)号：US20150132117A1
公开(公告)日：2015-05-14
申请号：US14074776
申请日：2013-11-08
申请人： John J. Marra , Jay A. Morrison , Ernie B. Campbell
发明人： John J. Marra , Jay A. Morrison , Ernie B. Campbell
IPC分类号： F01D9/02 , F23R3/46
CPC分类号： F01D9/023 , F05D2260/941 , F05D2270/114 , F23R3/425 , F23R3/46
摘要： A ducting arrangement (10), including: a plurality of discrete ducts (18), each defining a flow path and configured to receive a flow of combustion gases from a respective combustor can, where the plurality of discrete ducts merge to form a common duct structure; and a throat insert (50) configured to define at least part of a junction of one of the discrete ducts and the common duct structure.
摘要翻译：一种管道装置（10），包括：多个分立的管道（18），每个分配的管道（18）各限定一个流动路径并且被构造成从相应的燃烧器罐接收燃烧气体流，其中所述多个离散管道合流以形成公共管道结构体; 以及喉部插入件（50），其构造成限定所述离散管道和所述公共管道结构中的一个的至少部分接合部。

2. 发明申请

US20150033697A1 REGENERATIVELY COOLED TRANSITION DUCT WITH TRANSVERSELY BUFFERED IMPINGEMENT NOZZLES 有权
标题翻译：再生式冷却过渡管带横向缓冲式喷嘴
公开(公告)号：US20150033697A1
公开(公告)日：2015-02-05
申请号：US13956405
申请日：2013-08-01
申请人： Jay A. Morrison , Ching-Pang Lee , Michael E. Crawford
发明人： Jay A. Morrison , Ching-Pang Lee , Michael E. Crawford
IPC分类号： F01D9/02
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/201 , F23R3/002 , F23R2900/03043 , F23R2900/03044
摘要： A cooling arrangement (56) having: a duct (30) configured to receive hot gases (16) from a combustor; and a flow sleeve (50) surrounding the duct and defining a cooling plenum (52) there between, wherein the flow sleeve is configured to form impingement cooling jets (70) emanating from dimples (82) in the flow sleeve effective to predominately cool the duct in an impingement cooling zone (60), and wherein the flow sleeve defines a convection cooling zone (64) effective to cool the duct solely via a cross-flow (76), the cross-flow comprising cooling fluid (72) exhausting from the impingement cooling zone. In the impingement cooling zone an undimpled portion (84) of the flow sleeve tapers away from the duct as the undimpled portion nears the convection cooling zone. The flow sleeve is configured to effect a greater velocity of the cross-flow in the convection cooling zone than in the impingement cooling zone.
摘要翻译：一种冷却装置（56），其具有：构造成从燃烧器接收热气体（16）的管道（30）以及围绕所述管道并且在其间限定冷却气室（52）的流动套管（50），其中所述流动套筒构造成形成从所述流动套筒中的凹坑（82）发出的冲击冷却喷嘴（70），其有效地主要地冷却（60）中的管道，并且其中所述流动套管限定有效地仅通过交叉流（76）来冷却所述管道的对流冷却区域（64），所述交叉流动包括冷却流体（72）从冲击冷却区。在冲击冷却区域中，随着未折射部分靠近对流冷却区，流动套管的未折弯部分（84）从导管逐渐变细。流动套筒构造成在对流冷却区域中产生比在冲击冷却区域更大的交叉流速度。

3. 发明授权

US08826668B2 Two stage serial impingement cooling for isogrid structures 有权
标题翻译：用于等网格结构的两级串联冲击冷却
公开(公告)号：US08826668B2
公开(公告)日：2014-09-09
申请号：US13195947
申请日：2011-08-02
申请人： Ching-Pang Lee , Jay A. Morrison
发明人： Ching-Pang Lee , Jay A. Morrison
IPC分类号： H01L23/46 , F23R3/06 , F01D9/02 , F01D25/12 , F01D5/18
CPC分类号： F01D5/186 , F01D9/023 , F01D25/12 , F05D2260/201 , F05D2260/202 , F23R3/002 , F23R3/007 , F23R3/06 , F23R2900/00017 , F23R2900/03042 , F23R2900/03044 , Y10S165/908
摘要： A system for cooling a wall (24) of a component having an outer surface with raised ribs (12) defining a structural pocket (10), including: an inner wall (26) within the structural pocket and separating the wall outer surface within the pocket into a first region (28) outside of the inner wall and a second region (40) enclosed by the inner wall; a plate (14) disposed atop the raised ribs and enclosing the structural pocket, the plate having a plate impingement hole (16) to direct cooling air onto an impingement cooled area (38) of the first region; a cap having a skirt (50) in contact with the inner wall, the cap having a cap impingement hole (20) configured to direct the cooling air onto an impingement cooled area (44) of the second region, and; a film cooling hole (22) formed through the wall in the second region.
摘要翻译：一种用于冷却具有外表面的部件的壁（24）的系统，所述外壁具有限定结构袋（10）的凸肋（12），包括：在所述结构袋内的内壁（26），并将所述壁外表面分开口袋进入内壁外部的第一区域（28）和被内壁包围的第二区域（40）; 设置在所述凸肋顶部并包围所述结构袋的板（14），所述板具有板冲击孔（16），以将冷却空气引导到所述第一区域的冲击冷却区域（38）上; 具有与所述内壁接触的裙部（50）的盖，所述盖具有盖冲击孔（20），所述盖冲击孔构造成将所述冷却空气引导到所述第二区域的冲击冷却区域（44）上; 在所述第二区域中穿过所述壁形成的薄膜冷却孔（22）。

4. 发明授权

US08727714B2 Method of forming a multi-panel outer wall of a component for use in a gas turbine engine 有权
标题翻译：形成用于燃气涡轮发动机的部件的多面板外壁的方法
公开(公告)号：US08727714B2
公开(公告)日：2014-05-20
申请号：US13094948
申请日：2011-04-27
申请人： Raymond G. Snider , Jay A. Morrison
发明人： Raymond G. Snider , Jay A. Morrison
IPC分类号： F01D25/26
CPC分类号： F01D9/023 , F01D25/12 , F05D2230/60 , F05D2260/201 , F23R3/002 , F23R2900/00017 , F23R2900/03044 , Y10T29/49323 , Y10T29/49879
摘要： A method of forming and/or assembling a multi-panel outer wall (14) for a component (12) in a machine subjected to high thermal stresses comprising providing such a component (12) that includes an inner panel wall (16) having an outer surface, and an array of interconnecting ribs (38) on the outer surface of the component (12). An intermediate panel (22) is provided and preferably preformed to a general outer contour of the component (12), and is positioned over the inner panel (16). An external pressure force is applied across a surface area of the intermediate panel (22) against the outer surface of the component (12) to contour the intermediate panel (22) according to a geometric configuration formed by the ribs (38) thereby forming cooling chambers (24) between the outer surface and ribs (38) of the component (12) and the intermediate panel (22).
摘要翻译：一种在经受高热应力的机器中形成和/或组装用于部件（12）的多面板外壁（14）的方法，包括提供这样的部件（12），所述部件包括内板壁（16）外表面和在组件（12）的外表面上的互连肋（38）的阵列。中间板（22）设置并优选地预成型为部件（12）的一般外轮廓，并且定位在内板（16）上。根据由肋（38）形成的几何构型，外部压力力跨过中间板（22）的表面区域施加到部件（12）的外表面，以使中间板（22）轮廓化，从而形成冷却在组件（12）的外表面和肋（38）和中间板（22）之间的腔室（24）。

5. 发明授权

US08667682B2 Method of fabricating a nearwall nozzle impingement cooled component for an internal combustion engine 有权
标题翻译：制造用于内燃机的近壁喷嘴冲击冷却部件的方法
公开(公告)号：US08667682B2
公开(公告)日：2014-03-11
申请号：US13094966
申请日：2011-04-27
申请人： Ching-Pang Lee , Jay A. Morrison
发明人： Ching-Pang Lee , Jay A. Morrison
IPC分类号： B21D53/00
CPC分类号： B21K3/00 , F01D9/023 , F05D2260/201 , F23R3/425 , F23R3/46
摘要： A method of forming an internal combustion engine component having a multi-panel outer wall. The multi-panel outer wall has an inner panel (16) with an inner surface (18) and an outer surface (37). The inner panel outer surface (37) has discrete pockets (23) formed by integral structural ribs (38). Each pocket (23) has a film cooling hole (31) between the pocket (23) and the plenum (20). The method includes: forming dimples (40) in the intermediate panel (22), at least one dimple (40) having a nozzle (29); securing the intermediate panel (22) to the inner panel outer surface (37), thereby enclosing at least one pocket (23); and ensuring a respective dimple (40) having a nozzle (29) protrudes into a respective enclosed pocket (24) and a respective nozzle (29) is configured to direct a respective jet (35) of cooling fluid onto the inner panel outer surface within the respective enclosed pocket (23).
摘要翻译：一种形成具有多面板外壁的内燃机部件的方法。多面板外壁具有带有内表面（18）和外表面（37）的内板（16）。内板外表面（37）具有由整体结构肋（38）形成的分立的袋（23）。每个袋（23）在袋（23）和集气室（20）之间具有膜冷却孔（31）。该方法包括：在中间板（22）中形成凹坑（40），至少一个具有喷嘴（29）的凹坑（40）; 将所述中间板（22）固定到所述内板外表面（37）上，从而封闭至少一个凹槽（23）; 并且确保具有喷嘴（29）的相应的凹坑（40）突出到相应的封闭的袋（24）中，并且相应的喷嘴（29）构造成将相应的冷却流体喷射（35）引导到内板的外表面相应的封闭口袋（23）。

6. 发明申请

US20120201674A1 COOLING MODULE DESIGN AND METHOD FOR COOLING COMPONENTS OF A GAS TURBINE SYSTEM 有权
标题翻译：用于冷却气体涡轮机组件的冷却模块设计和方法
公开(公告)号：US20120201674A1
公开(公告)日：2012-08-09
申请号：US13023716
申请日：2011-02-09
申请人： Ching-Pang Lee , Humberto A. Zuniga , Jay A. Morrison , Brede J. Kolsrud , John J. Marra
发明人： Ching-Pang Lee , Humberto A. Zuniga , Jay A. Morrison , Brede J. Kolsrud , John J. Marra
IPC分类号： F01D5/18
CPC分类号： F01D5/184 , F01D5/186 , F01D5/187 , F05D2220/32 , F05D2230/51 , F05D2240/30 , F05D2240/40
摘要： A cooling arrangement in a gas turbine system (120). The arrangement includes a plurality of flow network units (208) to transfer heat to cooling fluid, at least one unit including first (218), second (220), and third (222) flow sections between openings (64a) in a first wall (66) and an opening in a second wall (68) to pass cooling fluid through the walls. The first section includes first flow paths, between the openings in the first wall and the second section, extending to the second section. The third section includes third flow paths, between the second section and the opening in the second wall, to effect flow of cooling fluid. The second section includes one or more cooling fluid flow paths between the first section and the third section. The number of flow paths in the second section is fewer than the number of first flow paths and fewer than the number of third flow paths.
摘要翻译：燃气轮机系统（120）中的冷却装置。该装置包括多个流动网络单元（208），用于将热量传递到冷却流体;至少一个单元，其包括在第一壁中的开口（64a）之间的第一（218），第二（220）和第三（222）（66）和第二壁（68）中的开口以使冷却流体通过壁。第一部分包括在第一壁的开口和第二部分之间延伸到第二部分的第一流动路径。第三部分包括在第二部分和第二壁中的开口之间的第三流动路径，以实现冷却流体的流动。第二部分包括在第一部分和第三部分之间的一个或多个冷却流体流动路径。第二部分中的流动路径的数量少于第一流动路径的数量，并且少于第三流动路径的数量。

7. 发明授权

US08215900B2 Turbine vane with high temperature capable skins 有权
标题翻译：涡轮叶片具有高温能力的皮肤
公开(公告)号：US08215900B2
公开(公告)日：2012-07-10
申请号：US12204115
申请日：2008-09-04
申请人： Jay A. Morrison
发明人： Jay A. Morrison
IPC分类号： F01D5/14 , F03D11/00 , F04D29/38
CPC分类号： F01D25/12 , B22D19/04 , F01D9/041 , F05D2230/21 , F05D2260/20 , F05D2300/603 , Y10T29/49332
摘要： A turbine vane assembly includes an airfoil extending between an inner shroud and an outer shroud. The airfoil can include a substructure having an outer peripheral surface. At least a portion of the outer peripheral surface is covered by an external skin. The external skin can be made of a high temperature capable material, such as oxide dispersion strengthened alloys, intermetallic alloys, ceramic matrix composites or refractory alloys. The external skin can be formed, and the airfoil can be subsequently bi-cast around or onto the skin. The skin and the substructure can be attached by a plurality of attachment members extending between the skin and the substructure. The skin can be spaced from the outer peripheral surface of the substructure such that a cavity is formed therebetween. Coolant can be supplied to the cavity. Skins can also be applied to the gas path faces of the inner and outer shrouds.
摘要翻译：涡轮叶片组件包括在内护罩和外护罩之间延伸的翼型件。翼型件可以包括具有外周表面的子结构。外周表面的至少一部分被外部皮肤覆盖。外部皮肤可以由耐高温材料制成，例如氧化物分散强化合金，金属间合金，陶瓷基复合材料或难熔合金。可以形成外部皮肤，并且可以随后将翼型围绕或附着在皮肤上。皮肤和下部结构可以通过在皮肤和下部结构之间延伸的多个附着构件附接。皮肤可以与子结构的外周表面间隔开，使得它们之间形成空腔。冷却液可以供应到空腔。皮肤也可以应用于内护罩和外护罩的气体通路面。

8. 发明申请

US20120121381A1 TURBINE TRANSITION COMPONENT FORMED FROM AN AIR-COOLED MULTI-LAYER OUTER PANEL FOR USE IN A GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的空气冷却多层外板组成的涡轮转换部件
公开(公告)号：US20120121381A1
公开(公告)日：2012-05-17
申请号：US12945943
申请日：2010-11-15
申请人： Richard C. Charron , Daniel J. Pierce , Jay A. Morrison , Ching-Pang Lee , Kenneth K. Landis , Walter Marussich
发明人： Richard C. Charron , Daniel J. Pierce , Jay A. Morrison , Ching-Pang Lee , Kenneth K. Landis , Walter Marussich
IPC分类号： F03B11/00
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/201 , F23R2900/03044
摘要： A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.
摘要翻译：公开了一种用于将来自燃烧器的气流引导到燃气涡轮发动机中的涡轮部分的第一级的过渡管道的冷却系统。过渡管道可以具有由内板形成的多面板外壁，该内板具有限定热气路径气室的至少一部分的内表面和从内板径向向外定位的中间板，使得至少一个冷却室形成在内板和中间板之间。过渡管还可以包括外板。内部，中间和外部面板可以包括一个或多个计量孔，用于在冷却室之间通过冷却流体以冷却面板。中间板和外板可以用连接系统固定到内板上，使得中间板和外板可在平面内移动。

9. 发明授权

US08079821B2 Turbine airfoil with dual wall formed from inner and outer layers separated by a compliant structure 有权
标题翻译：具有由内层和外层形成的具有双壁的涡轮翼型件由顺应结构隔开
公开(公告)号：US08079821B2
公开(公告)日：2011-12-20
申请号：US12435684
申请日：2009-05-05
申请人： Christian X. Campbell , Jay A. Morrison
发明人： Christian X. Campbell , Jay A. Morrison
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/147
摘要： A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation is disclosed. The compliant dual wall configuration may be formed a dual wall formed from inner and outer layers separated by a compliant structure. The compliant structure may be configured such that the outer layer may thermally expand without limitation by the inner layer. The compliant structure may be formed from a plurality of pedestals positioned generally parallel with each other. The pedestals may include a first foot attached to a first end of the pedestal and extending in a first direction aligned with the outer layer, and may include a second foot attached to a second end of the pedestal and extending in a second direction aligned with the inner layer.
摘要翻译：公开了一种可用于具有冷却系统的涡轮发动机的涡轮机翼型和被配置为在消除应力形成的同时在内层和外层之间实现热膨胀的顺应双壁结构。兼容的双壁结构可以形成由内层和外层形成的双层壁，其由柔顺结构隔开。顺应性结构可以被配置为使得外层可以热膨胀而不受内层的限制。柔性结构可以由大体上彼此平行地定位的多个基座形成。基座可以包括附接到基座的第一端并沿着与外层对准的第一方向延伸的第一脚，并且可以包括附接到基座的第二端并沿与第二脚对准的第二方向延伸的第二脚内层。

10. 发明申请

US20100322774A1 Airfoil Having an Improved Trailing Edge 审中-公开
标题翻译：翼型具有改进的后缘
公开(公告)号：US20100322774A1
公开(公告)日：2010-12-23
申请号：US12486274
申请日：2009-06-17
申请人： Jay A. Morrison
发明人： Jay A. Morrison
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2240/122 , F05D2240/304 , F05D2250/184 , F05D2250/70
摘要： An airfoil (101) is provided which includes a suction side and a pressure side joined along a trailing edge (106), wherein a trailing edge portion of the airfoil is configured to take a wavelike form along a radial direction of the airfoil, thereby improving the radial bending strength of the airfoil and reducing the magnitude of fluid flow wakes (128′) formed in a working fluid flowing over the airfoil.
摘要翻译：提供了一种翼缘（101），其包括沿后缘（106）连接的吸力侧和压力侧，其中所述翼型件的后缘部分被构造成沿着所述翼型件的径向取波形形状，从而改善翼型件的径向弯曲强度并且减小在流过翼型件的工作流体中形成的流体流动骤冷（128'）的大小。

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