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81. 发明申请

US20120201653A1 GAS TURBINE ENGINE AND COOLED FLOWPATH COMPONENT THEREFOR 审中-公开
标题翻译：燃气涡轮发动机和冷却流量组件
公开(公告)号：US20120201653A1
公开(公告)日：2012-08-09
申请号：US13337103
申请日：2011-12-24
申请人： Corina Moga , Jerry Layne , Jeffrey F. Rhodes
发明人： Corina Moga , Jerry Layne , Jeffrey F. Rhodes
IPC分类号： F01D9/02 , F01D25/12
CPC分类号： F01D5/147 , F01D5/186 , F01D5/187 , F05D2240/122 , F05D2240/126 , F05D2240/304 , F05D2250/18 , F05D2260/202 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： One embodiment of the present invention is a unique gas turbine engine. Another embodiment of the present invention is a unique cooled gas turbine engine flowpath component. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and cooled gas turbine engine flowpath components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
摘要翻译：本发明的一个实施例是独特的燃气涡轮发动机。本发明的另一个实施例是独特的冷却燃气涡轮发动机流路组件。其他实施例包括用于燃气涡轮发动机和冷却燃气涡轮发动机流路部件的装置，系统，装置，硬件，方法和组合。本申请的其它实施例，形式，特征，方面，益处和优点将从本文提供的描述和附图中变得显而易见。

82. 发明授权

US08109735B2 Cooled component with a featured surface and related manufacturing method 失效
标题翻译：冷却组件具有特色表面和相关制造方法
公开(公告)号：US08109735B2
公开(公告)日：2012-02-07
申请号：US12270372
申请日：2008-11-13
申请人： Raymond Gage , Adrian Allan
发明人： Raymond Gage , Adrian Allan
IPC分类号： F04D29/38
CPC分类号： B23P15/02 , F01D5/187 , F05D2260/202 , F05D2260/22141 , F05D2300/5024 , F23R2900/03045 , Y10T29/49336
摘要： An improved type of cooled component is disclosed. The cooled components, such as turbine airfoils and combustors, have a base metal structural member, including a metal sheet or blank, with a featured surface. The features, such as fins, pins, and other protrusions, as well as divots, indentions, slots, channels, and holes, are formed by lithographic processes. The protrusions can be formed from a different material than the metal sheet or blank, preferably one with superior heat-conductive or oxidation properties. A related method of manufacturing is also disclosed.
摘要翻译：公开了一种改进型的冷却部件。诸如涡轮机翼型和燃烧器的冷却部件具有贱金属结构件，包括具有特征表面的金属板或坯件。通过光刻工艺形成诸如翅片，销和其它突起以及凹陷，凹陷，槽，通道和孔的特征。突起可以由与金属板或坯料不同的材料形成，优选地具有优异的导热性或氧化性。还公开了相关的制造方法。

83. 发明授权

US08070441B1 Turbine airfoil with trailing edge cooling channels 有权
标题翻译：具有后缘冷却通道的涡轮翼型
公开(公告)号：US08070441B1
公开(公告)日：2011-12-06
申请号：US11880292
申请日：2007-07-20
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F01D9/02 , F05D2260/201 , F05D2260/202 , F05D2260/22141
摘要： A turbine airfoil such as a turbine stator vane used in an industrial gas turbine engine, the vane including a trailing edge region having a thin wall cooling channel arrangement of mini cooling channels formed by a series of rows of elongated flow blockers that form the mini cooling channels between adjacent flow blockers. The adjacent row of flow blockers are offset from the each other such that the inlet and the outlet flow of cooling air is discharged directly onto the flow blocker in order to produce impingement cooling. The mini cooling channels have a spacing to hydraulic diameter ratio of less than 4.0 and a mini channel length to hydraulic diameter ratio of 5.0 of less in order to maintain a high flow velocity within the mini channels. In one embodiment, the flow blockers have a progressively decreasing length in the flow direction of the cooling air.
摘要翻译：涡轮机翼片，例如在工业燃气涡轮发动机中使用的涡轮机定子叶片，叶片包括后缘区域，后缘区域具有由一系列细长流动阻塞器形成的迷你冷却通道的薄壁冷却通道布置，相邻流阻器之间的通道。相邻排的阻流器彼此偏移，使得冷却空气的入口和出口流直接排放到阻流器上以产生冲击冷却。迷你冷却通道具有小于4.0的间距与液压直径比，并且迷你通道长度与液压直径之比小于5.0以保持微通道内的高流速。在一个实施例中，阻流器在冷却空气的流动方向上具有逐渐减小的长度。

84. 发明授权

US08047788B1 Turbine airfoil with near-wall serpentine cooling 有权
标题翻译：涡轮翼型具有近壁蛇形冷却
公开(公告)号：US08047788B1
公开(公告)日：2011-11-01
申请号：US11975672
申请日：2007-10-19
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/185 , F05D2260/202 , F05D2260/22141
摘要： A turbine airfoil with a leading edge cooling air supply channel located along the leading edge region of the airfoil to supply cooling air from an outside source and a series of serpentine flow cooling circuits positioned along the leading edge of the airfoil connected to the cooling supply channel to pass cooling air through the series of serpentine passages in a direction from the airfoil root to the airfoil tip. The series of serpentine circuits includes legs on the pressure side and the suction side of the leading edge. Cooling air from the supply channel is metered into the first leg of the serpentine circuit located near the root, flows through a series of serpentine circuits along the leading edge of the airfoil, and flows out to the tip through a tip hole in the last leg of the last serpentine circuit.
摘要翻译：一种具有前缘冷却空气供应通道的涡轮机翼型件，其沿着翼型件的前缘区域设置，以从外部源供应冷却空气，并且沿着连接到冷却供应通道的翼型件的前缘定位一系列蛇形流冷却回路使冷却空气通过一系列蛇形通道在从翼型根到翼型端的方向上。一系列蛇形回路包括压力侧的腿和前缘的吸力侧。来自供应通道的冷却空气计量到位于根部附近的蛇形回路的第一条腿中，沿着翼型的前缘流过一系列蛇形回路，并通过最后一条腿的尖端孔流出到尖端的最后蛇形电路。

85. 发明申请

US20110250078A1 TURBINE BUCKET HAVING A RADIAL COOLING HOLE 有权
标题翻译：具有径向冷却孔的涡轮鼓
公开(公告)号：US20110250078A1
公开(公告)日：2011-10-13
申请号：US12758320
申请日：2010-04-12
申请人： Kevin Leon Bruce , Matthew Robert Piersall
发明人： Kevin Leon Bruce , Matthew Robert Piersall
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/085 , F05D2230/11 , F05D2260/22141
摘要： A turbine bucket is provided and includes a shank interconnectable with a rotor and formed to accommodate coolant therein and an airfoil blade coupled to a radially outward portion of the shank and including a body formed to define a substantially radially extending cooling hole therein, which is disposed to be solely receptive of the coolant accommodated within the shank for removing heat from the body, the cooling hole being further defined as having a substantially non-circular cross-sectional shape at a predefined radial position of the body.
摘要翻译：涡轮机桶被设置并且包括可与转子互连并形成以容纳冷却剂的柄，以及联接到柄的径向向外部分的翼型叶片，并且包括形成为在其中限定基本上径向延伸的冷却孔的主体，仅容纳容纳在柄内的冷却剂以便从身体移除热量，冷却孔被进一步限定为在身体的预定的径向位置处具有基本上非圆形的横截面形状。

86. 发明申请

US20110223004A1 APPARATUS FOR COOLING A PLATFORM OF A TURBINE COMPONENT 有权
标题翻译：用于冷却涡轮机组件平台的装置
公开(公告)号：US20110223004A1
公开(公告)日：2011-09-15
申请号：US12721040
申请日：2010-03-10
申请人： Benjamin Paul Lacy , Gary Michael Itzel , Bin Wei
发明人： Benjamin Paul Lacy , Gary Michael Itzel , Bin Wei
IPC分类号： F02C7/12
CPC分类号： F01D5/187 , F05D2230/11 , F05D2230/12 , F05D2240/81 , F05D2250/184 , F05D2250/71 , F05D2250/713 , F05D2260/22141 , Y02T50/67 , Y02T50/676
摘要： The present subject matter discloses a turbine component including a platform and an airfoil extending radially upward from the platform. A plurality of curved cooling passages may be defined in the platform. Each of the curved cooling passages may have at least one end disposed at an exterior surface of the platform. Additionally, each of the cooling passages may be configured to direct a cooling medium through the platform.
摘要翻译：本主题公开了一种涡轮机部件，包括平台和从平台径向向上延伸的翼型件。可以在平台中限定多个弯曲的冷却通道。每个弯曲的冷却通道可以具有设置在平台的外表面的至少一个端部。此外，每个冷却通道可构造成引导冷却介质通过平台。

87. 发明授权

US08016563B1 Turbine blade with tip turn cooling 有权
标题翻译：涡轮叶片带尖端冷却
公开(公告)号：US08016563B1
公开(公告)日：2011-09-13
申请号：US12004946
申请日：2007-12-21
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/081 , F05D2250/182 , F05D2250/185 , F05D2260/22141
摘要： A turbine blade with a conical shaped tip for use in a first or second stage of a turbine. The airfoil includes an aft flowing 3-pass serpentine flow cooling circuit with a serpentine tip turn located between the first and the second legs and underneath the tip. Mini serpentine flow cooling circuits are formed in the end of the first leg and the beginning of the second leg to reduce or eliminate the cooling flow separation and over temperature issues at the tip portion of the blade. A leading edge cooling supply channel is located forward of the first leg and has a decreasing flow area with an exit cooling hole at the tip to discharge cooling air. The last leg of the main serpentine circuit is formed by a slanted rib that produces a decreasing flow area in the last leg and includes an exit cooling hole on the tip to discharge cooling air. The last leg is connected to a row of exit cooling holes or slots formed along the trailing edge of the airfoil. The main serpentine flow circuit is separated from the leading edge cooling channel so that no cooling air mixes.
摘要翻译：一种涡轮叶片，其具有用于涡轮机的第一或第二阶段的锥形末端。翼型件包括一个尾流三通蛇形流冷却回路，其中蛇形末端转弯位于第一和第二腿之间并且在尖端下方。微型蛇形流冷却回路形成在第一支腿的末端和第二支腿的开始处，以减少或消除叶片末端处的冷却流分离和过温问题。前缘冷却供应通道位于第一支腿的前方，并具有减小的流动面积，在尖端具有出口冷却孔以排出冷却空气。主蛇形回路的最后一条腿由倾斜肋形成，该斜肋在最后一条腿上产生减小的流动面积，并且在尖端上包括排出冷却空气的出口冷却孔。最后一条腿连接到一排出口冷却孔或沿着翼型的后缘形成的槽。主蛇形流回路与前缘冷却通道分离，使冷却空气不混合。

88. 发明申请

US20110200449A1 MEMBER HAVING INTERNAL COOLING PASSAGE 有权
标题翻译：具有内部冷却通道的会员
公开(公告)号：US20110200449A1
公开(公告)日：2011-08-18
申请号：US13093400
申请日：2011-04-25
申请人： Nobuaki Kizuka , Yasuhiro HORIUCHI , Shinya MARUSHIMA , Hidetoshi Kuroki
发明人： Nobuaki Kizuka , Yasuhiro HORIUCHI , Shinya MARUSHIMA , Hidetoshi Kuroki
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/22141
摘要： Provided is a member having an internal cooling passage 7c formed therein and having opposed partition walls 6b, 6c between which a medium flows to cool a parent material, including a first heat transfer rib 25a which extends from almost the center between the opposed partition walls 6b, 6c to one partition wall 6c and slants in a downstream direction of the medium, and a second heat transfer rib 25b which extends from almost the center between the opposed partition walls 6b, 6c to the other partition wall 6b and slants in the downstream direction of the medium, wherein a slit 70a or 70b which passes through between an upstream side of the cooling passage 7c and a downstream side thereof is formed in the first heat transfer rib 70a or the second heat transfer rib 70b.
摘要翻译：本发明提供一种具有形成在其中的内部冷却通道7c并且具有相对的分隔壁6b，6c的构件，介质在其之间流动以冷却母材，其包括第一传热肋25a，第一传热肋25a从相对的间隔壁6b之间的大致中心延伸 6c连接到一个分隔壁6c并且在介质的下游方向上倾斜;以及第二传热肋25b，其从相对的分隔壁6b，6c之间的大致中心延伸到另一分隔壁6b，并且在下游方向上倾斜其中在第一传热肋70a或第二传热肋70b中形成有在冷却通道7c的上游侧和下游侧之间通过的狭缝70a或70b。

89. 发明申请

US20110135446A1 Castings, Casting Cores, and Methods 审中-公开
标题翻译：铸件，铸造芯和方法
公开(公告)号：US20110135446A1
公开(公告)日：2011-06-09
申请号：US12631082
申请日：2009-12-04
申请人： Bryan P. Dube , Edward F. Pietraszkiewicz , David J. Candelori
发明人： Bryan P. Dube , Edward F. Pietraszkiewicz , David J. Candelori
IPC分类号： F01D25/12 , B22C9/10 , B22C7/00 , F01D5/18 , G06F19/00 , B26F1/00
CPC分类号： B22C9/04 , B22C9/10 , B22C9/108 , B22C9/24 , F01D5/187 , F05D2230/21 , F05D2240/122 , F05D2240/304 , F05D2250/292 , F05D2260/22141 , Y02T50/67 , Y02T50/672 , Y02T50/673 , Y02T50/676 , Y10T83/0481 , Y10T428/12292
摘要： If a refractory metal core (RMC) is punched, the punching asymmetry may be reflected in an asymmetry of the cast article features cast by the punched features. The punched features may have a shear zone and a fracture zone. The shear zone of the RMC will cast a relatively narrow portion of the post near one end; whereas the fracture zone will cast a relatively broader portion near the other end. The broader portion will also have a relatively shallow transition to the adjacent face of the slot-like passageway cast by the RMC. Where there is a stress asymmetry in the cast article in-use, the punching direction may be chosen so that the relatively broad portions of the post fall along the relatively higher stress face of the passageway.
摘要翻译：如果冲压耐火金属芯（RMC），冲压不对称可能反映在由冲压特征铸造的铸造件特征的不对称性中。穿孔特征可以具有剪切带和断裂区。 RMC的剪切区域将在靠近一端的位置上投射柱的相对较窄的部分; 而断裂带将在另一端附近铸造相对较宽的部分。更宽的部分还将具有相对较浅的过渡到由RMC铸造的槽状通道的相邻面。在使用中的铸造制品中存在应力不对称的情况下，可以选择冲压方向，使得柱的相对较宽的部分沿着通道的相对较高的应力面落下。

90. 发明申请

US20110064585A1 COOLING DUCT ARRANGEMENT WITHIN A HOLLOW-CAST CASTING 有权
标题翻译：在中空铸造中冷却导管装置
公开(公告)号：US20110064585A1
公开(公告)日：2011-03-17
申请号：US12893307
申请日：2010-09-29
申请人： Jose Ma Anguisola Mcfeat , Erich Kreiselmaier , Christoph Nagler , Sergei Riazantsev
发明人： Jose Ma Anguisola Mcfeat , Erich Kreiselmaier , Christoph Nagler , Sergei Riazantsev
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2230/21 , F05D2240/122 , F05D2240/304 , F05D2260/22141
摘要： Described is a cooling passage arrangement inside a hollow-cast cast part, with a flow region, delimited by at least two spaced apart cast-part walls, for a cooling medium (K), which flow region is divided in the flow direction into two cooling passages (7) by at least one rib line (6) which is connected to the two cast-part walls.The invention is characterized in that provision is made along the at least one rib line (6) for at least one gap (13), at which two rib ends (61, 62) are oppositely disposed a distance apart, of which one rib end has a contour in the style of a “wish bone -“Y”-cross-section” (14).
摘要翻译：描述了一种在中空铸造铸件内部的冷却通道装置，其中流动区域由用于冷却介质（K）的至少两个间隔开的铸件壁限定，该流动区域沿流动方向分成两部分冷却通道（7）通过连接到两个铸件壁的至少一个肋线（6）。本发明的特征在于，沿着至少一个间隙（13）沿着至少一个肋线（6）进行设置，两个肋端部（61,62）相对地间隔一定距离，其中一个肋端部具有“希望骨 - ”Y“ - 横截面”的风格的轮廓（14）。

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