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91. 发明申请

US20130209231A1 NOZZLE GUIDE VANE WITH COOLED PLATFORM FOR A GAS TURBINE 有权
标题翻译：用于气体涡轮的冷却平台的喷嘴导向槽
公开(公告)号：US20130209231A1
公开(公告)日：2013-08-15
申请号：US13809963
申请日：2011-06-17
申请人： Anthony Davis , Paul Mathew Walker
发明人： Anthony Davis , Paul Mathew Walker
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D9/041 , F05D2240/81 , Y10T29/49316
摘要： A platform for supporting a nozzle guide vane for a gas turbine is provided. The platform has a gas passage surface arranged to be in contact with a streaming operation gas, and a cooling channel for guiding a cooling fluid within the cooling channel formed in an inside of the platform. A cooling portion of an inner surface of the cooling channel is in thermal contact with the gas passage surface. The platform is an integrally formed part representing a segment in a circumferential direction of the gas turbine. The cooling channel has a first cooling channel portion and a second cooling channel portion arranged downstream of the first cooling channel portion with respect to a streaming direction of the operation gas. The first cooling channel portion and the second cooling channel portion are interconnected.
摘要翻译：提供了一种用于支撑用于燃气轮机的喷嘴导向叶片的平台。平台具有布置成与流动操作气体接触的气体通道表面，以及用于引导形成在平台内部的冷却通道内的冷却流体的冷却通道。冷却通道的内表面的冷却部分与气体通道表面热接触。平台是表示燃气轮机的圆周方向上的节段的整体形成的部分。冷却通道具有相对于操作气体的流动方向布置在第一冷却通道部分的下游的第一冷却通道部分和第二冷却通道部分。第一冷却通道部分和第二冷却通道部分相互连接。

92. 发明申请

US20130209227A1 GAS TURBINE ENGINE COMPONENT WITH DIFFUSIVE COOLING HOLE 有权
标题翻译：气体涡轮发动机组件与扩散式冷却孔
公开(公告)号：US20130209227A1
公开(公告)日：2013-08-15
申请号：US13544153
申请日：2012-07-09
申请人： JinQuan Xu
发明人： JinQuan Xu
IPC分类号： F01D5/18 , F01D9/02
CPC分类号： F01D5/186 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/24 , F05D2240/81 , F05D2260/202 , F23R2900/03042 , Y02T50/676
摘要： A component for a gas turbine engine includes a gas path wall having a first surface, a second surface exposed to hot gas flow, and a cooling hole extending through the gas path wall. The cooling hole includes an inlet formed in the first surface, an outlet formed in the second surface, cooling hole surfaces that define the cooling hole between the inlet and the outlet, and a longitudinal ridge formed along at least one of the cooling hole surfaces. The longitudinal ridge separates the cooling hole into first and second lobes. The cooling hole diverges through the gas path wall, such that cross-sectional area of the cooling hole increases continuously from the inlet through the cooling hole to the outlet.
摘要翻译：用于燃气涡轮发动机的部件包括具有第一表面，暴露于热气流的第二表面和延伸穿过气体通道壁的冷却孔的气体通道壁。冷却孔包括形成在第一表面中的入口，形成在第二表面中的出口，限定入口和出口之间的冷却孔的冷却孔表面以及沿至少一个冷却孔表面形成的纵向脊。纵向脊将冷却孔分成第一和第二凸角。冷却孔分散通过气体通道壁，使得冷却孔的横截面积从入口通过冷却孔连续地增加到出口。

93. 发明申请

US20130205790A1 MULTI-LOBED COOLING HOLE AND METHOD OF MANUFACTURE 有权
标题翻译：多孔冷却孔及其制造方法
公开(公告)号：US20130205790A1
公开(公告)日：2013-08-15
申请号：US13544090
申请日：2012-07-09
申请人： JinQuan Xu , Mark F. Zelesky , Atul Kohli , Matthew S. Gleiner
发明人： JinQuan Xu , Mark F. Zelesky , Atul Kohli , Matthew S. Gleiner
IPC分类号： F02C7/18 , F01D25/12 , F04D29/58 , F01D5/18
CPC分类号： F23R3/06 , F01D5/186 , F01D9/065 , F05D2240/81 , F23R2900/03042 , Y02T50/676
摘要： A gas turbine engine component includes a cooling hole. The cooling hole includes an inlet, an outlet, a metering section and a diffusing section. The diffusing section extends from the metering section to the outlet and includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section, and a transition region having a portion that extends between the first and second lobes and an end adjacent the outlet.
摘要翻译：燃气涡轮发动机部件包括冷却孔。冷却孔包括入口，出口，计量部分和扩散部分。扩散部分从计量部分延伸到出口并且包括从计量部分纵向和横向发散的第一凸角，邻近第一凸角并从计量部分纵向和横向发散的第二凸角，以及过渡区域，其具有在第一和第二凸角之间延伸，并且邻近出口延伸。

94. 发明申请

US20130205787A1 TRI-LOBED COOLING HOLE AND METHOD OF MANUFACTURE 有权
标题翻译：三轴冷却孔及其制造方法
公开(公告)号：US20130205787A1
公开(公告)日：2013-08-15
申请号：US13544101
申请日：2012-07-09
申请人： Mark F. Zelesky , Atul Kohli , Scott D. Lewis
发明人： Mark F. Zelesky , Atul Kohli , Scott D. Lewis
IPC分类号： F01D25/12 , F23R3/02 , F02C7/00 , F01D5/18 , F01D9/02
CPC分类号： F23R3/06 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R2900/03041 , F23R2900/03042 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine component includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second wall surface and a diffusing section positioned between the inlet and the outlet. The diffusing section includes a first lobe, a second lobe adjacent the first lobe and a third lobe adjacent the second lobe. The first lobe and the second lobe meet at a first ridge and the second lobe and the third lobe meet at a second ridge.
摘要翻译：燃气涡轮发动机部件包括第一和第二壁表面，位于第一壁表面处的入口，位于第二壁表面处的出口和位于入口和出口之间的扩散部分。扩散部分包括第一凸角，与第一凸角相邻的第二凸角和与第二凸角相邻的第三凸角。第一个小叶和第二个小叶在第一个山脊相交，第二个叶和第三个叶在第二个山脊相遇。

95. 发明申请

US20130189110A1 TURBINE ARRANGEMENT AND GAS TURBINE ENGINE 有权
标题翻译：涡轮机布置和气体涡轮发动机
公开(公告)号：US20130189110A1
公开(公告)日：2013-07-25
申请号：US13876595
申请日：2011-09-19
申请人： Stephen Batt , Jonathan Mugglestone
发明人： Stephen Batt , Jonathan Mugglestone
IPC分类号： F01D5/30
CPC分类号： F01D5/30 , F01D9/041 , F05D2240/81 , F05D2260/201
摘要： A turbine arrangement includes first and second platforms forming a section of a main fluid path, aerofoils, and an impingement plate. Each aerofoil extends from the first to the second platform. The second platform has a surface opposite to the main fluid path with recesses surrounded by a raised edge, which provides support for the mountable impingement plate. The edge is formed as a first closed loop surrounding a first recess and further surrounding a first aperture of a first aerofoil and as a second closed loop surrounding a second recess and further surrounding a second aperture of a second aerofoil. A portion of the edge defines a continuous barrier between the first recess and the second recess for blocking cooling fluid. The barrier forms a mating surface for a central area of the impingement plate.
摘要翻译：涡轮装置包括形成主流体路径，翼状件和冲击板的一部分的第一和第二平台。每个机翼从第一平台延伸到第二平台。第二平台具有与主流体路径相对的表面，其具有由凸起边缘包围的凹部，其为可安装的冲击板提供支撑。边缘形成为围绕第一凹部的第一闭合环，并且进一步包围第一翼面的第一孔，以及围绕第二凹部的第二闭环，并且还包围第二翼型的第二孔。该边缘的一部分在第一凹部和第二凹部之间限定一个连续的阻挡层，用于阻止冷却流体。阻挡层形成冲击板的中心区域的配合表面。

96. 发明申请

US20130177447A1 Turbine Nozzle Assembly Methods 有权
标题翻译：涡轮喷嘴装配方法
公开(公告)号：US20130177447A1
公开(公告)日：2013-07-11
申请号：US13345777
申请日：2012-01-09
申请人： Robert Walter Coign , Aaron Gregory Winn
发明人： Robert Walter Coign , Aaron Gregory Winn
IPC分类号： F01D5/18 , B21K25/00
CPC分类号： F01D9/041 , F01D5/188 , F05D2240/81 , F05D2260/201 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323
摘要： The present application provides a method of installing an impingement cooling assembly in an inner platform of an airfoil of a turbine nozzle. The method may include the steps of positioning an insert within a cavity of the airfoil, positioning a core exit cover about an opening of the cavity, positioning an impingement plenum within a platform cavity, inserting an unfixed spoolie through an assembly port of the impingement plenum and into an airflow cavity of the insert, and closing the assembly port.
摘要翻译：本申请提供了一种将冲击冷却组件安装在涡轮喷嘴的翼型件的内平台中的方法。该方法可以包括以下步骤：将插入件定位在机翼的空腔内，将芯出口盖定位在空腔的开口周围，将冲击气室定位在平台空腔内，将未固定的轴套插入穿过冲击气室的组装端口并进入插入件的气流腔中，并关闭装配口。

97. 发明申请

US20130171005A1 TURBINE ROTOR BLADE PLATFORM COOLING 有权
标题翻译：涡轮转子叶片平台冷却
公开(公告)号：US20130171005A1
公开(公告)日：2013-07-04
申请号：US13341027
申请日：2011-12-30
申请人： Scott Edmond Ellis , Aaron Ezekiel Smith
发明人： Scott Edmond Ellis , Aaron Ezekiel Smith
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/188 , F05D2240/81 , Y02T50/676
摘要： A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage formed therein, wherein, in operation, the interior cooling passage comprises a high-pressure coolant region and a low-pressure coolant region, and wherein a suction side of the platform comprises a topside extending circumferentially from the airfoil to a suction side slashface, and wherein the suction side of the platform comprises an aft edge. The platform cooling arrangement may include: a manifold positioned within an aft side of the suction side of the platform; a high-pressure connector that connects the manifold to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the manifold to the low-pressure coolant region of the interior cooling passage; and heat transfer structure positioned within the manifold.
摘要翻译：涡轮转子叶片中的平台冷却装置，其具有在翼型件和根部之间的界面处的平台，其中转子叶片包括形成在其中的内部冷却通道，其中，在操作中，内部冷却通道包括高压冷却剂区域和低压冷却剂区域，并且其中所述平台的吸入侧包括从所述翼型件到所述翼型件的周向延伸到吸入侧斜面的顶侧，并且其中所述平台的吸入侧包括后缘。平台冷却装置可以包括：位于平台的吸入侧的后侧的歧管; 将歧管连接到内部冷却通道的高压冷却剂区域的高压连接器; 将所述歧管连接到所述内部冷却通道的低压冷却剂区域的低压连接器; 以及位于歧管内的传热结构。

98. 发明申请

US20130171004A1 TURBINE ROTOR BLADE PLATFORM COOLING 有权
标题翻译：涡轮转子叶片平台冷却
公开(公告)号：US20130171004A1
公开(公告)日：2013-07-04
申请号：US13341024
申请日：2011-12-30
申请人： Scott Edmond Ellis , Aaron Ezekiel Smith
发明人： Scott Edmond Ellis , Aaron Ezekiel Smith
IPC分类号： F01D5/18 , B22D23/00 , B22D25/02
CPC分类号： F01D5/187 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： A platform cooling arrangement in a turbine rotor blade having a platform positioned between an airfoil and a root. The rotor blade, along a side that coincides with a pressure side of the airfoil, includes a pressure side of the platform includes a topside extending from an airfoil base to a pressure side slashface. The platform cooling arrangement includes: a main plenum residing just inboard of the topside in the pressure side of the platform, the main plenum extending through the platform from an upstream end having an aft position to a downstream end having a forward position; and cooling apertures. Near the upstream end, the main plenum includes an aft switchback, and, between the aft switchback and the downstream end, a forward arc. Each of the cooling apertures extends from the main plenum to a port formed on the pressure side slashface.
摘要翻译：涡轮转子叶片中的平台冷却装置，其具有位于翼型件和根部之间的平台。转子叶片沿着与翼型件的压力侧重合的一侧，包括平台的压力侧，其包括从翼型基部延伸到压力侧斜面的顶侧。平台冷却装置包括：位于平台的压力侧的顶侧刚好内侧的主增压室，主增压室从具有后位的上游端延伸穿过平台到具有向前位置的下游端; 和冷却孔。在上游端附近，主增压室包括尾部折返，并且在后退和下游端之间具有前弧。每个冷却孔从主增压室延伸到形成在压力侧斜面上的端口。

99. 发明授权

US08459935B1 Turbine vane with endwall cooling 有权
标题翻译：涡轮叶片与端壁冷却
公开(公告)号：US08459935B1
公开(公告)日：2013-06-11
申请号：US13445078
申请日：2012-04-12
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/201
摘要： Turbine stator vane with endwall cooling that includes a number of impingement chambers that extend around the airfoil perpendicular to a hot gas flow over the endwall, the impingement chambers are connected by rows of near wall cooling channels offset so that impingement cooling occurs within the chambers, some of the impingement chambers are connected by resupply cooling air holes and some of the impingement chambers are connected to film cooling holes.
摘要翻译：具有端壁冷却的涡轮定子叶片包括多个冲击室，其围绕翼型垂直于端壁上的热气流延伸，冲击室通过偏移的近壁冷却通道排连接，使得在室内发生冲击冷却，一些冲击室通过再供给的冷却空气孔连接，并且一些冲击室连接到薄膜冷却孔。

100. 发明授权

US08444376B2 Cooled constructional element for a gas turbine 有权
标题翻译：用于燃气轮机的冷却结构元件
公开(公告)号：US08444376B2
公开(公告)日：2013-05-21
申请号：US13192656
申请日：2011-07-28
申请人： Joerg Krueckels , Milan Pathak
发明人： Joerg Krueckels , Milan Pathak
IPC分类号： F04D31/00
CPC分类号： F01D5/187 , F01D25/12 , F05D2240/81 , F05D2260/201
摘要： A cooled constructional element for a gas turbine includes a wall having a front and a rear side. The front side is configured to be thermally loaded during operation of the turbine, and the rear side has a plurality of pins projecting therefrom in a two-dimensional distribution, the two-dimensional distribution including a higher density distribution of pins in a critical zone of the cooled constructional element than in the remaining regions of the cooled constructional element. A device is configured to create jets of a cooling medium that are directed onto the rear side of the wall in a region of the plurality of pins so as to cool the rear side of the wall by impingement.
摘要翻译：用于燃气涡轮机的冷却结构元件包括具有前侧和后侧的壁。前侧被构造成在涡轮机的运行期间被热负载，并且后侧具有以二维分布从其突出的多个销，所述二维分布包括在关键区域中的销的较高密度分布冷却结构元件比冷却结构元件的其余区域要冷。一种装置构造成在多个销的区域中产生指向壁的后侧的冷却介质的喷嘴，以便通过冲击来冷却壁的后侧。

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