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公开(公告)号：US07377742B2
公开(公告)日：2008-05-27
申请号：US11250660
申请日：2005-10-14
申请人： Jason David Shapiro , Daniel Demers , Robert Patrick Tameo , Tyler F. Hooper , Robert Alexander Nicoll , Douglas Patrick Probasco
发明人： Jason David Shapiro , Daniel Demers , Robert Patrick Tameo , Tyler F. Hooper , Robert Alexander Nicoll , Douglas Patrick Probasco
IPC分类号： F01D25/26
CPC分类号： F01D11/24 , F01D11/08 , F05D2230/90 , F05D2240/11 , F05D2300/611
摘要： A method for assembling a gas turbine engine includes coupling a rotor assembly including a plurality of rotor blades about a rotatable main shaft of the gas turbine engine. The main shaft is aligned in an axial direction of the gas turbine engine. A shroud assembly is coupled to the gas turbine engine. The shroud assembly includes a plurality of shroud segments circumferentially coupled about the rotor assembly such that a shroud spacing gap is formed in the axial direction between adjacent shroud segments. A cooling fluid source is coupled to each shroud segment such that cooling fluid is channeled through each shroud segment into a corresponding shroud spacing gap to facilitate positive purge flow through the shroud spacing gap.
摘要翻译： 一种用于组装燃气涡轮发动机的方法包括将包括多个转子叶片的转子组件围绕燃气涡轮发动机的可旋转主轴联接。 主轴沿燃气轮机的轴向对准。 护罩组件联接到燃气涡轮发动机。 护罩组件包括围绕转子组件周向耦合的多个护罩段，使得在相邻护罩段之间沿轴向方向形成护罩间隔间隙。 冷却流体源联接到每个护罩段，使得冷却流体通过每个护罩段引导成相应的护罩间隔间隙，以促进穿过护罩间隔间隙的正净化流动。
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公开(公告)号：US08123473B2
公开(公告)日：2012-02-28
申请号：US12262606
申请日：2008-10-31
申请人： Jason David Shapiro
发明人： Jason David Shapiro
CPC分类号： F01D25/246 , F01D11/08 , F01D25/14 , F05D2260/205 , Y10T29/49323
摘要： A shroud hanger for a gas turbine engine has an arcuate body with opposed inner and outer faces and opposed forward and aft ends, the channel having at least one cooling passage therein which includes: (a) a generally axially-aligned channel extending through the body, the channel having one end open to an exterior of the body; and (b) a generally radially-aligned diffuser extending through the inner face and intersecting the channel.
摘要翻译： 用于燃气涡轮发动机的护罩悬挂器具有弓形体，其具有相对的内表面和外表面以及相对的前端和后端，所述通道在其中具有至少一个冷却通道，其包括：（a）延伸穿过本体的大致轴向对齐的通道 ，所述通道的一端向所述主体的外部敞开; 和（b）通过径向对齐的扩散器延伸穿过内表面并与通道相交。
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公开(公告)号：US07377743B2
公开(公告)日：2008-05-27
申请号：US11311104
申请日：2005-12-19
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D9/041 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle includes a mid vane mounted between a pair of end vanes in outer and inner bands. The mid vane includes a first pattern of film cooling holes configured to discharge more cooling air than each of the two end vanes having respective second patterns of film cooling holes.
摘要翻译： 涡轮喷嘴包括安装在外带和内带中的一对末端叶片之间的中间叶片。 中间叶片包括第一图案的薄膜冷却孔，其被配置为比具有相应的第二图案的薄膜冷却孔的两个末端叶片中的每一个排出更多的冷却空气。
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公开(公告)号：US08985944B2
公开(公告)日：2015-03-24
申请号：US13075740
申请日：2011-03-30
CPC分类号： F01D11/08 , F01D9/04 , F01D11/18 , F01D25/246 , F05D2300/603
摘要： A composite annular shroud supported by a support assembly including at least two single piece full 360 degree rings and at least partially disposed within an innermost one of the rings. The shroud is biased against and in sealing engagement with an inner flange of the innermost ring. A three ring assembly includes the inner ring disposed radially inwardly of a middle ring disposed radially inwardly of an outer ring and the shroud at least partially disposed within the inner ring. At least three clocking pins extend radially inwardly from the middle ring through slots in the inner ring into notches in the shroud.The middle ring may be an aft end of a support ring fixedly connected to an engine backbone. Mounting pins may be press fitted into pin holes in the middle ring and extend radially outwardly from the middle ring through radial holes in the outer ring.
摘要翻译： 一种由支撑组件支撑的复合环形罩，所述支撑组件包括至少两个单件全360度环并且至少部分地设置在所述环的最内一个环中。 护罩偏置在最内圈的内凸缘上并与之密封接合。 三环组件包括设置在外环的径向向内设置的中环的径向向内的内环，并且护罩至少部分地设置在内环内。 至少三个定时销从中间环径向向内延伸穿过内圈中的槽，使其处于护罩中的凹口。 中间环可以是固定地连接到发动机主干的支撑环的后端。 安装销可以压配合到中间环的销孔中，并从中间环径向向外延伸穿过外环的径向孔。
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公开(公告)号：US20090220331A1
公开(公告)日：2009-09-03
申请号：US12040482
申请日：2008-02-29
IPC分类号： F01D25/12
CPC分类号： F01D9/042 , F01D25/12 , F01D25/14 , F01D25/246 , F05D2240/81 , F05D2260/201
摘要： A turbine nozzle segment includes: (a) an arcuate outer band segment; (b) a hollow, airfoil-shaped turbine vane extending radially inward from the outer band segment; (c) a manifold cover secured to the outer band such that the manifold cover and the outer band segment cooperatively define an impingement cavity; and (d) an impingement blanket disposed in the impingement cavity, the impingement blanket having at least one impingement hole formed therethrough which is arranged to direct cooling air at the outer band segment. A method is provided for impingement cooling the outer band segment.
摘要翻译： 涡轮喷嘴段包括：（a）弓形外带段; （b）从外带段径向向内延伸的中空翼型涡轮叶片; （c）固定到外带的歧管盖，使得歧管盖和外带段协调地限定冲击腔; 和（d）设置在所述冲击腔中的冲击毯，所述冲击毯具有穿过其形成的至少一个冲击孔，所述冲击孔被布置成引导所述外带段处的冷却空气。 提供了一种冲击冷却外带段的方法。
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公开(公告)号：US20120247124A1
公开(公告)日：2012-10-04
申请号：US13075740
申请日：2011-03-30
CPC分类号： F01D11/08 , F01D9/04 , F01D11/18 , F01D25/246 , F05D2300/603
摘要： A composite annular shroud supported by a support assembly including at least two single piece full 360 degree rings and at least partially disposed within an innermost one of the rings. The shroud is biased against and in sealing engagement with an inner flange of the innermost ring. A three ring assembly includes the inner ring disposed radially inwardly of a middle ring disposed radially inwardly of an outer ring and the shroud at least partially disposed within the inner ring. At least three clocking pins extend radially inwardly from the middle ring through slots in the inner ring into notches in the shroud.The middle ring may be an aft end of a support ring fixedly connected to an engine backbone. Mounting pins may be press fitted into pin holes in the middle ring and extend radially outwardly from the middle ring through radial holes in the outer ring.
摘要翻译： 一种由支撑组件支撑的复合环形罩，所述支撑组件包括至少两个单件全360度环并且至少部分地设置在所述环的最内一个环中。 护罩偏置在最内圈的内凸缘上并与之密封接合。 三环组件包括设置在外环的径向向内设置的中环的径向向内的内环，并且护罩至少部分地设置在内环内。 至少三个定时销从中间环径向向内延伸穿过内圈中的槽，使其处于护罩中的凹口。 中间环可以是固定地连接到发动机主干的支撑环的后端。 安装销可以压配合到中间环的销孔中，并从中间环径向向外延伸穿过外环中的径向孔。
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公开(公告)号：US08172504B2
公开(公告)日：2012-05-08
申请号：US12055101
申请日：2008-03-25
申请人： David Allen Flodman , Jason David Shapiro , Robert Francis Manning , Mark Douglas Gledhill , Tyler Frederick Hooper
发明人： David Allen Flodman , Jason David Shapiro , Robert Francis Manning , Mark Douglas Gledhill , Tyler Frederick Hooper
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： A turbine nozzle for a gas turbine engine includes: (a) spaced-apart arcuate inner and outer bands; (b) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the interior of the vane defining at least a forward cavity and a mid-cavity positioned aft of the forward cavity; (c) a hollow impingement insert received inside the mid-cavity, the impingement insert having walls which are pierced with at least one impingement cooling hole; (d) a passage in the turbine vane at a radially outer end of the forward cavity adapted to be coupled to a source of cooling air; and (e) a passage in the inner band in fluid communication with a radially inner end of the forward cavity and a radially inner end of the impingement insert.
摘要翻译： 用于燃气涡轮发动机的涡轮喷嘴包括：（a）间隔开的弓形内部和外部带; （b）在所述内部和外部带之间延伸的中空翼型涡轮机叶片，所述叶片的内部至少限定前腔和位于所述前腔后面的中空腔; （c）容纳在中空腔内的中空冲击插入件，冲击插入件具有用至少一个冲击冷却孔刺穿的壁; （d）在所述前腔的径向外端处的涡轮叶片中的通道，其适于联接到冷却空气源; 和（e）内带中的与前腔的径向内端流体连通的通道和冲击插入件的径向内端。
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公开(公告)号：US08092163B2
公开(公告)日：2012-01-10
申请号：US12058972
申请日：2008-03-31
IPC分类号： F01D25/28
CPC分类号： F01D9/042
摘要： A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart from the first location. A stator assembly for a gas turbine engine is described, the stator assembly comprising a stator vane having an airfoil, an outer band located on a radially outer end of the airfoil, a shroud hanger located axially adjacent to the outer band, the shroud hanger comprising a post wherein at least a portion of the post extends in an axial direction over a portion of the outer band, and a reaction mount system located on the outer band wherein the reaction mount system engages with the post to provide support for the stator vane.
摘要翻译： 描述了提供对用于燃气涡轮发动机的定子叶片的支撑的反应安装系统，其包括位于第一位置处的外带上的定子悬挂器和位于与第一位置周向隔开的第二位置的定子止动器。 描述了一种用于燃气涡轮发动机的定子组件，该定子组件包括具有翼型的定子叶片，位于翼型件的径向外端的外带，位于轴向邻近外带的护罩，衣架悬挂器包括 柱，其中所述柱的至少一部分在所述外带的一部分上沿轴向方向延伸;以及反应安装系统，位于所述外带上，其中所述反作用安装系统与所述柱接合以为所述定子叶片提供支撑。
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公开(公告)号：US20100111670A1
公开(公告)日：2010-05-06
申请号：US12262606
申请日：2008-10-31
申请人： Jason David Shapiro
发明人： Jason David Shapiro
CPC分类号： F01D25/246 , F01D11/08 , F01D25/14 , F05D2260/205 , Y10T29/49323
摘要： A shroud hanger for a gas turbine engine has an arcuate body with opposed inner and outer faces and opposed forward and aft ends, the channel having at least one cooling passage therein which includes: (a) a generally axially-aligned channel extending through the body, the channel having one end open to an exterior of the body; and (b) a generally radially-aligned diffuser extending through the inner face and intersecting the channel.
摘要翻译： 用于燃气涡轮发动机的护罩悬挂器具有弓形体，其具有相对的内表面和外表面以及相对的前端和后端，所述通道在其中具有至少一个冷却通道，其包括：（a）延伸穿过本体的大致轴向对齐的通道 ，所述通道的一端向所述主体的外部敞开; 和（b）通过径向对齐的扩散器延伸穿过内表面并与通道相交。
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公开(公告)号：US20090246014A1
公开(公告)日：2009-10-01
申请号：US12058980
申请日：2008-03-31
CPC分类号： F01D9/042 , F01D25/246 , F04D29/526 , F04D29/644 , F05D2260/94 , F05D2260/941
摘要： A method and system of supporting removable static components in a turbine engine stator assembly is described. The method comprises the steps of engaging a stator hanger located at a first location on a first static component with a post located on a first static structure whereby the post supports at least a part of the weight of the first static component, engaging a stator stopper located at a second location on the first static component that is located circumferentially apart from the first location with the stator hanger that is located on a second static component, and engaging a hook located at a third location on the first static component with a second static structure whereby the second static structure supports at least a part of the weight of the first static component.
摘要翻译： 描述了一种在涡轮发动机定子组件中支撑可移除静态部件的方法和系统。 该方法包括以下步骤：将位于第一静态部件上的第一位置的定子吊架与位于第一静态结构上的柱接合，由此支柱支撑第一静态部件的重量的至少一部分， 位于所述第一静态部件上的第二位置，所述第二静止部件位于与所述第一位置周向隔开的位置处，所述第二静止部件位于所述第二静止部件上的所述定子衣架上，并且使位于所述第一静止部件上的第三位置的钩与第二静止部件 结构，由此第二静态结构支撑第一静态部件的重量的至少一部分。
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