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公开(公告)号：US20110262274A1
公开(公告)日：2011-10-27
申请号：US12764212
申请日：2010-04-21
CPC分类号： F01D5/26 , F01D11/006 , F05D2260/96
摘要： A system for creating a seal between a damper and a platform of a turbine engine component includes a turbine engine component having an airfoil portion, a platform, and a fir tree for joining the turbine engine component to a rotor, a damper located in an area beneath the platform, a seal having a sealing surface which seats against an underside of the platform, which seal has a seal retention feature which bends into contact with an underside of the damper, and which seal with the seal retention feature has a center of gravity which allows the seal retention feature to bend up as result of rotational movement of the rotor. A method for creating the seal is also described.
摘要翻译： 用于在阻尼器和涡轮发动机部件的平台之间产生密封的系统包括具有翼型部分，平台和用于将涡轮发动机部件连接到转子的冷杉树的涡轮发动机部件，位于区域 在该平台下面，具有密封表面的密封件，该密封表面抵靠平台的下侧，该密封件具有弯曲成与阻尼器的下侧接触的密封保持特征，并且与密封保持部件的密封具有重心 这允许密封保持特征由于转子的旋转运动而弯曲。 还描述了用于产生密封件的方法。
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公开(公告)号：US08016547B2
公开(公告)日：2011-09-13
申请号：US12009716
申请日：2008-01-22
IPC分类号： F03D11/00
CPC分类号： F01D5/188 , F05D2250/185 , F05D2270/301
摘要： A nozzle assembly for directing cooling fluid in a vane comprising a hollow airfoil containing at least two cooling chambers. The chambers are separated by a generally radial rib. A metering plate mount is attached to the rib. A metering plate, having at least one aperture for tuning the cooling fluid flow within the airfoil, is adjacent the metering plate mount.
摘要翻译： 用于将冷却流体引导到叶片中的喷嘴组件包括包含至少两个冷却室的中空翼型件。 这些腔室通常由大致径向的肋条分开。 计量板安装件连接到肋上。 具有用于调节翼型内的冷却流体流的至少一个孔的计量板与计量板安装件相邻。
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公开(公告)号：US20090016873A1
公开(公告)日：2009-01-15
申请号：US11775330
申请日：2007-07-10
CPC分类号： F01D11/008 , F01D9/041 , F01D11/005 , F05D2240/80 , F05D2260/94 , F05D2260/941
摘要： Systems involving feather seals are provided. A representative vane assembly for a gas turbine engine includes: a first mounting platform having a first slot; a first airfoil extending from the first mounting platform; and a feather seal having opposing faces, a first side extending between the faces, and a first tab, the first tab extending outwardly beyond the first side; the first slot being sized and shaped to receive the feather seal including the first tab.
摘要翻译： 提供涉及羽毛密封的系统。 用于燃气涡轮发动机的代表性叶片组件包括：具有第一槽的第一安装平台; 从所述第一安装平台延伸的第一翼型件; 以及具有相对面的羽毛密封件，在所述表面之间延伸的第一侧和第一突出部，所述第一突出部向外延伸超过所述第一侧面; 所述第一狭槽的尺寸和形状被设计成接收包括所述第一突出部的所述羽毛密封。
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公开(公告)号：US20080170944A1
公开(公告)日：2008-07-17
申请号：US11652434
申请日：2007-01-11
IPC分类号： F04D29/38
CPC分类号： F01D5/188 , B22C9/10 , F01D9/02 , F05D2230/21 , F05D2230/237 , F05D2230/60 , F05D2230/80 , F05D2240/12 , F05D2240/126 , F05D2240/55 , F05D2250/30 , F05D2260/201
摘要： An insertable impingement rib assembly inside of a turbine vane. The turbine vane has an airfoil portion with a leading edge and a trailing edge. The turbine vane has an inner diameter platform and an outer diameter platform. A guide channel is located in the airfoil portion of the turbine vane. The guide channel has an insertion point, a leading edge guide rail rib, a trailing edge guide rail rib, and a plurality of apertures therethrough. An impingement rib is insertable into the guide channel.
摘要翻译： 在涡轮叶片内部的可插入冲击肋组件。 涡轮叶片具有具有前缘和后缘的翼型部分。 涡轮叶片具有内径平台和外径平台。 引导通道位于涡轮叶片的翼型部分中。 引导通道具有插入点，前缘导轨肋，后缘导轨肋和穿过其中的多个孔。 冲击肋可插入引导通道。
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公开(公告)号：US09610644B2
公开(公告)日：2017-04-04
申请号：US13022641
申请日：2011-02-08
IPC分类号： F01D9/04 , B23K1/00 , B23K101/00
CPC分类号： B23K1/0018 , B23K2101/001 , F01D9/044 , F05D2230/237 , Y10T29/49229
摘要： A turbine component is formed of at least a plurality of adjacent turbine subcomponents. Each turbine component has a mate face secured to the mate face of an opposed turbine subcomponent. A wedge member is positioned between the mate faces of the turbine subcomponents, and a braze material between outer faces of the wedge and the mate faces of each of the turbine subcomponents.
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公开(公告)号：US09486854B2
公开(公告)日：2016-11-08
申请号：US13608210
申请日：2012-09-10
CPC分类号： B22D25/02 , B22C7/02 , B22C9/04 , B22C9/103 , B22C9/108 , B22C9/24 , B22D23/00 , F01D5/18 , F01D5/186 , F01D9/02 , F01D25/12 , F05D2220/32 , F05D2230/21 , F05D2230/211 , F05D2300/13
摘要： A core assembly for forming a cast component includes a refractory metal core and a ceramic core element. The refractory metal core includes first and second ends and sides extending from the first end to the second end. The ceramic core element includes a slot positioned between first and second lands, each land having an inner surface facing the slot and an adjacent outer surface. The first end of the refractory metal core is secured within the slot with an adhesive, and the refractory metal core extends from the ceramic core element in both a longitudinal and a transverse direction. The slot, lands, and refractory metal core form a core assembly providing access paths to the sides of the refractory metal core. Surplus adhesive is removed from the refractory metal core via the access paths. Investment casting provides the component with an internal passage and an internal cooling circuit.
摘要翻译： 用于形成铸件的芯组件包括难熔金属芯和陶瓷芯元件。 难熔金属芯包括从第一端延伸到第二端的第一端和第二端和侧面。 陶瓷芯体元件包括位于第一和第二焊盘之间的槽，每个焊盘具有面向槽的内表面和相邻的外表面。 耐火金属芯的第一端用粘合剂固定在槽内，耐火金属芯从纵向和横向方向从陶瓷芯体延伸。 槽，焊盘和难熔金属芯形成芯组件，提供通向耐火金属芯的侧面的通路。 剩余的粘合剂经由进入路径从难熔金属芯中除去。 投资铸造为部件提供内部通道和内部冷却回路。
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公开(公告)号：US09296039B2
公开(公告)日：2016-03-29
申请号：US13454197
申请日：2012-04-24
申请人： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Dominic J. Mongillo, Jr. , Matthew A. Devore , Steven Bruce Gautschi , Benjamin T. Fisk
发明人： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Dominic J. Mongillo, Jr. , Matthew A. Devore , Steven Bruce Gautschi , Benjamin T. Fisk
CPC分类号： B22C9/04 , B22C9/10 , B22C9/24 , B22F3/1017 , B22F3/105 , B22F3/1055 , B22F5/04 , B23K15/0086 , B33Y10/00 , B33Y80/00 , C21D9/0068 , F01D5/187 , F05D2240/303 , F05D2260/201 , F05D2260/202 , F05D2260/205 , Y02P10/292 , Y02P10/295
摘要： An airfoil has a body that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. A leading edge wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the leading edge wall to provide an impingement cavity between the leading edge wall and the impingement wall and multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall. A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of an airfoil, and producing the airfoil.
摘要翻译： 机翼具有主体，其包括通过间隔开的压力和吸力侧连接的前缘和后缘以提供外部翼面表面。 前缘壁在前缘提供外部翼型表面。 冲击壁与前缘壁一体地形成，以在前缘壁和冲击壁之间提供冲击腔，并且多个冲击孔设置在冲击壁中。 冲击孔横向穿过冲击壁间隔开。 一种制造翼型件的方法包括以下步骤：将多层粉末金属沉积到彼此上，参考与翼型的特定横截面相关的CAD数据并将翼片相互连接，并产生翼型件。
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公开(公告)号：US09279335B2
公开(公告)日：2016-03-08
申请号：US13196980
申请日：2011-08-03
CPC分类号： F01D9/041 , F01D17/162 , F05D2250/30 , F05D2250/70 , F05D2250/73 , Y10T29/49229
摘要： A vane assembly for a gas turbine engine includes a first platform, a second platform, and an airfoil that extends radially across an annulus between the first platform and the second platform. The airfoil is centered relative to a centerline axis of the second platform and is offset relative to a centerline axis of the first platform.
摘要翻译： 用于燃气涡轮发动机的叶片组件包括第一平台，第二平台和径向延伸穿过第一平台和第二平台之间的环的翼型件。 翼型件相对于第二平台的中心线轴线居中，并且相对于第一平台的中心线轴线偏移。
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公开(公告)号：US08727710B2
公开(公告)日：2014-05-20
申请号：US13012025
申请日：2011-01-24
IPC分类号： F01D5/00
CPC分类号： F01D11/005 , F01D9/041 , F05D2240/11 , F05D2240/57 , F05D2260/201 , F05D2260/30
摘要： A feather seal assembly includes a seal having a directional passage to direct an airflow generally non-perpendicular to the seal.
摘要翻译： 羽毛密封组件包括具有定向通道以密封通常不垂直于密封件的气流的密封件。
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公开(公告)号：US08672626B2
公开(公告)日：2014-03-18
申请号：US12764212
申请日：2010-04-21
IPC分类号： F01D5/10
CPC分类号： F01D5/26 , F01D11/006 , F05D2260/96
摘要： A system for creating a seal between a damper and a platform of a turbine engine component includes a turbine engine component having an airfoil portion, a platform, and a fir tree for joining the turbine engine component to a rotor, a damper located in an area beneath the platform, a seal having a sealing surface which seats against an underside of the platform, which seal has a seal retention feature which bends into contact with an underside of the damper, and which seal with the seal retention feature has a center of gravity which allows the seal retention feature to bend up as result of rotational movement of the rotor. A method for creating the seal is also described.
摘要翻译： 用于在阻尼器和涡轮发动机部件的平台之间产生密封的系统包括具有翼型部分，平台和用于将涡轮发动机部件连接到转子的冷杉树的涡轮发动机部件，位于区域 在该平台下面，具有密封表面的密封件，该密封表面抵靠平台的下侧，该密封件具有弯曲成与阻尼器的下侧接触的密封保持特征，并且与密封保持部件的密封具有重心 这允许密封保持特征由于转子的旋转运动而弯曲。 还描述了用于产生密封件的方法。
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