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61. 发明授权

US09279335B2 Vane assembly for a gas turbine engine 有权
标题翻译：燃气轮机的叶片组件
公开(公告)号：US09279335B2
公开(公告)日：2016-03-08
申请号：US13196980
申请日：2011-08-03
申请人： Tracy A. Propheter-Hinckley
发明人： Tracy A. Propheter-Hinckley
IPC分类号： F01D9/04 , F01D17/16
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。

62. 发明授权

US08727710B2 Mateface cooling feather seal assembly 有权
标题翻译：面板冷却羽毛密封组件
公开(公告)号：US08727710B2
公开(公告)日：2014-05-20
申请号：US13012025
申请日：2011-01-24
申请人： Tracy A. Propheter-Hinckley , Stephanie Santoro , Evan Petrakis
发明人： Tracy A. Propheter-Hinckley , Stephanie Santoro , Evan Petrakis
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。

63. 发明授权

US08672626B2 Engine assembled seal 有权
标题翻译：发动机组装密封
公开(公告)号：US08672626B2
公开(公告)日：2014-03-18
申请号：US12764212
申请日：2010-04-21
申请人： Lynn M. Boy , Tracy A. Propheter-Hinckley , Malcolm C. Staddon
发明人： Lynn M. Boy , Tracy A. Propheter-Hinckley , Malcolm C. Staddon
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。

64. 发明申请

US20130216361A1 VANE ASSEMBLY FOR A GAS TURBINE ENGINE 有权
标题翻译：用于燃气涡轮发动机的VANE组件
公开(公告)号：US20130216361A1
公开(公告)日：2013-08-22
申请号：US13401872
申请日：2012-02-22
申请人： Tracy A. Propheter-Hinckley
发明人： Tracy A. Propheter-Hinckley
IPC分类号： F01D17/16 , B23P15/00
CPC分类号： F01D17/162 , F01D9/041 , F05D2230/64 , Y10T29/49321
摘要： A vane assembly for a gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible features, a first platform, a second platform spaced from the first platform, and a first variable airfoil that extends radially across an annulus between the first platform and the second platform. One of a radial outer portion and a radial inner portion of the variable airfoil includes a rotational shaft and the other of the radial outer portion and the radial inner portion includes a ball and socket joint that rotationally connect the first variable airfoil relative to the first platform and the second platform.
摘要翻译：根据本公开的示例性实施例的用于燃气涡轮发动机的叶片组件除了其它可能的特征之外还包括第一平台，与第一平台间隔开的第二平台，以及第一可变翼型件，其径向延伸穿过第一平台和第二平台。可变翼型件的径向外部部分和径向内部部分中的一个包括旋转轴，并且径向外部部分和径向内部部分中的另一个包括球窝接头，其将第一可变翼型件相对于第一平台和第二个平台。

65. 发明授权

US08480366B2 Recessed metering standoffs for airfoil baffle 有权
标题翻译：翼形挡板的嵌入式计量支座
公开(公告)号：US08480366B2
公开(公告)日：2013-07-09
申请号：US13272784
申请日：2011-10-13
申请人： Stacy T. Malecki , Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
发明人： Stacy T. Malecki , Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2230/21 , F05D2240/126 , F05D2240/127 , F05D2250/70 , F05D2260/202
摘要： An internally cooled airfoil comprises an airfoil body, a baffle and a plurality of standoffs. The airfoil body is shaped to form leading and trailing edges, and pressure and suction sides surrounding an internal cooling channel. The baffle is disposed within the internal cooling channel and comprises a liner body having a perimeter shaped to correspond to the shape of the internal cooling channel and to form a cooling air supply duct. The baffle includes a plurality of cooling holes extending through the liner body to direct cooling air from the supply duct into the internal cooling channel. The standoffs are recessed into a surface of either the baffle or the airfoil body such that a height of the standoffs is greater than the spacing.
摘要翻译：内部冷却的翼型件包括翼型本体，挡板和多个支座。翼型体成形为形成前缘和后缘，围绕内部冷却通道的压力和吸力侧。挡板设置在内部冷却通道内，并且包括衬套主体，其具有成形为对应于内部冷却通道的形状的周边并且形成冷却空气供应管道。挡板包括多个冷却孔，其延伸穿过衬套主体，以将冷却空气从供应管道引导到内部冷却通道中。支座凹入到挡板或翼型体的表面中，使得支座的高度大于间隔。

66. 发明申请

US20130156601A1 GAS TURBINE ENGINE AIRFOIL COOLING CIRCUIT 有权
标题翻译：气体涡轮发动机空气冷却电路
公开(公告)号：US20130156601A1
公开(公告)日：2013-06-20
申请号：US13326720
申请日：2011-12-15
申请人： Tracy A. Propheter-Hinckley , Rafael A. Perez , Edward F. Pietraszkiewicz
发明人： Tracy A. Propheter-Hinckley , Rafael A. Perez , Edward F. Pietraszkiewicz
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D9/041 , F05D2240/12 , F05D2250/185 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： An airfoil for a gas turbine engine includes an airfoil body and a cooling circuit defined within the airfoil body. The cooling circuit includes at least a first cavity in fluid communication with a second cavity. A first portion of the first cavity extends between an outer diameter and an inner diameter of the airfoil body and a second portion of the first cavity extends across a space between a leading edge and a trailing edge of the airfoil body.
摘要翻译：用于燃气涡轮发动机的翼型件包括翼型体和限定在翼型体内的冷却回路。冷却回路包括至少与第二腔流体连通的第一空腔。第一空腔的第一部分在翼型件主体的外径和内径之间延伸，并且第一腔的第二部分延伸穿过机翼本体的前缘和后缘之间的空间。

67. 发明申请

US20130034434A1 VANE ASSEMBLY FOR A GAS TURBINE ENGINE 有权
标题翻译：用于燃气涡轮发动机的VANE组件
公开(公告)号：US20130034434A1
公开(公告)日：2013-02-07
申请号：US13196969
申请日：2011-08-03
申请人： Tracy A. Propheter-Hinckley
发明人： Tracy A. Propheter-Hinckley
IPC分类号： F01D9/02
CPC分类号： F01D9/042 , F05D2230/64 , F05D2240/80 , F05D2260/30 , F05D2260/31
摘要： A vane assembly for a gas turbine engine includes a first vane and a second vane. The first vane and the second vane include an inner platform, an outer platform and an airfoil that extends between the inner platform and the outer platform. The first vane and the second vane are attached at least at one of their inner platforms or their outer platforms with a first attachment mechanism and a second attachment mechanism.
摘要翻译：用于燃气涡轮发动机的叶片组件包括第一叶片和第二叶片。第一叶片和第二叶片包括在内平台和外平台之间延伸的内平台，外平台和翼型件。第一叶片和第二叶片至少在其内平台或其外平台中的一个处附接有第一附接机构和第二附接机构。

68. 发明授权

US08347945B1 Platform interconnected with mid-body core interface for molding airfoil platforms 有权
标题翻译：平台与用于成型翼型平台的中体核心界面相互连接
公开(公告)号：US08347945B1
公开(公告)日：2013-01-08
申请号：US13193956
申请日：2011-07-29
申请人： Steven Taffet , Tracy A. Propheter-Hinckley
发明人： Steven Taffet , Tracy A. Propheter-Hinckley
IPC分类号： B22C9/10
CPC分类号： F01D5/187 , B22C9/103 , F05D2230/10 , F05D2230/20 , F05D2230/50
摘要： A method of molding a platform opening includes the steps of providing a main body core and a platform core, with the main body core having a portion that forms a portion of the platform. The platform core has at least one side portion that will form a side opening. Molten metal is directed around the cores within a mold and solidifies. The cores are removed, leaving cavities where the cores were within the molten metal, and includes an opening in a side face formed by the side portion of the platform body core. Lost core components are also disclosed and claimed.
摘要翻译：模制平台开口的方法包括提供主体芯和平台芯的步骤，主体芯具有形成平台的一部分的部分。平台芯具有形成侧开口的至少一个侧部。熔融金属被引导在模具中的芯周围并固化。将芯除去，留下芯在熔融金属内的空腔，并且包括由平台本体芯的侧部形成的侧面中的开口。丢失的核心组件也被披露并要求保护。

69. 发明授权

US08308428B2 Seal assembly retention feature and assembly method 有权
标题翻译：密封组件保持特性和装配方法
公开(公告)号：US08308428B2
公开(公告)日：2012-11-13
申请号：US11869142
申请日：2007-10-09
申请人： Joseph W. Bridges, Jr. , Tracy A. Propheter-Hinckley
发明人： Joseph W. Bridges, Jr. , Tracy A. Propheter-Hinckley
IPC分类号： F01D11/00
CPC分类号： F16J15/0887 , F01D9/041 , F01D11/005 , F01D11/008 , F02C7/28 , F05D2240/80
摘要： A seal assembly includes a body having two circumferential sides, a leading end, and a trailing end. At least one of the circumferential sides includes a first channel sidewall, a second channel sidewall, and a channel bottom wall that together define a seal channel for receiving a seal. The seal channel includes a slot that cooperates with a tab on the seal to facilitate securing the seal within the seal channel.
摘要翻译：密封组件包括具有两个圆周侧的主体，前端和后端。周向侧中的至少一个包括第一通道侧壁，第二通道侧壁和通道底壁，其一起限定用于接收密封件的密封通道。密封通道包括与密封件上的突片配合的狭槽，以便将密封件固定在密封通道内。

70. 发明授权

US08206118B2 Airfoil attachment 有权
标题翻译：机翼附件
公开(公告)号：US08206118B2
公开(公告)日：2012-06-26
申请号：US11969363
申请日：2008-01-04
申请人： Tracy A. Propheter-Hinckley , Michael G. McCaffrey
发明人： Tracy A. Propheter-Hinckley , Michael G. McCaffrey
IPC分类号： F01D5/14
CPC分类号： F01D5/3007 , F01D5/3084 , F01D5/3092 , F05D2230/60 , F05D2250/10 , F05D2250/182 , F05D2250/71 , F05D2260/30 , F05D2300/10 , F05D2300/603
摘要： A rotor blade for a gas turbine engine includes an airfoil that extends in span between a tip and a root opposite from the tip. The root includes a plug, a looped portion that surrounds the plug and a clamp. The clamp contacts only a portion of the looped portion on an opposite side of the looped portion from the plug.
摘要翻译：用于燃气涡轮发动机的转子叶片包括在尖端和与尖端相对的根部之间跨度延伸的翼型件。根部包括塞子，围绕塞子和夹具的环形部分。夹具仅接触环形部分的与插塞相对的一侧上的环形部分的一部分。

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