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41. 发明申请

US20090257875A1 PLATFORMLESS TURBINE BLADE 有权
标题翻译：平板式涡轮叶片
公开(公告)号：US20090257875A1
公开(公告)日：2009-10-15
申请号：US12101326
申请日：2008-04-11
申请人： Michael G. McCaffrey , Eric A. Hudson
发明人： Michael G. McCaffrey , Eric A. Hudson
IPC分类号： F01D5/22 , F01D5/14 , F01D5/18 , F01D5/02
CPC分类号： F01D5/3015 , F01D11/008 , F05D2240/80
摘要： A turbine blade rotor assembly is disclosed for a gas turbine engine. The assembly includes a rotor having nickel alloy turbine blades secured thereto. Each of the blades includes a root and an airfoil. The roots are supported by the rotor. A ceramic matrix composite platform separate from the turbine blades is supported between each pair of the turbine blades adjacent to the airfoils. In another example, the airfoil includes a perimeter. A shroud having an aperture receives the airfoil with a single shroud substantially surrounding the airfoil at the perimeter. In one example, the turbine blade includes high and low pressure sides opposite one another that extend from a tip to a root. The airfoil is free from any protrusions extending from the high and low pressure sides on a portion of the blade axially outward from the root.
摘要翻译：公开了一种用于燃气涡轮发动机的涡轮叶片转子组件。组件包括具有固定在其上的镍合金涡轮叶片的转子。每个叶片包括根部和翼型件。根部由转子支撑。与涡轮机叶片分离的陶瓷基体复合平台被支撑在与翼型件相邻的每对涡轮机叶片之间。在另一示例中，翼型件包括周边。具有孔径的护罩接收具有在周边基本上围绕翼型件的单个护罩的翼型件。在一个示例中，涡轮机叶片包括从尖端延伸到根部的彼此相对的高压和低压侧。叶片从根部的轴向向外的叶片的一部分上的高压侧和低压侧延伸的任何突起都没有。

42. 发明授权

US09574455B2 Blade outer air seal with cooling features 有权
标题翻译：叶片外部空气密封具有冷却功能
公开(公告)号：US09574455B2
公开(公告)日：2017-02-21
申请号：US13549874
申请日：2012-07-16
申请人： Michael G. McCaffrey
发明人： Michael G. McCaffrey
IPC分类号： F01D11/12 , F01D11/24 , F01D25/12
CPC分类号： F01D11/127 , F01D11/12 , F01D11/24 , F01D25/12 , F05D2260/22141 , Y10T29/49245
摘要： A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. At least one cooling fin is disposed on the radially outer face between the leading edge portion and the trailing edge portion.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的叶片外部空气密封件（BOAS）包括其中包括径向内表面和径向外表面的密封体，所述径向内表面和径向外表面在前缘部分和后缘部分。至少一个冷却翅片设置在前缘部分和后缘部分之间的径向外表面上。

43. 发明申请

US20160084101A1 GAS TURBINE ENGINE BLADE OUTER AIR SEAL ASSEMBLY 审中-公开
标题翻译：气体涡轮发动机叶片外部空气密封组件
公开(公告)号：US20160084101A1
公开(公告)日：2016-03-24
申请号：US14834918
申请日：2015-08-25
申请人： Michael G. McCaffrey
发明人： Michael G. McCaffrey
IPC分类号： F01D11/08 , F01D5/12 , F01D5/02
CPC分类号： F01D11/08 , F01D5/02 , F01D5/12 , F01D5/225 , F01D11/12 , F01D11/14 , F01D11/22 , F05D2220/32 , F05D2240/24 , F05D2240/55 , F05D2260/97
摘要： A gas turbine engine includes a rotating stage of blades. A circumferential array of blade outer air seal segments are arranged radially outward of the blades. Adjacent blade outer air seal segments provide a circumferential gap. Facing ends of the adjacent blade outer air seal segments include surfaces. A gap seal engages the surfaces and obstructs the circumferential gap. A biasing member is configured to urge the gap seal radially inward toward the surfaces.
摘要翻译：燃气涡轮发动机包括叶片的旋转级。叶片外部空气密封段的圆周阵列布置在叶片的径向外侧。相邻的叶片外部空气密封段提供周向间隙。相邻叶片外部空气密封段的面对端部包括表面。间隙密封件接合表面并阻碍周向间隙。偏置构件被构造成朝向表面径向向内推动间隙密封件。

44. 发明授权

US09133726B2 Seal for gas turbine engine component 有权
标题翻译：燃气轮机组件密封
公开(公告)号：US09133726B2
公开(公告)日：2015-09-15
申请号：US11856132
申请日：2007-09-17
申请人： Michael G. McCaffrey , Eric A. Hudson
发明人： Michael G. McCaffrey , Eric A. Hudson
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F01D9/065 , F01D17/162 , Y02T50/672
摘要： A gas turbine engine component includes a pressurized fluid source, an airfoil, and a seal member for selectively providing sealing at an end of the airfoil. The seal member includes a stowed position for non-sealing and a deployed position for sealing. The seal member is operatively connected with a pressurized fluid source for moving the seal member between the stowed position and the deployed position.
摘要翻译：燃气涡轮发动机部件包括加压流体源，翼型件和用于在翼型的端部选择性地提供密封的密封构件。密封构件包括用于非密封的收起位置和用于密封的展开位置。密封构件与加压流体源可操作地连接，用于使密封构件在收起位置和展开位置之间移动。

45. 发明授权

US08943796B2 Variable cycle turbine engine 有权
标题翻译：可变循环涡轮发动机
公开(公告)号：US08943796B2
公开(公告)日：2015-02-03
申请号：US13170502
申请日：2011-06-28
申请人： Michael G. McCaffrey
发明人： Michael G. McCaffrey
IPC分类号： F02C3/10 , F01D13/00 , F01D17/16
CPC分类号： F01D13/003 , F01D17/162 , Y02T50/671
摘要： A gas turbine engine comprises a high spool, a low spool and an intermediate spool. The high spool comprises a high pressure turbine coupled to a high pressure compressor. The intermediate spool comprises an intermediate pressure turbine coupled to a ducted fan. The low spool comprises a low pressure turbine coupled to an open-rotor propeller. A variable area turbine section positioned between the intermediate pressure turbine and the low pressure turbine variable turbine section is configured to vary an expansion ratio across the intermediate pressure turbine to control rotational speeds of the low spool and the intermediate spool.
摘要翻译：燃气涡轮发动机包括高阀芯，低阀芯和中间阀芯。高阀芯包括联接到高压压缩机的高压涡轮机。中间阀芯包括联接到管道风扇的中间压力涡轮机。低阀芯包括联接到开式转子螺旋桨的低压涡轮机。位于中压涡轮机和低压涡轮机可变涡轮机部分之间的可变区域涡轮机部分构造成改变跨过中压涡轮机的膨胀比，以控制低滑阀和中间滑阀的转速。

46. 发明申请

US20130142660A1 CERAMIC MATRIX COMPOSITE AIRFOIL STRUCTURE WITH TRAILING EDGE SUPPORT FOR A GAS TURBINE ENGINE 有权
标题翻译：陶瓷基体复合材料结构与气体涡轮发动机的边缘支撑
公开(公告)号：US20130142660A1
公开(公告)日：2013-06-06
申请号：US13309514
申请日：2011-12-01
申请人： Michael G. McCaffrey
发明人： Michael G. McCaffrey
IPC分类号： F01D5/14 , B23P15/02
CPC分类号： F01D5/18 , F01D5/147 , F01D5/284 , F05D2240/122 , F05D2300/603 , Y10T29/49336
摘要： An airfoil for a gas turbine engine includes an aft trailing edge support between a pressure side and a suction side.
摘要翻译：用于燃气涡轮发动机的翼型件包括在压力侧和吸力侧之间的后尾缘支撑件。

47. 发明申请

US20100290898A1 KNIFE EDGE SEAL ASSEMBLY 有权
标题翻译：刀刃密封组件
公开(公告)号：US20100290898A1
公开(公告)日：2010-11-18
申请号：US12466978
申请日：2009-05-15
申请人： Michael G. McCaffrey
发明人： Michael G. McCaffrey
IPC分类号： F01D11/00 , F16J15/44
CPC分类号： F01D11/001 , F01D11/02 , F05D2260/22141
摘要： A seal assembly for a gas turbine engine is provided that includes a seal support member, at least one knife edge seal blade member, and at least one cooling member. The seal support member is configured for rotation within the gas turbine engine around an axial centerline of the engine. The support member has a thickness extending between a first surface and a second surface. The blade member extends outwardly from the first surface of the support member. The blade member has a central portion that extends between a base end and a distal knife edge end. The base end is attached to the first surface of the seal support member. The cooling member extends outwardly from the second surface, and is oppositely aligned with the blade member.
摘要翻译：提供了一种用于燃气涡轮发动机的密封组件，其包括密封支撑构件，至少一个刀刃密封叶片构件和至少一个冷却构件。密封支撑构件被构造成围绕发动机的轴向中心线在燃气涡轮发动机内旋转。支撑构件具有在第一表面和第二表面之间延伸的厚度。刀片构件从支撑构件的第一表面向外延伸。叶片构件具有在基端和远端刀刃端之间延伸的中心部分。基端附接到密封支撑构件的第一表面。冷却构件从第二表面向外延伸并且与叶片构件相对地对准。

48. 发明授权

US07779540B2 Apparatus and method for quadrail ergonomic assembly 有权
标题翻译：用于四边形人体工程学组装的装置和方法
公开(公告)号：US07779540B2
公开(公告)日：2010-08-24
申请号：US11203026
申请日：2005-08-12
申请人： Michael G. McCaffrey , Robert P. Rojas , Mark F. Zelesky , Gilbert B. Cutler , Gene V. Flenke
发明人： Michael G. McCaffrey , Robert P. Rojas , Mark F. Zelesky , Gilbert B. Cutler , Gene V. Flenke
IPC分类号： B23Q7/00 , B66C17/00
CPC分类号： F01D25/28 , B66C11/04 , B66C11/12 , F01D25/285 , F05D2230/68 , Y02T50/671 , Y10T29/4932 , Y10T29/49828 , Y10T29/49895 , Y10T29/49998 , Y10T29/53435 , Y10T29/53539 , Y10T29/53543 , Y10T29/53548
摘要： A quadrail ergonomic apparatus includes two or more pathways designed to permit movement in two or more directions mounted to a static object above a surface. One or more carriages designed to move in two or more directions are disposed within the pathways. Each carriage is suspended above the surface from the pathways and capable of maintaining a workload in place and permitting movement of the workload in at least four directions.
摘要翻译：四边形人体工程学装置包括设计成允许在安装到表面上方的静态物体的两个或更多个方向上移动的两个或更多个路径。设计成沿两个或更多个方向移动的一个或多个托架设置在通道内。每个车厢从路径悬挂在地面上方，并能够将工作量保持在原位，并允许工作量在至少四个方向上移动。

49. 发明授权

US07637709B2 Safety interlock system for mechanical manipulators 有权
标题翻译：机械操纵器的安全联锁系统
公开(公告)号：US07637709B2
公开(公告)日：2009-12-29
申请号：US11484264
申请日：2006-07-11
申请人： Michael G. McCaffrey
发明人： Michael G. McCaffrey
IPC分类号： B66F9/00
CPC分类号： B25J9/1065 , B25J19/0004 , B66C15/00 , B66C23/005 , Y10T403/599 , Y10T403/602
摘要： A safety interlock system including a rotatable lever operably connected to a lift component and to a load supporting component of a mechanical manipulator, where the rotatable lever is biased in a first rotational direction, and is configured to rotate in an opposite rotational direction in response to a lifting force applied by the lift component. The safety interlock system also includes a locking component configured to engage a support frame of the mechanical manipulator based on a rotational position of the rotatable lever.
摘要翻译：一种安全互锁系统，包括可操作地连接到提升部件和机械操纵器的负载支撑部件的旋转杆，其中所述可旋转杆在第一旋转方向上被偏置，并且构造成响应于由提升部件施加的提升力。安全联锁系统还包括锁定部件，其构造成基于可旋转杆的旋转位置接合机械操纵器的支撑框架。

50. 发明申请

US20090142181A1 Gas Turbine Engine Systems Involving Mechanically Alterable Vane Throat Areas 有权
标题翻译：燃气轮机发动机系统涉及机械可变叶片喉区
公开(公告)号：US20090142181A1
公开(公告)日：2009-06-04
申请号：US11947160
申请日：2007-11-29
申请人： Michael G. McCaffrey , Shankar S. Magge , Joel H. Wagner , Daniel R. Sabatino , Joseph Clayton Burge
发明人： Michael G. McCaffrey , Shankar S. Magge , Joel H. Wagner , Daniel R. Sabatino , Joseph Clayton Burge
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D9/02 , F05D2270/17
摘要： Gas turbine engine systems involving mechanically alterable vane throat areas are provided. In this regard, a representative vane for a gas turbine engine includes: a leading edge; a trailing edge; a suction side surface extending between the leading edge and the trailing edge; a cavity having an aperture located in the suction side surface; and a barrel located within the cavity and being moveable therein such that movement of the barrel alters an extent to which the barrel protrudes through the aperture.
摘要翻译：提供涉及可机械地改变的叶片喉部区域的燃气涡轮发动机系统。在这方面，用于燃气涡轮发动机的代表性叶片包括：前缘; 后缘吸引侧表面，其在前缘和后缘之间延伸; 空腔，其具有位于所述吸力侧表面中的孔; 以及位于腔体内且可在其中移动的筒体，使得筒体的移动改变了筒体穿过该孔突出的程度。

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