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1. 发明授权

US09169780B2 Connection for generator in a gas turbine engine 有权
标题翻译：燃气轮机发电机连接
公开(公告)号：US09169780B2
公开(公告)日：2015-10-27
申请号：US13183848
申请日：2011-07-15
申请人： Barry Barnett , Daniel Alecu , Andreas Eleftheriou
发明人： Barry Barnett , Daniel Alecu , Andreas Eleftheriou
IPC分类号： F02C7/06 , F02C7/32 , F02C7/36
CPC分类号： F02C7/06 , F02C7/32 , F02C7/36 , F05D2260/202
摘要： A gas turbine engine having an electric generator includes a transmission shaft extending along a longitudinal axis of the engine and drivingly interconnecting a turbine shaft of the engine and a rotor shaft of the electric generator. The transmission shaft is engaged by splined mating connections with the turbine shaft and the rotor shaft. The transmission shaft has a shear neck defining a reduced radial wall thickness with respect to a remainder of the transmission shaft such as to provide a weakened region of the transmission shaft. An annular support structure, concentric with and surrounding the transmission shaft, is axially located between the shear neck and a forward end of the transmission shaft engaged to the turbine shaft, and includes a bearing operable to rotationally support the transmission shaft.
摘要翻译：具有发电机的燃气涡轮发动机包括：沿着发动机的纵轴延伸的传动轴，并将发动机的涡轮轴与发电机的转子轴驱动连接。传动轴通过与涡轮轴和转子轴的花键配合连接接合。传动轴具有剪切颈部，其相对于传动轴的其余部分限定径向壁厚度减小，以便提供传动轴的弱化区域。与传动轴同心并且围绕传动轴的环形支撑结构轴向地位于剪切颈部和接合到涡轮轴的传动轴的前端之间，并且包括可操作以可旋转地支撑传动轴的轴承。

2. 发明授权

US09169730B2 Fan hub design 有权
标题翻译：风扇轮毂设计
公开(公告)号：US09169730B2
公开(公告)日：2015-10-27
申请号：US13297300
申请日：2011-11-16
申请人： Barry Barnett
发明人： Barry Barnett
IPC分类号： F01D5/14 , F02K3/06
CPC分类号： F01D5/30 , F01D5/02 , F01D5/14 , F02K3/06 , F05D2220/32 , F05D2240/20 , F05D2260/941
摘要： A fan rotor has a fan web and a plurality of circumferentially spaced-apart fan blades extending radially outwardly from an outer rim of the fan web. The outer rim is integrally connected to an inner rim through an axially facing web section. The web section has an inward concavature and extends aft of the center of gravity of the fan blades to shift the center of gravity of the hub rearwards while maintaining airfoil stress below critical levels. The rim section may have an inwardly projecting annular channel formed in a leading edge thereof and tuned to the 2M3ND mode of the fan hub.
摘要翻译：风扇转子具有风扇腹板和从风扇腹板的外缘径向向外延伸的多个周向间隔开的风扇叶片。外缘通过轴向面对的腹板部分整体连接到内缘。腹板部分具有向内的凹陷并且延伸到风扇叶片的重心的后方，以使桨毂的重心向后移动，同时保持翼型压力低于临界水平。边缘部分可以具有形成在其前缘中的向内突出的环形通道并且被调谐到风扇轮毂的2M3ND模式。

3. 发明申请

US20120082559A1 AIRFOIL BLADE 有权
标题翻译： AIRFOIL刀片
公开(公告)号：US20120082559A1
公开(公告)日：2012-04-05
申请号：US13189118
申请日：2011-07-22
申请人： George Guglielmin , Joe Lanzino , Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Thomas McDonough
发明人： George Guglielmin , Joe Lanzino , Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Thomas McDonough
IPC分类号： F01D5/14 , B23P15/02
CPC分类号： F04D29/388 , B22F2998/00 , B82Y30/00 , C23C4/01 , C23C30/00 , F01D5/147 , F01D5/282 , F01D5/288 , F01D9/041 , F01D25/162 , F04D29/023 , F04D29/325 , Y02T50/672 , Y02T50/673 , Y10T29/49336 , C22C1/08
摘要： A fan blade of a gas turbine engine, and a method of producing same, is disclosed which is composed of a core substrate and a nanocrystalline metal coating provided on at least a portion of the airfoil of the fan blade. The method includes the steps of providing a fan blade core having an airfoil and then applying a nanocrystalline metal coating over at least a portion of the fan blade core.
摘要翻译：公开了一种燃气涡轮发动机的风扇叶片及其制造方法，其由芯基板和设置在风扇叶片的翼型的至少一部分上的纳米晶体金属涂层构成。该方法包括以下步骤：提供具有翼型件的风扇叶片芯，然后在风扇叶片芯的至少一部分上施加纳米晶体金属涂层。

4. 发明授权

US07494316B2 Foreign object damage resistant vane assembly 有权
标题翻译：异物损坏叶片组件
公开(公告)号：US07494316B2
公开(公告)日：2009-02-24
申请号：US11468036
申请日：2006-08-29
申请人： Barry Barnett , David Denis
发明人： Barry Barnett , David Denis
IPC分类号： F03B11/02
CPC分类号： F01D9/042 , F02C7/05 , F05D2260/30
摘要： A vane including a root, a tip and an airfoil portion extending between the root and the tip, the vane also including a button portion interconnecting the airfoil portion and the root. The button portion protrudes beyond a profile of the airfoil a distance less than the root. The button portion includes leading and trailing ends free of sharp edges. The leading and trailing ends respectively protrude beyond leading and trailing edges of the airfoil portion.
摘要翻译：叶片包括根部，尖端和在根部和尖端之间延伸的翼型部分，叶片还包括将翼型部分和根部相互连接的按钮部分。按钮部分突出超过翼型的轮廓，其距离小于根部。按钮部分包括没有锋利边缘的前端和后端。前端和尾端分别突出超过翼型部分的前缘和后缘。

5. 发明申请

US20080086880A1 ANNULAR GAS TURBINE ENGINE CASE AND METHOD OF MANUFACTURING 有权
标题翻译：环形气体涡轮发动机及其制造方法
公开(公告)号：US20080086880A1
公开(公告)日：2008-04-17
申请号：US11537884
申请日：2006-10-02
申请人： Barry Barnett , Steven Hunt , Czeslaw Wojtyczka
发明人： Barry Barnett , Steven Hunt , Czeslaw Wojtyczka
IPC分类号： B23P15/04
CPC分类号： F01D25/24 , F05D2230/232 , F05D2230/26 , F05D2240/14 , F05D2250/231 , F05D2250/232 , Y02T50/671 , Y10T29/4932
摘要： The method is used for making an annular gas turbine engine case from a preform. The method comprises comprising flowforming at least one section of the preform, and then outwardly bending at least one portion of the perform.
摘要翻译：该方法用于从预制件制造环形燃气涡轮发动机壳体。该方法包括流动成形预成型件的至少一个部分，然后向外弯曲该部件的至少一部分。

6. 发明授权

US09429029B2 Gas turbine blade and method of protecting same 有权
标题翻译：燃气轮机叶片及其保护方法
公开(公告)号：US09429029B2
公开(公告)日：2016-08-30
申请号：US13189043
申请日：2011-07-22
申请人： Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Tom McDonough , George Guglielmin , Joe Lanzino
发明人： Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Tom McDonough , George Guglielmin , Joe Lanzino
IPC分类号： F03B3/12 , F01D5/30
CPC分类号： F01D5/3092 , F01D5/005 , F01D5/28 , F05B2230/90 , F05D2220/32 , F05D2230/80 , F05D2230/90 , F05D2260/94 , F05D2300/11 , F05D2300/121 , F05D2300/13 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/134 , F05D2300/143 , F05D2300/16 , F05D2300/1614 , F05D2300/1616 , F05D2300/609
摘要： An airfoil blade of a gas turbine engine includes a root configured for mating attachment with a cooperating rotor hub and an airfoil extending away from the root. The root is composed of a first metal and has a nanocrystalline metal coating, composed of a second metal, over at least a portion thereof. A method of protecting such a blade by applying a nanocrystalline metal coating to a portion of the blade root is also disclosed.
摘要翻译：燃气涡轮发动机的翼型叶片包括配置成与配合的转子毂配合连接的根部以及远离根部延伸的翼型件。根由第一金属组成，并且在其至少一部分上具有由第二金属组成的纳米晶体金属涂层。还公开了通过将纳米晶体金属涂层施加到叶片根部的一部分来保护这种叶片的方法。

7. 发明申请

US20140116061A1 COUPLING ELEMENT FOR TORQUE TRANSMISSION IN A GAS TURBINE ENGINE 有权
标题翻译：燃气轮机发动机扭矩传递的耦合元件
公开(公告)号：US20140116061A1
公开(公告)日：2014-05-01
申请号：US13660039
申请日：2012-10-25
申请人： Barry BARNETT , Phillipe BONNIERE , Daniel ALECU
发明人： Barry BARNETT , Phillipe BONNIERE , Daniel ALECU
IPC分类号： F16D3/80 , F02C7/12
CPC分类号： F16D1/101 , F01D5/026 , F05D2260/20 , F16D2001/103 , Y02T50/675 , Y10T403/25 , Y10T464/10
摘要： A gas turbine engine having a coupling element for coupling a first shaft to a second shaft, the second shaft being substantially axially aligned with the first shaft, the coupling element provided with an exterior surface that engages an opposing interior surface of the first shaft and an interior surface that engages an opposing exterior surface of the second shaft to facilitate torque transfer between the first shaft and the second shaft when rotated together, wherein the coupling element and at least one of the first and second shafts cooperate to define at least one fluid passageway therebetween.
摘要翻译：一种燃气涡轮发动机，其具有用于将第一轴联接到第二轴的联接元件，所述第二轴与所述第一轴基本上轴向对齐，所述联接元件设置有与所述第一轴的相对的内表面接合的外表面，内表面，其接合所述第二轴的相对的外表面，以便当一起旋转时促进在所述第一轴和所述第二轴之间的扭矩传递，其中所述联接元件和所述第一和第二轴中的至少一个协作以限定至少一个流体通道之间。

8. 发明授权

US08708656B2 Blade fixing design for protecting against low speed rotation induced wear 有权
标题翻译：刀片固定设计，用于防止低速旋转引起的磨损
公开(公告)号：US08708656B2
公开(公告)日：2014-04-29
申请号：US12786902
申请日：2010-05-25
申请人： Barry Barnett , Philippe Bonniere
发明人： Barry Barnett , Philippe Bonniere
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F05D2260/30
摘要： The blade dovetails and associated dovetail slots of a gas turbine engine rotor assembly are shaped so that during windmilling the high stress regions of the blade dovetails are shielded from rubbing against the disk and vice versa. Bumper surfaces are provided in low stress regions of the dovetail assembly such that the windmilling contact points between the blade dovetails and the disk are in non-critical areas of the dovetail assembly.
摘要翻译：燃气涡轮发动机转子组件的叶片燕尾榫和相关联的燕尾槽成形为使得在风车期间，叶片燕尾榫的高应力区域被遮蔽而不与盘摩擦，反之亦然。缓冲表面设置在燕尾组件的低应力区域中，使得叶片燕尾榫和盘之间的风向接触点位于燕尾组件的非关键区域。

9. 发明申请

US20130255277A1 GAS TURBINE ENGINE NOSE CONE 审中-公开
标题翻译：燃气涡轮发动机油
公开(公告)号：US20130255277A1
公开(公告)日：2013-10-03
申请号：US13435738
申请日：2012-03-30
申请人： Enzo Macchia , Andreas Eleftheriou , Thomas Peter McDonough , George Guglielmin , Joe Lanzino , Barry Barnett
发明人： Enzo Macchia , Andreas Eleftheriou , Thomas Peter McDonough , George Guglielmin , Joe Lanzino , Barry Barnett
IPC分类号： F02C7/00 , F02C3/04 , B05D1/18 , F01D25/00
CPC分类号： F02C7/04 , F05D2250/232 , F05D2300/605 , F05D2300/608 , F05D2300/612
摘要： A nose cone for a turbofan gas turbine engine includes a central tip, an outer perimeter and a substantially conical outer wall extending therebetween which encloses a cavity therewithin. The outer wall includes an inner substrate layer facing the cavity and an outer layer which overlies and at least partially encloses the inner substrate layer. The outer layer is composed entirely of a nanocrystalline metal forming an outer surface of the nose cone.
摘要翻译：用于涡轮风扇燃气涡轮发动机的鼻锥包括中心尖端，外周边和在其间延伸的基本上圆锥形的外壁，其在其中封闭空腔。外壁包括面向空腔的内部基底层和覆盖并至少部分地包围内部基底层的外层。外层完全由形成鼻锥外表面的纳米晶体金属构成。

10. 发明申请

US20130133336A1 SUPPORT FOR ELECTRIC MACHINE IN A TURBINE ENGINE 有权
标题翻译：涡轮发动机电机支持
公开(公告)号：US20130133336A1
公开(公告)日：2013-05-30
申请号：US13304960
申请日：2011-11-28
申请人： Barry Barnett , David Denis
发明人： Barry Barnett , David Denis
IPC分类号： F02C6/00 , F16M13/02 , B23P11/00
CPC分类号： F01D25/164 , F01D15/10 , F01D25/04 , F02C7/20 , F02C7/32 , F05D2220/76 , Y02T50/671 , Y10T29/49009
摘要： Devices and methods for supporting an accessory (32) in a gas turbine engine (10) are disclosed. The accessory (32) may have an interface (36) for coupling to a shaft (24) of the gas turbine engine (10). The device may comprise a first support (38) configured to support a first portion (34) of the accessory (32) proximal the interface (36) and a second support (40) configured to support a second portion (35) of the accessory (32) distal from the interface (36). The second support (40) may be configured to provide a lower resistance to relative displacement between the accessory (32) and structure (42) of the engine (10) than does the first support (34).
摘要翻译：公开了一种在燃气涡轮发动机（10）中支撑附件（32）的装置和方法。附件（32）可以具有用于联接到燃气涡轮发动机（10）的轴（24）的接口（36）。该装置可以包括构造成支撑靠近接口（36）的附件（32）的第一部分（34）的第一支撑件（38）和构造成支撑附件的第二部分（35）的第二支撑件（40）（32）远离界面（36）。第二支撑件（40）可以构造成比第一支撑件（34）提供对发动机（10）的附件（32）和结构（42）之间的相对位移的较低阻力。

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