公开(公告)号：US20120082783A1

公开(公告)日：2012-04-05

申请号：US13188938

申请日：2011-07-22

Applicant: Barry Barnett ,  Kin-Leung Cheung ,  Thomas McDonough ,  Andreas Eleftheriou ,  Enzo Macchia

Inventor： Barry Barnett ,  Kin-Leung Cheung ,  Thomas McDonough ,  Andreas Eleftheriou ,  Enzo Macchia

IPC: B05D5/00 ,  B05D1/36 ,  B05D7/14 ,  B82Y40/00

CPC classification number: B05D3/102 ,  B05D1/36 ,  B22F1/0018 ,  B82Y30/00 ,  C23C18/1637 ,  C23C18/1651 ,  C23C28/023 ,  C23C30/00 ,  F01D5/288 ,  F01D5/3092 ,  F05D2300/172

Abstract: A method of applying a nanocrystalline coating to a gas turbine engine component is described. The method comprises the steps of applying an intermediate bond coat to at least a portion of the component, and then applying the nanocrystalline coating to at least the portion of the component overtop of the intermediate bond coat. The component may include, for example, a blade of which a dovetail portion of the blade root is protected by applying the intermediate bond coat and the nanocrystalline coating thereto.

Abstract translation: 描述了将纳米晶体涂层应用于燃气涡轮发动机部件的方法。 该方法包括以下步骤：将中间粘合涂层施加到部件的至少一部分，然后将纳米晶体涂层施加到中间粘结涂层顶部的至少部分部分。 组件可以包括例如通过将中间粘合涂层和纳米晶体涂层施加到其上来保护叶片根部的燕尾部分的叶片。

公开(公告)号：US20110293429A1

公开(公告)日：2011-12-01

申请号：US12786902

申请日：2010-05-25

Applicant: Barry Barnett ,  Philippe Bonniere

Inventor： Barry Barnett ,  Philippe Bonniere

IPC: F01D5/30

CPC classification number: F01D5/3007 ,  F05D2260/30

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US07637718B2

公开(公告)日：2009-12-29

申请号：US11467406

申请日：2006-08-25

Applicant: Barry Barnett ,  David Denis

Inventor： Barry Barnett ,  David Denis

IPC: F01D5/10

CPC classification number: F01D9/042 ,  F02C7/05 ,  F05D2250/70 ,  F05D2260/30 ,  F05D2300/222 ,  F05D2300/43 ,  F05D2300/431

Abstract: A compressor vane having a root, a tip and an airfoil portion extending between the root and the tip is disclosed. A grommet is used in conjunction with the vane and has a lip sealingly surrounding a portion of the vane root and a circumferential portion protruding around a perimeter of the lip in engagement with a surface of a platform of the vane root. The circumferential portion has a profile similar to that of the airfoil portion.

Abstract translation: 公开了一种具有根，尖端和在根部和尖端之间延伸的翼型部分的压缩机叶片。 索环与叶片一起使用，并且具有密封地围绕叶片根部的一部分的唇缘和围绕唇缘的周边突出地与叶根的平台的表面接合的周向部分。 圆周部分具有类似于翼型部分的轮廓。

公开(公告)号：US20080063517A1

公开(公告)日：2008-03-13

申请号：US11516600

申请日：2006-09-07

Applicant: Barry Barnett

Inventor： Barry Barnett

IPC: F01D11/00

CPC classification number: F02K3/06 ,  F01D25/32 ,  F05D2240/14 ,  F05D2260/602 ,  Y02T50/672

Abstract: A fan case for a gas turbine engine is provided to prevent water from pooling and freezing inside the fan case when the gas turbine is not in operation, and potentially prevent the engine from starting and/or cause engine damage. The fan case is therefore adapted to provide a drainage system allowing water to freely escape the fan case without compromising the structural integrity of the fan case. The fan case comprises: a hollow body; an abradable liner disposed inside the hollow body; a flange on the hollow body defining a surface for mating to a forward part of the engine; and, a first radial slot extending across the mating surface of the hollow body. The abradable liner has an inside surface for circumscribing the fan blades wherein the first radial slot is in a free-draining relation with the inside surface of the abradable liner.

Abstract translation: 提供一种用于燃气涡轮发动机的风扇箱，用于当燃气轮机不运行时防止水在风扇壳内积聚和冻结，并且可能防止发动机起动和/或引起发动机损坏。 因此，风扇壳体适于提供排水系统，其允许水自由地逸出风扇壳体而不损害风扇壳体的结构完整性。 风扇壳体包括：中空体; 布置在中空体内的可磨损衬垫; 空心体上的凸缘限定用于与发动机前部配合的表面; 以及横跨所述中空体的配合表面延伸的第一径向槽。 可磨损衬垫具有用于外接风扇叶片的内表面，其中第一径向槽与耐磨衬垫的内表面处于自由排水关系。

公开(公告)号：US07303377B2

公开(公告)日：2007-12-04

申请号：US10823591

申请日：2004-04-14

Applicant: Sean André Rockarts ,  Barry Barnett

Inventor： Sean André Rockarts ,  Barry Barnett

IPC: F01D5/10

CPC classification number: F02K3/04 ,  F01D5/027 ,  F16F15/34 ,  G01M1/32 ,  Y02T50/671

Abstract: An apparatus for balancing a shaft of an aircraft engine preferably includes a plate and the use of standard fasteners. The plate provides mounting for a nose cone, and the balancing apparatus may be accessed from the front of the assembled engine.

Abstract translation: 用于平衡飞机发动机的轴的装置优选地包括板和标准紧固件的使用。 该板提供用于鼻锥的安装，并且平衡装置可以从组装的发动机的前部进入。

公开(公告)号：US20070239989A1

公开(公告)日：2007-10-11

申请号：US11277653

申请日：2006-03-28

Applicant: Barry Barnett ,  Daniel Eisenhauer ,  Matthew Landt

Inventor： Barry Barnett ,  Daniel Eisenhauer ,  Matthew Landt

IPC: H04L9/00

CPC classification number: H04L67/1097 ,  H04L63/101

Abstract: A computer-implemented method, apparatus, and computer program product are disclosed for securing node port access in a switched-fabric storage area network. Permitted combinations of fabric port identifiers and node port identifiers are specified. A node port receives a request to access the node port. A node port identifier, which identifies the device that is attempting to access the node port, is determined from the request. A fabric port identifier is determined that identifies a fabric port through which the device transmitted the request. Access to the node port is granted if the fabric port identifier and node port identifier form a permitted combination.

Abstract translation: 公开了一种计算机实现的方法，装置和计算机程序产品，用于保护交换式结构存储区域网络中的节点端口访问。 指定了Fabric端口标识符和节点端口标识符的允许组合。 节点端口接收到访问节点端口的请求。 根据请求确定标识尝试访问节点端口的设备的节点端口标识符。 确定结构端口标识符，其标识设备通过其发送请求的结构端口。 如果结构端口标识符和节点端口标识符形成允许的组合，则允许访问节点端口。

公开(公告)号：US20070059169A1

公开(公告)日：2007-03-15

申请号：US11468036

申请日：2006-08-29

Applicant: Barry Barnett ,  David Denis

Inventor： Barry Barnett ,  David Denis

IPC: F03B11/02

CPC classification number: F01D9/042 ,  F02C7/05 ,  F05D2260/30

Abstract: A vane assembly for a gas turbine engine including a shroud with openings defined therein about a circumference thereof and vanes extending radially from the shroud with a vane tip in each opening. Isolating means are disposed in each opening to isolate the vane tip from the shroud ring. Each vane tip is engaged with the shroud by retaining means for restricting movement of the vane tip in an axial direction relative to said shroud.

Abstract translation: 一种用于燃气涡轮发动机的叶片组件，其包括围绕其周围限定的开口的护罩和在每个开口中具有叶片从护罩径向延伸的叶片。 隔离装置设置在每个开口中以将叶片尖端与护罩环隔离。 每个叶片尖端通过用于限制叶片尖端在相对于所述护罩的轴向上的运动的保持装置与护罩接合。

公开(公告)号：US20050231052A1

公开(公告)日：2005-10-20

申请号：US10823591

申请日：2004-04-14

Applicant: Sean Rockarts ,  Barry Barnett

Inventor： Sean Rockarts ,  Barry Barnett

IPC: F01D5/02 ,  F02C7/20 ,  F16F15/22 ,  F16F15/32 ,  F16F15/34 ,  G01M1/32 ,  H02K5/16 ,  H02K7/08

CPC classification number: F02K3/04 ,  F01D5/027 ,  F16F15/34 ,  G01M1/32 ,  Y02T50/671

Abstract: An apparatus for balancing a shaft of an aircraft engine preferably includes a plate and the use of standard fasteners. The plate provides mounting for nose cone, and the balancing apparatus may be accessed from the front of the assembled engine.

Abstract translation: 用于平衡飞机发动机的轴的装置优选地包括板和标准紧固件的使用。 该板提供鼻锥的安装，并且平衡装置可以从组装的发动机的前部进入。

公开(公告)号：US09097134B2

公开(公告)日：2015-08-04

申请号：US13616230

申请日：2012-09-14

Applicant: Gordon Ferch ,  Daniel Alecu ,  Xiaoliu Liu ,  Barry Barnett ,  Dileepan Sivalingam ,  Carmine Forgione

Inventor： Gordon Ferch ,  Daniel Alecu ,  Xiaoliu Liu ,  Barry Barnett ,  Dileepan Sivalingam ,  Carmine Forgione

IPC: F02C7/12 ,  F01D15/10

CPC classification number: F01D15/10 ,  F02C7/12 ,  Y02T50/671 ,  Y02T50/675

Abstract: A system for cooling a generator mounted in the tail-cone of an engine. The system comprises a fairing, which receives through an inlet thereof air from a bypass duct and directs the bypass air towards a cavity of the tail-cone for cooling the generator. The bypass air is then expelled through an outlet of a support strut positioned in fluid communication with the tail-cone cavity. The fairing inlet and the strut outlet are both positioned in a plane substantially perpendicular to a longitudinal plane of the engine. In this manner, circulation of the bypass air through the fairing, the tail-cone cavity, and the strut may be achieved. The bypass air directed through the fairing further enables cooling of service lines accommodated in the fairing. A lobe mixer is further used to direct the fairing and shield the latter from core exhaust.

Abstract translation: 一种用于冷却安装在发动机尾锥中的发电机的系统。 该系统包括整流罩，其通过入口从旁路管道接收空气，并将旁路空气引导到尾锥的空腔以冷却发电机。 然后，旁路空气通过与尾锥腔流体连通的支撑支柱的出口排出。 整流罩入口和支柱出口都位于基本上垂直于发动机的纵向平面的平面内。 以这种方式，可以实现旁路空气通过整流罩，尾锥腔和支柱的循环。 引导通过整流罩的旁路空气进一步使得容纳在整流罩中的服务线的冷却。 进一步使用叶片混合器来引导整流罩并将其从核心排气屏蔽起来。

公开(公告)号：US09003811B2

公开(公告)日：2015-04-14

申请号：US13304960

申请日：2011-11-28

Applicant: Barry Barnett ,  David Denis

Inventor： Barry Barnett ,  David Denis

IPC: F02C7/20 ,  F16M13/00 ,  F01D15/10 ,  F01D25/04 ,  F01D25/16 ,  F02C7/32

CPC classification number: F01D25/164 ,  F01D15/10 ,  F01D25/04 ,  F02C7/20 ,  F02C7/32 ,  F05D2220/76 ,  Y02T50/671 ,  Y10T29/49009

Abstract: 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).

Abstract translation: 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。