公开(公告)号：US20070098548A1

公开(公告)日：2007-05-03

申请号：US11467413

申请日：2006-08-25

Applicant: Barry Barnett ,  David Denis

Inventor： Barry Barnett ,  David Denis

IPC: F04D29/54

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

Abstract: A vane for a vane assembly of a gas turbine engine includes a vane root connected to the airfoil portion opposite a tip thereof. The vane root includes a platform and a button portion interconnecting the platform and the airfoil position. The button portion has relatively blunt leading and trailing ends which respectively protrude beyond leading and trailing edges of the airfoil portion.

Abstract translation: 用于燃气涡轮发动机的叶片组件的叶片包括连接到与其顶端相对的翼型部的叶根。 叶片根部包括平台和连接平台和翼型位置的按钮部分。 按钮部分具有分别突出超过翼型部分的前缘和后缘的相对钝的前端和后端。

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。

公开(公告)号：US20120082553A1

公开(公告)日：2012-04-05

申请号：US13189059

申请日：2011-07-22

Applicant: Andreas Eleftheriou ,  Barry Barnett ,  Joe Lanzino ,  Tom McDonough ,  George Guglelmin ,  Enzo Macchia ,  Melinda Bissinger

Inventor： Andreas Eleftheriou ,  Barry Barnett ,  Joe Lanzino ,  Tom McDonough ,  George Guglelmin ,  Enzo Macchia ,  Melinda Bissinger

IPC: F01D5/14 ,  B23P15/02

CPC classification number: F01D5/147 ,  F01D9/02 ,  F05D2230/90 ,  F05D2300/43 ,  Y10T29/49336

Abstract: A hybrid vane airfoil for a gas turbine engine, such as a vane of a compressor stator, is disclosed which includes a non-metallic core, and an outer metallic shell at least partially covering the non-metallic core and which defines an outer surface of the airfoil. The non-metallic core is composed for example of a polymer, and the metallic outer shell is composed of a nanocrystalline metallic coating.

Abstract translation: 公开了一种用于燃气涡轮发动机的混合叶片翼片，例如压缩机定子的叶片，其包括非金属芯和至少部分地覆盖非金属芯的外部金属壳，并且限定外部表面 机翼。 非金属芯由例如聚合物组成，金属外壳由纳米晶体金属涂层组成。

公开(公告)号：US07726021B2

公开(公告)日：2010-06-01

申请号：US11528648

申请日：2006-09-28

Applicant: Barry Barnett

Inventor： Barry Barnett

IPC: B23P6/00 ,  F01D11/02

CPC classification number: F01D11/02 ,  B23P6/005 ,  B23P11/025 ,  F05D2230/80 ,  Y10T29/49318 ,  Y10T29/49719 ,  Y10T29/4973

Abstract: A method for repairing damaged fins in a labyrinth seal without the use of welding or metallurgical bonding by removing a section of the shaft containing the damaged fins, and providing a sleeve with replacement fins.

Abstract translation: 一种用于在不使用焊接或冶金接合的情况下修复迷宫式密封件中的损坏的翅片的方法，通过移除包含损坏的翅片的轴的一部分，以及提供具有替换翅片的套筒。

公开(公告)号：US20080063508A1

公开(公告)日：2008-03-13

申请号：US11517299

申请日：2006-09-08

Applicant: Barry Barnett ,  David Denis ,  Andreas Eleftheriou

Inventor： Barry Barnett ,  David Denis ,  Andreas Eleftheriou

IPC: F01D21/00

CPC classification number: F01D11/122 ,  F02K3/06

Abstract: A fan case and method of manufacturing a fan case, for a gas turbine engine, where the fan case has a hollow tubular metal shell with: a central axis of symmetry; an inlet; an outlet; and peripheral wall about the axis to encompass the tips of a plurality of rotary fan blades, and the shell wall includes an upstream portion defining an annular abradable material recess that extends axially having an upstream end at the shell inlet and a downstream end located upstream from the shell outlet.

Abstract translation: 一种用于燃气涡轮发动机的风扇壳体和风扇壳体的制造方法，其中所述风扇壳体具有中空管状金属壳体，所述中空管状金属壳体具有中心对称轴线; 一个入口 一个出口 围绕所述轴线的周壁围绕多个旋转风扇叶片的顶端，并且所述壳壁包括限定环形可磨损材料凹部的上游部分，所述环形可磨损材料凹部轴向延伸，具有在所述壳入口处的上游端和位于所述壳体入口上游的下游端 外壳出口。

公开(公告)号：US20070237633A1

公开(公告)日：2007-10-11

申请号：US11223148

申请日：2005-09-12

Applicant: Barry Barnett

Inventor： Barry Barnett

IPC: F01D9/00

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

Abstract: A vane assembly for a gas turbine engine including a shroud ring with openings and isolating means isolating a vane extremity within each opening, the isolating means cooperating to form a continuous gas path surface completely covering at least an axial portion of a surface of the shroud ring.

Abstract translation: 一种用于燃气涡轮发动机的叶片组件，其包括具有开口的护罩环和隔离每个开口内的叶片末端的隔离装置，该隔离装置配合以形成完全覆盖护罩环表面的至少一个轴向部分的连续气体路径表面 。

公开(公告)号：US20070237632A1

公开(公告)日：2007-10-11

申请号：US11223129

申请日：2005-09-12

Applicant: Barry Barnett ,  Bruce Fielding

Inventor： Barry Barnett ,  Bruce Fielding

IPC: F01D9/00

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：US20070098557A1

公开(公告)日：2007-05-03

申请号：US11467406

申请日：2006-08-25

Applicant: Barry Barnett ,  David Denis

Inventor： Barry Barnett ,  David Denis

IPC: F01D11/00

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：US08871297B2

公开(公告)日：2014-10-28

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: B05C13/00 ,  B05D3/10 ,  B82Y30/00 ,  C23C18/16 ,  C23C30/00 ,  F01D5/30 ,  C23C28/02 ,  B22F1/00

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。