公开(公告)号：US20130014513A1

公开(公告)日：2013-01-17

申请号：US13183848

申请日：2011-07-15

Applicant: Barry Barnett ,  Daniel Alecu ,  Andreas Eleftheriou

Inventor： Barry Barnett ,  Daniel Alecu ,  Andreas Eleftheriou

IPC: F02C6/00

CPC classification number: F02C7/06 ,  F02C7/32 ,  F02C7/36 ,  F05D2260/202

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20120082551A1

公开(公告)日：2012-04-05

申请号：US13189043

申请日：2011-07-22

Applicant: Enzo Macchia ,  Barry Barnett ,  Andreas Eleftheriou ,  Tom McDonough ,  George Guglielmin ,  Joe Lanzino

Inventor： Enzo Macchia ,  Barry Barnett ,  Andreas Eleftheriou ,  Tom McDonough ,  George Guglielmin ,  Joe Lanzino

IPC: F01D5/30

CPC classification number: 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

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20120082541A1

公开(公告)日：2012-04-05

申请号：US13189100

申请日：2011-07-22

Applicant: Enzo Macchia ,  Barry Barnett ,  Andreas Eleftheriou ,  Tom McDonough ,  George Guglielmin ,  Joe Lanzino

Inventor： Enzo Macchia ,  Barry Barnett ,  Andreas Eleftheriou ,  Tom McDonough ,  George Guglielmin ,  Joe Lanzino

IPC: F01D25/24 ,  B23P17/00

CPC classification number: F01D25/246 ,  F01D21/045 ,  F02K3/06 ,  Y02T50/672 ,  Y10T29/49229

Abstract: An engine casing for a gas turbine engine, such as, but not limited to, a gas turbine engine fan case, is disclosed which includes an annular case shell formed of a substrate material that is at least partially coated by a nanocrystalline metal coating. A method of manufacturing such an engine casing is also provided. The present engine casing provides improved containment capability in the event of a blade release or other failure during operation of the engine.

Abstract translation: 公开了一种用于燃气涡轮发动机的发动机壳体，例如但不限于燃气涡轮发动机风扇壳体，其包括由至少部分地由纳米晶体金属涂层涂覆的基底材料形成的环形壳体壳体。 还提供了制造这种发动机壳体的方法。 本发动机壳体在发动机操作期间在叶片释放或其他故障的情况下提供改进的容纳能力。

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：US20160153290A1

公开(公告)日：2016-06-02

申请号：US14529652

申请日：2014-10-31

Applicant: Enzo MACCHIA ,  Barry BARNETT ,  Andreas ELEFTHERIOU ,  Tom McDONOUGH ,  George GUGLIELMIN ,  Joe LANZINO

Inventor： Enzo MACCHIA ,  Barry BARNETT ,  Andreas ELEFTHERIOU ,  Tom McDONOUGH ,  George GUGLIELMIN ,  Joe LANZINO

IPC: F01D5/30 ,  F01D5/28 ,  F01D5/00

CPC classification number: 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

Abstract: A method of protecting a blade of a gas turbine engine by applying a nanocrystalline metal coating to a portion of the blade root is disclosed, which includes preparing at least a portion of a dovetail of the blade root for coating; and then applying a nanocrystalline metal coating to said portion.

Abstract translation: 公开了一种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燃气涡轮发动机的叶片的方法，其包括制备用于涂覆的叶片根部的至少一部分燕尾榫; 然后对所述部分施加纳米晶体金属涂层。

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。

公开(公告)号：US08613591B2

公开(公告)日：2013-12-24

申请号：US11516600

申请日：2006-09-07

Applicant: Barry Barnett

Inventor： Barry Barnett

IPC: F01D25/32

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：US20130121834A1

公开(公告)日：2013-05-16

申请号：US13297300

申请日：2011-11-16

Applicant: BARRY BARNETT

Inventor： BARRY BARNETT

IPC: F01D5/02

CPC classification number: F01D5/30 ,  F01D5/02 ,  F01D5/14 ,  F02K3/06 ,  F05D2220/32 ,  F05D2240/20 ,  F05D2260/941

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US08397383B2

公开(公告)日：2013-03-19

申请号：US11537884

申请日：2006-10-02

Applicant: Barry Barnett ,  Steven Hunt ,  Czeslaw Wojtyczka

Inventor： Barry Barnett ,  Steven Hunt ,  Czeslaw Wojtyczka

IPC: B21K25/00

CPC classification number: F01D25/24 ,  F05D2230/232 ,  F05D2230/26 ,  F05D2240/14 ,  F05D2250/231 ,  F05D2250/232 ,  Y02T50/671 ,  Y10T29/4932

Abstract: 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.

Abstract translation: 该方法用于从预成型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。

公开(公告)号：US07628578B2

公开(公告)日：2009-12-08

申请号：US11467413

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 ,  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。