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：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。

公开(公告)号：US07530782B2

公开(公告)日：2009-05-12

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 about a circumference of the shroud and vanes extending radially from the shroud with a vane tip in each opening. Isolating apparatus are disposed in each opening to isolate the vane tip from the shroud ring. Each vane tip is engaged with the shroud by retaining apparatus for restricting movement of the vane tip in an axial direction relative to the shroud.

Abstract translation: 一种用于燃气涡轮发动机的叶片组件，其包括具有围绕所述护罩的圆周限定的开口的护罩和在每个开口中具有从所述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。 每个叶片尖端通过保持装置与护罩接合，以限制叶片尖端在相对于护罩的轴向上的运动。

公开(公告)号：US07413400B2

公开(公告)日：2008-08-19

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 arrangement isolating a vane extremity within each opening, the isolating arrangement 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将每个开口内的叶片末端隔离的隔离装置，所述隔离装置配合以形成完全覆盖所述护罩环的表面的至少轴向部分的连续气体路径表面 。

公开(公告)号：US20080086881A1

公开(公告)日：2008-04-17

申请号：US11537890

申请日：2006-10-02

Applicant: Andreas Eleftheriou ,  Steven Bokan ,  Barry Barnett ,  Steven Hunt ,  Czeslaw Wojtyczka ,  John Paterson

Inventor： Andreas Eleftheriou ,  Steven Bokan ,  Barry Barnett ,  Steven Hunt ,  Czeslaw Wojtyczka ,  John Paterson

IPC: B23P15/04

CPC classification number: F01D25/24 ,  F01D21/045 ,  F05D2230/20 ,  F05D2230/26 ,  F05D2230/50 ,  F05D2240/14 ,  Y02T50/671 ,  Y10T29/4932

Abstract: The method is used for making an annular gas turbine engine case, the method comprises flowforming a first area of the preform to provide a first annular case portion having a first thickness and a second area having a second thickness, the first and the second average thickness being different.

Abstract translation: 该方法用于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第一区域以提供具有第一厚度的第一环形壳体部分和具有第二厚度的第二区域，第一和第二平均厚度 不同

公开(公告)号：US20080080971A1

公开(公告)日：2008-04-03

申请号：US11528648

申请日：2006-09-28

Applicant: Barry Barnett

Inventor： Barry Barnett

IPC: F03B11/00

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

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

Abstract translation: 用于修复迷宫式密封件中损坏的翅片的方法和装置，密封件不使用焊接或冶金结合。 该方法包括以下步骤：去除包含损坏的翅片的轴的一部分，并为套筒提供替换翅片。

公开(公告)号：US07306432B2

公开(公告)日：2007-12-11

申请号：US11224090

申请日：2005-09-13

Applicant: Sean André Rockarts ,  Barry Barnett

Inventor： Sean André Rockarts ,  Barry Barnett

IPC: F01D5/02

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 nose cone and the use of standard fasteners. The nose cone is adapted to cooperate with at least one standard fastener to retain the standard fastener to the nose cone to rotationally balance the shaft.

Abstract translation: 用于平衡飞机发动机的轴的装置优选地包括鼻锥和使用标准紧固件。 鼻锥体适于与至少一个标准紧固件配合，以将标准紧固件保持在鼻锥体上以旋转平衡轴。

公开(公告)号：US20060188379A1

公开(公告)日：2006-08-24

申请号：US11224090

申请日：2005-09-13

Applicant: Sean Rockarts ,  Barry Barnett

Inventor： Sean Rockarts ,  Barry Barnett

IPC: F01D5/30

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 nose cone and the use of standard fasteners. The nose cone is adapted to cooperate with at least one standard fastener to retain the standard fastener to the nose cone to rotationally balance the shaft.

Abstract translation: 用于平衡飞机发动机的轴的装置优选地包括鼻锥和使用标准紧固件。 鼻锥体适于与至少一个标准紧固件配合，以将标准紧固件保持在鼻锥体上以旋转平衡轴。

公开(公告)号：US09429029B2

公开(公告)日：2016-08-30

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: F03B3/12 ,  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。