公开(公告)号：US20050106009A1

公开(公告)日：2005-05-19

申请号：US10713641

申请日：2003-11-13

Applicant: Kevin Cummings ,  Christopher Demers ,  James Hodgson ,  Gabriel Suciu ,  Brian Merry

Inventor： Kevin Cummings ,  Christopher Demers ,  James Hodgson ,  Gabriel Suciu ,  Brian Merry

IPC: F01D17/16 ,  F01D17/10 ,  F01D17/14 ,  F02C6/08 ,  F04D27/02 ,  F04D29/54 ,  F01D17/00

CPC classification number: F04D19/02 ,  F01D17/105 ,  F01D25/162 ,  F04D27/0215 ,  F04D27/023 ,  F04D29/545 ,  Y10T29/49323

Abstract: A gas turbine engine compressor has a number of shroud rings, at least a bleed one of which defines a number of bleed ports. A structural hub is downstream of the shroud rings and secured relative to the shroud rings. A structural hub case extends from an aft joint with the structural hub to a fore joint with a joined one of the shroud rings and has a number of valve ports. At least a portion of the structural case extends structurally between the fore and aft joints. A valve element is shiftable between first and second conditions for respectively blocking and not blocking communication through the valve ports.

Abstract translation: 燃气涡轮发动机压缩机具有多个护罩环，至少其中一个排气口限定了多个排放口。 结构轮毂在护罩环的下游并相对于护罩环固定。 结构轮毂壳从与结构轮毂的后接头延伸到具有连接的一个护罩环的前接头并且具有多个阀口。 结构壳体的至少一部分在结构上在前后关节之间延伸。 阀元件可在第一和第二条件之间移动，以分别阻塞并阻止通过阀口的连通。

公开(公告)号：US07921636B2

公开(公告)日：2011-04-12

申请号：US11719887

申请日：2004-12-01

Applicant: Gabriel Suciu ,  James W. Norris ,  Craig A. Nordeen ,  Brian Merry

Inventor： Gabriel Suciu ,  James W. Norris ,  Craig A. Nordeen ,  Brian Merry

IPC: F02K3/02

CPC classification number: F02K3/068 ,  F02C3/073 ,  F23R3/52

Abstract: A tip turbine engine has a more efficient core airflow path from the hollow fan blades, through the combustor and to the combustion chamber of a combustor. The turbine engine includes a rotatable fan having a plurality of radially-extending fan blades each defining compressor chambers extending radially therein. A turbine is mounted to the outer periphery of the fan. A diffuser at a radially outer end of each compressor chamber turns core airflow through the compressor chamber toward the combustor. The high velocity, high pressure core airflow from the compressor chambers in the hollow fan blades is diffused before the compressed core airflow enters the combustor, thereby improving the efficiency of the tip turbine engine. Further, the overall diameter of the tip turbine engine is reduced by the arrangement of the diffuser case in a position not directly radially outward of the fan blades.

Abstract translation: 尖端涡轮发动机具有从中空风扇叶片通过燃烧器和燃烧器的燃烧室的更有效的核心气流路径。 涡轮发动机包括具有多个径向延伸的风扇叶片的可旋转风扇，每个风扇叶片限定其径向延伸的压缩机室。 涡轮机安装在风扇的外周。 在每个压缩机室的径向外端处的扩散器使得通过压缩机室的核心气流朝向燃烧器。 来自中空风扇叶片中的压缩机室的高速，高压核心气流在压缩空气流进入燃烧器之前扩散，从而提高顶端涡轮发动机的效率。 此外，通过在不直接径向向外的风扇叶片的外部的扩散器壳体的布置来减小顶端涡轮发动机的总直径。

公开(公告)号：US20080092552A1

公开(公告)日：2008-04-24

申请号：US11718519

申请日：2004-12-01

Applicant: Gabriel Suciu ,  Lawrence Portlock ,  Brian Merry

Inventor： Gabriel Suciu ,  Lawrence Portlock ,  Brian Merry

IPC: F16H57/02 ,  F02C3/073 ,  F02K3/068

CPC classification number: F02C3/073 ,  F01D5/022 ,  F01D25/183 ,  F02C7/32 ,  F02K3/068 ,  F05D2260/40311

Abstract: A hydraulic seal (170) for a tip turbine engine includes an inner radial flange (171) and an outer radial flange (172). The inner radial flange (171) rotates relative the outer radial seal section and the planet carrier face (94) to prevent lubrication from entering into the air flow streams within the engine without additional engine assembly procedures.

Abstract translation: 用于顶端涡轮发动机的液压密封件（170）包括内径向凸缘（171）和外径向凸缘（172）。 内部径向凸缘（171）相对于外部径向密封部分和行星架面（94）旋转，以防止润滑进入发动机内的空气流动流，而无需额外的发动机组装程序。

公开(公告)号：US20080019830A1

公开(公告)日：2008-01-24

申请号：US11720470

申请日：2004-12-01

Applicant: Gabriel Suciu ,  James Norris ,  Brian Merry

Inventor： Gabriel Suciu ,  James Norris ,  Brian Merry

IPC: F01D25/28

CPC classification number: F02K3/068 ,  B64D27/26 ,  F02C3/073 ,  F02C7/20

Abstract: A tip turbine engine assembly (8) includes a fan (32) rotatable in a fan plane (22) about an engine centerline (112). The fan (32) includes a fan blade (34) that defines a core airflow passage therethrough. An engine case (10) surrounds and supports the fan and engine. A plurality of engine mounts (20) for mounting the engine to an aircraft are positioned circumferentially about the outside of the engine case in a single mounting plane (22) that is perpendicular to the engine centerline.

Abstract translation: 顶端涡轮发动机组件（8）包括可围绕发动机中心线（112）在风扇平面（22）中旋转的风扇（32）。 风扇（32）包括限定通过其中的芯气流通道的风扇叶片（34）。 发动机壳体（10）围绕并支撑风扇和发动机。 用于将发动机安装到飞行器的多个发动机支架（20）在垂直于发动机中心线的单个安装平面（22）中周向地围绕发动机壳体的外部定位。

公开(公告)号：US20060130456A1

公开(公告)日：2006-06-22

申请号：US11016453

申请日：2004-12-17

Applicant: Gabriel Suciu ,  James Norris

Inventor： Gabriel Suciu ,  James Norris

IPC: F02K3/04

CPC classification number: F01D5/066 ,  F01D11/001 ,  F05D2260/4031

Abstract: A turbine engine has a first disk and a second disk, each extending radially from an inner aperture to an outer periphery. A coupling, transmits a torque and a longitudinal compressive force between the first and second disks. The coupling has first means for transmitting a majority of the torque and a majority of the force and second means, radially outboard of the first means, for vibration stabilizing.

Abstract translation: 涡轮发动机具有第一盘和第二盘，每个盘从内孔径向延伸到外周。 联接器在第一和第二盘之间传递扭矩和纵向压缩力。 联接器具有用于传递大部分扭矩的第一装置和大部分力和第二装置，第一装置的径向外侧，用于振动稳定。