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公开(公告)号：US09003759B2
公开(公告)日：2015-04-14
申请号：US11719799
申请日：2004-12-01
Applicant: Gabriel Suciu , Gary D. Roberge , Brian Merry
Inventor： Gabriel Suciu , Gary D. Roberge , Brian Merry
Abstract: A particle separator (20) for a tip turbine engine (10) includes a generally conical inclined leading surface (24) leading to a maximum radius (25) and a tapered trailing surface (56) having a radius at all points therealong less than the maximum radius (25). The trailing surface (56) of the particle separator (20) is tapered and/or curved radially inwardly away from the maximum radius (25). Air flowing toward the core airflow inlet is first diverted radially outwardly by the inclined leading surface (24) of the particle separator (20) to the maximum radius (25) of the particle separator (20). The air then follows the trailing surface (56) radially inwardly to flow axially into the core airflow inlet. While the air can follow the contours of the particle separator (20) around the maximum radius (25) and into the core airflow inlet, any particles, such as dirt, will have more inertia and will pass radially outwardly of the core airflow inlet through the bypass fan.
Abstract translation: 用于尖端涡轮发动机（10）的颗粒分离器（20）包括通向圆锥形的倾斜前导表面（24），其导致最大半径（25）和锥形后表面（56），所述锥形后表面在所有点处具有小于 最大半径（25）。 颗粒分离器（20）的后表面（56）从最大半径（25）向内径向向内渐缩和/或弯曲。 首先通过颗粒分离器（20）的倾斜引导表面（24）向颗粒分离器（20）的最大半径（25）径向向外转向空气流向核心气流入口。 然后空气径向向内跟随后表面（56），从而轴向流入核心气流入口。 当空气可以沿着最大半径（25）和颗粒气流入口跟随颗粒分离器（20）的轮廓时，任何颗粒（例如污物）将具有更大的惯性并且将通过核心气流入口的径向向外通过 旁路风扇。
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公开(公告)号：US08950171B2
公开(公告)日：2015-02-10
申请号：US13089450
申请日：2011-04-19
Applicant: Gabriel Suciu , Brian Merry , Michael E. McCune
Inventor： Gabriel Suciu , Brian Merry , Michael E. McCune
CPC classification number: F02C3/08 , F02C3/073 , F02C3/107 , F02C7/36 , F02K3/068 , F04D25/045 , F05D2260/40311 , F16H48/10
Abstract: A tip turbine engine provides an axial compressor rotor that is counter-rotated relative to a fan. A planetary gearset couples rotation of a fan to an axial compressor rotor, such that the axial compressor rotor is driven by rotation of the fan in a rotational direction opposite that of the fan. By counter-rotating the axial compressor rotor, a final stage of compressor vanes between the final stage of compressor blades and inlets to the hollow fan blades of the fan are eliminated. As a result, the length of the axial compressor and the overall length of the tip turbine engine are decreased.
Abstract translation: 尖端涡轮发动机提供相对于风扇反向旋转的轴向压缩机转子。 行星齿轮组将风扇的旋转耦合到轴向压缩机转子，使得轴向压缩机转子通过风扇沿与风扇相反的旋转方向的旋转来驱动。 通过逆向旋转轴向压缩机转子，消除了在压缩机叶片的最后阶段和到风扇的中空风扇叶片的入口之间的压缩机叶片的最后阶段。 结果，轴流压缩机的长度和末端涡轮发动机的总长度减小。
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公开(公告)号：US07500365B2
公开(公告)日：2009-03-10
申请号：US11122336
申请日：2005-05-05
Applicant: Gabriel Suciu , Brian Merry
Inventor： Gabriel Suciu , Brian Merry
IPC: F02C6/00
CPC classification number: F02C7/36 , F02C7/32 , Y02T50/671 , Y10S74/05
Abstract: Provided is an accessory gearbox for a gas turbine engine that contributes minimally to engine weight and complexity. An accessory gearbox comprises a stationary frame that is circumferentially disposed about a central longitudinal axis of the engine. The frame includes a forward-directed axial face and a rearward-directed axial face for fastening the frame to the engine. A central bore accepts a rotational driving means and an outermost rim circumscribes the outer diameter of the frame. A compartment is located between the bore and the rim. At least one primary accessory is mounted to a face and proximate the compartment, remotely engaging the driving means and able to be driven concurrently therewith.
Abstract translation: 提供了一种用于燃气涡轮发动机的附件齿轮箱，其对发动机重量和复杂性最小化。 附件齿轮箱包括围绕发动机的中心纵向轴线周向设置的固定框架。 框架包括前向轴向面和向后定向的轴向面，用于将框架紧固到发动机。 中心孔接受旋转驱动装置，最外边缘包围框架的外径。 隔间位于孔和边缘之间。 至少一个主要附件被安装到面部并且靠近隔室，远程地接合驱动装置并且能够与其同时驱动。
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公开(公告)号：US20080095628A1
公开(公告)日：2008-04-24
申请号：US11718424
申请日：2004-12-01
Applicant: Gabriel Suciu , Lawrence Portlock , Brian Merry
Inventor： Gabriel Suciu , Lawrence Portlock , Brian Merry
CPC classification number: F01D5/022 , F02C3/073 , F02C3/107 , F02C7/32 , F02C7/36 , F02K3/068 , F05D2260/40311
Abstract: A gearbox assembly (90) closely couples a fan-turbine rotor assembly (25) and an axial compressor rotor (46) to reduce the overall engine length and minimizes the number of engine bearings.
Abstract translation: 齿轮箱组件（90）将风扇 - 涡轮转子组件（25）和轴向压缩机转子（46）紧密连接，以减少整个发动机长度并使发动机轴承的数量最小化。
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公开(公告)号：US20080044281A1
公开(公告)日：2008-02-21
申请号：US11718420
申请日：2004-12-01
Applicant: Gabriel Suciu , Brian Merry , Lawrence Portlock
Inventor： Gabriel Suciu , Brian Merry , Lawrence Portlock
IPC: F01D25/24
CPC classification number: F02C7/32 , F02C3/073 , F02C3/08 , F02C7/36 , F02K3/02 , F02K3/068 , F05D2260/40311
Abstract: A non-rotating compartment along an engine centerline of a tip turbine engine is defined between an inner support housing, an outer support housing and an aft housing. The non-rotating compartment provides a space that may be utilized for a multitude of engine accessories and components including an engine lubricating fluid system.
Abstract translation: 沿着顶部涡轮发动机的发动机中心线的非旋转舱被限定在内部支撑壳体，外部支撑壳体和后部壳体之间。 非旋转隔室提供可用于多个发动机附件和部件的空间，包括发动机润滑流体系统。
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Patent Agency Ranking
公开(公告)号：US20070295011A1
公开(公告)日：2007-12-27
申请号：US11719956
申请日：2004-12-01
Applicant: Gabriel Suciu , James Norris , Craig Nordeen
Inventor： Gabriel Suciu , James Norris , Craig Nordeen
IPC: F02C7/18
CPC classification number: F02C3/073 , F01D5/022 , F01D5/187 , F02K3/068 , F05D2260/205 , Y02T50/676
Abstract: A fan-turbine rotor assembly (24) includes a multitude of turbine blades (34) which each define a turbine blade passage which bleed air from a diffuser section (74) to provide for regenerative cooling. Regenerative cooling airflow is communicated from the radial core airflow passage (80) through the diffuser passages (144), through diffuser aspiration passages (146A, 146B) and into the turbine blade passages (150a). The regenerative cooling airflow exits from the turbine blade passage (150a) and transfers received thermal energy into an annular combustor (30). The received thermal energy is recovered at the highest temperature in the cycle.
Abstract translation: 风扇涡轮转子组件（24）包括多个涡轮机叶片（34），每个涡轮机叶片限定一个涡轮机叶片通道，其从扩散器部分（74）排出空气以提供再生冷却。 再生冷却气流通过扩散器抽吸通道（146A，146B）从径向芯气流通道80通过扩散器通道144进入涡轮叶片通道150a。 再生冷却气流从涡轮机叶片通道（150a）流出并将接收到的热能转移到环形燃烧器（30）中。 接收的热能在循环中的最高温度下回收。
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公开(公告)号：US07201558B2
公开(公告)日：2007-04-10
申请号：US11122368
申请日：2005-05-05
Applicant: James W. Norris , Craig A. Nordeen , Gary Roberge , Gabriel Suciu
Inventor： James W. Norris , Craig A. Nordeen , Gary Roberge , Gabriel Suciu
IPC: F04D31/00
CPC classification number: F01D11/005 , F02C3/073 , F02K3/06 , F02K3/068 , Y02T50/672
Abstract: A fan-turbine rotor hub includes an outer periphery scalloped by a multitude of elongated openings. Each elongated opening defines an inducer receipt section to receive an inducer section and a hollow fan blade section. An inducer exit from each inducer section is located adjacent a core airflow passage within each fan blade section to provide communication therebetween. A seal is located between an inner fan blade mount and a blade receipt section to minimize airflow leakage between the inducer exit and the core airflow passage.
Abstract translation: 风扇涡轮转子毂包括由多个细长开口扇形的外周。 每个细长的开口限定了一个诱导器接收部分，以便接纳一个导流部分和一个中空的风扇叶片部分。 每个导流部分的导流器出口位于每个风扇叶片部分内的核心气流通道附近，以在它们之间提供连通。 密封件位于内部风扇叶片安装件和叶片接收部分之间，以最小化引导器出口和芯气流通道之间的气流泄漏。
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公开(公告)号：US20060130488A1
公开(公告)日：2006-06-22
申请号：US11016454
申请日：2004-12-17
Applicant: Gabriel Suciu , James Norris
Inventor： Gabriel Suciu , James Norris
IPC: F02C7/00
CPC classification number: F01D5/066 , 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 second means, radially outboard of the first means, for transmitting a majority of the force.
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。 联接器具有用于传送大部分扭矩和第二装置的第一装置，第一装置的径向外侧，用于传递大部分的力。
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公开(公告)号：US20050111970A1
公开(公告)日：2005-05-26
申请号：US10720875
申请日：2003-11-26
Applicant: Gabriel Suciu , Brian Merry
Inventor： Gabriel Suciu , Brian Merry
CPC classification number: F01D5/063 , F01D11/001 , F05D2220/3215 , Y10T29/4932
Abstract: The present invention relates to an improved turbine structure for use in a gas turbine engine. The turbine structure includes a one-piece drum rotor and a plurality of turbine blades attached to the one-piece drum rotor. The one-piece drum rotor includes integrally formed, welded disks for supporting the plurality of turbine blades. A method for installing the turbine structure is also described.
Abstract translation: 本发明涉及一种用于燃气涡轮发动机的改进的涡轮机结构。 涡轮机结构包括一体式鼓转子和附接到一体式转鼓的多个涡轮叶片。 一体式滚筒转子包括用于支撑多个涡轮叶片的一体形成的焊接盘。 还描述了一种用于安装涡轮机结构的方法。
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公开(公告)号：US20110200424A1
公开(公告)日：2011-08-18
申请号：US13089450
申请日：2011-04-19
Applicant: Gabriel Suciu , Brian Merry , Michael E. McCune
Inventor： Gabriel Suciu , Brian Merry , Michael E. McCune
IPC: F01D1/26
CPC classification number: F02C3/08 , F02C3/073 , F02C3/107 , F02C7/36 , F02K3/068 , F04D25/045 , F05D2260/40311 , F16H48/10
Abstract: A tip turbine engine provides an axial compressor rotor that is counter-rotated relative to a fan. A planetary gearset couples rotation of a fan to an axial compressor rotor, such that the axial compressor rotor is driven by rotation of the fan in a rotational direction opposite that of the fan. By counter-rotating the axial compressor rotor, a final stage of compressor vanes between the final stage of compressor blades and inlets to the hollow fan blades of the fan are eliminated. As a result, the length of the axial compressor and the overall length of the tip turbine engine are decreased.
Abstract translation: 尖端涡轮发动机提供相对于风扇反向旋转的轴向压缩机转子。 行星齿轮组将风扇的旋转耦合到轴向压缩机转子，使得轴向压缩机转子通过风扇沿与风扇相反的旋转方向的旋转来驱动。 通过逆向旋转轴向压缩机转子，消除了在压缩机叶片的最后阶段和到风扇的中空风扇叶片的入口之间的压缩机叶片的最后阶段。 结果，轴流压缩机的长度和末端涡轮发动机的总长度减小。
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