专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

US20080019830A1 Tip Turbine Single Plane Mount 有权
标题翻译：涡轮机单平面安装
公开(公告)号：US20080019830A1
公开(公告)日：2008-01-24
申请号：US11720470
申请日：2004-12-01
申请人： Gabriel Suciu , James Norris , Brian Merry
发明人： Gabriel Suciu , James Norris , Brian Merry
IPC分类号： F01D25/28
CPC分类号： F02K3/068 , B64D27/26 , F02C3/073 , F02C7/20
摘要： 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.
摘要翻译：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。

2. 发明申请

US20080092514A1 Tip Turbine Engine Composite Tailcone 有权
标题翻译：涡轮发动机复合式Tailcone
公开(公告)号：US20080092514A1
公开(公告)日：2008-04-24
申请号：US11720463
申请日：2004-12-01
申请人： Gabriel Suciu , James Norris , Brian Merry
发明人： Gabriel Suciu , James Norris , Brian Merry
IPC分类号： F02K1/04
CPC分类号： F02C3/073 , F02K1/04 , F02K3/068 , F05D2300/603 , F05D2300/614 , Y02T50/672 , Y10T29/49346
摘要： A non-metallic tailcone (202) in a tip turbine engine includes a tapered wall structure disposed (208) about a central axis. The non-metallic tailcone is fastened to a structural frame (44) in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.
摘要翻译：尖端涡轮发动机中的非金属尾管（202）包括围绕中心轴线设置（208）的锥形壁结构。非金属尾管紧固在顶端涡轮发动机的后部的结构框架（44）上。尖端涡轮发动机产生来自第一输出源的第一温度气体流和来自第二输出源的第二温度气体流。第二温度气体流是比第一温度气体流更低的温度。第二温度气流在末端涡轮发动机的内径处在尾骨的外表面上排出。在内径处排出较冷的第二温度气流允许非金属物质用于形成尾骨。

3. 发明申请

US20080008583A1 Tip Turbine Case, Vane, Mount And Mixer 有权
标题翻译：涡轮机壳，叶片，安装和搅拌机
公开(公告)号：US20080008583A1
公开(公告)日：2008-01-10
申请号：US11720543
申请日：2004-12-01
申请人： Gabriel Suciu , James Norris , Brian Merry
发明人： Gabriel Suciu , James Norris , Brian Merry
IPC分类号： F03B11/02 , F03B1/00
CPC分类号： F01D9/044 , F01D9/042 , F01D25/28 , F02C3/073 , F02C3/14 , F02C7/20
摘要： A tip turbine engine assembly includes an engine support structure with a rear case, exit guide vanes, an exhaust mixer, and engine mounts. The rear case is disposed about an engine centerline. The exit guide vanes extend radially inwardly from the rear case. The exhaust mixer extends in a flow path of a combustor to mix a high energy gas stream from the combustor with bypass air from a bypass fan. The engine mounts are located on the periphery of the rear case for mounting the engine to an aircraft. The rear case, exit guide vanes, exhaust mixer, and engine mounts form a unitary engine support structure which is installable as a single piece into an engine.
摘要翻译：尖端涡轮发动机组件包括具有后壳体，出口导向叶片，排气混合器和发动机支架的发动机支撑结构。后壳围绕发动机中心线设置。出口导向叶片从后壳径向向内延伸。排气混合器在燃烧器的流路中延伸，以将来自燃烧器的高能气流与旁路风扇的旁路空气混合。发动机支架位于后壳的外围，用于将发动机安装到飞机上。后壳体，出口导向叶片，排气混合器和发动机支架形成一体的发动机支撑结构，其可作为单件安装到发动机中。

4. 发明申请

US20060130456A1 Turbine engine rotor stack 有权
标题翻译：涡轮发动机转子堆
公开(公告)号：US20060130456A1
公开(公告)日：2006-06-22
申请号：US11016453
申请日：2004-12-17
申请人： Gabriel Suciu , James Norris
发明人： Gabriel Suciu , James Norris
IPC分类号： F02K3/04
CPC分类号： F01D5/066 , F01D11/001 , F05D2260/4031
摘要： 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.
摘要翻译：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。

5. 发明申请

US20070295011A1 Regenerative Turbine Blade and Vane Cooling for a Tip Turbine Engine 有权
标题翻译：涡轮发动机的再生涡轮叶片和叶片冷却
公开(公告)号：US20070295011A1
公开(公告)日：2007-12-27
申请号：US11719956
申请日：2004-12-01
申请人： Gabriel Suciu , James Norris , Craig Nordeen
发明人： Gabriel Suciu , James Norris , Craig Nordeen
IPC分类号： F02C7/18
CPC分类号： F02C3/073 , F01D5/022 , F01D5/187 , F02K3/068 , F05D2260/205 , Y02T50/676
摘要： 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.
摘要翻译：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。

6. 发明申请

US20060130488A1 Turbine engine rotor stack 有权
标题翻译：涡轮发动机转子堆
公开(公告)号：US20060130488A1
公开(公告)日：2006-06-22
申请号：US11016454
申请日：2004-12-17
申请人： Gabriel Suciu , James Norris
发明人： Gabriel Suciu , James Norris
IPC分类号： F02C7/00
CPC分类号： F01D5/066 , F05D2260/4031
摘要： 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.
摘要翻译：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。

7. 发明申请

US20070107219A1 Turbine engine rotor retainer 有权
标题翻译：涡轮发动机转子保持架
公开(公告)号：US20070107219A1
公开(公告)日：2007-05-17
申请号：US11479334
申请日：2006-06-30
申请人： Gabriel Suciu , James Norris
发明人： Gabriel Suciu , James Norris
IPC分类号： B23P11/00
CPC分类号： F01D5/066 , F01D5/025 , F01D11/001 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323 , Y10T29/49947
摘要： A rotor stack is assembled to a turbine engine shaft. A force is exerted to at least one of the rotor stack and the shaft to at least one of place the shaft under tension and place the rotor stack under compression. One or more retainer segments are inserted into a rebate in the shaft. The exerted force is released to permit the rotor stack to bear against the retainer segments.
摘要翻译：转子堆叠组装到涡轮发动机轴上。对转子堆和轴中的至少一个施加力至至少一个将轴处于张紧状态，并将转子叠层置于压缩状态。一个或多个保持器段被插入轴中的槽口中。施加的力被释放以允许转子堆叠抵靠保持器段。

8. 发明申请

US20060099070A1 Turbine engine disk spacers 有权
标题翻译：涡轮发动机圆盘垫片
公开(公告)号：US20060099070A1
公开(公告)日：2006-05-11
申请号：US10985863
申请日：2004-11-10
申请人： Gabriel Suciu , James Norris
发明人： Gabriel Suciu , James Norris
IPC分类号： F01D1/02
CPC分类号： F01D11/001 , F01D5/066 , F05D2250/70 , F05D2250/712 , F05D2260/30
摘要： A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. Outboard surfaces of the spacers may be in close facing proximity to inboard tips of vane airfoils. The spacers may provide a longitudinal compression force that increases with rotational speed.
摘要翻译：燃气涡轮发动机转子堆叠包括一个或多个纵向向外凹的间隔件。间隔件的外侧表面可以靠近翼片翼型的内侧尖端。间隔件可以提供随着转速而增加的纵向压缩力。

9. 发明申请

US20050232774A1 Turbine engine rotor retainer 有权
标题翻译：涡轮发动机转子保持架
公开(公告)号：US20050232774A1
公开(公告)日：2005-10-20
申请号：US10825256
申请日：2004-04-15
申请人： Gabriel Suciu , James Norris
发明人： Gabriel Suciu , James Norris
IPC分类号： F02C7/00 , F01D5/02 , F01D5/06 , F01D11/00 , H02K5/16
CPC分类号： F01D5/066 , F01D5/025 , F01D11/001 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323 , Y10T29/49947
摘要： A gas turbine engine has a rotor stack carried by a central shaft. A number of retainer segments each have a first surface engaging the rotor stack and a second surface engaging the central shaft so as to transmit a precompression force from the central shaft to the rotor stack.
摘要翻译：燃气涡轮发动机具有由中心轴承载的转子堆。多个保持器段各自具有接合转子堆叠的第一表面和接合中心轴的第二表面，以便将预压力从中心轴传递到转子堆叠。

10. 发明申请

US20070292270A1 Tip Turbine Engine Comprising Turbine Blade Clusters and Method of Assembly 有权
标题翻译：涡轮发动机包括涡轮叶片组和组装方法
公开(公告)号：US20070292270A1
公开(公告)日：2007-12-20
申请号：US11718522
申请日：2004-12-01
申请人： Gabriel Suciu , James Norris , Craig Nordeen
发明人： Gabriel Suciu , James Norris , Craig Nordeen
IPC分类号： F01D5/22 , B21K25/00
CPC分类号： F02C3/073 , F01D5/225 , F01D5/3007 , F02C3/08 , F02K3/068 , F05D2260/30 , Y10T29/49321
摘要： A tip turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. Assembly of a multitude of turbine blade clusters to a diffuser includes axial installation and radial rotation. The clusters are axially installed, then rotated toward a radial stop in a direction which will maintain each cluster against the radial stop during operation of the fan-turbine rotor assembly. A multitude of turbine rotor ring stages may also be locked together to future increase the rigidity of the turbine
摘要翻译：顶端涡轮发动机包括包括一个或多个涡轮机环形转子的风扇 - 涡轮机转子组件。每个涡轮环由多个涡轮机叶片组装配。将多个涡轮机叶片组装配到扩散器包括轴向安装和径向旋转。簇被轴向地安装，然后沿着在风扇 - 涡轮机转子组件的操作期间将每个簇抵靠径向停止件保持的方向朝向径向止动件旋转。许多涡轮机转子环级也可以被锁定在一起以便未来增加涡轮机的刚性

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式