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11. 发明申请

WO2006059994A1 SEAL ASSEMBLY FOR A FAN-TURBINE ROTOR OF A TIP TURBINE ENGINE 审中-公开
标题翻译：一种涡轮涡轮发动机的风力涡轮机转子的密封组件
公开(公告)号：WO2006059994A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040106
申请日：2004-12-01
申请人： UNITED TECHNOLOGIES CORPORATION , SUCIU, Gabriel L. , NORRIS, James W. , NORDEEN, Craig A. , MERRY, Brian
发明人： SUCIU, Gabriel L. , NORRIS, James W. , NORDEEN, Craig A. , MERRY, Brian
IPC分类号： F02K3/068 , F02C3/073 , F02C7/28 , F01D11/00 , F01D11/08 , F04D29/16
CPC分类号： F04D25/045 , F01D11/003 , F01D11/08 , F02C3/073 , F02C7/28 , F02K3/068 , F04D29/083
摘要： A seal assembly (116) mounted within a rotationally fixed static outer support structure (14) for engagement with an annular seal face surface (172) located upon a fan-turbine rotor assembly. The seal assembly provides minimal leakage of core airflow when the airflow is turned and diffused by the diffuser section (74) to increase the engine operating efficiency.
摘要翻译：安装在旋转固定的静态外部支撑结构（14）内的密封组件（116），用于与位于风扇 - 涡轮转子组件上的环形密封面表面（172）接合。当气流被扩散器部分（74）转动并扩散时，密封组件提供核心气流的最小泄漏，以提高发动机的运行效率。

12. 发明申请

WO2006059980A2 DIFFUSER ASPIRATION FOR A TIP TURBINE ENGINE 审中-公开
标题翻译：用于提升涡轮发动机的增压器吸气
公开(公告)号：WO2006059980A2
公开(公告)日：2006-06-08
申请号：PCT/US2004/039996
申请日：2004-12-01
申请人： UNITED TECHNOLOGIES CORPORATION , SUCIU, Gabriel L. , NORRIS, James W. , NORDEEN, Craig A.
发明人： SUCIU, Gabriel L. , NORRIS, James W. , NORDEEN, Craig A.
CPC分类号： F01D5/326 , F02C3/073 , F02C3/08
摘要： A fan-turbine rotor assembly includes a diffuser section which turns and diffuses the airflow from a radial core airflow passage toward an axial airflow direction. Diffuser flow passages communicate with the diffuser passages at a location which reduces separation of the airflow as the airflow is turned from the radial core airflow passage toward an axial airflow direction through airflow aspiration at the potentially turbulent locations.
摘要翻译：风扇 - 涡轮转子组件包括扩散器部分，其将来自径向核心气流通道的气流转向和扩散到轴向气流方向。扩散器流动通道在气流从径向核心气流通道朝向轴向气流方向通过在潜在湍流位置处的气流抽吸转动而减小气流分离的位置处与扩散通道连通。

13. 发明申请

WO2015148845A1 GAS TURBINE GENERATOR WITH A PRE-COMBUSTION POWER TURBINE 审中-公开
标题翻译：燃气涡轮发电机与预燃机功率涡轮机
公开(公告)号：WO2015148845A1
公开(公告)日：2015-10-01
申请号：PCT/US2015/022823
申请日：2015-03-26
申请人： SCALED POWER CORP.
发明人： KEOGH, Rory, C. , THOMAS, Gregory
IPC分类号： F02C7/36
CPC分类号： H02K7/1823 , F01D15/10 , F02C1/02 , F02C3/073 , F02C3/10 , F02C3/103 , F05D2220/76 , F05D2250/82
摘要： A turbine generator uses a common bearing carrier to support a high-speed spool and a low-speed spool, thereby enabling a more axially compact turbine generator design. The high-speed spool includes a high-speed compressor assembly mechanically powered by a high-speed turbine, which receives power from a combustion chamber between the high¬ speed turbine and the high-speed compressor assembly. The low-speed spool includes a pre- combustion power turbine aerodynamically powered by the compressor assembly and upstream of the combustion chamber. The pre-combustion turbine mechanically powers an electrical generator, which includes coreless stators and a rotor assembly. The stators have a planar configuration to receive axial flux from magnets of the rotor assembly. Optionally, the low-speed spool may include a post-combustion turbine that is arranged downstream of the combustion chamber and that mechanically powers the electrical generator.
摘要翻译：涡轮发电机使用普通的轴承载体来支撑高速滑阀和低速滑阀，从而实现更轴向紧凑的涡轮发电机设计。高速滑阀包括由高速涡轮机械机械动力的高速压缩机组件，高速涡轮机从高速涡轮机和高速压缩机组件之间的燃烧室接收动力。低速卷轴包括由压缩机组件和燃烧室上游空气动力学驱动的预燃动力涡轮机。预燃涡轮机械机械地驱动发电机，其包括无芯定子和转子组件。定子具有平面构造以接收来自转子组件的磁体的轴向通量。可选地，低速线轴可以包括设置在燃烧室下游并且为发电机机械供电的后燃烧涡轮机。

14. 发明申请

WO2014126696A1 GAS TURBINE ENGINE GEARED ARCHITECTURE 审中-公开
标题翻译：气体涡轮发动机齿轮架构
公开(公告)号：WO2014126696A1
公开(公告)日：2014-08-21
申请号：PCT/US2014/012957
申请日：2014-01-24
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ROBERGE, Gary D.
IPC分类号： F02C7/36 , F01D25/00
CPC分类号： F02C7/36 , F02C3/073
摘要： A gas turbine engine assembly according to an exemplary aspect of the present disclosure includes, among other things, a geared architecture configured to rotatably couple a turbine and a compressor of an engine to rotate the compressor at a different speed than the turbine and a fan.
摘要翻译：根据本公开的示例性方面的燃气涡轮发动机组件包括构造成可旋转地连接发动机的涡轮机和压缩机的齿轮架构，其以与涡轮机和风扇不同的速度旋转压缩机。

15. 发明申请

WO2007015916A2 REINFORCEMENT RINGS FOR A TIP TURBINE ENGINE FAN-TURBINE ROTOR ASSEMBLY 审中-公开
标题翻译：提升涡轮发动机风力涡轮机转子总成的加固环
公开(公告)号：WO2007015916A2
公开(公告)日：2007-02-08
申请号：PCT/US2006/028122
申请日：2006-07-20
申请人： UNITED TECHNOLOGIES CORPORATION , NORRIS, James W. , NORDEEN, Craig A. , ROBERGE, Gary , MERRY, Brian
发明人： NORRIS, James W. , NORDEEN, Craig A. , ROBERGE, Gary , MERRY, Brian
IPC分类号： F02K3/068 , F02C3/073 , F04D25/04 , F01D5/30
CPC分类号： F04D29/541 , F01D5/022 , F02C3/073 , F02K3/068 , F05D2300/702 , Y02T50/672
摘要： A fan-turbine rotor assembly includes a diffuser mountable to the outer periphery of a multitude of fan blade sections to provide structural support to the outer tips of the fan blade sections and to turn and diffuse the airflow from the radial core airflow passage toward an axial airflow direction. The diffuser includes a fan blade tip shroud inner portion which forms a planar ring about the multiple of fan blade sections. Diffuser support rings are mounted to the fan blade tip shroud to further share the radial load applied to the fan blade sections by the blade mounted diffuser and annular turbine.
摘要翻译：风扇涡轮转子组件包括可安装到多个风扇叶片部分的外周的扩散器，以向风扇叶片部分的外部末端提供结构支撑，并且使来自径向芯气流通道的气流向轴向气流方向扩散器包括风扇叶片尖端护罩内部，其围绕多个风扇叶片部分形成平面环。扩散器支撑环安装到风扇叶片尖端护罩，以进一步共享由叶片安装的扩散器和环形涡轮机施加到风扇叶片部分的径向载荷。

16. 发明申请

WO2006110125A2 STACKED ANNULAR COMPONENTS FOR TURBINE ENGINES 审中-公开
标题翻译：用于涡轮发动机的堆叠式环形构件
公开(公告)号：WO2006110125A2
公开(公告)日：2006-10-19
申请号：PCT/US2004/040206
申请日：2004-12-01
申请人： UNITED TECHNOLOGIES CORPORATION , SUCIU, Gabriel L. , ROBERGE, Gary D. , MERRY, Brian
发明人： SUCIU, Gabriel L. , ROBERGE, Gary D. , MERRY, Brian
IPC分类号： F01D5/34 , F01D5/06 , F01D5/02 , F02C3/073 , F02K3/068
CPC分类号： F02K3/068 , F01D5/025 , F01D5/34 , F02C3/067 , F02C3/073 , Y02T50/671 , Y10T29/49321
摘要： Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies as an example. Each compressor rotor airfoil assembly comprises an annular rotor portion, a spacer portion extending axially therefrom and a plurality of airfoils extending radially thereform. The plurality of airfoils may be integrally formed with the annular portion. The compressor rotor airfoil assemblies are stacked sequentially on a center-tie or outer circumferential tie. The spacer portion of one compressor rotor airfoil assembly abuts the annular rotor portion of the adjacent compressor rotor airfoil assembly to retain one another on the center-tied outer circumferential tie. By stacking the compressor rotor airfoil assemblies sequentially and then retaining them, the typical split cases, flanges and rotor bolts may be eliminated.
摘要翻译：作为示例，关于具有多个环形压缩机转子翼型组件的轴向压缩机来描述改进的环形部件和用于将环形部件组装到涡轮发动机中的改进方法。每个压缩机转子翼型件组件包括环形转子部分，从其轴向延伸的间隔部分和沿其径向延伸的多个翼型件。多个翼型件可以与环形部分一体地形成。压缩机转子翼型组件依次堆叠在中心系或外圆环上。一个压缩机转子翼型组件的间隔部分邻接相邻的压缩机转子翼型组件的环形转子部分，以将其彼此保持在中心连接的外圆环上。通过依次堆叠压缩机转子叶片组件然后保持它们，可以消除典型的分体式壳体，凸缘和转子螺栓。

17. 发明申请

WO2006060012A1 TIP TURBINE ENGINE COMPRISING TURBINE BLADE CLUSTERS AND METHOD OF ASSEMBLY 审中-公开
标题翻译：包括涡轮叶片组的提升涡轮发动机及其组装方法
公开(公告)号：WO2006060012A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040212
申请日：2004-12-01
申请人： UNITED TECHNOLOGIES CORPORATION , SUCIU, Gabriel L. , NORRIS, James W. , NORDEEN, Craig A.
发明人： SUCIU, Gabriel L. , NORRIS, James W. , NORDEEN, Craig A.
IPC分类号： F01D5/22 , F02K3/068 , F02C3/073 , F02C3/08 , F01D5/30
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点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

18. 发明申请

WO2006059996A1 BALANCED TURBINE ROTOR FAN BLADE FOR A TIP TURBINE ENGINE 审中-公开
标题翻译：平衡式涡轮转子风扇叶片涡轮发动机
公开(公告)号：WO2006059996A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040124
申请日：2004-12-01
申请人： UNITED TECHNOLOGIES CORPORATION , NORDEEN, Craig A. , SUCIU, Gabriel L.
发明人： NORDEEN, Craig A. , SUCIU, Gabriel L.
IPC分类号： F02C3/073 , F04D25/04 , F01D5/18 , F02K3/068
CPC分类号： F02C3/073 , F01D5/18 , F02K3/068 , F04D25/045 , F04D29/321 , Y02T50/673 , Y02T50/676
摘要： A fan-turbine rotor assembly for a tip turbine engine includes a multiple of fan blades, which include an inducer section (66), a hollow fan blade section (72) and a diffuser section (74). The hollow fan blade section defines a airflow passage (80). The core airflow is turned, spread and split toward opposite ends of the diffuser section by a multiple of internal turning vanes (122). The airflow streams are then further turned by discharge turning vanes (124) before discharge from a diffuser discharge outlet. Along with turning and splitting the core airflow, the fan blade profile balances the mass of the diffuser section such that the center of mass thereof is over the hollow airfoil section structure.
摘要翻译：用于尖端涡轮发动机的风扇涡轮转子组件包括多个风扇叶片，其包括导流部分（66），中空风扇叶片部分（72）和扩散器部分（74）。中空风扇叶片部分限定了气流通道（80）。核心气流通过多个内部转向叶片（122）转动，展开并且分散到扩散器部分的相对端部。然后在从扩散器排出口排放之前，排气转向叶片（124）进一步转动气流。随着转动和分离核心气流，风扇叶片轮廓使扩散器部分的质量平衡，使得其中心在中空翼型部分结构之上。

19. 发明申请

WO2006059993A1 TIP TURBINE ENGINE WITH MULTIPLE FAN AND TURBINE STAGES 审中-公开
标题翻译： TIP涡轮发动机具有多个风扇和涡轮机台阶
公开(公告)号：WO2006059993A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040105
申请日：2004-12-01
申请人： UNITED TECHNOLOGIES CORPORATION , NORRIS, James W. , NORDEEN, Craig A. , ROBERGE, Gary
发明人： NORRIS, James W. , NORDEEN, Craig A. , ROBERGE, Gary
IPC分类号： F02C3/073 , F02K3/068 , F02K3/072 , F02C3/067 , F02C3/14
CPC分类号： F02C3/14 , F01D5/022 , F02C3/067 , F02C3/073 , F02K3/068 , F02K3/072 , F05D2260/40311 , Y02T50/673
摘要： A tip turbine engine (10) provides first and second turbines (32) rotatably driven by a combustor (30) generating a high-energy gas stream. The first turbine (32) is mounted at an outer periphery of a first fan (24a) , such that the first fan is rotatably driven by the first turbine (32a) . The second turbine (32b) is mounted at an outer periphery of a second fan (24b) , and is rotatably driven by the high-energy gas stream. In one embodiment, the first turbine (32a) rotatably drives a plurality of stages of first compressor blades (54) in an axial compressor (22) in a first rotational direction, while the second turbine (32b) rotatably drives a plurality of stages of second compressor blades (52) in the axial compressor (22) in a second rotational direction opposite the first. By rotatably driving alternating stages of compressor blades in opposite directions, the efficiency of the axial compressor (22) is increased and/or the number of stages of compressor blades can be reduced. Other variations are described in additional embodiments.
摘要翻译：顶端涡轮发动机（10）提供由可产生高能气流的燃烧器（30）可旋转地驱动的第一和第二涡轮机（32）。第一涡轮（32）安装在第一风扇（24a）的外周，使得第一风扇由第一涡轮机（32a）旋转驱动。第二涡轮（32b）安装在第二风扇（24b）的外周，由高能气流旋转驱动。在一个实施例中，第一涡轮机（32a）在第一旋转方向上可旋转地驱动轴向压缩机（22）中的第一压缩机叶片（54）的多级，而第二涡轮（32b）可旋转地驱动多个阶段第二压缩机叶片（52）在轴向压缩机（22）中沿与第一压缩机相反的第二旋转方向。通过以相反的方向旋转地驱动压缩机叶片的交替级，轴流式压缩机（22）的效率提高和/或压缩机叶片的级数可以减少。在另外的实施例中描述了其它变型。

20. 发明申请

WO2006059992A1 INDUCER FOR A FAN BLADE OF A TIP TURBINE ENGINE 审中-公开
标题翻译：一种TIP涡轮发动机的风扇叶片的感应器
公开(公告)号：WO2006059992A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040102
申请日：2004-12-01
申请人： UNITED TECHNOLOGIES CORPORATION , SUCIU, Gabriel L. , NORDEEN, Craig A. , MERRY, Brian
发明人： SUCIU, Gabriel L. , NORDEEN, Craig A. , MERRY, Brian
IPC分类号： F02C3/073 , F02K3/068 , F02C3/08
CPC分类号： F01D5/022 , F02C3/073 , F02C3/08 , F02K3/068 , F05D2260/60 , Y02T50/672
摘要： A fan-turbine rotor assembly for a tip turbine engine includes an inducer with an inducer inlet section and an inducer passage section in communication with a core airflow passage within a fan blade. Each inducer inlet section is canted toward a rotational direction of the fan-turbine rotor assembly such that the inducer inlet section operates as an air scoop during rotation of the fan-turbine rotor assembly. Both axial and centrifugal compression of the airflow occurs within the inducer passage section to effectively pump the airflow through the inducer section and into the core airflow passage.
摘要翻译：用于顶端涡轮发动机的风扇涡轮转子组件包括具有导流器入口部分和与风扇叶片内的气流通道连通的导流通道部分的导流器。每个诱导器入口部分朝着风扇 - 涡轮转子组件的旋转方向倾斜，使得在风扇 - 涡轮转子组件旋转期间，导流器入口部分作为空气铲斗操作。气流的轴向和离心压缩都发生在导流通道部分内，以有效地泵送通过导流部分并进入芯气流通道的气流。

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