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

WO2006060013A1 SEAL ASSEMBLY FOR A FAN ROTOR OF A TIP TURBINE ENGINE 审中-公开
标题翻译：涡轮发动机风扇转子的密封组件
公开(公告)号：WO2006060013A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040214
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： F01D11/001 , F01D11/003 , F02C3/073 , F02C7/28 , F02K3/068 , F04D25/045 , F04D29/083 , F04D29/162 , F05D2240/52 , F05D2240/54 , F05D2240/56
摘要： A seal assembly (118) mounted within a nonrotatable static inner support structure (16) for engagement with an axial seal face surface (114) and a radial seal face surface (116). The radial seal (120) engages the axial seal face surface and the axial seal (122) engages the radial seal face surface. The seal assembly provides minimal leakage of core airflow to increase the tip turbine engine operating efficiency.
摘要翻译：安装在不可旋转的静态内支撑结构（16）内的密封组件（118），用于与轴向密封面表面（114）和径向密封面表面（116）接合。径向密封件（120）接合轴向密封面表面并且轴向密封件（122）接合径向密封面表面。密封组件提供核心气流的最小泄漏以增加顶端涡轮发动机的运行效率。

2. 发明申请

WO2006060010A1 COMPRESSOR INLET GUIDE VANE FOR TIP TURBINE ENGINE AND CORRESPONDING CONTROL METHOD 审中-公开
标题翻译：压缩机入口引导涡轮发动机叶片和相应的控制方法
公开(公告)号：WO2006060010A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040207
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： F02C3/073 , F02K3/068 , F02C9/18 , F01D17/16 , F04D27/02 , F02C7/057 , F01D5/18
CPC分类号： F01D17/14 , F01D5/022 , F01D5/147 , F01D5/148 , F01D9/06 , F01D17/162 , F02C3/073 , F02K3/068 , F04D25/045 , F04D27/0246 , F05D2270/10 , Y02T50/671 , Y02T50/673
摘要： A tip turbine engine (30) includes a low pressure compressor (22) having a plurality of inlet guide vanes (55) that are mounted at an inlet to the compressor case (50). Each inlet guide vane (55) includes at least one fluid outlet (56) proximate a trailing edge of the inlet guide vane (55), such that fluid flow through the fluid outlet (56) modulates and controls the air flow into the compressor (22). A supply of pressurized fluid may be supplied from compressed air from the compressor (22).
摘要翻译：顶端涡轮发动机（30）包括具有多个入口导向叶片（55）的低压压缩机（22），其安装在压缩机壳体（50）的入口处。每个入口引导叶片（55）包括靠近入口引导叶片（55）的后缘的至少一个流体出口（56），使得流过流体出口（56）的流体流体调节并控制进入压缩机的空气流 22）。可以从压缩机（22）的压缩空气供应加压流体。

3. 发明申请

WO2006060005A1 FAN-TURBINE ROTOR ASSEMBLY WITH INTEGRAL INDUCER SECTION FOR A TIP TURBINE ENGINE 审中-公开
标题翻译：风机涡轮发电机整体电机部分的风机转子总成
公开(公告)号：WO2006060005A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040174
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： F02C3/073 , F02K3/068 , F02C3/08
CPC分类号： F01D5/022 , F02C3/073 , F02C3/08 , F02K3/068 , F05D2260/60
摘要： A fan-turbine rotor assembly for a tip turbine engine includes a fan hub with an outer periphery scalloped by a multitude of elongated openings which extend into a fan hub web. Each elongated opening defines an inducer section and a blade receipt section to retain a hollow fan blade section. The blade receipt section retains each of the hollow fan blade sections adjacent each inducer section. The inducer sections are cast directly into the fan hub which minimizes leakage between each fan blade section and each of the respective inducer sections to minimize airflow leakage and increase engine efficiency.
摘要翻译：用于顶端涡轮发动机的风扇涡轮机转子组件包括具有外部扇形的风扇轮毂，所述外部圆周由多个延伸到风扇轮毂网中的细长开口扇形。每个细长的开口限定了一个导流部分和一个叶片接收部分，以保持中空的风扇叶片部分。刀片接收部分将每个中空风扇叶片部分保持在每个诱导部分附近。导流器部分直接浇注到风扇毂中，从而最小化每个风扇叶片部分和每个相应的诱导部分之间的泄漏，以最小化气流泄漏并提高发动机效率。

4. 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。

5. 发明申请

WO2006060003A2 FAN BLADE WITH INTEGRAL DIFFUSER SECTION AND TIP TURBINE BLADE SECTION FOR A TIP TURBINE ENGINE 审中-公开
标题翻译：具有整体式发动机部分的风扇叶片和提升涡轮发动机的提升涡轮叶片部分
公开(公告)号：WO2006060003A2
公开(公告)日：2006-06-08
申请号：PCT/US2004/040170
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
CPC分类号： F01D5/3007 , F01D1/023 , F01D1/06 , F01D5/022 , F01D5/147 , F01D5/30 , Y02T50/672
摘要： A fan-turbine rotor assembly for a tip turbine engine includes an outer periphery scalloped by a multitude of elongated openings which define an inducer receipt section to receive an inducer section and a hollow fan blade section. Each fan blade section includes a turbine section which extends from a diffuser section.
摘要翻译：用于尖端涡轮发动机的风扇涡轮机转子组件包括由许多细长开口扇形的外周，所述多个细长的开口限定了用于接纳导流部分和中空的风扇叶片部分的诱导器接收部分。每个风扇叶片部分包括从扩散器部分延伸的涡轮部分。

6. 发明申请

WO2006059997A2 ANNULAR TURBINE RING ROTOR 审中-公开
标题翻译：环形涡轮机转子
公开(公告)号：WO2006059997A2
公开(公告)日：2006-06-08
申请号：PCT/US2004/040125
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
CPC分类号： F01D11/02 , F01D5/30
摘要： A fan-turbine rotor assembly includes one or more turbine ring rotors. Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring includes axial installation and radial locking of each turbine ring rotor.
摘要翻译：风扇 - 涡轮转子组件包括一个或多个涡轮机环形转子。每个涡轮机环形转子都被铸造为一个整体的环形环。通过将涡轮机形成为一个或多个环，相邻的叶片平台之间的泄漏被最小化，这提高了发动机效率。涡轮环转子到扩散器环的组装包括每个涡轮环转子的轴向安装和径向锁定。

7. 发明申请

WO2006059969A1 COUNTER-ROTATING COMPRESSOR CASE AND ASSEMBLY METHOD FOR TIP TURBINE ENGINE 审中-公开
标题翻译：逆向旋转压缩机壳体和TIP涡轮发动机的组装方法
公开(公告)号：WO2006059969A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/039971
申请日：2004-12-01
申请人： UNITED TECHNOLOGIES CORPORATION , MERRY, Brian , SUCIU, Gabriel L. , NORRIS, James W. , NORDEEN, Craig A.
发明人： MERRY, Brian , SUCIU, Gabriel L. , NORRIS, James W. , NORDEEN, Craig A.
IPC分类号： F02C3/067 , F02K3/068 , F02C3/073 , F01D25/24
CPC分类号： F01D5/022 , F01D25/24 , F02C3/067 , F02C3/073 , F02K3/068 , F05D2230/60
摘要： A tip turbine engine (10) provides an axial compressor (22) having a compressor case (50) from which extend radially inwardly a plurality of outer compressor airfoils (54). The compressor case (50) is directly driven by the rotation of the turbine (32) and fan (28), while at least one gear (77) couples the rotation of the turbine (32) and fan (28) to an axial compressor rotor (46) having a plurality of inner compressor airfoils (52). In this manner, the axial compressor rotor (46) is driven in a direction opposite the direction of the outer compressor airfoils (54), thereby increasing the compression provided by the compressor without increasing the number of airfoils. The outer compressor airfoils (54) are formed on a plurality of outer airfoil assemblies (56) each having an arcuate substratem (58) from which the outer compressor airfoils (54) extend. Each of the outer compressor airfoil assemblies (56) includes more than one axially-spaced stage of outer compressor airfoils (54). For assembly, the outer compressor airfoil assemblies (56) are moved toward the axial compressor rotor (46) and then inserted into the compressor case (50).
摘要翻译：顶端涡轮发动机（10）提供具有压缩机壳体（50）的轴向压缩机（22），径向向内延伸有多个外部压缩机翼型件（54）。压缩机壳体（50）由涡轮机（32）和风扇（28）的旋转直接驱动，而至少一个齿轮（77）将涡轮机（32）和风扇（28）的旋转与轴向压缩机转子（46）具有多个内部压缩机翼型件（52）。以这种方式，轴向压缩机转子（46）沿与外压缩机翼片（54）的方向相反的方向被驱动，从而增加由压缩机提供的压缩而不增加翼型件的数量。外压缩机翼片（54）形成在多个具有弓形基板（58）的外翼型组件（56）上，外压缩机翼型件（54）从该外形翼片组件延伸。每个外部压缩机翼型组件（56）包括多于一个轴向隔开的外压缩机翼片（54）。为了组装，外压缩机翼型组件（56）朝向轴向压缩机转子（46）移动，然后插入压缩机壳体（50）中。

8. 发明申请

WO2006060009A1 TURBINE BLADE ENGINE COMPRISING TURBINE CLUSTERS AND RADIAL ATTACHMENT LOCK ARRANGEMENT THEREFOR 审中-公开
标题翻译：涡轮叶片发动机包括涡轮机组和径向附件锁定装置
公开(公告)号：WO2006060009A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040205
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： F02K3/068 , F02C3/073 , F02C3/08 , F01D5/22 , F01D5/30
CPC分类号： F02C3/08 , F01D5/225 , F01D5/3007 , F02C3/073 , F02K3/068 , F05D2260/30 , F05D2260/33 , Y10T29/49245
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. By forming the turbine blades in clusters, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine blade clusters to a diffuser surface includes axial installation and radial locking of each turbine blade cluster. This is accomplished by attachment lugs protruding from the underside of the arcuate base of the turbine blade clusters. Torque load surfaces are also integrated into the arcuate base.
摘要翻译：顶端涡轮发动机包括风扇 - 涡轮转子组件，其包括一个或多个涡轮环形转子。每个涡轮环由多个涡轮机叶片组装配。通过将涡轮机叶片组成簇，相邻叶片平台之间的泄漏被最小化，这提高了发动机效率。将涡轮机叶片组组装到扩散器表面包括每个涡轮叶片组的轴向安装和径向锁定。这是通过从涡轮机叶片组的弧形底部的下侧突出的附接凸耳来实现的。扭矩负载表面也集成在弧形底座中。

9. 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。

10. 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

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