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公开(公告)号：US08672630B2
公开(公告)日：2014-03-18
申请号：US13350937
申请日：2012-01-16
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最小化，这增加了发动机效率。 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。
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公开(公告)号：US08468795B2
公开(公告)日：2013-06-25
申请号：US11718525
申请日：2004-12-01
IPC分类号： F02K3/02
摘要： A fan-turbine rotor assembly includes a diffuser section (114) which turns and diffuses the airflow from a radial core airflow passage (80) toward an axial airflow direction. Diffuser flow passages communicate with the diffuser passages (144) at a location which reduces separation of the airflow as the airflow is turned from the radial core airflow passage (80) 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（114），其将来自径向芯气流通道（80）的气流朝向轴向气流方向扩散。 扩散器流动通道在一个位置处与扩散通道（144）连通，当气流从径向核心气流通道（80）通过在潜在湍流位置处的气流抽吸朝向轴向气流方向转动时，气流的分离减小。
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公开(公告)号：US08033092B2
公开(公告)日：2011-10-11
申请号：US11720539
申请日：2004-12-01
IPC分类号： F02K3/02
CPC分类号： F01D5/187 , F01D1/023 , F01D5/022 , F01D21/045 , F02C3/045 , F02C3/08 , F02C3/107 , F05D2300/433 , Y02T50/676
摘要： A tip turbine engine assembly includes an integral engine outer case located radially outward from a fan assembly. The integral outer case includes a rear portion and a forward portion with an arcuate portion that curves radially inwardly to form a compartment. An annular combustor is housed and mounted in the compartment. Fan inlet guide vanes are integrally formed with the arcuate portion to form the integral case portion. The rear portion, forward portion, and fan inlet guide vanes are integrally formed in a casting process.
摘要翻译： 顶端涡轮发动机组件包括从风扇组件径向向外定位的一体式发动机外壳。 一体的外壳包括后部和具有弓形部分的向前部分，其径向向内弯曲以形成隔间。 环形燃烧器容纳并安装在隔室中。 风扇入口导向叶片与弓形部分一体地形成，以形成一体的壳体部分。 后部，前部和风扇入口导向叶片在铸造过程中一体地形成。
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公开(公告)号：US07927075B2
公开(公告)日：2011-04-19
申请号：US11719757
申请日：2004-12-01
CPC分类号： F01D5/02 , F01D5/022 , F01D5/3007 , F02C3/073 , F02K3/068 , F04D25/045 , F04D29/54 , F05D2240/55 , F05D2260/30 , F05D2300/603 , Y02T50/672 , Y10T29/49321
摘要： A fan-turbine rotor assembly (24) for a tip turbine engine (10 )includes a fan hub (64) with an outer periphery (112) scalloped by a multitude of elongated openings (114) which extend into a fan hub web (115). Each elongated opening defines an inducer receipt section (117) to receive an inducer section (66)and a hollow fan blade section (72). An inducer exhaust from each inducer section is located adjacent a core airflow passage (80) within each fan blade section to provide communication therebetween.
摘要翻译： 一种用于尖端涡轮发动机（10）的风扇涡轮机转子组件（24）包括风扇轮毂（64），其具有由多个细长的开口（114）扇形的外周边（112），所述多个细长的开口延伸到风扇轮毂腹板 ）。 每个细长的开口限定了一个诱导器收容部分（117），用于容纳一个导流部分（66）和一个中空的风扇叶片部分（72）。 来自每个引导部分的诱导物排放物位于每个风扇叶片部分内的核心气流通道80附近，以在它们之间提供连通。
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公开(公告)号：US07921635B2
公开(公告)日：2011-04-12
申请号：US11719221
申请日：2004-12-01
IPC分类号： F02K3/02
CPC分类号： F02C3/073 , F02C3/14 , F02K3/068 , F05D2250/311
摘要： A tip turbine engine (40) provides a peripheral combustor (30) with a more efficient combustion path through the combustor and through the tip turbine blades (34). In the combustor, the core airflow is received generally axially from compressor chambers in hollow fan blades (28) and then turned radially outwardly into a combustion chamber (112), where it is then mixed with the fuel and ignited. The combustor has a combustion path extending axially from a forward end of its combustion chamber through a combustion chamber outlet (122) and through a turbine (32) mounted to the fan. Thus, when the core airflow begins to expand in a high-energy gas stream, it has a substantially axial path from the combustion chamber through the turbine.
摘要翻译： 尖端涡轮发动机（40）为周边燃烧器（30）提供通过燃烧器和尖端涡轮机叶片（34）的更有效的燃烧路径。 在燃烧器中，核心气流从中空风扇叶片（28）中的压缩机室大致轴向地接收，然后径向向外转入燃烧室（112），然后与燃料混合并点燃。 燃烧器具有从其燃烧室的前端轴向延伸通过燃烧室出口（122）并通过安装到风扇的涡轮机（32）的燃烧路径。 因此，当核心气流在高能量气流中开始膨胀时，其具有从燃烧室通过涡轮机的基本上轴向的路径。
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公开(公告)号：US20090169386A1
公开(公告)日：2009-07-02
申请号：US11719855
申请日：2004-12-01
IPC分类号： F01D5/22
摘要： A fan-turbine rotor assembly (24) includes one or more turbine ring rotors (32). 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 (114) includes axial installation and radial locking of each turbine ring rotor.
摘要翻译： 风扇 - 涡轮转子组件（24）包括一个或多个涡轮环转子（32）。 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最小化，这增加了发动机效率。 涡轮环转子到扩散器环（114）的组装包括每个涡轮环转子的轴向安装和径向锁定。
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7.发明申请FAN-TURBINE ROTOR ASSEMBLY WITH INTEGRAL INDUCER SECTION FOR A TIP TURBINE ENGINE 审中-公开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：US20090169385A1
公开(公告)日：2009-07-02
申请号：US11719854
申请日：2004-12-01
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。
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公开(公告)号：US20090148276A1
公开(公告)日：2009-06-11
申请号：US11719543
申请日：2004-12-01
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。
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9.发明申请COMPRESSOR INLET GUIDE VANE FOR TIP TURBINE ENGINE AND CORRESPONDING CONTROL METHOD 审中-公开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：US20090148273A1
公开(公告)日：2009-06-11
申请号：US11719812
申请日：2004-12-01
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。
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公开(公告)号：US20090142188A1
公开(公告)日：2009-06-04
申请号：US11719296
申请日：2004-12-01
IPC分类号： F01D11/08
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。
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