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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：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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4.发明授权公开(公告)号：US08061968B2
公开(公告)日：2011-11-22
申请号：US11719892
申请日：2004-12-01
IPC分类号： F01D1/24
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 substrate (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）形成在多个外翼型组件（56）上，每个外翼型组件（56）具有弓形基板（58），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。
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5.发明申请COUNTER-ROTATING COMPRESSOR CASE AND ASSEMBLY METHOD FOR TIP TURBINE ENGINE 有权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：US20090162187A1
公开(公告)日：2009-06-25
申请号：US11719892
申请日：2004-12-01
IPC分类号： F01D1/24
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 substrate (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）形成在多个外翼型组件（56）上，每个外翼型组件（56）具有弓形基板（58），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。
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公开(公告)号：US20090148297A1
公开(公告)日：2009-06-11
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：US20090120058A1
公开(公告)日：2009-05-14
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
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是一体的
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公开(公告)号：US20120121425A1
公开(公告)日：2012-05-17
申请号：US13350937
申请日：2012-01-16
IPC分类号： F01D5/22
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：US07883315B2
公开(公告)日：2011-02-08
申请号：US11719543
申请日：2004-12-01
IPC分类号： F01D11/00
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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公开(公告)号：US07883314B2
公开(公告)日：2011-02-08
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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