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71. 发明授权

US07901185B2 Variable rotor blade for gas turbine engine 有权
标题翻译：用于燃气轮机的可变转子叶片
公开(公告)号：US07901185B2
公开(公告)日：2011-03-08
申请号：US11709013
申请日：2007-02-21
申请人： Gabriel L. Suciu , Craig A. Nordeen
发明人： Gabriel L. Suciu , Craig A. Nordeen
IPC分类号： B64C11/44
CPC分类号： F01D7/02 , F01D5/148 , F01D5/30 , F04D29/323 , F05D2220/36 , F05D2260/71 , F05D2260/74 , F05D2260/76 , F05D2260/79 , Y02T50/673 , Y10S416/05
摘要： A variable rotor blade mechanism for use in a gas turbine engine comprises a blade rotor, a blade, a harmonic drive system, a stepper motor and a bracket. The blade rotor rotates absolutely about an axial engine centerline during operation of the gas turbine engine. The blade extends radially from the blade rotor and is configured to be adjustable by rotation about a radial axis. The harmonic drive system is mounted to the blade rotor and connected to the blade to rotate the blade about the radial axis. The stepper motor drives the harmonic drive with relative rotational input with respect to the absolute rotation of the blade rotor. The bracket is disposed about the engine centerline and supports the stepper motor stationary with respect to the rotation of blade rotor such that the relative rotational input to the stepper motor is generated.
摘要翻译：用于燃气涡轮发动机的可变转子叶片机构包括叶片转子，叶片，谐波驱动系统，步进马达和支架。在燃气涡轮发动机的运行期间，叶片转子绝对围绕轴向发动机中心线旋转。叶片从叶片转子径向延伸并且构造成通过围绕径向轴线的旋转来调节。谐波驱动系统安装到叶片转子并连接到叶片以使叶片围绕径向轴线旋转。步进电机以相对于叶片转子的绝对转动的相对旋转输入驱动谐波驱动器。支架围绕发动机中心线设置，并且相对于叶片转子的旋转支撑步进马达固定，使得产生对步进马达的相对旋转输入。

72. 发明授权

US07883315B2 Seal assembly for a fan rotor of a tip turbine engine 有权
标题翻译：尖端涡轮发动机的风扇转子的密封组件
公开(公告)号：US07883315B2
公开(公告)日：2011-02-08
申请号：US11719543
申请日：2004-12-01
申请人： Gabriel L. Suciu , James W. Norris , Craig A. Nordeen , Brian Merry
发明人： Gabriel L. Suciu , James W. Norris , Craig A. Nordeen , Brian Merry
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。

73. 发明授权

US07883314B2 Seal assembly for a fan-turbine rotor of a tip turbine engine 有权
标题翻译：尖端涡轮发动机的风机 - 涡轮转子的密封组件
公开(公告)号：US07883314B2
公开(公告)日：2011-02-08
申请号：US11719296
申请日：2004-12-01
申请人： Gabriel L. Suciu , James W. Norris , Craig A. Nordeen , Brian Merry
发明人： Gabriel L. Suciu , James W. Norris , Craig A. Nordeen , Brian Merry
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。

74. 发明授权

US07882694B2 Variable fan inlet guide vane assembly for gas turbine engine 有权
标题翻译：用于燃气轮机的可变风机入口导叶组件
公开(公告)号：US07882694B2
公开(公告)日：2011-02-08
申请号：US11719143
申请日：2004-12-01
申请人： Gabriel L. Suciu , Brian Merry , James W. Norris , Steven J. Sirica
发明人： Gabriel L. Suciu , Brian Merry , James W. Norris , Steven J. Sirica
IPC分类号： F02K3/02
CPC分类号： F01D17/162 , F02C3/073 , F02K3/068
摘要： A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes.
摘要翻译：涡轮发动机包括多个可变风扇入口导向叶片。在涡轮发动机是顶端涡轮发动机的情况下，即使风扇 - 涡轮转子组件以固定的速率直接联接到轴向压缩机，可变风扇入口导叶允许控制发动机稳定性的能力。风扇入口导向叶片可以从风扇入口导叶的内径致动。

75. 发明授权

US07878762B2 Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor 有权
标题翻译：涡轮发动机包括涡轮机组和其径向附接锁定装置
公开(公告)号：US07878762B2
公开(公告)日：2011-02-01
申请号：US11718517
申请日：2004-12-01
申请人： Gabriel L. Suciu , James W. Norris , Craig A. Nordeen
发明人： Gabriel L. Suciu , James W. Norris , Craig A. Nordeen
IPC分类号： 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。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。

76. 发明授权

US07631485B2 Tip turbine engine with a heat exchanger 有权
标题翻译：带涡轮发动机的带热交换器
公开(公告)号：US07631485B2
公开(公告)日：2009-12-15
申请号：US11718429
申请日：2004-12-01
申请人： Gabriel L. Suciu , Brian Merry
发明人： Gabriel L. Suciu , Brian Merry
IPC分类号： F02C3/073
CPC分类号： F01D25/20 , F01D15/12 , F01D25/12 , F02C3/073 , F02C7/32 , F02K3/068 , Y02T50/675
摘要： A liquid-air heat exchanger extracts thermal energy from an engine lubricating fluid system. The liquid-air heat exchanger is located within a tailcone section and is in communication with a portion of the fan bypass airflow which enters the tailcone section through an annular tailcone exhaust nozzle entrance to transfer thermal energy into the combined airflow out of the engine to recover thrust loss ducted from the fan bypass stream.
摘要翻译：液体 - 空气热交换器从发动机润滑流体系统中提取热能。液体 - 空气热交换器位于尾部部分内，并且与通过环形尾气排气喷嘴入口进入尾部部分的风扇旁路气流的一部分连通，以将热能传递到从发动机外部的组合气流中以回收从风扇旁路流引导的推力损失。

77. 发明申请

US20090188234A1 SHARED FLOW THERMAL MANAGEMENT SYSTEM 有权
标题翻译：共享流量热管理系统
公开(公告)号：US20090188234A1
公开(公告)日：2009-07-30
申请号：US12019837
申请日：2008-01-25
申请人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye
发明人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye
IPC分类号： F02K3/02 , F02C7/12 , F02C7/18
CPC分类号： F02K3/115 , F02C7/14 , F02C7/185 , F02C7/224 , Y02T50/671 , Y02T50/675
摘要： A thermal management system includes at least two of a multiple of heat exchangers arranged in an at least partial-series relationship.
摘要翻译：热管理系统包括以至少部分系列关系布置的多个热交换器中的至少两个。

78. 发明申请

US20090188232A1 THERMAL MANAGEMENT SYSTEM INTEGRATED PYLON 有权
标题翻译：热管理系统集成PYLON
公开(公告)号：US20090188232A1
公开(公告)日：2009-07-30
申请号：US12020728
申请日：2008-01-28
申请人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye
发明人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye
IPC分类号： F02C7/141 , F02C6/08
CPC分类号： F02K3/06 , B64D27/18 , B64D29/00 , B64D33/10 , F02C6/08 , F02C7/14 , F02C7/185 , F02C7/224 , F02K3/115 , Y02T50/44 , Y02T50/671 , Y02T50/675
摘要： A thermal management system includes at least one heat exchanger in communication with a bypass flow of a gas turbine engine. The placement of the heat exchanger(s) minimizes weight and aerodynamic losses and contributes to overall performance increase over traditional ducted heat exchanger placement schemes.
摘要翻译：热管理系统包括与燃气涡轮发动机的旁路流相通的至少一个热交换器。热交换器的放置使重量和空气动力学损失最小化，并且有助于整体性能提高超过传统的管道式热交换器放置方案。

79. 发明申请

US20090180864A1 GAS TURBINE ENGINE CASE 有权
标题翻译：气体涡轮发动机箱
公开(公告)号：US20090180864A1
公开(公告)日：2009-07-16
申请号：US12013617
申请日：2008-01-14
申请人： Ioannis Alvanos , Gabriel L. Suciu , Brian D. Merry
发明人： Ioannis Alvanos , Gabriel L. Suciu , Brian D. Merry
IPC分类号： F01D25/24 , B23P15/04
CPC分类号： F01D25/24 , F01D25/243 , F01D25/246 , F05D2230/60 , Y02T50/671 , Y10T29/49826
摘要： A case for a gas turbine engine includes a single-piece case that includes a combustor case portion and a turbine case portion that is integrally formed with the combustor case portion as one piece. In one example, the single-piece case includes a transition duct/mid-turbine frame case portion is integrally formed with the combustor and turbine case portions.
摘要翻译：燃气涡轮发动机的壳体包括单件壳体，其包括燃烧器壳体部分和与燃烧器壳体部分一体形成为一体的涡轮壳体部分。在一个示例中，单件式壳体包括过渡管道/中涡轮机壳体部分，其与燃烧器和涡轮机壳体部分整体形成。

80. 发明申请

US20090148287A1 FAN BLADE WITH INTEGRAL DIFFUSER SECTION AND TIP TURBINE BLADE SECTION FOR A TIP TURBINE ENGINE 有权
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：US20090148287A1
公开(公告)日：2009-06-11
申请号：US11719755
申请日：2004-12-01
申请人： Gabriel L. Suciu , James W. Norris , Craig A. Nordeen , Brian Merry
发明人： Gabriel L. Suciu , James W. Norris , Craig A. Nordeen , Brian Merry
IPC分类号： F01D5/18
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，所述多个细长开口限定了用于容纳导流部分和中空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。

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