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1. 发明授权

US10072570B2 Reverse flow gas turbine engine core 有权
公开(公告)号：US10072570B2
公开(公告)日：2018-09-11
申请号：US14651801
申请日：2013-01-28
申请人： United Technologies Corporation
发明人： Daniel Bernard Kupratis
IPC分类号： F02C3/06 , F01D1/04 , F02K1/78 , F02K3/075 , F02C3/14
CPC分类号： F02C3/06 , F01D1/04 , F02C3/145 , F02K1/78 , F02K3/075 , F05D2250/31
摘要： A gas turbine engine has a fan rotor for delivering air into a bypass duct and into a core airflow duct. Air in the core flow duct passes axially downstream from the fan and past a reverse core engine including a turbine section, a combustor section, and a compressor section. The core airflow duct reaches a turning duct which turns the airflow radially inwardly to communicate with an inlet for the compressor section. Air in the compressor section passes to the combustor section. Products of the combustion pass downstream across a turbine rotor. An exhaust turning duct communicates products of the combustion from a full cylindrical portion downstream of the turbine rotor through a plurality of circumferentially separated mixing lobe outlets to mix with the bypass air in the bypass duct. The bypass duct extends past the mixing lobe outlets, and is defined circumferentially intermediate the mixing lobe outlets.

2. 发明授权

US09933012B1 Bearing centering spring with integral outer rings 有权
公开(公告)号：US09933012B1
公开(公告)日：2018-04-03
申请号：US14616990
申请日：2015-02-09
申请人： United Technologies Corporation
发明人： Joseph Grillo , Kevin Duffy , Ronnie K. Kovacik
IPC分类号： F16C27/00 , F16C27/04
CPC分类号： F16C33/605 , F01D25/162 , F01D25/164 , F02C7/06 , F05D2230/64 , F05D2240/50 , F05D2250/31 , F05D2250/36 , F05D2250/37 , F16C19/28 , F16C19/54 , F16C27/04 , F16C27/045 , F16C33/581 , F16C2226/50 , F16C2240/40 , F16C2360/23
摘要： A bearing centering spring includes a cylindrical body with outer rings at each end, wherein each outer ring has outer raceways on the inner surface of the body. There is also a retaining feature on an end of the body and ports through the body that are positioned between the outer rings.

3. 发明授权

US09724791B2 Aircraft engine rotor assembly method and device 有权
公开(公告)号：US09724791B2
公开(公告)日：2017-08-08
申请号：US15118803
申请日：2014-12-26
申请人： HARBIN INSTITUTE OF TECHNOLOGY
发明人： Bo Zhao , Lei Wang , Jiubin Tan , Chuanzhi Sun
IPC分类号： B23P15/04 , G01B5/20 , F01D25/28 , F01D5/00 , G01B5/207 , F01D5/02
CPC分类号： B23P15/04 , F01D5/005 , F01D5/02 , F01D5/027 , F01D5/26 , F01D25/285 , F05D2220/323 , F05D2230/64 , F05D2250/31 , G01B5/205 , G01B5/207
摘要： Aircraft engine rotors traditionally have low coaxiality after assembly. This is solved by the methods and devices described herein, having advantages that the rotors have high coaxiality after assembly, reduced vibration, easy installation, high flexibility, and improved engine performance. A measurement method and device use an air flotation rotary shaft system determining a rotary reference. An induction synchronizer determines angular positioning of a turntable. Using a four probe measurement device, a radial error of a rotor radial assembly surface and an inclination error of an axial mounting surface are extracted and an influence weight value of the rotor on the coaxiality of assembled rotors is obtained. All rotors required for assembly are measured and an influence weight value of each on the coaxiality of the assembled rotors is obtained. Vector optimization is performed on the weight value of each rotor and an assembly angle of each rotor is obtained.

4. 发明申请

US20170050275A1 AIRCRAFT ENGINE ROTOR ASSEMBLY METHOD AND DEVICE 有权
标题翻译：飞机发动机转子总成方法和装置
公开(公告)号：US20170050275A1
公开(公告)日：2017-02-23
申请号：US15118803
申请日：2014-12-26
申请人： HARBIN INSTITUTE OF TECHNOLOGY
发明人： Bo ZHAO , Lei WANG , Jiubin TAN , Chuanzhi SUN
IPC分类号： B23P15/04 , G01B5/207 , F01D5/02 , G01B5/20
CPC分类号： B23P15/04 , F01D5/005 , F01D5/02 , F01D5/027 , F01D5/26 , F01D25/285 , F05D2220/323 , F05D2230/64 , F05D2250/31 , G01B5/205 , G01B5/207
摘要： Aircraft engine rotors traditionally have low coaxiality after assembly. This is solved by the methods and devices described herein, having advantages that the rotors have high coaxiality after assembly, reduced vibration, easy installation, high flexibility, and improved engine performance. A measurement method and device use an air flotation rotary shaft system determining a rotary reference. An induction synchronizer determines angular positioning of a turntable. Using a four probe measurement device, a radial error of a rotor radial assembly surface and an inclination error of an axial mounting surface are extracted and an influence weight value of the rotor on the coaxiality of assembled rotors is obtained. All rotors required for assembly are measured and an influence weight value of each on the coaxiality of the assembled rotors is obtained. Vector optimization is performed on the weight value of each rotor and an assembly angle of each rotor is obtained.
摘要翻译：飞机发动机转子在组装后传统上具有低同轴度。这通过本文所述的方法和装置来解决，其优点在于转子在组装之后具有高的同轴度，减少的振动，易于安装，高灵活性和改进的发动机性能。测量方法和装置使用确定旋转参考的空气浮选旋转轴系统。感应同步器确定转台的角度定位。使用四探头测量装置，提取转子径向组件表面的径向误差和轴向安装表面的倾斜误差，并且获得转子对组装转子同轴度的影响重量值。测量组装所需的所有转子，并且获得各组合转子的同轴度的影响重量值。对每个转子的重量值执行向量优化，并获得每个转子的组装角度。

5. 发明申请

US20150377125A1 REVERSE-FLOW CORE GAS TURBINE ENGINE WITH A PULSE DETONATION SYSTEM 审中-公开
标题翻译：具有脉冲爆震系统的反向流核心燃气涡轮发动机
公开(公告)号：US20150377125A1
公开(公告)日：2015-12-31
申请号：US14764186
申请日：2013-01-29
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Daniel B. Kupratis , Francis R Moon
IPC分类号： F02C3/14 , F02C3/107
CPC分类号： F02C3/145 , F02C3/107 , F02C3/14 , F02C5/02 , F02C7/06 , F02C7/36 , F02K3/06 , F02K3/11 , F05D2250/31 , F05D2250/311 , F05D2260/16 , F23G7/065 , F23R7/00
摘要： The engine (10) includes a low spool (16) disposed aft of an air inlet (12) and a high spool (34) disposed aft of the low spool (16). An intake reverse-duct (44) is disposed radially outward of the high spool (34) and reverses direction of low pressure compressed air from the low spool (16) into a forward-flow high pressure compressor (40) of the high spool (34). A discharge reverse-manifold (48) directs flow of an exhaust gas stream (50} from a forward-flow low pressure turbine (20) into a rearward-flow direction and into at least one pulse detonation firing tube (54). An annular bypass air duct (72) directs cooling air along the engine (10)—The at least, one firing tube is positioned radially outward of the high spool (34), overlies the high spool (34) and is also positioned within the bypass air duct (72).
摘要翻译：发动机（10）包括设置在空气入口（12）后面的低阀芯（16）和设置在低阀芯（16）后面的高阀芯。进气反向管道（44）设置在高阀芯（34）的径向外侧，并将低压压缩空气的方向从低阀芯（16）反向转向高阀芯的前进高压压缩机（40） 34）。排放反向歧管（48）引导排气流（50）从前向流动的低压涡轮（20）流向向后流动方向并进入至少一个脉冲爆燃发射管（54），环形旁路空气管道（72）沿着发动机（10）引导冷却空气 - 至少一个发射管定位在高线轴（34）的径向外侧，覆盖在高线轴（34）上，并且还位于旁路空气导管（72）。

6. 发明申请

US20150369134A1 Reverse Core Gas Turbine Engine with High Temperature Third Stream 有权
标题翻译：逆向核燃料涡轮发动机与高温第三流
公开(公告)号：US20150369134A1
公开(公告)日：2015-12-24
申请号：US14759979
申请日：2013-01-28
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Daniel Bernard Kupratis
IPC分类号： F02C9/18 , F02K3/10 , F02C3/14 , F02K3/02 , F02C3/04 , F02C7/08
CPC分类号： F02C9/18 , F01D1/04 , F02C3/04 , F02C3/145 , F02C7/08 , F02K1/78 , F02K3/025 , F02K3/075 , F02K3/077 , F02K3/10 , F05D2220/32 , F05D2250/31
摘要： A gas turbine engine has a fan rotor for delivering air axially downstream into a core engine duct, which sequentially passes a turbine, a combustor, and a compressor. The core engine duct extends to a turning supply duct configured to turn the core air flow axially upstream so that the core air sequentially passes through the compressor, combustor and turbine, and into an exhaust conduit which turns the core airflow radially outwardly and axially downstream into an exhaust duct. A door is selectively opened to communicate a portion of the core airflow in the core engine duct to an augmentor with the exhaust duct isolated from the augmentor. The door is at a location prior to the core airflow reaching the compressor. A method is also disclosed.
摘要翻译：燃气涡轮发动机具有用于将轴向下游的空气输送到核心发动机管道的风扇转子，所述核心发动机管道依次通过涡轮机，燃烧器和压缩机。核心发动机管道延伸到转向供应管道，该转向供应管道构造成使核心空气流轴向上游，使得核心空气顺序地通过压缩机，燃烧器和涡轮机，并进入排气管道，该排气管道将核心气流径向向外和轴向下游转入排气管。选择性地打开门以将核心发动机管道中的核心气流的一部分与增压器通信，排气管与增压器隔离。门处于核心气流到达压缩机之前的位置。还公开了一种方法。

7. 发明申请

US20130111923A1 GAS TURBINE ENGINE COMPONENT AXIS CONFIGURATIONS 审中-公开
标题翻译：气体涡轮发动机组件轴配置
公开(公告)号：US20130111923A1
公开(公告)日：2013-05-09
申请号：US13655128
申请日：2012-10-18
申请人： ICR Turbine Engine Corporation
发明人： Frank Wegner Donnelly , David William Dewis , John D. Watson , Douglas W. Swartz
IPC分类号： F02C7/143
CPC分类号： F02C7/143 , F01D25/243 , F02C3/103 , F02C6/003 , F02C6/12 , F05D2250/31 , F05D2250/312 , F05D2250/313 , Y02T50/675
摘要： A method is disclosed to enable the efficient physical packaging of gas turbine engine components to optimize power density, more readily integrate with other equipment and facilitate maintenance. The method illustrates dense packaging of turbomachinery by close-coupling of components, and rotation of various engine components with respect to engines and/or other engine components, and reversal of spool shaft rotational direction to suit the application. Engines can be dense-packed because of a number of features of the basic engine including the use of compact centrifugal compressors and radial inlet turbine assemblies, the close coupling of turbomachinery, the ability to rotate key components to facilitate ducting and preferred placement of other components, the ability to control spool shaft rotational direction and full power operation at high overall pressure ratios.
摘要翻译：公开了一种能够使燃气涡轮发动机部件的有效物理包装以优化功率密度，更容易与其他设备集成并便于维护的方法。该方法示出了通过组件的紧密耦合以及相对于发动机和/或其他发动机部件的各种发动机部件的旋转以及卷筒轴旋转方向的反转以适应该应用的涡轮机械的密集包装。由于基本发动机的许多特征包括使用紧凑型离心压缩机和径向进气涡轮机组件，涡轮机械的紧密耦合，旋转关键部件以促进管道的能力以及其他部件的优选放置的能力，发动机可以密集，能够在高整体压力比下控制卷筒轴的旋转方向和全功率运行。

8. 发明申请

US20060288707A1 Support system for transition ducts 有权
公开(公告)号：US20060288707A1
公开(公告)日：2006-12-28
申请号：US11249790
申请日：2005-10-13
申请人： Adam Weaver , Jody Wilson
发明人： Adam Weaver , Jody Wilson
IPC分类号： F02C7/20
CPC分类号： F02C7/20 , F01D9/023 , F05D2250/25 , F05D2250/31 , F05D2250/322 , F05D2300/603 , F23R3/425 , F23R3/60 , Y02T50/672 , Y02T50/675
摘要： Aspects of the invention relate to a system for supporting the exit end of a transition duct. The system includes a plurality of support ring segments that collectively form an annular support ring assembly. Each support ring segment can have an outer span and an inner span that are joined by a central column. Lateral openings can be defined on each side of the central column. The lateral openings of two adjacent support ring segments can cooperate to form an opening. An outlet region of a transition duct can be inserted into a respective opening and engage seals provided along the opening. The interface of adjacent ring segments occurs along an imaginary line across the outlet of the common transition duct body. Each support ring segment can be attached to the transition duct as well as to a fixed portion of the engine such as the turbine stationary support structure.

9. 发明授权

US5215257A Divergent seal arrangement for a convergent/divergent nozzle 失效
标题翻译：会聚/发散喷嘴的分歧密封装置
公开(公告)号：US5215257A
公开(公告)日：1993-06-01
申请号：US914291
申请日：1992-07-16
申请人： W. Kevin Barcza
发明人： W. Kevin Barcza
IPC分类号： F02K1/12 , F02K1/80
CPC分类号： F02K1/12 , F02K1/805 , F05D2250/31 , F05D2250/323 , F05D2250/324
摘要： The divergent seal of a thrust vectoring nozzle has an elongated corrugated stiffening sheet with a backbone secured to the air side. The backbone is stiff perpendicular to the sheet, but flexible in torsion. A face sheet secured only at the upstream end covers the gas side of the stiffening sheet.
摘要翻译：推力矢量喷嘴的发散密封件具有细长的波纹状加强板，其主轴固定到空气侧。骨架垂直于片材是刚性的，但扭转灵活。仅在上游端部固定的面板覆盖加强板的气体侧。

10. 发明授权

US5215256A Flap hinge arrangement for a convergent/divergent nozzle 失效
标题翻译：用于收敛/发散喷嘴的瓣铰链装置
公开(公告)号：US5215256A
公开(公告)日：1993-06-01
申请号：US914289
申请日：1992-07-16
申请人： W. Kevin Barcza
发明人： W. Kevin Barcza
IPC分类号： F02K1/00 , F02K1/12 , F02K1/80
CPC分类号： F02K1/1223 , F02K1/008 , F02K1/805 , F05D2250/31 , F05D2250/323 , F05D2250/324
摘要： A divergent flap hinge seal for a thrust vectoring nozzle is pivotally connected to the convergent flap, and the divergent flap is pivotally connected to this flap hinge seal An extension on the hinge seal sealingly overlies a recess in the divergent flap. The flap hinge seal is connected to the convergent flap by two pins and the divergent flap is connected to the flap hinge seal by a pin.
摘要翻译：用于推力矢量喷嘴的发散翼片铰链密封件枢转地连接到会聚翼片，并且发散翼片枢转地连接到该翼片铰链密封件。铰链密封件上的延伸部密封地覆盖在发散片中的凹部。翼片铰链密封件通过两个销连接到会聚舌片，并且发散片通过销连接到翼片铰链密封件。

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