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1. 发明申请

US20190226407A1 ON-BOARD ESTIMATOR ACTUATOR SYSTEM FAULT ACCOMMODATION IN ENGINE CONTROL 审中-公开
公开(公告)号：US20190226407A1
公开(公告)日：2019-07-25
申请号：US15879718
申请日：2018-01-25
申请人： United Technologies Corporation
发明人： Boris Karpman , Richard P. Meisner , Subhradeep Chowdhury
IPC分类号： F02C9/00 , G05B13/02
CPC分类号： F02C9/00 , F05D2220/323 , F05D2260/80 , F05D2270/09 , F05D2270/094 , F05D2270/46 , F05D2270/60 , F05D2270/71 , F05D2270/821 , G05B13/024 , G05B13/041 , G05B23/0291
摘要： An engine control system includes an electronic hardware engine controller and an actuator that operates at different positions to control operation of an engine. An actuator sensor measures an actuator position, and the engine controller generates a synthesized actuator position. In response to detecting a faulty actuator, a faulty actuator sensor, or both, the engine controller adjusts the position of the actuator based on the synthesized actuator position.

2. 发明授权

US09441500B2 Steam turbine casing position adjusting apparatus 有权
标题翻译：蒸汽轮机壳体位置调节装置
公开(公告)号：US09441500B2
公开(公告)日：2016-09-13
申请号：US13817983
申请日：2011-11-02
申请人： Takumi Hori , Megumu Tsuruta , Shin Asano , Tamiaki Nakazawa , Ryokichi Hombo
发明人： Takumi Hori , Megumu Tsuruta , Shin Asano , Tamiaki Nakazawa , Ryokichi Hombo
IPC分类号： F01D25/24 , F01D11/20 , F01D11/22 , F01D21/08 , F01D25/26 , F01D25/28
CPC分类号： F01D11/20 , F01D11/22 , F01D21/08 , F01D25/24 , F01D25/26 , F01D25/28 , F05D2220/31 , F05D2260/57 , F05D2270/60 , F05D2270/80 , F05D2270/821
摘要： A steam turbine casing position adjusting apparatus capable of employing a compact low-resolution actuator is provided. A steam turbine casing position adjusting apparatus 40 includes turbine casings 21 and 37, a rotor 23, and actuators 14 and 15 that move the turbine casings 21 and 37 in the axial direction. The actuators 14 and 15 are disposed radially outside outer peripheries forming the turbine casings 21 and 37 .
摘要翻译：提供一种能够采用紧凑型低分辨率致动器的汽轮机壳体位置调节装置。蒸汽涡轮机壳体位置调节装置40包括涡轮机壳体21和37，转子23以及沿轴向移动涡轮机壳体21和37的致动器14和15。致动器14和15径向设置在形成涡轮机壳体21和37的外周的外侧。

3. 发明授权

US09091230B2 Linked ring petal actuation for variable area fan nozzle 有权
标题翻译：可变区域风扇喷嘴的连接环花瓣致动
公开(公告)号：US09091230B2
公开(公告)日：2015-07-28
申请号：US13473367
申请日：2012-05-16
申请人： Rainer Dittmann , Reid A. McCracken
发明人： Rainer Dittmann , Reid A. McCracken
IPC分类号： F02K1/12 , F01D17/14 , F02K1/00 , F02K1/15
CPC分类号： F02K1/1207 , F01D17/141 , F02K1/004 , F02K1/1223 , F02K1/15 , F05D2250/42 , F05D2260/50 , F05D2260/56 , F05D2270/60 , F05D2270/62 , Y02T50/672
摘要： A variable area fan nozzles comprising an array of rigid petals hinged to a lip area at the downstream end of a thrust reverser sleeve (or half-sleeve). In one embodiment, the actuation system comprises a rotatable ring segment, a drive system for rotating the ring segment, a plurality of cams attached or integrally formed with the ring segment, a plurality of cam followers, and a plurality of petal linkages which operatively couple the petals to the cam followers. This actuation system controls the deflection of the petals, thereby controlling the amount of opening and the rate at which the fan nozzle throat area changes. Each cam may have forward- and rearward-facing camming surfaces that interact with the cam followers to force the petals to pivot outward or inward respectively.
摘要翻译：一种可变区域的风扇喷嘴，其包括刚性花瓣的阵列，其铰接到推力反向器套筒（或半套筒）的下游端处的唇部区域。在一个实施例中，致动系统包括可旋转环段，用于旋转环段的驱动系统，与环段连接或整体形成的多个凸轮，多个凸轮从动件和多个花键联动件，其可操作地联接花瓣到凸轮追随者。该致动系统控制花瓣的偏转，从而控制开口量和风扇喷嘴喉部区域变化的速率。每个凸轮可以具有与凸轮从动件相互作用的向前和向后的凸轮表面，以迫使花瓣分别向外或向内枢转。

4. 发明申请

US20100139285A1 THRUST VECTORABLE FAN VARIABLE AREA NOZZLE FOR A GAS TURBINE ENGINE FAN NACELLE 有权
公开(公告)号：US20100139285A1
公开(公告)日：2010-06-10
申请号：US12616750
申请日：2009-11-11
申请人： Michael Winter , Russell B. Hanson
发明人： Michael Winter , Russell B. Hanson
IPC分类号： F02K1/06
CPC分类号： F01D17/141 , F02K1/06 , F02K1/1207 , F02K1/15 , F02K3/06 , F02K3/075 , F05D2260/50 , F05D2270/60 , F05D2270/62
摘要： A thrust vectorable fan variable area nozzle (FVAN) includes a synchronizing ring, a static ring, and a flap assembly mounted within a fan nacelle. An actuator assembly selectively rotates synchronizing ring segments relative the static ring to adjust segments of the flap assembly to vary the annular fan exit area and vector the thrust through asymmetrical movement of the thrust vectorable FVAN segments. In operation, adjustment of the entire periphery of the thrust vectorable FVAN in which all segments are moved simultaneously to maximize engine thrust and fuel economy during each flight regime. By separately adjusting the segments of the thrust vectorable FVAN, engine trust is selectively vectored to provide, for example only, trim balance or thrust controlled maneuvering.

5. 发明授权

US07637095B2 Thrust vectorable fan variable area nozzle for a gas turbine engine fan nacelle 有权
标题翻译：用于燃气涡轮发动机风扇机舱的推力矢量风机可变面积喷嘴
公开(公告)号：US07637095B2
公开(公告)日：2009-12-29
申请号：US11582219
申请日：2006-10-17
申请人： Michael Winter , Russell B. Hanson
发明人： Michael Winter , Russell B. Hanson
IPC分类号： F02K3/02
CPC分类号： F01D17/141 , F02K1/06 , F02K1/1207 , F02K1/15 , F02K3/06 , F02K3/075 , F05D2260/50 , F05D2270/60 , F05D2270/62
摘要： A thrust vectorable fan variable area nozzle (FVAN) includes a synchronizing ring, a static ring, and a flap assembly mounted within a fan nacelle. An actuator assembly selectively rotates synchronizing ring segments relative the static ring to adjust segments of the flap assembly to vary the annular fan exit area and vector the thrust through asymmetrical movement of the thrust vectorable FVAN segments. In operation, adjustment of the entire periphery of the thrust vectorable FVAN in which all segments are moved simultaneously to maximize engine thrust and fuel economy during each flight regime. By separately adjusting the segments of the thrust vectorable FVAN, engine trust is selectively vectored to provide, for example only, trim balance or thrust controlled maneuvering.
摘要翻译：推力可动风扇可变区域喷嘴（FVAN）包括安装在风扇机舱内的同步环，静止环和挡板组件。致动器组件选择性地相对于静态环旋转同步环段，以调整翼片组件的段以改变环形风扇出口区域，并且通过推力可动的FVAN段的不对称运动来矢量推力。在操作中，调整可推力矢量FVAN的整个周边，其中所有段同时移动，以在每个飞行状态期间最大化发动机推力和燃料经济性。通过单独调节推力可矢量的FVAN的段，选择性地引导发动机信任，以提供例如仅修剪平衡或推力控制的操纵。

6. 发明申请

US20170218853A1 METHODS AND APPARATUS TO ADJUST BLEED PORTS ON AN AIRCRAFT ENGINE 审中-公开
公开(公告)号：US20170218853A1
公开(公告)日：2017-08-03
申请号：US15489383
申请日：2017-04-17
申请人： The Boeing Company
发明人： Steve G. Mackin , Sean C. Thomas , Brian W. Debronsky
IPC分类号： F02C9/18 , B64D15/04 , B64D27/16 , B64D13/02 , F02C6/08 , F04D27/00
CPC分类号： F02C9/18 , B64D13/02 , B64D15/04 , B64D27/16 , F02C6/08 , F04D27/009 , F04D27/0215 , F04D27/023 , F05D2270/60 , F05D2270/65
摘要： Methods and apparatus to adjust bleed ports on an aircraft engine are disclosed. An example method to extract bleed air from an aircraft engine includes extracting, via a plenum positioned in a compressor of the aircraft engine, bleed air from a first bleed port associated with a first stage of a compressor and a second bleed port associated with a second stage of the compressor. The plenum is configured to combine the extracted bleed air from the first and second bleed ports and fluidly couple the extracted bleed air to one or more systems of an aircraft. The method includes regulating a pressure of the extracted bleed air in the plenum by adjusting a flow of bleed air through the first bleed port via a first valve associated with the first bleed port and adjusting a flow of bleed air through the second port via a second valve associated with the second bleed port.

7. 发明申请

US20160356170A1 GAS TURBINE ENGINE RAPID RESPONSE CLEARANCE CONTROL SYSTEM 审中-公开
标题翻译：气体涡轮发动机快速响应间隙控制系统
公开(公告)号：US20160356170A1
公开(公告)日：2016-12-08
申请号：US14913785
申请日：2014-07-23
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Timothy M. Davis , Brian Duguay
IPC分类号： F01D11/22 , F04D29/16
CPC分类号： F01D11/22 , F01D11/08 , F01D11/14 , F04D29/164 , F05D2220/32 , F05D2260/50 , F05D2270/60
摘要： An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a sync ring with a multiple of graduation sets. Each of the graduation sets is associated with one of the multiple of blade outer air seal assemblies. An active clearance control system of a gas turbine engine includes a sync ring with a multiple of graduation sets. Each of the graduation sets includes a multiple of graduations to define an associated radial position for each of a respective multiple of blade outer air seal assemblies.
摘要翻译：燃气涡轮发动机的主动间隙控制系统包括多个叶片外部空气密封组件和具有多个分级组的同步环。每个分级组与多个叶片外部空气密封组件中的一个相关联。燃气涡轮发动机的主动间隙控制系统包括具有多个分级组的同步环。每个分级组包括多个刻度以确定相应的多个叶片外部空气密封组件中的每一个的相关的径向位置。

8. 发明申请

US20150104289A1 METHODS AND APPARATUS TO ADJUST BLEED PORTS ON AN AIRCRAFT ENGINE 有权
标题翻译：在飞机发动机上调整出料口的方法和装置
公开(公告)号：US20150104289A1
公开(公告)日：2015-04-16
申请号：US14189846
申请日：2014-02-25
申请人： The Boeing Company
发明人： Steve G. Mackin , Sean C. Thomas , Brian W. Debronsky
IPC分类号： F02C9/18 , F04D27/02
CPC分类号： F02C9/18 , B64D13/02 , B64D15/04 , B64D27/16 , F02C6/08 , F04D27/009 , F04D27/0215 , F04D27/023 , F05D2270/60 , F05D2270/65
摘要： Methods and apparatus to adjust bleed ports on an aircraft engine are disclosed. An example apparatus for bleeding air from a multi-stage compressor of an aircraft engine includes a compressor case having a plurality of bleed ports. A first bleed port is associated with a first stage of a compressor, and a second bleed port is associated with a second stage of the compressor. The apparatus includes a plenum connected to the compressor case to define a plenum cavity. The plenum fluidly coupling the first and second bleed ports to a fluid conduit for providing bleed air to one or more systems of an aircraft. The apparatus also includes a bleed port selection mechanism located within the plenum cavity. The bleed port selection mechanism including a first portion proximate the first bleed port and operable to prevent fluid flow through the first bleed port.
摘要翻译：公开了一种用于调整飞机发动机上的排放口的方法和装置。用于从飞机发动机的多级压缩机排出空气的示例性装置包括具有多个排气口的压缩机壳体。第一泄放端口与压缩机的第一级相关联，并且第二排放口与压缩机的第二级相关联。该装置包括连接到压缩机壳体以限定增压腔的增压室。气室将第一和第二排放口流体耦合到流体导管，用于向飞行器的一个或多个系统提供排气。该装置还包括位于气室内的排气口选择机构。排出口选择机构包括靠近第一排放口的第一部分，并且可操作以防止流体流过第一排放口。

9. 发明申请

US20100050596A1 THRUST VECTORABLE FAN VARIABLE AREA NOZZLE FOR A GAS TURBINE ENGINE FAN NACELLE 有权
标题翻译：燃气涡轮发动机风扇风扇可变风扇变风量喷嘴
公开(公告)号：US20100050596A1
公开(公告)日：2010-03-04
申请号：US12616759
申请日：2009-11-11
申请人： Michael Winter , Russell B. Harison
发明人： Michael Winter , Russell B. Harison
IPC分类号： F02K3/02 , F02K1/06
CPC分类号： F01D17/141 , F02K1/06 , F02K1/1207 , F02K1/15 , F02K3/06 , F02K3/075 , F05D2260/50 , F05D2270/60 , F05D2270/62
摘要： A thrust vectorable fan variable area nozzle (FVAN) includes a synchronizing ring, a static ring, and a flap assembly mounted within a fan nacelle. An actuator assembly selectively rotates synchronizing ring segments relative the static ring to adjust segments of the flap assembly to vary the annular fan exit area and vector the thrust through asymmetrical movement of the thrust vectorable FVAN segments. In operation, adjustment of the entire periphery of the thrust vectorable FVAN in which all segments are moved simultaneously to maximize engine thrust and fuel economy during each flight regime. By separately adjusting the segments of the thrust vectorable FVAN, engine trust is selectively vectored to provide, for example only, trim balance or thrust controlled maneuvering.
摘要翻译：推力可动风扇可变区域喷嘴（FVAN）包括安装在风扇机舱内的同步环，静止环和挡板组件。致动器组件选择性地相对于静态环旋转同步环段，以调整翼片组件的段以改变环形风扇出口区域，并且通过推力可动的FVAN段的不对称运动来矢量推力。在操作中，调整可推力矢量FVAN的整个周边，其中所有段同时移动，以在每个飞行状态期间最大化发动机推力和燃料经济性。通过单独调节推力可矢量的FVAN的段，选择性地引导发动机信任，以提供例如仅修剪平衡或推力控制的操纵。

10. 发明申请

US20040016239A1 Miniature gas turbine engine with unitary rotor shaft for power generation 失效
标题翻译：具有发电单体转子轴的微型燃气轮机
公开(公告)号：US20040016239A1
公开(公告)日：2004-01-29
申请号：US10431345
申请日：2003-05-06
发明人： Tibor Fabian , Frank Holman , Sangkyun Kang , Hao-Chih Liu , Minoru Matsunaga , Fritz B. Prinz , Hideaki Tsuru
IPC分类号： F02C003/05
CPC分类号： H02K7/1823 , B33Y70/00 , B33Y80/00 , F01D5/048 , F01D5/284 , F01D25/16 , F02C3/05 , F05D2220/768 , F05D2250/82 , F05D2270/60 , F05D2300/2283 , H02K1/2726 , Y10S415/915
摘要： The present invention provides a miniature gas turbine engine for power generation. The engine has a highly integrated unitary rotor shaft where turbine, compressor and shaft are made in one piece in one fabrication process. The turbine and compressor are positioned back to back on the shaft in an overhung configuration, allowing the front bearings to be located in the cold zone of the engine. Preferably, the Mold SDM fabrication technique is utilized to make the unitary rotor shaft in one monolithic part out of ceramics such as silicon nitride, eliminating the need for post process assembly while strengthening the integrity, reliability, and performance of the unitary rotor shaft. Integrated with a permanent magnet in the unitary rotor shaft, the miniature gas turbine engine can generate electric power of 1 kW or less. Additionally, the axial length of the miniature gas turbine engine is about 100 mm or less. The miniature gas turbine engine according to the present invention is therefore particularly useful for powering lightweight, self-sustaining mobile devices such as unmanned vehicles and-autonomous robots.
摘要翻译：本发明提供一种用于发电的微型燃气轮机。发动机具有高度集成的单一转子轴，其中涡轮机，压缩机和轴在一个制造过程中制成一体。涡轮机和压缩机以悬垂构造背靠背地定位在轴上，允许前轴承位于发动机的冷区中。优选地，使用模具SDM制造技术来使整体式转子轴在诸如氮化硅的陶瓷之外的一个整体部分中，从而消除了后加工组装的需要，同时增强了整体转子轴的完整性，可靠性和性能。在整体式转子轴中与永磁体一体化，微型燃气涡轮发动机可以产生1kW以下的电力。此外，微型燃气涡轮发动机的轴向长度为约100mm或更小。因此，根据本发明的微型燃气涡轮发动机特别可用于为诸如无人驾驶车辆和自主机器人的轻量级，自维持的移动设备供电。

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