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61. 发明申请

US20150377147A1 ACTUATOR CONTROL DEVICE 有权
标题翻译：执行器控制装置
公开(公告)号：US20150377147A1
公开(公告)日：2015-12-31
申请号：US14849126
申请日：2015-09-09
申请人： IHI Corporation
发明人： Hiroyuki FURUKAWA , Takafumi IMAZU
IPC分类号： F02C9/20 , F15B11/16
CPC分类号： F02C9/20 , F15B11/16 , F15B2211/6336 , F15B2211/7107 , F15B2211/76
摘要： An actuator control device detects a displacement of a piston in a first actuator, controls the first actuator by feedback control, measures both of forces generated in first and second actuators, corrects a target position command value for a piston in the second actuator in accordance with an amount of imbalance between the forces, and controls the second actuator in accordance with the difference between the corrected command value and a feedback value of a displacement position of the second piston.
摘要翻译：致动器控制装置检测活塞在第一致动器中的位移，通过反馈控制来控制第一致动器，测量在第一和第二致动器中产生的两个力，根据第二致动器中的活塞校正目标位置指令值力之间的不平衡量，并且根据校正后的指令值与第二活塞的位移位置的反馈值之间的差来控制第二致动器。

62. 发明申请

US20150345385A1 GAS TURBINES IN MECHANICAL DRIVE APPLICATIONS AND OPERATING METHODS 有权
标题翻译：机械驱动应用中的气体涡轮机和操作方法
公开(公告)号：US20150345385A1
公开(公告)日：2015-12-03
申请号：US14655195
申请日：2013-12-18
申请人： NUOVO PIGNONIE SRL
发明人： Marco SANTINI
IPC分类号： F02C6/00 , F01D15/10 , F02C9/20 , F02C9/28 , F02C3/05 , F02C7/275
CPC分类号： F02C6/00 , F01D15/005 , F01D15/10 , F02C3/05 , F02C3/10 , F02C7/268 , F02C7/275 , F02C9/20 , F02C9/28 , F05D2220/76 , F05D2260/4023
摘要： A drive system for driving a load by a gas turbine. The gas turbine comprises a gas generator having a gas-generator rotor and comprising at least one gas-generator compressor and one high-pressure turbine driving the gas-generator compressor. The gas turbine further comprises a power turbine having a power-turbine rotor, which is torsionally independent of the gas-generator rotor. The load is connected to the power-turbine rotor. The system further comprises an electric motor/generator mechanically connected to the gas-generator rotor and electrically connected to an electric power grid. The electric motor/generator is adapted to function alternatively: as a generator for converting mechanical power from the gas turbine into electrical power; and as a motor for supplementing driving power to the load. A set of movable nozzle guide vanes is arranged at the inlet of the power turbine.
摘要翻译：一种用于通过燃气轮机驱动负载的驱动系统。燃气轮机包括具有气体发生器转子并且包括至少一个气体发生器压缩机和驱动气体发生器压缩机的一个高压涡轮机的气体发生器。燃气轮机还包括具有动力涡轮转子的动力涡轮机，该动力涡轮机转子是扭转地独立于气体发生器转子的。负载连接到动力 - 水轮机转子。该系统还包括机电连接到气体发生器转子并电连接到电网的电动机/发电机。电动机/发电机适用于作为替代的功能：作为用于将来自燃气轮机的机械功率转换成电力的发电机; 并作为用于补充负载的驱动力的电动机。一组可动喷嘴导向叶片设置在动力涡轮机的入口处。

63. 发明授权

US09194301B2 Protecting the operating margin of a gas turbine engine having variable vanes from aerodynamic distortion 有权
标题翻译：保护具有可变叶片的燃气轮机的运行裕度不受气动变形的影响
公开(公告)号：US09194301B2
公开(公告)日：2015-11-24
申请号：US13487585
申请日：2012-06-04
申请人： Wayne P. Parente
发明人： Wayne P. Parente
IPC分类号： F02C9/20 , F01D17/16 , F02C7/057 , F01D17/00
CPC分类号： F02C9/20 , F01D17/00 , F01D17/16 , F02C7/057 , F05D2240/12 , F05D2270/102 , F05D2270/1022
摘要： A method of protecting operating margin of the gas turbine engine includes calculating an aerodynamic distortion of air entering an inlet of a gas turbine engine that has a compressor section with variable vanes that are movable subject to a control parameter. The control parameter is selectively modified in response to the aerodynamic distortion.
摘要翻译：一种保护燃气涡轮发动机的运行裕度的方法包括计算进入燃气轮机发动机入口的空气的空气动力学变形，所述空气动力学变形具有可变叶片的压缩机部分，所述变量叶片可移动受制于控制参数。响应于空气动力学失真选择性地修改控制参数。

64. 发明申请

US20150285158A1 AIRCRAFT VAPOUR TRAIL CONTROL SYSTEM 有权
标题翻译：飞机蒸汽拖车控制系统
公开(公告)号：US20150285158A1
公开(公告)日：2015-10-08
申请号：US14644799
申请日：2015-03-11
申请人： ROLLS-ROYCE PLC
发明人： Malcolm HILLEL , Peter SWANN , Andrew Martin ROLT , Paul FLETCHER
IPC分类号： F02C9/20 , B64D31/06 , B64D33/04 , F02K1/76
CPC分类号： F02C9/20 , B64D31/06 , B64D33/04 , F02K1/1207 , F02K1/16 , F02K1/76 , F02K1/825 , F02K3/075 , F05D2220/323 , F05D2270/08 , F05D2270/311 , F05D2270/312 , F05D2270/313 , Y02T50/677
摘要： The invention concerns an aircraft propulsion control system in which a gas turbine engine has an actuable flow opening for control of flow to or from a portion of the engine. One or more sensor is arranged to sense a condition indicative of vapour trail formation by the exhaust flow from the engine. A controller is arranged to control actuation of the flow opening so as to reduce the efficiency of the engine upon sensing of said condition by the one or more sensor. In one example, the flow opening is a variable area fan nozzle.
摘要翻译：本发明涉及一种飞机推进控制系统，其中燃气涡轮发动机具有用于控制流向或来自发动机的一部分的流动的可启动流动开口。一个或多个传感器被布置成通过来自发动机的排气流感测指示蒸气轨道形成的状况。控制器被布置成控制流动开口的致动，以便在通过一个或多个传感器检测到所述状态时降低发动机的效率。在一个示例中，流动开口是可变区域风扇喷嘴。

65. 发明授权

US09140188B2 Gas turbine engine with intercooling turbine section 有权
标题翻译：具有中冷涡轮机段的燃气轮机
公开(公告)号：US09140188B2
公开(公告)日：2015-09-22
申请号：US13287105
申请日：2011-11-01
申请人： Daniel B. Kupratis
发明人： Daniel B. Kupratis
IPC分类号： F02C7/143 , F02C9/20 , F02C9/22 , F02K3/075
CPC分类号： F02C7/143 , F02C9/20 , F02C9/22 , F02K3/075 , F02K3/077 , Y02T50/675
摘要： A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a combustor section, a low spool including a fan section and an intercooling turbine section along an engine axis aft of the fan section and forward of a combustor section. The fan section and the intercooling turbine section are coaxial with the low spool. A high spool along the engine axis includes a high pressure compressor section and a high pressure turbine section, the high pressure compressor section is aft of the intercooling turbine section and forward of the combustor section, and the high pressure turbine section is aft of the combustor section. The high pressure compressor section and the high pressure turbine section are coaxial with the high spool. A method of operating a gas turbine engine is also disclosed.
摘要翻译：根据本公开的示例性方面的燃气涡轮发动机包括燃烧器部分，包括风扇部分的低阀芯和沿着风扇部分的发动机轴后部的中间冷却涡轮机部分，以及燃烧器部分。风扇部分和中间冷却涡轮部分与低卷轴同轴。沿着发动机轴线的高线轴包括高压压缩机部分和高压涡轮部分，高压压缩机部分是中间冷却涡轮机部分的后部，并且在燃烧器部分的前方，高压涡轮机部分是燃烧器的后部部分。高压压缩机部分和高压涡轮部分与高阀芯同轴。还公开了一种操作燃气涡轮发动机的方法。

66. 发明授权

US09057280B2 Contacting vanes 有权
标题翻译：接触叶片
公开(公告)号：US09057280B2
公开(公告)日：2015-06-16
申请号：US13363137
申请日：2012-01-31
申请人： Nicolas Morand , Olivier Espasa , Francis Abel , Lorrain Sausse , Julien Mailfert , Frederic Favray , Emmanuel Bouvier
发明人： Nicolas Morand , Olivier Espasa , Francis Abel , Lorrain Sausse , Julien Mailfert , Frederic Favray , Emmanuel Bouvier
IPC分类号： F01D17/16 , F01D9/04 , F02C6/12 , F02C9/20
CPC分类号： F01D17/165 , F01D9/048 , F02C6/12 , F02C9/20 , Y10T29/49229
摘要： An assembly can include vanes and a base configured to seat the vanes at a radial distance about an axis where each vane includes a leading edge and a trailing edge, a pair of lateral surfaces that meet at the leading edge and at the trailing edge, an extension that extends from one of the lateral surfaces and that has a contact surface, and a stop surface to form a contact with a contact surface of another vane to define a minimum flow distance between the vane and the other vane. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.
摘要翻译：组件可以包括叶片和基座，其构造成将叶片围绕轴线径向距离地安置，其中每个叶片包括前缘和后缘，在前缘和后缘处相交的一对侧面，延伸部，其从一个侧面延伸并具有接触表面，以及止动表面，以与另一个叶片的接触表面形成接触，以限定叶片和另一个叶片之间的最小流动距离。还公开了装置，组件，系统，方法等的各种其它示例。

67. 发明授权

US08882438B2 Methods and systems for variable geometry inlets nozzles for use in turboexpanders 有权
标题翻译：用于涡轮膨胀机的可变几何入口喷嘴的方法和系统
公开(公告)号：US08882438B2
公开(公告)日：2014-11-11
申请号：US13113616
申请日：2011-05-23
申请人： Antonio Asti , Alberto Scotti Del Greco , Paolo Del Turco , Alessio Miliani
发明人： Antonio Asti , Alberto Scotti Del Greco , Paolo Del Turco , Alessio Miliani
IPC分类号： F02C9/20 , F01K23/10 , F01D17/16 , F02C9/24 , F01K7/04 , F02C6/18 , F01K25/10
CPC分类号： F01D17/165 , F01K7/04 , F01K23/10 , F01K25/10 , F02C6/18 , F02C9/20 , F02C9/24 , F05D2220/40 , F05D2240/12 , F05D2240/40 , F05D2270/3011
摘要： A method and system for power generation including a turboexpander with at least two expansion stages, the turboexpander being connected to a power generation unit, is provided. The system includes a controller configured to control (i) an angle of a first inlet guide vane provided at an inlet of a first expansion stage of the turboexpander for maintaining an inlet pressure of the first expansion stage in a predetermined range, and (ii) an angle of a second inlet guide vane provided at an inlet of a second expansion stage of the turboexpander. The controller is configured to determine a highest power from determined powers of the power generation unit and a corresponding angle of the second inlet guide vane and to adjust the angle of the second inlet guide vane independent of the angle of the first inlet guide vane to achieve the highest power.
摘要翻译：提供一种用于发电的方法和系统，包括具有至少两个膨胀级的涡轮膨胀机，所述涡轮膨胀机连接到发电单元。该系统包括：控制器，被配置为控制（i）设置在涡轮膨胀机的第一膨胀级的入口处的第一入口引导叶片的角度，用于将第一膨胀级的入口压力保持在预定范围内，以及（ii）设置在涡轮膨胀机的第二膨胀级的入口处的第二入口引导叶片的角度。所述控制器构造成从所述发电单元的确定的功率和所述第二入口导向叶片的相应角度确定最大功率，并且调整所述第二入口导向叶片的角度而与所述第一入口导叶的角度无关，以实现最高的权力。

68. 发明授权

US08864450B2 Gas turbine engine synchronizing ring bumper 有权
标题翻译：燃气轮机发动机同步环保险杠
公开(公告)号：US08864450B2
公开(公告)日：2014-10-21
申请号：US13018512
申请日：2011-02-01
申请人： Eugene C. Gasmen , Stanley Wiecko
发明人： Eugene C. Gasmen , Stanley Wiecko
IPC分类号： F01D17/12 , F01D25/24 , F01D17/16 , F02C9/20
CPC分类号： F01D17/162 , F01D25/243 , F01D25/246 , F02C9/20 , F05D2260/50 , F05D2270/60 , Y10T29/53
摘要： A gas turbine engine includes a synchronizing ring. A cradle includes an integrally formed anti-rotation feature. The cradle is secured to the synchronizing ring and located relative thereto with the anti-rotation feature. A bumper is slidably supported within the cradle. In one example, a bushing is provided within a hole in the bumper. A fastener is inserted into the hole and a bushing to secure the bumper to the synchronizing ring.
摘要翻译：燃气涡轮发动机包括同步环。托架包括整体形成的防旋转特征。托架被固定到同步环并且通过防旋转特征与其相对定位。缓冲器可滑动地支撑在支架内。在一个示例中，衬套设置在保险杠内的孔内。将紧固件插入孔和衬套中以将保险杠固定到同步环。

69. 发明授权

US08650883B2 System and method for operating a gas turbine 有权
标题翻译：用于操作燃气轮机的系统和方法
公开(公告)号：US08650883B2
公开(公告)日：2014-02-18
申请号：US12854361
申请日：2010-08-11
申请人： Shahryar Rabiei , Gilbert Otto Kraemer , Geoffrey David Myers
发明人： Shahryar Rabiei , Gilbert Otto Kraemer , Geoffrey David Myers
IPC分类号： F02C9/20 , G01J5/10
CPC分类号： F02C9/28 , F05D2270/083 , Y02T50/67
摘要： A system for operating a gas turbine includes a compressor, a combustor, and a turbine. The combustor and turbine define a hot gas path. A sensor disposed outside the hot gas path measures internal thermal emissions from the combustor or turbine and generates a first signal reflective of the internal thermal emissions. The internal thermal emissions are infrared or ultraviolet emissions. A controller connected to the sensor receives the first signal and adjusts the compressor, combustor, or turbine in response to the first signal from the sensor. A method for operating a gas turbine includes measuring internal thermal emissions from inside a combustor or turbine using a sensor disposed outside the hot gas path. The method further includes generating a first signal reflective of the internal thermal emissions and adjusting the operation of the compressor, combustor, or turbine in response to the first signal from the sensor.
摘要翻译：用于操作燃气轮机的系统包括压缩机，燃烧器和涡轮机。燃烧器和涡轮限定热气路径。设置在热气路径之外的传感器测量来自燃烧器或涡轮机的内部热量排放，并产生反映内部热辐射的第一信号。内部热辐射是红外线或紫外线辐射。连接到传感器的控制器响应于来自传感器的第一信号接收第一信号并调节压缩机，燃烧器或涡轮机。用于操作燃气轮机的方法包括使用设置在热气体路径外部的传感器来测量来自燃烧室或涡轮机内部的热量排放。该方法还包括响应于来自传感器的第一信号产生反映内部热量排放的第一信号和调节压缩机，燃烧室或涡轮机的运行。

70. 发明申请

US20120023963A1 POWER PLANT AND METHOD OF OPERATION 有权
标题翻译：动力装置和操作方法
公开(公告)号：US20120023963A1
公开(公告)日：2012-02-02
申请号：US13217713
申请日：2011-08-25
申请人： Lisa Anne Wichmann , Daniel David Snook , Noémie Dion Ouellet , Scott Allen Rittenhouse
发明人： Lisa Anne Wichmann , Daniel David Snook , Noémie Dion Ouellet , Scott Allen Rittenhouse
IPC分类号： F02C9/54 , F02C9/20 , F02C9/26 , F02C9/00
CPC分类号： F02C9/42 , F02C3/34 , F02C9/18
摘要： At least one main air compressor makes a compressed ambient gas flow. The compressed ambient gas flow is delivered to both master and slave turbine combustors at a pressure that is greater than or substantially equal to an output pressure delivered to each turbine combustor from each turbine compressor as at least a first portion of a recirculated gas flow. A fuel stream is delivered to each turbine combustor, and combustible mixtures are formed and burned, forming the recirculated gas flows. A master and slave turbine power are produced, and each is substantially equal to at least a power required to rotate each turbine compressor. At least a portion of the recirculated gas flow is recirculated through recirculation loops. At least a second portion of the recirculated gas flow bypasses the combustors or an excess portion of each recirculated gas flow is vented or both.
摘要翻译：至少一个主要空气压缩机使压缩的环境气体流动。压缩的环境气体流以大于或基本上等于从每个涡轮压缩机作为再循环气流的至少第一部分输送到每个涡轮机燃烧器的输出压力的压力被输送到主涡轮燃烧器和从属涡轮机燃烧器。燃料流被输送到每个涡轮机燃烧器，并且形成并燃烧可燃混合物，形成再循环的气体流。制造主和从属涡轮机功率，并且每个主要和从属涡轮机功率基本上等于旋转每个涡轮压缩机所需的至少一个功率。再循环气体的至少一部分通过再循环回路再循环。再循环气体流的至少第二部分绕过燃烧器，或者每个再循环气体流的多余部分被排出或两者。

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