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1. 发明授权

EP3209563B1 SYSTEME PROPULSIF HYBRIDE D'UN AERONEF MULTI-MOTEUR 有权
公开(公告)号：EP3209563B1
公开(公告)日：2018-08-01
申请号：EP15793869.7
申请日：2015-10-15
申请人： Safran Helicopter Engines
发明人： MOULON, Frédéric , MERCIER-CALVAIRAC, Fabien , LE MAUX, David
IPC分类号： B64D33/00 , B64C27/12 , F01D15/10 , F02C9/42 , B64D27/02
CPC分类号： B64D27/02 , B64C27/12 , B64D33/00 , B64D2027/026 , F01D15/10 , F02C7/268 , F02C9/42 , F05D2220/329 , F05D2220/76 , Y02T50/64

2. 发明公开

EP3333380A1 SYSTEM AND METHOD FOR FAST STARTUP OF A COMBINED CYCLE POWER PLANT 有权
公开(公告)号：EP3333380A1
公开(公告)日：2018-06-13
申请号：EP17204203.8
申请日：2017-11-28
申请人： Doosan Heavy Industries & Construction Co., Ltd.
发明人： Cheong, Seung Gyun
IPC分类号： F01K23/10 , F01K13/02 , F01K7/16
CPC分类号： F01K23/101 , F01K7/165 , F01K13/02 , F02C6/18 , F02C7/268 , F05D2220/32 , F05D2220/72 , F05D2220/76 , F05D2260/81 , F05D2260/941 , Y02E20/16
摘要： Provided is a system for controlling start-up of a combined cycle power plant that includes a gas turbine that includes a rotor, an HRSG that generates steam, a steam turbine that includes a rotor, and generators that generate electric power using rotation forces, respectively, of the rotor of the gas turbine and the rotor of the steam turbine, the system including; a sensor that measures operating states of components of the combined cycle power plant; and a controller that controls the start-up, based on the operating states, which are acquired from the sensor, in which the controller verifies one or more restrictive conditions that restrict setting of an operational value of an operational parameter for the combined cycle power plant, based on the operating states, which are acquired from the sensor, and, based on a result of the verification, sets the operational value.

3. 发明授权

EP3052771B1 TURBOMACHINE ADAPTÉE À FONCTIONNER EN MODE VIREUR 有权
标题翻译：涡轮机适合在维拉模式下运行
公开(公告)号：EP3052771B1
公开(公告)日：2018-02-28
申请号：EP14789317.6
申请日：2014-09-29
申请人： Safran Helicopter Engines
发明人： THIRIET, Romain , POUMAREDE, Vincent , SERGHINE, Camel
IPC分类号： F01D25/10 , F01D25/36 , F01D25/18 , F02C7/06
CPC分类号： F02C7/06 , F01D25/10 , F01D25/18 , F01D25/36 , F02C3/04 , F02C6/18 , F02C7/268 , F05D2220/32 , F05D2220/76 , F05D2240/35 , F05D2260/213 , F05D2260/85 , Y02T50/675

4. 发明公开

EP3266995A1 PINNED MECHANICAL FUSE FOR ENGINE MOTORING SYSTEM 有权
标题翻译： PINNED机械熔丝用于发动机驱动系统
公开(公告)号：EP3266995A1
公开(公告)日：2018-01-10
申请号：EP17179832.5
申请日：2017-07-05
申请人： Hamilton Sundstrand Corporation
发明人： SLAYTER, Matthew Allen , DAVIS, Richard Alan , FOX, Paul F. , ROBERTS, Jeffrey Todd , BROWN, Jeff A. , NGUYEN, James Vandung , HARDER, Benjamin T. , WILSON, Dwayne Leon , MCMASTERS, Brian , WALKER, Daniel Richard
IPC分类号： F01D25/36 , F02C7/32
CPC分类号： F02C7/268 , F01D15/12 , F01D25/36 , F02C7/32 , F05D2220/32 , F05D2230/60 , F05D2260/311 , F05D2260/85
摘要： A motoring system (100) for a gas turbine engine (54) having: a reduction gear train (122) having an input (122a) and output (122b); a motor (110) operably connected to the input (122a); a clutch (124) operably connected to the output (122b), the clutch (124) in operation engages and disengages the reduction gear train (122); and a pinned mechanical fuse (200) operably connecting the output (122b) to the clutch (124), the pinned mechanical fuse (200) having at least one shear pin (240). The pinned mechanical fuse (200) having: an outer sleeve (220) having a first section (220a), second section (220b), inner chamber (221), outer wall (222), and at least one through hole (250) connecting the inner chamber (221) to the outer wall (222) within the first section (220a); and an inner sleeve (210) having a first portion (210a), second portion (210b), outer surface (212), and at least one blind hole (223) located in the outer surface (212) within the second portion (210b). The second portion (210b) being located within the inner chamber (221) and operably connected to the outer sleeve (220) through at least one shear pin (240).
摘要翻译：一种用于燃气涡轮发动机（54）的驱动系统（100），具有：减速齿轮系（122），其具有输入端（122a）和输出端（122b）; 电动机（110），其可操作地连接到所述输入端（122a）; 可操作地连接到所述输出部（122b）的离合器（124），所述离合器（124）在操作中接合和脱离所述减速齿轮系（122）; 和可操作地将所述输出端（122b）连接到所述离合器（124）的销式机械熔断器（200），所述销式机械熔断器（200）具有至少一个剪切销（240）。（200）具有：具有第一部分（220a），第二部分（220b），内腔室（221），外壁（222）和至少一个通孔（250）的外套管（220）将所述内室（221）连接到所述第一部分（220a）内的所述外壁（222）; 和具有位于第二部分（210b）内的外表面（212）中的第一部分（210a），第二部分（210b），外表面（212）和至少一个盲孔（223）的内套筒）。第二部分（210b）位于内室（221）内并通过至少一个剪切销（240）可操作地连接到外套筒（220）。

5. 发明公开

EP2733312A3 Gas turbine engine optimization by electric power transfer 有权转让
标题翻译：电力传输优化燃气轮机发动机
公开(公告)号：EP2733312A3
公开(公告)日：2017-12-13
申请号：EP13189603.7
申请日：2013-10-21
申请人： Honeywell International Inc.
发明人： Anghel, Cristian , Pearson, Wayne , Gehrke, Jens , Condon, Kevin
IPC分类号： F01D15/10 , F02C7/32 , F02C9/00
CPC分类号： F01D15/10 , F02C7/268 , F02C7/32 , F02C7/36 , F02C9/00 , F05B2220/706 , F05D2220/32 , F05D2240/40
摘要： A method of increasing the operational efficiency of an operating gas turbine engine includes supplying mechanical power from a first spool of the operating gas turbine engine to a first electrical machine to thereby generate electrical power using the first electrical machine and supplying mechanical power from a second spool of the operating gas turbine engine to a second electrical machine to thereby generate electrical power using the second electrical machine. The method further includes sensing one or more operational parameters of the operating gas turbine engine and, based on the one or more sensed operational parameters, ceasing to generate electrical power using the second electrical machine, and instead supplying at least a part of the electrical power generated by the first electrical machine to the second electrical machine to operate in motoring mode and to thereby generate and supply mechanical output power to the second spool of the engine.
摘要翻译：一种提高运行的燃气涡轮发动机的运行效率的方法包括：将机械功率从运行的燃气涡轮发动机的第一阀芯提供给第一电机，从而使用第一电机产生电力并且从第二阀芯将运行中的燃气涡轮发动机的运转传递给第二电机，从而使用第二电机产生电力。该方法进一步包括感测操作燃气涡轮发动机的一个或多个操作参数，并且基于一个或多个感测到的操作参数，停止使用第二电机产生电力，并且替代地提供至少一部分电功率由第一电机产生到第二电机以在电动模式下操作并由此产生机械输出功率并将其供应到发动机的第二阀芯。

6. 发明公开

EP3207223A1 ARCHITECTURE D'UN SYSTEME PROPULSIF D'UN HELICOPTERE COMPRENANT UN TURBOMOTEUR HYBRIDE ET UN SYSTEME DE REACTIVATION DE CE TURBOMOTEUR HYBRIDE 有权
标题翻译：德国联邦体系推进剂与联合国直升机协议联合国机动车混合动力联合国系统重新启动德国汽轮机混合动力
公开(公告)号：EP3207223A1
公开(公告)日：2017-08-23
申请号：EP15791693.3
申请日：2015-10-06
申请人： Safran Helicopter Engines , Safran Electrical & Power
发明人： VALLART, Philippe , BAZET, Jean-Michel , LE DUIGOU, Loïc
IPC分类号： F01D13/00 , F01D19/00 , F02C7/36
CPC分类号： B64C27/14 , B64D27/24 , B64D2027/026 , F01D13/00 , F01D13/003 , F01D19/00 , F02C7/268 , F02C7/36 , F05D2220/329 , F05D2220/76 , F05D2270/13 , Y02T50/671
摘要： The invention relates to an architecture for a propulsion system of a multi-engine helicopter including turboshaft engines connected to a power gearbox. Said architecture is characterized in that it includes: - at least one hybrid turboshaft engine (20) capable of operating in at least one standby mode during a stabilized coasting flight of the helicopter; - at least two chains (30, 40) for controlling each hybrid turboshaft engine (20), each chain (30, 40) including an electrical machine (31, 41) connected to the hybrid turboshaft engine (20) and being suitable for rotating a gas producer thereof; and - at least one source (33, 43) for supplying electrical power to said electrical machine (31, 41). Each reactivation chain (30, 40) is configured so as to be able to drive said turboshaft engine (20) in at least one operation mode from among a plurality of predetermined modes.
摘要翻译：本发明涉及用于包括连接到动力齿轮箱的涡轮轴发动机的多引擎直升机的推进系统的架构。所述体系结构的特征在于其包括： - 至少一个混合式涡轮轴发动机（20），其能够在直升机的稳定的滑行飞行期间以至少一种待机模式操作; - 用于控制每个混合式涡轮轴发动机（20）的至少两个链条（30,40），每个链条（30,40）包括连接到混合式涡轮轴发动机（20）并且适于旋转的电机（31,41）其生产气体; 和 - 至少一个用于向所述电机（31,41）供电的电源（33,43）。每个重新启动链（30,40）构造成能够在多个预定模式中的至少一个操作模式中驱动所述涡轮轴发动机（20）。

7. 发明公开

EP3205859A1 GAS TURBINE ENGINE BOWED ROTOR AVOIDANCE SYSTEM 有权转让
标题翻译：燃气轮机发动机转子避让系统
公开(公告)号：EP3205859A1
公开(公告)日：2017-08-16
申请号：EP17155807.5
申请日：2017-02-13
申请人： United Technologies Corporation
发明人： SCHWARZ, Frederick M. , GRACE, Amy R.
IPC分类号： F02C7/277 , F01D25/36 , F01D25/34 , F01D21/00 , F02C7/32
CPC分类号： F02C9/00 , F01D21/00 , F01D25/34 , F01D25/36 , F02C7/268 , F02C7/32 , F05D2220/323 , F05D2260/20 , F05D2260/85 , F05D2270/114 , F05D2270/54 , Y02T50/676
摘要： A bowed rotor prevention system 101 for a gas turbine engine 10 of an aircraft includes a bowed rotor prevention motor 152 operable to drive rotation of a starting spool 32 of the gas turbine engine 10 through an engine accessory gearbox 124, and a controller 102 operable to engage the bowed rotor prevention motor 152 and drive rotation of the starting spool 32 until a bowed rotor prevention threshold condition is met or a bowed rotor prevention shutdown request to halt rotation of the starting spool 32 is received.
摘要翻译：用于飞行器的燃气涡轮发动机10的弓形转子预防系统101包括弓形转子预防马达152和控制器102，该弓形转子预防马达152可操作以驱动燃气涡轮发动机10的起动绕组32的旋转通过发动机附件变速箱124，接合弓形转子防止马达152并且驱动起动绕轴32的旋转直到满足弓形转子预防阈值条件或者接收到用于停止起动绕线轴32的旋转的弓形转子阻止关闭请求。

8. 发明授权

EP2264297B1 Dispositif et procédé pour le démarrage d'un moteur à turbine équipant un hélicoptère, mettant en oeuvre une source d'énergie électrique comprenant des organes d'appoint à décharge 有权转让
标题翻译： Dispositionif etprocédépour ledémarraged'un moteuràturbineéquipantunhélicoptère，mettant en oeuvre une source d'énergieélectriquecomprenant des organes d'appointàdécharge
公开(公告)号：EP2264297B1
公开(公告)日：2017-08-09
申请号：EP10005723.1
申请日：2010-06-02
申请人： Airbus Helicopters
发明人： Gazzino, Marc , Lancelevee, Pierre-Bertrand
IPC分类号： F02C7/26 , F02C7/268 , H02J7/34
CPC分类号： F02C7/26 , F02C7/268 , F05D2220/329 , F05D2260/85 , Y02T50/671

9. 发明公开

EP3123013A1 PROCÉDÉ ET SYSTÈME DE RÉACTIVATION RAPIDE DE TURBOMACHINE 有权
标题翻译： TURBINENMOTORSCHNELLREAKTIVIERUNGSVERFAHREN UND -SYSTEM
公开(公告)号：EP3123013A1
公开(公告)日：2017-02-01
申请号：EP15714880.0
申请日：2015-03-19
申请人： Safran Helicopter Engines
发明人： KLONOWSKI, Thomas , BAZET, Jean-Michel , POUMAREDE, Vincent , HARRIET, Pierre
IPC分类号： F02C6/20 , F02N11/08 , F02C7/268
CPC分类号： F02C7/268 , B64C27/04 , B64D31/00 , B64D2221/00 , F02C6/206 , F02N11/04 , F02N11/0866 , F02N11/087 , F02N2011/0885 , F02N2300/2002 , F05D2220/323 , F05D2220/76 , F05D2260/42 , F05D2260/85 , F05D2270/304 , H02J7/1423 , H02J7/345 , Y02T50/671
摘要： The aircraft turbine engine rapid reactivation system includes an electrical machine (60) supplied with DC power by an onboard electrical power supply network (10). The system also includes: - a switch (50) positioned between the onboard network (10) and the electrical machine (60); - an additional assembly (30) including a plurality N of electrical power storage elements (30a,…,30n); and - a control unit (20) for controlling a device (40) for discharging the storage elements. Said control unit is suitable for placing the onboard network (10) in parallel with a series circuit including at least a portion of the N electrical power storage elements (30a,…,30n) such that, when the rapid reactivation system is in operation, the electrical machine (60) is supplied with power at a voltage level above that of the nominal characteristics thereof.
摘要翻译：飞机涡轮发动机快速再起动系统包括由机载电力供应网络（10）提供直流电力的电机（60）。该系统还包括： - 位于车载网络（10）和电机（60）之间的开关（50）; - 包括多个N个蓄电元件（30a，...，30n）的附加组件（30）; 以及 - 用于控制用于排出存储元件的装置（40）的控制单元（20）。所述控制单元适用于将板载网络（10）与包括N个蓄电元件（30a，...，30n）的至少一部分的串联电路并联放置，使得当快速再起动系统运行时，该电机（60）的电压高于其额定特性的电压。

10. 发明公开

EP3092389A1 PROCÈDE ET SYSTÈME DE DÉMARRAGE FIABILISÉ DE TURBOMACHINE 审中-公开
标题翻译： VERFAHREN UND系统ZUMZUVERLÄSSIGERENSTARTEN EINER TURBOMASCHINE
公开(公告)号：EP3092389A1
公开(公告)日：2016-11-16
申请号：EP14827838.5
申请日：2014-12-15
申请人： Turbomeca
发明人： POUMAREDE, Vincent , HARRIET, Pierre
IPC分类号： F02C7/275 , F02C7/26 , F02C7/268
CPC分类号： F02C7/268 , F02C7/26 , F02C7/275 , F05D2220/323 , F05D2260/85 , H02K7/116 , H02K11/21 , H02K11/25 , H02K23/00 , Y02T50/671
摘要： The starting system comprises a battery of accumulator cells (110), a DC starter (120), an electronic regulator computer (142), a transmission relay (162), starting accessories (168) and a gas generator (160) itself comprising a compressor (164), a combustion chamber (165) and a high-pressure turbine (166) as well as a free turbine (167). First and second circuits are mounted in parallel and interposed between the battery of accumulator cells (110) and the DC starter (120). The first circuit comprises a DC/DC converter (130) mounted in series with a first circuit breaker (132) and the second circuit comprises a second circuit breaker (133). Furthermore, the system comprises at least one sensor (163) sensing the rotational speed of the compressor (164), a sensor (151) sensing the temperature at the inlet of the free turbine (167), and a control circuit (141) controlling the first and second circuit breakers (132, 133) on the basis of the information supplied by the sensor (163) sensing the rotational speed of the compressor (164) and by the sensor (151) sensing the temperature at the inlet to the free turbine (167).
摘要翻译：提供了一种用于可靠启动涡轮发动机的启动系统，该系统包括并联连接并布置在发动机的电池和发动机的直流起动器之间的第一和第二回路，第一电路包括连接在发动机的DC-DC转换器串联第一开关，第二电路包括第二开关; 被配置为感测发动机的压缩机的旋转速度的传感器; 传感器，被配置为感测发动机的空气涡轮机入口处的温度; 以及控制电路，其被配置为根据被配置为感测压缩机的旋转速度的传感器以及构造成感测自由涡轮机的入口温度的传感器提供的信息的函数来控制第一和第二开关。

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