专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

21. 发明公开

EP3656997A1 HYBRID ELECTRIC PROPULSION WITH SUPERPOSITION GEARBOX 有权转让
公开(公告)号：EP3656997A1
公开(公告)日：2020-05-27
申请号：EP19210618.5
申请日：2019-11-21
申请人： United Technologies Corporation
发明人： LEQUE, Nicholas D. , MCCUNE, Michael E. , POLLY, Joseph H.
IPC分类号： F02C3/113 , F02K3/06 , B64D27/02
摘要： A gas turbine engine (20) includes a core engine (22), a fan section, and a superposition gearbox (42) that includes a sun gear (74). A plurality of intermediate gears (76) are engaged to the sun gear (74) and supported in a carrier (78) and a ring gear (80) circumscribing the intermediate gears (76). The core engine (72) drives the sun gear (74) and an output from the superposition gearbox (42) driving the fan section. An electric motor (66) is coupled to a portion of the superposition gearbox (42) to provide a portion of power to drive the fan section through the superposition gearbox (42).

22. 发明公开

EP3409935A1 TURBINE SECTION OF HIGH BYPASS TURBOFAN 有权转让
公开(公告)号：EP3409935A1
公开(公告)日：2018-12-05
申请号：EP18184558.7
申请日：2012-06-15
申请人： United Technologies Corporation
发明人： ADAMS, Paul R. , MAGGE, Shankar S. , STAUBACH, Joseph B. , LORD, Wesley K. , SCHWARZ, Frederick M. , SUCIU, Gabriel L.
IPC分类号： F02K3/06 , F02C7/36 , F02C3/107 , F02K3/075 , F02C3/113
CPC分类号： F02C9/18 , F01D1/02 , F01D5/02 , F01D9/041 , F01D25/24 , F02C3/04 , F02C3/107 , F02C3/113 , F02C7/20 , F02C7/36 , F02K3/025 , F02K3/06 , F02K3/075 , F02K7/06 , F05D2220/32 , F05D2260/40311 , F05D2260/606 , Y02T50/671
摘要： A turbofan engine (20) has an engine case (22) and a gaspath through the engine case (22). A fan (42) has a circumferential array of fan blades (70). The engine further has a compressor, a combustor, a gas generating turbine (26), and a low pressure turbine section (27). A speed reduction mechanism (46) couples the low pressure turbine section (27) to the fan (42). A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio ratio is below about 170.

23. 发明公开

EP3354876A1 GAS TURBINE ENGINE ARCHITECTURE WITH SPLIT COMPRESSOR SYSTEM 有权
公开(公告)号：EP3354876A1
公开(公告)日：2018-08-01
申请号：EP18154161.6
申请日：2018-01-30
申请人： Pratt & Whitney Canada Corp.
发明人： PLANTE, Ghislain , VALOIS, Patrick , DUBREUIL, Jean , BLAIS, Daniel
IPC分类号： F02C3/107 , F02C7/36 , F02C3/113
摘要： A gas turbine engine (10) has an engine core including a low pressure compressor (12a), a high pressure compressor (14a), a high pressure turbine (14b) and a low pressure turbine (12b) coaxially mounted about an engine axis (CL) and fluidly connected in series by a core gaspath (11). The low pressure turbine (12b) is drivingly connected to the low pressure compressor (12a) via an external shaft (12d) disposed radially outwardly of the core gaspath (11).

24. 发明授权

EP2809922B1 GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 有权转让
公开(公告)号：EP2809922B1
公开(公告)日：2018-06-20
申请号：EP13778330.4
申请日：2013-01-30
申请人： United Technologies Corporation
发明人： KUPRATIS, Daniel Bernard , SCHWARZ, Frederick M.
IPC分类号： F02C7/36 , F02C3/113 , F02C7/06
CPC分类号： F02C3/113 , F02C7/06 , F02C7/36 , F05D2260/40311 , Y02T50/671
摘要： A gas turbine engine (20) includes a fan (42), a compressor section (24), a combustor section (26) and a turbine section (28). A speed reduction device (48), such as an epicyclical gear assembly, may be utilized to drive the fan (42) at a speed different than the turbine section (28) so as to increase the overall propulsive efficiency of the engine (20). A shaft driven (30) by the turbine section (28) provides an input to the epicyclical gear assembly (48) such that both the turbine section (28) and the fan (42) can rotate at closer to optimal speeds providing increased performance attributes and performance.

25. 发明公开

EP2728140A3 Booster assembly for gas turbine engine comprising a gearing 有权
标题翻译：用于燃气涡轮发动机的增压器组件，包括传动装置
公开(公告)号：EP2728140A3
公开(公告)日：2018-03-21
申请号：EP13005088.3
申请日：2013-10-24
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Ventor, Gideon Daniel
IPC分类号： F02C3/113
CPC分类号： F02C7/36 , F02C3/064 , F02C3/067 , F02C3/107 , F02C3/113 , F02K3/04 , F02K3/06 , F05D2260/40311
摘要： A booster assembly for a gas turbine engine having a first rotor assembly comprising a low pressure turbine drivingly connected to a fan via a first shaft and a second rotor assembly comprising a second turbine drivingly connected to a high pressure compressor via a second shaft. The first and second rotor assemblies are arranged to undergo relative rotation in use about a common axis. The booster assembly comprises a further compressor arranged to be disposed about said common axis between the fan and high-pressure compressor in a direction of flow and a gearing having first and second input rotors and an output rotor. The first input rotor is arranged to be driven by the first rotor assembly and the second input rotor is arranged to be driven by the second rotor assembly such that the output rotor drives the further compressor in dependence upon the difference in rotational speed between the first and second rotor assemblies.
摘要翻译：一种用于燃气涡轮发动机的增压器组件，该增压器组件具有第一转子组件和第二转子组件，该第一转子组件包括通过第一轴驱动地连接至风扇的低压涡轮，该第二转子组件经由第二轴驱动地连接至高压压缩机。第一和第二转子组件布置成在使用时围绕共同轴线进行相对旋转。增压器组件包括另外的压缩机，该另外的压缩机布置成围绕风扇和高压压缩机之间在流动方向上的公共轴线设置并且具有第一输入转子和第二输入转子以及输出转子的传动装置。第一输入转子布置成由第一转子组件驱动，并且第二输入转子布置成由第二转子组件驱动，使得输出转子根据第一和第二输入转子之间的转速差来驱动另外的压缩机第二转子组件。

26. 发明授权

EP2809927B1 SPEED SENSOR PROBE LOCATION IN GAS TURBINE ENGINE 有权转让
标题翻译：燃气轮机发动机转速传感器探头位置
公开(公告)号：EP2809927B1
公开(公告)日：2017-11-01
申请号：EP12867609.5
申请日：2012-12-23
申请人： United Technologies Corporation
发明人： DAVIS, Todd A. , CIGAL, Brian P.
IPC分类号： F02C3/113 , F02C9/28 , F02C7/00 , F02K3/00
CPC分类号： F01D21/003 , F02C3/107 , F02C3/113 , F05D2220/326 , F05D2220/36 , F05D2260/40311 , F05D2270/021 , F05D2270/023 , F05D2270/304 , F05D2270/80 , Y02T50/671 , Y10T29/49231

27. 发明公开

EP2602458A3 Multiple turboshaft engine control method and system for helicopters 有权
标题翻译：用于多个涡轮发动机和系统用于直升机的控制方法
公开(公告)号：EP2602458A3
公开(公告)日：2016-10-12
申请号：EP12195626.2
申请日：2012-12-05
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Morgan, Keith
IPC分类号： F02C7/36 , F02C9/00 , F01D15/10 , F02C3/10 , F02C3/113 , F02C9/56 , F01D25/36 , F02C6/02 , F02C9/42
CPC分类号： F02C6/02 , F01D15/10 , F01D25/36 , F02C3/10 , F02C3/113 , F02C7/36 , F02C9/00 , F02C9/42 , F02C9/56 , F05B2220/309 , F05D2220/329 , F05D2270/053
摘要： Electric power from the low spool (18) of a turboshaft engine (10,30) is transferred to drive the compressor of an other turboshaft engine (10,30). This is used to assist in maintaining the other turboshaft idling while a single engine provides flight power or to increase acceleration for instance.

28. 发明公开

EP2540991A3 Mechanism for turbine engine start from low spool 有权转让
标题翻译： Mechanismus zum Turbinenmotorstart aus der Niederdruckspule
公开(公告)号：EP2540991A3
公开(公告)日：2015-03-18
申请号：EP12169823.7
申请日：2012-05-29
申请人： United Technologies Corporation
发明人： Berryann, Andrew P. , Suciu, Gabriel L.
IPC分类号： F01D19/00 , F02C3/113 , F02C7/36 , F02K3/04
CPC分类号： F02K3/04 , F01D19/00 , F02C3/113 , F02C7/36 , F02K3/00 , F02K3/02 , F02K3/06 , F02K3/072
摘要： A gas turbine engine (10) includes a high spool (14), a low spool (12) mechanically connected to a fan (26, 28), a gear system (24), an actuator (22; 22'), and a starter (50). The gear system is actuable to engage and disengage the low spool to and from the high spool. The actuator is connected to the gear system for selectively engaging and disengaging the gear system. The starter is connected to the low spool and can drive rotation of the high spool through the low spool when the gear system is engaged.
摘要翻译：一种燃气涡轮发动机（10）包括一个高速滑阀（14），一个与风扇（26,28）机械连接的低阀芯（12），一个齿轮系统（24），一个致动器（22; 22'）和起动器（50）。齿轮系统是致动的，以使低滑阀接合和脱离高速滑阀。致动器连接到齿轮系统，用于选择性地接合和分离齿轮系统。启动器连接到低阀芯，并且当齿轮系统接合时可以通过低阀芯驱动高阀芯的旋转。

29. 发明公开

EP2812540A1 ROTOR FÜR EINE DAMPFTURBINE 有权
标题翻译：转子的蒸汽涡轮机
公开(公告)号：EP2812540A1
公开(公告)日：2014-12-17
申请号：EP13718307.5
申请日：2013-04-05
申请人： Siemens Aktiengesellschaft
发明人： DEVRIES, Jörg
IPC分类号： F01D15/12 , F02C3/113 , F16H37/04
CPC分类号： F01D15/12 , F01D3/02 , F01D5/02 , F01D25/183 , F02C3/113 , F05D2260/40311
摘要： The invention relates to a rotor (3) for a turbomachine, wherein the rotor (3) comprises a planetary gear (1) on which low-pressure end stage blades (17) are arranged, wherein the planetary gear (1) is designed in such a way that the frequency of the rotating blades (17) is lower than the frequency of the rotor (3).

30. 发明公开

EP1777390A3 Gas turbine engine assembly and methods of assembling same 审中-公开
标题翻译：燃气轮机及其组件的方法
公开(公告)号：EP1777390A3
公开(公告)日：2014-02-12
申请号：EP06255241.9
申请日：2006-10-12
申请人： GENERAL ELECTRIC COMPANY
发明人： Orlando, Robert Joseph , Moniz, Thomas Ory
IPC分类号： F02C3/073 , F02K3/072 , F02C7/36 , F02C7/32 , F02C3/067 , F02C3/107 , F02C3/113
CPC分类号： F02K3/072 , F02C3/107 , F02C7/36 , F05D2240/40 , F05D2260/4031 , Y02T50/671
摘要： A method for assembling a gas turbine engine (10) includes coupling a low-pressure turbine (14) to a core turbine engine (12), and coupling a counter-rotating fan assembly (16) including a first fan assembly (50) and a second fan assembly (52) to the low-pressure turbine such that the first fan assembly rotates in a first direction (80) and the second fan assembly rotates in an opposite second direction (82).

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式