专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明公开

EP3394408A1 MÉCANISME DE TRANSMISSION COMPRENANT UN ORGANE D'ACCOUPLEMENT, TURBOMACHINE ÉQUIPÉE D'UN TEL MÉCANISME ET PROCÉDÉ DE FONCTIONNEMENT DUDIT MÉCANISME 有权
公开(公告)号：EP3394408A1
公开(公告)日：2018-10-31
申请号：EP16826105.5
申请日：2016-12-15
申请人： Safran Transmission Systems
发明人： BAUDUIN, Lionel , LECURU, Julian , GUILLEMONT, Maxence
IPC分类号： F02C7/36 , F02C7/32
CPC分类号： F16D43/22 , F02C7/32 , F02C7/36 , F05D2220/50 , F05D2220/76 , F05D2250/25 , F16D21/04 , F16D2011/006 , Y02T50/671
摘要： The invention relates to a power transmission mechanism (30) for a turbomachine (100) comprising: – a reduction gear (31) comprising a first gear (32) and a second gear (33) having different reduction ratios and each comprising a first gear wheel (37) mounted so as to be able to rotate freely on a shared first axle (34) and a second gear wheel (38) mounted on a shared second axle (35); and – a coupling member (1) comprising an annular body (2) with an axis of revolution (O) which comprises first and second rows (6, 7) of helical coupling teeth (8) which are respectively oriented opposite and essentially parallel to the first and second directions, the coupling member being mounted so as to rotate with and slide axially on said first axle (34) so as to occupy at least two predetermined axial meshing positions in which the coupling teeth (8) mesh with complementary meshing projections (47, 48) of one of the first gear wheels (37, 38) which is then made to rotate with the first axle (34).

2. 发明公开

EP3369891A1 GAS TURBINE ENGINE VANES 失效转让
公开(公告)号：EP3369891A1
公开(公告)日：2018-09-05
申请号：EP18155136.7
申请日：2018-02-05
申请人： Rolls-Royce plc
发明人： Northall, Richard , Rae, Anthony J , Krautheim, Michael S , Walker, Alastair D , Carrotte, Jonathan F , Mariah, Ian
IPC分类号： F01D5/14 , F01D9/04 , F01D9/06 , F01D9/02
CPC分类号： F01D9/041 , F01D5/141 , F01D5/142 , F01D9/023 , F01D9/065 , F02K3/04 , F05D2220/323 , F05D2220/50 , F05D2240/128 , F05D2240/129 , Y02T50/671 , Y02T50/673
摘要： An annular array of turning vanes 200 is provided in a duct 100 of a gas turbine engine 10. The annular array of turning vanes 200 comprises aerodynamic vanes 220 and strut-vanes 240. The strut-vanes 240 have greater chord length and extend further axially downstream than the aerodynamic vanes 220. The leading edge of the strut-vanes 240 is upstream of the trailing edge of the aerodynamic vanes 220. The strut-vanes provide flow turning. The space to chord ratio of the aerodynamic vanes that are closest to the suction surface of a strut-vane is higher than the space to chord ratio of aerodynamic vanes that are closest to a pressure surface of the strut-vane. The arrangement allows the duct 100 to be axially short.

3. 发明授权

EP2514926B1 HYBRID CONTROL SYSTEM 有权
公开(公告)号：EP2514926B1
公开(公告)日：2018-07-04
申请号：EP11162762.6
申请日：2011-04-17
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Dooley, Kevin Allan
IPC分类号： F01D15/10 , F01D19/00 , F02C7/32 , F02C9/00 , F02C9/28
CPC分类号： F01D15/10 , F01D19/00 , F02C7/32 , F02C9/00 , F02C9/28 , F05D2220/50 , F05D2220/76 , F05D2270/701 , F05D2270/702 , F05D2270/703 , F05D2270/704 , F05D2270/705 , F05D2270/706
摘要： A hybrid control system (26) for controlling an electric machine (20) coupled to a gas turbine engine (10) is provided. The control system comprises: a primary analog control loop (28) including an analog controller (32) for controlling the electric machine based on a set point and a measured output of the electric machine; and a digital controller (30) of the turbine engine operationally connected to the primary analog control loop to adjust at least one control parameter associated with the analog controller.

4. 发明公开

EP3336329A1 UNITÉ DE GÉNÉRATION DE PUISSANCE ÉLECTRIQUE NON PROPULSIVE 有权
公开(公告)号：EP3336329A1
公开(公告)日：2018-06-20
申请号：EP17207214.2
申请日：2017-12-14
申请人： Safran Power Units , Institut National Polytechnique de Toulouse , CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE
发明人： VAILLANT, Stéphane, Richard, Dominique , FAUCHER, Mickael , TURPIN, Christophe
IPC分类号： F02C3/00 , F02C3/04 , F01D15/10
CPC分类号： B64D27/24 , B64C27/22 , B64D13/06 , B64D2027/026 , B64D2041/002 , F01D15/10 , F02C3/00 , F02C3/04 , F02C7/08 , F02C7/32 , F05D2220/50 , F05D2220/76 , F05D2270/03
摘要： Une unité (1', 10', 100') de génération de puissance électrique non propulsive destinée à être embarquée à bord d'un aéronef, l'unité (1', 10', 100') comprenant un dispositif de production d'électricité (3, 30) comportant une turbine à gaz (31) et un générateur électrique (32) mécaniquement raccordé à un arbre de sortie (33) de la turbine à gaz (31), ledit générateur électrique (32) comportant des connexions électriques (320) de sortie destinées à être électriquement raccordées à un réseau d'alimentation électrique embarqué (2, 20, 200) d'un aéronef.
L'unité (1', 10', 100') comprend des moyens de stockage d'énergie (5) et des moyens de régulation (6) configurés pour commander la vitesse de rotation de la turbine à gaz (31) en fonction de la puissance électrique requise par le réseau d'alimentation électrique embarqué (2, 20, 200).

5. 发明授权

EP3155234B1 TURBOMACHINE COMPRENANT UN SYSTEME D'ENTRAINEMENT D'UN EQUIPEMENT TEL QU'UN BOITIER D'ACCESSOIRES 有权
公开(公告)号：EP3155234B1
公开(公告)日：2018-05-23
申请号：EP15732861.8
申请日：2015-06-11
申请人： SAFRAN AIRCRAFT ENGINES
发明人： LEPRETRE, Jean-Baptiste, Etienne, Bernard
IPC分类号： F01D25/16 , F02C7/32
CPC分类号： F01D15/12 , F01D15/08 , F01D15/10 , F01D25/04 , F01D25/16 , F01D25/20 , F01D25/24 , F02C7/32 , F02C7/36 , F05D2220/30 , F05D2220/50 , F05D2240/60 , F05D2260/96

6. 发明授权

EP2870351B1 FUEL PREHEATING USING ELECTRIC PUMP 失效转让
标题翻译：燃油预热使用电动泵
公开(公告)号：EP2870351B1
公开(公告)日：2018-04-25
申请号：EP13813176.8
申请日：2013-07-02
申请人： United Technologies Corporation
发明人： RIPLEY, David, Lloyd , HAGSHENAS, Behzad
IPC分类号： F02M37/18 , F02M31/02 , B64D37/34 , F02M37/06 , F02M37/08 , F02C7/236 , F02M37/16 , F02M31/16 , F02M37/00 , F02C7/224 , F02C9/26 , F02C9/44
CPC分类号： F02M31/166 , B64D37/34 , F02C7/224 , F02C7/236 , F02C9/263 , F02C9/44 , F02M37/0052 , F02M37/06 , F02M37/08 , F02M37/18 , F05D2220/50 , F05D2260/606 , F05D2260/85 , Y02T10/126 , Y02T50/671
摘要： A fuel system for an auxiliary power unit includes a mechanical fuel pump, an electric fuel pump, and a controller. The mechanical fuel pump provides fuel flow to the auxiliary power unit and has an output dependent upon an operational speed of the auxiliary power unit. The electric fuel pump is located in flow series with the mechanical fuel pump. The controller causes the electric fuel pump to circulate and thereby warm fuel prior to start up of the auxiliary power unit.

7. 发明公开

EP3305372A1 INTEGRATED APU BUILT-IN EXTINGUISHING BOTTLE SYSTEM 审中-实审
标题翻译：集成APU内置灭菌瓶系统
公开(公告)号：EP3305372A1
公开(公告)日：2018-04-11
申请号：EP16192736.3
申请日：2016-10-07
申请人： Airbus Operations S.L.
发明人： Fernandez Lopez, Pio , Angulo Ibáñez, Fernando
IPC分类号： A62C3/08 , F02C7/25
CPC分类号： A62C3/08 , F02C7/25 , F05D2220/50 , Y02T50/671
摘要： The invention is an auxiliary power unit (300) for aircraft, comprising:
- a power section (310) supplied with fuel,
- an electric generator (320), able to provide electric power,
- a load compressor (330), able to provide pneumatic power,
- a gearbox (340), able to adjust the different speeds of rotation needed between the power section (310) and the electric generator (320) in order to deliver solely electric, or pneumatic, or any combination of these powers used simultaneously,
wherein a fire extinguishing system (250) is incorporated as a constitutive part into the auxiliary power unit (300) structure, and able to operate in discharging a flow of extinguisher agent, when a detection system detects an excessive temperature or fire in the APU compartment (200).
摘要翻译：本发明是一种用于飞行器的辅助动力单元（300），包括： - 供应有燃料的动力部分（310）; - 能够提供电力的发电机（320）; - 负荷压缩机（330），能够提供气动动力， - 变速箱（340），其能够调节动力部分（310）和发电机（320）之间所需的不同转速，以便仅传递电动或气动或这些动力的任何组合同时使用，其中灭火系统（250）作为组成部分并入辅助动力单元（300）结构中，并且当检测系统检测到过度温度或火灾时能够操作以排出灭火剂流 APU隔室（200）。

8. 发明公开

EP3287625A1 GAS TURBINE ENGINE COMPRESSOR SURGE AVOIDANCE CONTROL SYSTEM AND METHOD 有权
标题翻译：燃气涡轮发动机压缩机喘振控制系统和方法
公开(公告)号：EP3287625A1
公开(公告)日：2018-02-28
申请号：EP17184600.9
申请日：2017-08-03
申请人： Honeywell International Inc.
发明人： MOECKLY, Kevin , LING, Richard , MORRIS, David
IPC分类号： F02C9/52 , F02C9/54
CPC分类号： F04D27/0246 , F02C9/52 , F02C9/54 , F04D27/001 , F04D29/563 , F05D2220/50 , F05D2270/101 , F05D2270/3011 , F05D2270/303 , F05D2270/312 , F05D2270/313
摘要： A compressor surge avoidance control system and method for a gas turbine engine includes sensing a plurality of engine inlet parameters, and receiving a fuel command value. The sensed parameters are processed to determine a surge fuel value that is representative of a fuel flow above which, for the sensed engine inlet parameters, a compressor surge will likely occur. The surge fuel value and the fuel command value are compared, and a protective action signal is generated if the fuel command value exceeds the surge fuel value.
摘要翻译：一种用于燃气涡轮发动机的压缩机喘振避免控制系统和方法包括感测多个发动机进气参数并接收燃料命令值。处理所感测的参数以确定表示燃料流量的喘振燃料值，在所述燃料流量以上，对于所感测的发动机入口参数，压缩机喘振可能发生。比较浪涌燃料值和燃料指令值，并且如果燃料指令值超过喘振燃料值，则产生保护动作信号。

9. 发明公开

EP3269648A1 POWER GENERATING DEVICE FOR AIRCRAFT 有权
标题翻译：飞机发电装置
公开(公告)号：EP3269648A1
公开(公告)日：2018-01-17
申请号：EP16761305.8
申请日：2016-03-08
申请人： Kawasaki Jukogyo Kabushiki Kaisha
发明人： TANAKA, Kenichiro , IMAI, Hideyuki , FUJII, Isao , GOI, Tatsuhiko , FUCHIWAKI, Shogo
IPC分类号： B64D41/00 , F01D15/10 , F02C7/00 , F02C7/32 , F02C7/36 , F16H1/06 , F16H15/38 , F16H57/023 , H02K7/116 , H02K7/18
CPC分类号： B64D41/00 , F01D15/10 , F02C7/32 , F02C7/36 , F05D2220/50 , F05D2220/76 , F05D2250/312 , F05D2250/36 , F05D2260/39 , F05D2260/402 , F16H1/06 , F16H15/38 , F16H57/023 , F16H2015/386 , F16H2057/02082 , H02K7/116 , H02K7/18 , H02K7/1823 , Y02T50/671
摘要： An electric power generating device for an aircraft, which is driven by an output of an aircraft engine, comprises an input shaft to which a driving force of the engine is transmitted; a transmission arranged with the input shaft; an electric power generator arranged with the input shaft and the transmission and driven by an output of the transmission; a driving force transmission mechanism disposed on a first end side of the input shaft in an axial direction thereof, the driving force transmission mechanism being configured to transmit the output from the transmission to the electric power generator; and a casing including a mounting section on the first end side of the input shaft in the axial direction, wherein the transmission includes an input section provided on a second end side of the input shaft in the axial direction, the input section being configured to receive as an input a rotational driving force from the input shaft, and an output section provided on the first end side of the input shaft in the axial direction, the output section being configured to output to the driving force transmission mechanism the rotational driving force whose speed has been changed, and wherein the driving force transmission mechanism has an inner space and the input shaft is inserted into the inner space.
摘要翻译：一种由飞机发动机的输出驱动的用于飞机的发电装置包括：输入轴，发动机的驱动力被传递至所述输入轴; 与输入轴布置的传动装置; 发电机，其与所述输入轴和所述变速器一起布置并且由所述变速器的输出来驱动; 驱动力传递机构，其设置在所述输入轴的轴向一端侧，所述驱动力传递机构将来自所述变速器的输出传递到所述发电机; 以及壳体，其在所述输入轴的所述第一端侧沿轴向具有安装部，所述变速器包括输入部，所述输入部设置在所述输入轴的所述轴向的第二端侧，所述输入部被构造成接收作为来自所述输入轴的旋转驱动力的输入，以及设置在所述输入轴的所述轴向一端侧的输出部，所述输出部构成为向所述驱动力传递机构输出旋转驱动力，所述旋转驱动力的速度已被改变，并且其中驱动力传递机构具有内部空间并且输入轴被插入到内部空间中。

10. 发明公开

EP3263848A1 DEFORMABLE TURBINE BEARING MOUNT FOR AIR TURBINE STARTER 无效
标题翻译：用于空气涡轮启动的变形涡轮轴承座
公开(公告)号：EP3263848A1
公开(公告)日：2018-01-03
申请号：EP17176741.1
申请日：2017-06-19
申请人： Honeywell International Inc.
发明人： GENTILE, David P. , ZEINER, Peter Kenneth
IPC分类号： F01D21/04 , F02C7/277
CPC分类号： F02C7/277 , F01D21/045 , F02C7/20 , F05D2220/50 , F05D2260/311 , Y02T50/672
摘要： An air turbine starter (10) includes a support structure (44) and a turbine (36) having a shaft (38) and a rotor (39) that extends away from the shaft in a radial direction. The air turbine starter (10) also includes a mount structure (42) that supports the turbine (36) for rotation relative to the support structure (44). The mount structure (42) is configured to transfer a force from the turbine to the support structure. The mount structure (42) includes a deformable member (46) that is configured to deform when the force exceeds a predetermined threshold.
摘要翻译：一种空气涡轮启动器（10）包括支撑结构（44）和涡轮（36），涡轮（36）具有轴（38）和沿径向远离轴延伸的转子（39）。空气涡轮启动器（10）还包括支撑涡轮（36）以相对于支撑结构（44）旋转的安装结构（42）。安装结构（42）构造成将力从涡轮机传递到支撑结构。安装结构（42）包括可变形构件（46），该可变形构件构造成当力超过预定阈值时变形。

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