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51. 发明公开

EP3002220A1 GAS TURBINE ENGINE MOUNTING ARRANGEMENT 有权转让
标题翻译： MONTAGEANORDNUNGFÜREINEN GASTURBINENMOTOR
公开(公告)号：EP3002220A1
公开(公告)日：2016-04-06
申请号：EP15185914.7
申请日：2015-09-18
申请人： Rolls-Royce plc
发明人： Brain, Glyn
IPC分类号： B64D27/26 , F16B41/00 , F16B39/10 , F16B19/02
CPC分类号： F01D25/28 , B64D27/26 , B64D2027/266 , B64D2027/268 , F05D2220/323 , F05D2230/60 , F05D2240/90 , F05D2260/31 , F16B19/02 , F16B39/10 , F16B41/005 , F16B43/00 , F16C11/045 , G01M17/00
摘要： A failsafe pin (230) for providing a backup load path for attaching a gas turbine engine to an aircraft structure is provided with a driving element that allows a torque to be provided to the pin in order to check whether the pin has been engaged, and thus whether a primary load path has failed. The pin is provided with anti-tamper arrangements in order to ensure that the pin itself is not compromised when being tested for engagement.
摘要翻译：提供用于提供用于将燃气涡轮发动机附接到飞机结构的备用负载路径的故障安全销（230）设置有驱动元件，其允许向销提供扭矩，以便检查销是否已经接合，以及因此主负载路径是否失败。该销具有防篡改装置，以确保在测试接合时销钉本身不受损害。

52. 发明授权

EP2837775B1 Fixation device for turbine and method for applying fixation 有权
标题翻译：用于涡轮机和安装在固定的方法固定装置
公开(公告)号：EP2837775B1
公开(公告)日：2016-03-30
申请号：EP13180510.3
申请日：2013-08-15
申请人： ALSTOM Technology Ltd
发明人： Gerzner, Stefan , Rauch, Marc
IPC分类号： F16B31/04 , F01D11/00 , F16J13/12 , F01D5/00 , F01D25/28 , F01D25/24 , F01D25/26 , F01D17/08
CPC分类号： F01D25/243 , F01D5/005 , F01D11/00 , F01D17/08 , F01D17/085 , F01D25/24 , F01D25/246 , F01D25/26 , F01D25/28 , F01D25/285 , F05D2240/90 , F16B31/043 , F16J13/12 , Y10T29/4932
摘要： The invention provides a fixation device for a turbine, comprising a flange (100) mounted on a housing (400) of the turbine and a nut assembly (200) received in the flange to apply fixation to an component (300) inside the housing, wherein the flange (100) is fixed to the housing by a plurality of first bolts (101) and comprises a central threaded hole, wherein the nut assembly (200) comprises a nut body (201) with a first hole (206) formed along the central axis of the nut body and a plurality of second holes (207) formed around the central axis, and a plurality of second bolts (202) received in the respective second holes (207), wherein the nut body (201) is formed with thread on its outer circumferential surface and fitted within the central threaded hole of the flange (100), and the second bolts (202) are screwed in the second holes (207) to apply fixation against the component (300) inside the housing of the turbine. The nut assembly (200) further comprises a plurality of sleeves (203) received in the respective second holes (207), and the plurality of second bolts (202) are received in the respective sleeves (203). The fixation device in the present invention is able to apply for small and restricted space condition, which makes it possible to position the device very close to the split plane of the turbine. Further, the whole structure of the fixation device is simple with lightweight and easy to assemble with standard tools.

53. 发明公开

EP2971730A1 DISPOSITIF D'INHIBITION MÉCANIQUE INTÉGRÉ À UNE LIGNE DE DÉFENSE D'UN INVERSEUR DE POUSSÉE 有权转让
标题翻译：在国防反向推力装置一体化机械阻挡装置的的线路
公开(公告)号：EP2971730A1
公开(公告)日：2016-01-20
申请号：EP14720992.8
申请日：2014-03-13
申请人： Aircelle
发明人： KIOUA, Hazem , VALLEROY, Laurent Georges , LESCURE, Jérôme , CORFA, Jérôme
IPC分类号： F02K1/72 , F02K1/76
CPC分类号： F02K1/766 , F02K1/72 , F05D2240/90
摘要： The invention relates to a thrust reverser device (19) comprising: - means for deflecting an air flow, comprising at least one mobile element movable between a deployed position and a retracted position, - a locking/unlocking system (23) for locking/unlocking said mobile element, movable between a closed position in which a bolt (25) engages with a striker (27, 29) so as to hold said mobile element in the retracted position of same, and an open position in which said bolt releases said striker, so as to allow said mobile element to shift from the retracted position of same to the deployed position of same, - a mechanical inhibiting device that inhibits said mobile element, holding same in the retracted position thereof. The thrust reverser device according to the invention is remarkable in that the mechanical inhibiting device comprises means (41, 43) for keeping the locking/unlocking system (23) in the closed position of same.

54. 发明公开

EP2901067A2 AUXILIARY COMPONENT MOUNTS 有权转让
标题翻译：辅助元件CARRIER
公开(公告)号：EP2901067A2
公开(公告)日：2015-08-05
申请号：EP13856339.0
申请日：2013-09-13
申请人： United Technologies Corporation
发明人： ROBERTSON, Thomas, J. , CLARKSON, Steven , COSTA, Mark, W.
IPC分类号： F16M13/00
CPC分类号： F02C7/32 , F01D21/045 , F02C7/20 , F05D2220/32 , F05D2240/90 , F05D2260/30 , F05D2260/311
摘要： A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load. A method for protecting a component mounted to a gas turbine engine is also disclosed. The method may include attaching a mount to a casing of the gas turbine engine, the mount including a fusible region that breaks at a predetermined load. The method may further include attaching the component to the mount. The method may further include the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.

55. 发明公开

EP2878774A1 TURBOMACHINE COMPORTANT DES MOYENS DE SUPPORT D'AU MOINS UN ÉQUIPEMENT 有权转让
标题翻译：至少有一种设备支持手段的涡轮机
公开(公告)号：EP2878774A1
公开(公告)日：2015-06-03
申请号：EP14190731.1
申请日：2014-10-28
申请人： SNECMA
发明人： Ancuta, Carmen , Fert, Jérémy, Edmond
IPC分类号： F01D25/28 , F02C7/20 , F02C7/32
CPC分类号： F01D25/28 , B64D2027/266 , B64D2027/268 , F01D25/04 , F02C7/20 , F02C7/32 , F05D2220/323 , F05D2240/90
摘要： Turbomachine, comportant des moyens de reprise des efforts de poussée de son moteur, qui comprennent des bielles longitudinales (32) dont les extrémités sont reliées à des carters annulaires (16, 22) structuraux de la turbomachine, caractérisée en ce qu'elle comprend des moyens (38) de support d'au moins un équipement (34, 36) sur lesdites bielles de reprise de poussée et/ou de suspension d'au moins un équipement auxdites bielles de reprise de poussée.
摘要翻译：涡轮机，包括用于占用发动机的推力，其包括纵向杆（32），其端部被连接到涡轮机的结构的环形壳体（16，22），其特征在于它包括用于在所述杆上支撑至少一件设备（34,36）的装置（38），用于在所述推力回收杆处承受推力和/或悬挂至少一件设备。

56. 发明公开

EP2784267A3 A gas turbine engine cooling arrangement 失效转让
标题翻译：燃气轮机发动机冷却装置
公开(公告)号：EP2784267A3
公开(公告)日：2015-04-15
申请号：EP14158097.7
申请日：2014-03-06
申请人： Rolls-Royce plc
发明人： Mulcaire, Thomas
IPC分类号： F01D9/06 , F02C7/18 , F01D5/08 , F01D25/24 , F02C6/08 , F04D29/54
CPC分类号： F01D25/12 , F01D5/082 , F01D5/085 , F01D9/065 , F01D25/246 , F02C6/08 , F02C7/185 , F04D29/321 , F04D29/542 , F05D2240/90 , F05D2260/213 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine (10) comprises a compressor (14), a combustion chamber (15), an outer casing (20), an inner casing (22) and a cooling arrangement (24). The outer casing (20) surrounds the compressor (14) and the combustion chamber (15) and the combustion chamber (15) has turbine nozzle guide vanes (26). The compressor (14) has load carrying outlet guide vanes (28) connected to the outer casing (20) and the inner casing (22). The turbine nozzle guide vanes (26) connect the outer casing (20) and the inner casing (22). The cooling arrangement (24) comprises a cooling air duct (38) located between the compressor (14) and the combustion chamber (15). The compressor outlet guide vanes (28) carry at least one aerodynamic fairing (40). A support structure (42) supports the cooling air duct (38) from the inner casing (22) at two spaced positions and the support structure (42) forms a chamber (50) with the inner casing (22). The support structure (42) comprises at least one hollow duct (48) and each hollow duct (48) locates behind a respective one of the aerodynamic fairings (40).
摘要翻译：燃气涡轮发动机10包括压缩机14，燃烧室15，外壳20，内壳22和冷却装置24。外壳（20）围绕压缩机（14）和燃烧室（15），燃烧室（15）具有涡轮喷嘴导向叶片（26）。压缩机14具有与外壳20和内壳22连接的载重输出导向叶片28。涡轮喷嘴导向叶片26连接外壳20和内壳22。冷却装置（24）包括位于压缩机（14）和燃烧室（15）之间的冷却空气管道（38）。压缩机出口导叶（28）带有至少一个空气动力整流罩（40）。支撑结构（42）在两个间隔位置处从内壳（22）支撑冷却空气管道（38），并且支撑结构（42）与内壳（22）形成腔室（50）。支撑结构（42）包括至少一个空心导管（48），并且每个空心导管（48）位于相应的一个空气动力学整流件（40）的后面。

57. 发明公开

EP2837775A1 Fixation device for turbine and method for applying fixation 有权
标题翻译： Fixiervorrichtungfüreine Turbine und Verfahren zum Anbringen der Fixierung
公开(公告)号：EP2837775A1
公开(公告)日：2015-02-18
申请号：EP13180510.3
申请日：2013-08-15
申请人： ALSTOM Technology Ltd
发明人： Gerzner, Stefan , Rauch, Marc
IPC分类号： F01D25/24 , F01D25/26 , F01D25/28 , F16B31/00 , F01D5/00 , F16J13/12 , F01D17/08
CPC分类号： F01D25/243 , F01D5/005 , F01D11/00 , F01D17/08 , F01D17/085 , F01D25/24 , F01D25/246 , F01D25/26 , F01D25/28 , F01D25/285 , F05D2240/90 , F16B31/043 , F16J13/12 , Y10T29/4932
摘要： The invention provides a fixation device for a turbine, comprising a flange (100) mounted on a housing (400) of the turbine and a nut assembly (200) received in the flange to apply fixation to an component (300) inside the housing, wherein the flange (100) is fixed to the housing by a plurality of first bolts (101) and comprises a central threaded hole, wherein the nut assembly (200) comprises a nut body (201) with a first hole (206) formed along the central axis of the nut body and a plurality of second holes (207) formed around the central axis, and a plurality of second bolts (202) received in the respective second holes (207), wherein the nut body (201) is formed with thread on its outer circumferential surface and fitted within the central threaded hole of the flange (100), and the second bolts (202) are screwed in the second holes (207) to apply fixation against the component (300) inside the housing of the turbine. The nut assembly (200) further comprises a plurality of sleeves (203) received in the respective second holes (207), and the plurality of second bolts (202) are received in the respective sleeves (203). The fixation device in the present invention is able to apply for small and restricted space condition, which makes it possible to position the device very close to the split plane of the turbine. Further, the whole structure of the fixation device is simple with lightweight and easy to assemble with standard tools.
摘要翻译：本发明提供了一种用于涡轮机的固定装置，包括安装在涡轮机的壳体（400）上的凸缘（100）和容纳在凸缘中的螺母组件（200），以对壳体内的部件（300）施加固定，其中所述凸缘（100）通过多个第一螺栓（101）固定到所述壳体并且包括中心螺纹孔，其中所述螺母组件（200）包括螺母体（201），所述螺母体（201）具有沿着所述第一孔螺母主体的中心轴线和围绕中心轴线形成的多个第二孔（207）和容纳在各个第二孔（207）中的多个第二螺栓（202），其中形成螺母体（201）在其外圆周表面上具有螺纹并且装配在凸缘（100）的中心螺纹孔内，并且第二螺栓（202）被拧入第二孔（207）中以将固定件抵靠在壳体内的部件（300）的内部涡轮机。螺母组件（200）还包括容纳在相应的第二孔（207）中的多个套筒（203），并且多个第二螺栓（202）被容纳在相应的套筒（203）中。本发明中的固定装置能够应用小且受限的空间状态，这使得可以将装置定位得非常靠近涡轮机的分裂平面。此外，固定装置的整体结构简单，重量轻，易于与标准工具组装。

58. 发明公开

EP2826709A1 Installation motrice modulaire et aéronef muni d'un rotor de sustentation 有权
标题翻译：模块化驱动系统和飞机用浮力转子
公开(公告)号：EP2826709A1
公开(公告)日：2015-01-21
申请号：EP14002129.6
申请日：2014-06-20
申请人： Airbus Helicopters
发明人： Honnorat, Olivier
IPC分类号： B64C27/12 , B64D35/08
CPC分类号： B64C27/12 , B64C27/473 , B64D27/14 , F02C7/12 , F02C7/20 , F02C7/36 , F05D2220/328 , F05D2220/329 , F05D2240/90 , F05D2260/40311 , F16H57/025
摘要： La présente invention concerne une installation motrice (10) munie d'une boîte de transmission de puissance (20), d'un moteur à turbine (40) et d'un échangeur thermique (60), la boîte de transmission de puissance (20) comprenant un mât rotor (21) sensiblement vertical. La boîte de transmission de puissance (20) comporte au moins un étage de réduction de vitesse de rotation agencé dans un carter plat (22) et un pylône (23). Le moteur à turbine (40) comporte un carter moteur (42) et un arbre de sortie saillant dudit carter moteur (42) et pénétrant dans ledit carter plat (22), ledit arbre de sortie (41) étant sensiblement parallèle au mât rotor (21), ledit carter moteur (42) étant longitudinalement décalé par rapport au pylône (23) et n'étant pas en contact avec ce pylône (23). L'échangeur thermique (60) s'étend longitudinalement en arrière dudit moteur à turbine (40), ledit mât rotor (21) étant à l'inverse situé longitudinalement devant ledit moteur à turbine (40).

59. 发明公开

EP2809891A1 GAS TURBINE ENGINE MID TURBINE FRAME BEARING SUPPORT 有权转让
标题翻译：支持用于燃气轮机涡轮的介质帧仓库
公开(公告)号：EP2809891A1
公开(公告)日：2014-12-10
申请号：EP13775408.1
申请日：2013-01-24
申请人： United Technologies Corporation
发明人： MAYER, Robert, Russell , KRAMER, George, J. , PALMER, Paul, W.
IPC分类号： F01D25/16
CPC分类号： F02C7/06 , F01D25/164 , F01D25/243 , F02C3/045 , F02C7/20 , F02C7/36 , F05D2220/32 , F05D2240/90 , F05D2260/30 , F05D2260/40311 , F23R3/002 , F23R3/60 , Y02T50/671
摘要： A gas turbine engine includes high and low pressure turbines. A mid turbine frame is arranged axially between the high and low pressure turbines. A bearing is operatively supported by a support structure. An inner case is secured to the support structure and includes a first conical member and a bearing support to which the bearing is mounted. The bearing support includes a second conical member that is secured to the first conical member at a joint. The first and second conical members are arranged radially inward of the joint.

60. 发明授权

EP1840364B1 Chambre de post-combustion 有权
标题翻译：加力
公开(公告)号：EP1840364B1
公开(公告)日：2014-05-07
申请号：EP07290289.3
申请日：2007-03-06
申请人： SNECMA
发明人： Bunel, Jacques Marcel , Page, Alain Pierre , Roche, Jacques, André, Michel , Vuillemenot, Yann, Francois, Jean-Claude
IPC分类号： F02K3/10
CPC分类号： F02K3/10 , F05D2240/14 , F05D2240/90 , F05D2260/30

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