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1. 发明公开

EP3394401A1 TURBORÉACTEUR AVEC UN MOYEN DE REPRISE DE POUSSÉE SUR LE CARTER INTER-COMPRESSEURS 有权
公开(公告)号：EP3394401A1
公开(公告)日：2018-10-31
申请号：EP16826089.1
申请日：2016-12-12
申请人： Safran Aircraft Engines
发明人： BRAULT, Michel, Gilbert, Roland , BORDONI, Nils, Edouard, Romain , CUVILLIER, Romain, Guillaume , KUBIAK, Guillaume, Patrice , NEGRI, Arnaud, Nicolas , NOWAKOWSKI, Nathalie
IPC分类号： F01D25/16 , F01D25/24 , F01D25/28 , F02K3/06 , F02C7/20
CPC分类号： F02C7/20 , F01D25/162 , F01D25/24 , F01D25/246 , F01D25/28 , F02K3/06 , F05D2230/642 , F05D2240/90 , F05D2250/41 , Y02T50/671
摘要： The present invention relates to a multiflow turbojet engine comprising: a. an upstream fan (2) driven by a gas generator; b. the gas generator comprising first (3) and second (4) coaxial compressors; c. an intake case (8) forming a mounting for the rotors of the fan (2) and the first compressor (3); d. an inter-compressor case (9) downstream from the intake case (8) and forming a mounting for the rotor of the second compressor (4); and e. attachment means for thrust take-up control rods (95) arranged in the inter-compressor case. The turbojet engine is characterised in that it comprises a structural force shroud (32) connecting the intake case (8) to the inter-compressor case (9), the case (31) of the first compressor being floating.

2. 发明公开

EP3354863A3 GAS TURBINE ENGINE CASE MOUNT WITH VIBRATION DAMPING 审中-公开
公开(公告)号：EP3354863A3
公开(公告)日：2018-10-10
申请号：EP18152525.4
申请日：2018-01-19
申请人： United Technologies Corporation
发明人： BINSBERGER, Dale R.
IPC分类号： F01D25/04 , F01D25/28 , F16B5/02 , F16B43/00 , F16B19/02 , F16B37/12
CPC分类号： F01D25/04 , F01D25/24 , F01D25/28 , F05D2240/70 , F05D2240/90 , F05D2260/31 , F05D2260/96 , F05D2300/501 , F05D2300/603 , F16B5/0241 , F16B37/122 , F16B43/001 , Y02T50/672
摘要： The present invention is related to an assembly (46) for a gas turbine engine for providing vibration damping between a component and a mount. This assembly (46) includes a mount (50), a component (48) and a fastener assembly (52) attaching the component (48) to the mount (50). The fastener assembly (52) includes a fastener (68), a bushing (70) and a damper (72). The fastener (68) extends axially along an axis through an aperture in the component (48) and into the mount (50). The bushing (70) extends axially along the axis through the aperture and axially engages the mount (50) and the fastener (68). The damper (72) is configured to damp vibration transmission between the mount (50) and the component (48). The damper (72) is arranged between the mount (50) and the component (48) and between the component (48) and the bushing (70). This assembly improves attachment of composites and metals.

3. 发明公开

EP3350420A1 INTERFACE ET DISPOSITIF DE SUPPORT POUR CARTER MOTEUR 有权
公开(公告)号：EP3350420A1
公开(公告)日：2018-07-25
申请号：EP16785191.4
申请日：2016-09-15
申请人： Safran Aircraft Engines
发明人： DUBOIS, Margaux, Justine, Emma , CAETANO, Nelson , DEMOULIN, Alexandre, Christophe, Adrien
IPC分类号： F01D25/28 , F01D25/24 , B64F5/00 , B66C1/00
CPC分类号： F01D25/285 , B64F5/50 , B66C1/107 , F01D25/24 , F05D2220/32 , F05D2230/60 , F05D2240/14 , F05D2240/90 , F05D2260/31
摘要： The invention relates to the field of supporting interfaces, and particularly a supporting interface (30a, 30b) of this kind for an engine crankcase (90) and including a coupling part (50), a first plurality of bolts (80) and a plurality of pins (70). The coupling part (50) includes an outer surface (52) having a cavity (42) capable of receiving a support arm (20a, 20b), an inner surface (51) which can be mounted on an outer surface (93) of the engine crankcase (90), and a first plurality of openings (53) between the outer surface (52) and the inner surface (51) of the coupling part (50). The bolts (80) each include a threaded rod (82) received in one opening (53) of the first plurality of openings (53), and a head (81) capable of bearing on the outer surface (52) of the coupling part (50). Each pin (70) includes a threaded opening (71) in which the threaded rod (82) of one of the bolts (80) of the first plurality of bolts (80) is inserted through a first end of the pin (70), and a second widened end capable of bearing on an inner surface (92) of the engine crankcase (90). The invention also relates to a method for mounting such a supporting interface.

4. 发明授权

EP2784267B1 A gas turbine engine cooling arrangement 失效转让
公开(公告)号：EP2784267B1
公开(公告)日：2018-07-25
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).

5. 发明授权

EP2299067B1 Turbomachine core coupling assembly 有权转让
标题翻译：涡轮机械核心联轴器组件
公开(公告)号：EP2299067B1
公开(公告)日：2018-03-07
申请号：EP10173135.4
申请日：2010-08-17
申请人： Honeywell International Inc.
发明人： Watson, Bill Russell , Warden, Max
IPC分类号： F01D25/28 , F02C7/20 , F02K3/06
CPC分类号： F01D25/28 , F02C7/20 , F02K3/06 , F05D2240/90
摘要： A coupling assembly for an engine core of a turbomachine is provided. The coupling assembly comprises a duct (114) having a substantially circular shape and surrounding the engine core (112), and a plurality of coupling struts (116), each coupling strut extending only in a substantially vertical direction relative to the direction of gravity when the engine core is at a rest position with zero pitch and zero roll, each of the plurality of coupling struts (116) coupling the engine core to the duct.

6. 发明公开

EP3186490A1 GAS TURBINE ENGINE PACKAGE AND CORRESPONDING METHOD 有权转让
标题翻译：燃气轮机发动机包装及其对应方法
公开(公告)号：EP3186490A1
公开(公告)日：2017-07-05
申请号：EP15760002.4
申请日：2015-08-25
申请人： Rolls-Royce Energy Systems Inc.
发明人： KERSEY, Brent R. , GROSS, Christopher D. , HANSON, Allan G. , STEADY, Loren J. , MACZURA, Anthony
IPC分类号： F01D25/28 , F02C7/20 , F16M5/00 , F02B63/04
CPC分类号： F01D25/285 , F02C7/20 , F05D2230/72 , F05D2240/90 , F16M5/00 , F16M7/00 , F16M9/00
摘要： A gas turbine engine unit (110) for use in a modular power generation system includes an engine package (112) and a mechanical handling system adapted to convey components (114) out of and into the engine package (112). The engine package (112) includes a floor (132), a plurality of side walls (136), and a ceiling (134) that cooperate to define a sheltered space (140) sized to receive a gas turbine engine. The mechanical handling system includes rails (121) adapted to support components (114) conveyed out of and into the sheltered space (140) defined by the engine package (112).
摘要翻译：用于模块化发电系统中的燃气涡轮发动机单元（110）包括发动机组件（112）和适于将部件（114）输出和输入发动机组件（112）的机械处理系统。发动机包装（112）包括配合以限定尺寸设定为容纳燃气涡轮发动机的遮蔽空间（140）的地板（132），多个侧壁（136）和天花板（134）。机械搬运系统包括适于支撑从发动机组件（112）限定的遮蔽空间（140）输送出并进入其中的部件（114）的轨道（121）。

7. 发明公开

EP3156603A1 ASSEMBLING AID FOR ASSEMBLING/DE-ASSEMBLING BLADES ON A DISK 审中-公开
标题翻译： MONTAGEHILFE ZUR MONTAGE / DEMONTAGE VON SCHAUFELN AUF EINER ROTORSCHEIBE
公开(公告)号：EP3156603A1
公开(公告)日：2017-04-19
申请号：EP15189515.8
申请日：2015-10-13
申请人： Siemens Aktiengesellschaft
发明人： Twell, Philip
IPC分类号： F01D5/30 , F01D25/28
CPC分类号： F01D25/285 , B25B11/02 , F01D5/3007 , F05D2230/60 , F05D2230/64 , F05D2230/70 , F05D2240/90 , F05D2250/323 , F05D2250/324
摘要： The present invention relates to an assembling aid (10) for assembling or de-assembling a turbine assembly (12) comprising at least two aerofoil assemblies (14, 16) connected to each other by at least two interlocking platforms (18, 20), wherein the at least two aerofoil assemblies (14, 16) are brought from a free-state untwisted position to an assembled twisted position during assembling, comprising at least one slot (22, 22a, 22') embodied in such a way to receive at least one part (24) of an aerofoil assembly (14, 16), wherein the at least one slot (22, 22a, 22') has an entry aperture (26) and an exit aperture (28).
In order to provide an easy and quick assembling a width (W) of the entry aperture (26) of the at least one slot (22, 22a, 22') is wider than a width (w) of the exit aperture (28) of the at least one slot (22, 22a, 22').
摘要翻译：本发明涉及用于组装或拆卸涡轮机组件（12）的组装辅助装置（10），该组件辅助装置（12）包括至少两个通过至少两个互锁平台（18,20）相互连接的机翼组件（14,16）其中所述至少两个机翼组件（14,16）在组装期间从自由状态未扭转位置带到组装的扭转位置，包括至少一个槽（22,22a，22'）机翼组件（14,16）的至少一个部分（24），其中所述至少一个狭槽（22,22a，22'）具有入口孔（26）和出口孔（28）。为了提供容易且快速的组装，至少一个槽（22,22a，22'）的入口孔（26）的宽度（W）比出口孔（28）的宽度（w）宽，的所述至少一个槽（22,22a，22'）。

8. 发明公开

EP2971579A4 BENCH AFT SUB-ASSEMBLY FOR TURBINE EXHAUST CASE FAIRING 有权转让
标题翻译：背后BANK FOR集团汽轮机排房屋事务委员会
公开(公告)号：EP2971579A4
公开(公告)日：2016-12-21
申请号：EP14807208
申请日：2014-03-11
申请人： UNITED TECHNOLOGIES CORP
发明人： CONWAY CHUONG , LILES JASON DAVID , SCOTT JONATHAN ARIEL
IPC分类号： F01D9/04 , F01D25/28 , F01D25/30 , F02C7/20
CPC分类号： F02C7/20 , F01D25/162 , F01D25/246 , F01D25/30 , F05D2220/32 , F05D2230/232 , F05D2230/50 , F05D2240/90

9. 发明公开

EP2978668A1 DISPOSITIF D'ARTICULATION À ROTULE POUR LA SUSPENSION D'UNE TURBOMACHINE A UN PYLONE OU LA SUSPENSION D'UN EQUIPEMENT AU CORPS DE LA TURBOMACHINE 有权转让
标题翻译：与球窝接头挂涡轮机上的桥塔或挂一个设备以船体涡轮机设备
公开(公告)号：EP2978668A1
公开(公告)日：2016-02-03
申请号：EP14718661.3
申请日：2014-03-21
申请人： SNECMA
发明人： BESNARD, Maryline , LAPORTE, Arnaud
IPC分类号： B64D27/26 , B64D27/18
CPC分类号： F01D25/28 , B64D27/26 , B64D2027/266 , F05D2220/30 , F05D2240/90 , F16C11/06 , F16C11/106
摘要： Ball-jointed device (10) for suspending a turbomachine from a pylon or for suspending equipment from the body of a turbomachine, comprising a link rod (12) of which one end bears a ball (14) and which is interposed between the two flanges (16) of a yoke (18), the ball comprising a bore (28) through which there passes a spindle (30) having an axial bore (31) in which to mount a screw (60) that clamps and axially immobilizes the ball, the ball being axially immobilized by clamping between a bushing (38) and a ring (54) which carries removable means (56) of axially retaining the ring on the yoke during an operation of dismantling the device.

10. 发明公开

EP2961974A1 DISPOSITIF D'INVERSION DE POUSSEE 审中-公开
公开(公告)号：EP2961974A1
公开(公告)日：2016-01-06
申请号：EP14711834.3
申请日：2014-03-03
申请人： Aircelle
发明人： BOILEAU, Patrick , SEGAT, Peter , CARUEL, Pierre , TISSOT, Sarah
IPC分类号： F02K1/09 , F02K1/72
CPC分类号： F02K1/72 , F02K1/09 , F02K1/827 , F05D2240/129 , F05D2240/90 , F05D2250/34
摘要： The subject of the present invention is a thrust reverser device for an aircraft turbojet engine comprising: - a mobile cowl, translating cascades of vanes 1, connected to the mobile cowl able to be moved between a direct-jet position in which they are retracted inside a fan casing, on the one hand, and on the other hand an indirect-jet position in which they are deployed out of said fan casing, - a strut 2, - a front suspension means 4 of said turbojet engine, notable in that the translating cascades of vanes 1 have a sliding connection with the strut 2 via at least one spacer piece 3 connected to the strut 2 downstream of the front suspension 4.
摘要翻译：本发明的主题是一种用于飞机涡轮喷气发动机的推力反向器装置，其包括： - 移动罩，其将连接到移动罩的叶片的叶栅1平移，所述移动罩能够在直接喷射位置和直接喷射位置之间移动，一方面是风扇壳体，另一方面是间接喷射位置，其中它们从所述风扇壳体中展开， - 支柱2， - 所述涡轮喷气发动机的前悬架装置4，其特征在于，平移叶片1的叶栅通过连接到前悬架4下游的支柱2的至少一个间隔件3与支柱2具有滑动连接。

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