-
公开(公告)号：US09945259B2
公开(公告)日：2018-04-17
申请号：US14765680
申请日：2014-03-14
发明人： Brian P. Cigal , Todd A. Davis
CPC分类号： F01D25/28 , F01D25/04 , F01D25/16 , F01D25/162 , F01D25/164 , F01D25/18 , F01D25/243 , F02C7/20 , F02K3/06 , F05D2220/32 , F05D2220/327 , F05D2230/10 , F05D2230/21 , F05D2260/30 , F05D2260/40311 , F05D2260/96
摘要： A gas turbine engine is provided. The gas turbine engine may include a geared architecture, a central body support and a bearing package. The geared architecture may interconnect a spool and a fan rotatable about an axis. The central body support may provide an annular wall for a core flow path and an integral flex support inwardly extending therefrom. The integral flex support may couple the geared architecture to the central body support. The bearing package may include a bearing support removably coupled to the integral flex support.
-
公开(公告)号：US20180066541A1
公开(公告)日：2018-03-08
申请号：US15560430
申请日：2016-03-11
发明人： Masayuki HARA , Satoru YOKOSHIMA , Tooru IIJIMA , Yasunori KOZUKA , Etsuo KOBAYASHI , Naoki TOBARI
CPC分类号： F01D25/26 , B23K9/00 , B23K9/02 , F01D21/045 , F01D25/04 , F01D25/24 , F02B37/00 , F02B39/00 , F02B39/16 , F05D2220/40 , F05D2230/232 , F05D2260/96
摘要： A turbine housing includes an inner pipe that forms an exhaust air flow path in which a turbine wheel accommodating a turbine shaft is arranged; and an outer pipe that is spaced from the inner pipe at a predetermined distance and covers the inner pipe. At least one reinforcing plate is secured to an inner surface of the outer pipe.
-
公开(公告)号：US20180016939A1
公开(公告)日：2018-01-18
申请号：US15642613
申请日：2017-07-06
发明人： Christoph KLAUS
CPC分类号： F01D25/04 , F02C7/36 , F02K3/04 , F05D2260/40311 , F05D2260/96 , F05D2300/501 , F16H1/28 , F16H57/0006 , F16H57/08
摘要： A gas turbine engine comprising a gearbox, the gearbox comprising a sun gear, an annulus gear, a plurality of planet gears and a carrier, each planet gear being rotatably mounted in the carrier by at least one bearing, the sun gear meshing with the planet gears and the planet gears meshing with the annulus gear, the sun gear, the planet gears and the annulus gear comprising gear teeth, the annulus gear having a length in the axial direction and an axially forward end and an axially rearward end and wherein the annulus gear is resiliently mounted to a supporting structure at both its axially forward and axially rearward ends.
-
公开(公告)号：US20180010482A1
公开(公告)日：2018-01-11
申请号：US15207207
申请日：2016-07-11
CPC分类号： F01D25/04 , F01D25/162 , F01D25/30 , F02C7/20 , F02C7/22 , F02K3/10 , F05D2220/323 , F05D2230/237 , F05D2260/96 , F16F7/116
摘要： A tuned mass damper for reducing vibration on a component includes a shaft connector member configured to be coupled to the component and a cable termination member. The tuned mass damper also includes at least one cable coupled to the shaft connector member and to the cable termination member such that vibration of the component is transferred to the at least one cable via the shaft connector member and increased or decreased by the at least one cable.
-
公开(公告)号：US20180003075A1
公开(公告)日：2018-01-04
申请号：US15635313
申请日：2017-06-28
CPC分类号： F01D25/04 , F01D25/166 , F01D25/18 , F05D2220/32 , F05D2240/50 , F05D2260/98 , F16C17/02 , F16C17/022 , F16C17/24 , F16C23/04 , F16C33/108 , F16C2233/00 , F16C2360/00 , F16C2360/23
摘要： A bearing configured to actively damp vibration of a shaft in a turbine. In one implementation, the bearing can include actuating members that move in a manner that changes properties of fluid, typically a thin film of lubricant, disposed in the bearing to facilitate rotation of the shaft. These changes effectively manipulate the stiffness and damping of the thin film according to a time periodicity that matches a parametric anti-resonance of the bearing. In turn, the resulting interaction of vibrating modes is favorable to damp vibration amplitudes at critical speeds.
-
公开(公告)号：US09840937B2
公开(公告)日：2017-12-12
申请号：US14596684
申请日：2015-01-14
申请人： Siemens Energy, Inc.
CPC分类号： F01D25/04 , F01D25/162 , F01D25/30 , F05D2230/644
摘要： Disclosed are a casing arrangement and a method to reduce vibrations in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer.
-
公开(公告)号：US09828876B2
公开(公告)日：2017-11-28
申请号：US14696963
申请日：2015-04-27
发明人： Matthew J. Kappes
CPC分类号： F01D25/24 , F01D11/122 , F01D21/045 , F01D25/04 , F05D2220/32 , F05D2220/36 , F05D2230/50 , F05D2230/60 , F05D2300/6012 , F05D2300/603 , F05D2300/615 , Y02T50/672
摘要： A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.
-
公开(公告)号：US20170335702A1
公开(公告)日：2017-11-23
申请号：US15156993
申请日：2016-05-17
摘要： Aspects of the disclosure are directed to a seal comprising: a first fitting configured to couple to a first disk, and a curvic joint including curvic teeth, where a first distance between the first fitting and the curvic teeth is equal to or greater than a first thickness of the first disk. In some embodiments, an engine comprises: a compressor disk, a turbine disk, and a seal including: a first fitting configured to couple to the turbine disk, a second fitting configured to couple to the compressor disk, and a curvic joint including curvic teeth, where a first axial distance between the first fitting and the curvic teeth is greater than or equal to a first radial thickness of the turbine disk.
-
公开(公告)号：US20170314397A1
公开(公告)日：2017-11-02
申请号：US15488544
申请日：2017-04-17
申请人： MTU Aero Engines AG
发明人： Andreas Hartung , Manfred Schill
CPC分类号： F01D5/16 , F01D9/02 , F04D29/322 , F04D29/324 , F04D29/542 , F04D29/668 , F05D2220/323 , F05D2250/232 , F05D2260/96 , Y02T50/671
摘要： The present invention relates to a turbomachine blade or vane arrangement having a first turbomachine blade or vane (10), a second turbomachine blade or vane (20) adjacent to it, and at least one tuning element guide housing (30) with at least one cavity, in which at least one tuning element (5) is arranged with play of movement for impact contact with the tuning element guide housing, with the tuning element guide housing being arranged at least in part in a recess (11), in particular in a frame (12), of the first turbomachine blade or vane (10), where the second turbomachine blade or vane (20) has at least one first rib (21) for securing the tuning element guide housing (30) arranged in the recess (11).
-
公开(公告)号：US09790809B2
公开(公告)日：2017-10-17
申请号：US14666458
申请日：2015-03-24
CPC分类号： F01D25/04 , F01D5/26 , F01D9/041 , F01D11/001 , F01D11/122 , F05D2220/32 , F05D2240/12 , F05D2240/55 , F05D2240/80
摘要： A stator assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, at least one stator vane including a platform, a seal member connected to the platform, and a damper between the platform and the seal member. The damper includes a plurality of first fingers and a plurality of second fingers, which are provided in an alternating arrangement.
-
-
-
-
-
-
-
-
-
搜索结果
696 条记录 (耗时 0.045 秒)