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1. 发明申请

US20180238240A1 COMPOSITE PISTON RING SEAL FOR AXIALLY AND CIRCUMFERENTIALLY TRANSLATING DUCTS 审中-公开
公开(公告)号：US20180238240A1
公开(公告)日：2018-08-23
申请号：US15913105
申请日：2018-03-06
申请人： United Technologies Corporation
发明人： Steven D. Porter , Donald W. Peters , James P. Bangerter
IPC分类号： F02C7/28 , F02C3/04 , F02K1/80 , F16J15/34
CPC分类号： F02C7/28 , F02C3/04 , F02K1/805 , F05D2220/32 , F05D2240/55 , F05D2240/58 , F05D2250/14 , F05D2250/314 , F05D2250/34 , F05D2250/41 , F05D2260/38 , F05D2260/57 , F05D2300/603 , F05D2300/6034 , F16J15/3488 , Y02T50/672
摘要： A seal system is provided. The seal system may comprise a first duct having an annular geometry, a second duct overlapping the first duct in a radial direction, and a seal disposed between the first duct and the second duct. The seal may comprise a groove defined by the first duct and a piston configured to slideably engage the groove.

2. 发明授权

US09777671B2 Actuation system for a translating variable area fan nozzle 有权
公开(公告)号：US09777671B2
公开(公告)日：2017-10-03
申请号：US13769599
申请日：2013-02-18
申请人： Rohr, Inc. , Goodrich Actuation Systems Limited
发明人： Jihad I. Ramlaoui , Geoffrey Pinto , Daniel Shetzer , Daniel M. Amkraut , Andrew Robert Hawksworth , John Harvey , Alan K. Evans , Vikram Chandarana , Roger Moorhouse
IPC分类号： F02K1/09 , F02K1/64 , F02K1/72 , F02K1/76 , F02K1/70
CPC分类号： F02K1/763 , F02K1/09 , F02K1/30 , F02K1/70 , F02K1/72 , F02K3/06 , F05D2250/34 , Y10T74/18576 , Y10T74/18648
摘要： A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating thrust reverser sleeve with a trailing edge. The thrust reverser sleeve is movably disposed aft of the nacelle's aft edge and is movable between a forward position and an aft position. A translating fan nozzle having a forward edge is movably disposed behind the trailing edge, and is movable between a stowed position and a deployed position. An upstream bypass flow exit is defined between the trailing edge and the forward edge when the fan nozzle is in the deployed position. An extendable actuation system is configured to move the fan nozzle between the stowed position and the deployed position.

3. 发明申请

US20170175750A1 METHOD AND SYSTEM FOR VARYING TIP CLEARANCE GAP USING AN ACTUATED SHROUD 审中-公开
公开(公告)号：US20170175750A1
公开(公告)日：2017-06-22
申请号：US14978908
申请日：2015-12-22
申请人： General Electric Company
发明人： Kevin Randall McManus
IPC分类号： F04D27/00 , F02C3/06 , F04D29/08 , F04D29/32 , F04D29/52 , F04D29/54 , F02K3/06 , F04D19/02
CPC分类号： F04D29/526 , F01D11/22 , F04D19/02 , F04D27/0246 , F04D29/164 , F05D2220/323 , F05D2240/11 , F05D2250/34 , F05D2260/56 , F05D2270/58
摘要： An actuated shroud system configured to control tip clearances in a rotatable machine is provided. The system includes a rotor including a plurality of blades. Each of the plurality of blades includes a blade tip, and each blade tip includes a radially outer tip surface angled in the radial direction. The system also includes a shroud circumscribing the plurality of blades and including a radially inner surface angled complementarily to the radially outer tip surface of the blade tip. The radially inner surface and the radially outer tip surface define a tip clearance gap therebetween. The system further includes a shroud actuator operably coupled to the shroud, the shroud actuator configured to translate the shroud in at least one of an axial direction and the radial direction such that the tip clearance gap is variable based on a position of the shroud actuator.

4. 发明申请

US20160186688A1 INTEGRATED THRUST REVERSER ACTUATION SYSTEM 审中-公开
标题翻译：集成式逆变器启动系统
公开(公告)号：US20160186688A1
公开(公告)日：2016-06-30
申请号：US14293605
申请日：2014-06-02
申请人： GE Aviation Systems LLC
发明人： John S. Mears , George Stephen Billisits , Chad Russell Wentling
IPC分类号： F02K1/56 , F02C7/20
CPC分类号： F02K1/56 , F02C7/20 , F02K1/09 , F02K1/15 , F02K1/72 , F02K1/763 , F05D2250/34 , F05D2260/57 , F05D2270/60 , F05D2270/62 , F05D2270/64 , F05D2270/66
摘要： A turbofan engine having a turbine engine, a nacelle surrounding a portion of the turbine engine, and a thrust reverser. The thrust reverser comprises a movable control surface movable to and from a reversing position and a thrust reverser actuation system having at least one actuator operably coupled to the movable control surface to move the movable control surface into and out of the reversing position. A guide comprising a rail and a bogie having at least one rotatable bearing surface coupled to the rail for relative translational movement between the rail and bogie connects the turbine engine to the movable control surface such that operation of the at least one actuator moves the movable control surface by translation movement between the rail and the bogie.
摘要翻译：具有涡轮发动机，围绕涡轮发动机的一部分的机舱和推力反向器的涡轮风扇发动机。推力反向器包括可移动到可逆位置的可移动控制表面和推力反向器致动系统，其具有可操作地联接到可移动控制表面的至少一个致动器，以将可移动控制表面移入和移出反转位置。包括轨道和转向架的引导件具有联接到轨道的至少一个可旋转支承表面，用于在轨道和转向架之间的相对平移运动将涡轮发动机连接到可移动控制表面，使得至少一个致动器的操作使可移动控制器轨道与转向架之间的平移运动。

5. 发明申请

US20160169158A9 ACTUATION SYSTEM FOR A TRANSLATING VARIABLE AREA FAN NOZZLE 有权
公开(公告)号：US20160169158A9
公开(公告)日：2016-06-16
申请号：US13769599
申请日：2013-02-18
申请人： ROHR, INC. , GOODRICH ACTUATION SYSTEMS LIMITED
发明人： Jihad I. Ramlaoui , Geoffrey Pinto , Daniel Shetzer , Daniel M. Amkraut , Andrew Robert Hawksworth , John Harvey , Alan K. Evans , Vikram Chandarana , Roger Moorehouse
IPC分类号： F02K1/76
CPC分类号： F02K1/763 , F02K1/09 , F02K1/30 , F02K1/70 , F02K1/72 , F02K3/06 , F05D2250/34 , Y10T74/18576 , Y10T74/18648
摘要： A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating thrust reverser sleeve with a trailing edge. The thrust reverser sleeve is movably disposed aft of the nacelle's aft edge and is movable between a forward position and an aft position. A translating fan nozzle having a forward edge is movably disposed behind the trailing edge, and is movable between a stowed position and a deployed position. An upstream bypass flow exit is defined between the trailing edge and the forward edge when the fan nozzle is in the deployed position. An extendable actuation system is configured to move the fan nozzle between the stowed position and the deployed position.

6. 发明申请

US20130280053A1 AXIAL COMPRESSOR 有权
标题翻译：轴压缩机
公开(公告)号：US20130280053A1
公开(公告)日：2013-10-24
申请号：US13917933
申请日：2013-06-14
申请人： ALSTOM Technology Ltd
发明人： Marco MICHELI , Wolfgang KAPPIS , Luis Federico PUERTA
IPC分类号： F04D19/00
CPC分类号： F04D19/00 , F01D5/142 , F01D5/146 , F04D29/544 , F05D2250/34 , F05D2250/38
摘要： The axial compressor has a two-stage guide vane cascade at the discharge-side end of the rotor. The guide vanes of the second stage of the cascade are staggered in the circumferential direction in relation to the guide vanes of the first stage in such a way that vortex streamers created by the guide vanes of the first stage cannot impinge upon the guide vanes of the second stage.
摘要翻译：轴向压缩机在转子的排出侧端部具有两级导叶叶栅级联。级联的第二级的引导叶片相对于第一级的引导叶片在圆周方向上交错，使得由第一级的导向叶片产生的涡旋飘带不会撞击到第一级的导向叶片第二阶段

7. 发明授权

US08511062B2 Actuation system for a translating variable area fan nozzle 有权
标题翻译：可变区风扇喷嘴的启动系统
公开(公告)号：US08511062B2
公开(公告)日：2013-08-20
申请号：US12485559
申请日：2009-06-16
申请人： Jihad I. Ramlaoui , Geoffrey Pinto , Daniel Shetzer , Daniel M. Amkraut , Andrew Robert Hawksworth , John Harvey , Alan K. Evans , Vikram Chandarana , Roger Moorhouse
发明人： Jihad I. Ramlaoui , Geoffrey Pinto , Daniel Shetzer , Daniel M. Amkraut , Andrew Robert Hawksworth , John Harvey , Alan K. Evans , Vikram Chandarana , Roger Moorhouse
IPC分类号： F02K1/09 , F02K1/64 , F02K1/72
CPC分类号： F02K1/763 , F02K1/09 , F02K1/30 , F02K1/70 , F02K1/72 , F02K3/06 , F05D2250/34 , Y10T74/18576 , Y10T74/18648
摘要： A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating thrust reverser sleeve with a trailing edge. The thrust reverser sleeve is movably disposed aft of the nacelle's aft edge and is movable between a forward position and an aft position. A translating fan nozzle having a forward edge is movably disposed behind the trailing edge, and is movable between a stowed position and a deployed position. An upstream bypass flow exit is defined between the trailing edge and the forward edge when the fan nozzle is in the deployed position. An extendable actuation system is configured to move the fan nozzle between the stowed position and the deployed position.
摘要翻译：用于涡轮风扇发动机的可变区域风扇喷嘴组件包括具有后缘的机舱和具有后缘的平移推力反向器套筒。推力反向器套筒可移动地设置在机舱的后边缘的后部并且可以在前进位置和后部位置之间移动。具有前边缘的平移风扇喷嘴可移动地设置在后缘的后面，并且可在收起位置和展开位置之间移动。当风扇喷嘴处于展开位置时，在后缘和前缘之间限定上游旁路流出口。可延伸致动系统构造成使风扇喷嘴在收起位置和展开位置之间移动。

8. 发明授权

US08402765B2 Translating variable area fan nozzle providing an upstream bypass flow exit 有权
标题翻译：翻译可变区域风扇喷嘴，提供上游旁路流出口
公开(公告)号：US08402765B2
公开(公告)日：2013-03-26
申请号：US12485551
申请日：2009-06-16
申请人： Daniel M. Amkraut , Michael John Layland , Norman John James
发明人： Daniel M. Amkraut , Michael John Layland , Norman John James
IPC分类号： F02K1/09 , F02K3/075 , F02K1/70
CPC分类号： F02K1/763 , F02K1/09 , F02K1/30 , F02K1/70 , F02K1/72 , F02K3/06 , F05D2250/34 , Y10T74/18576 , Y10T74/18648
摘要： A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end.
摘要翻译：用于涡轮风扇发动机的可变区域风扇喷嘴组件包括具有后边缘的机舱和具有前边缘和第一端的平移喷嘴段。喷嘴段可移动地设置在后边缘之后，使得当喷嘴段处于展开位置时，在后边缘和前边缘之间限定上游旁路流出口。偏转器设置在靠近第一端的后边缘和前边缘之间。偏转器基本上防止在接近第一端的区域中旁路流离开上游旁路流出口。

9. 发明申请

US20120217320A1 THRUST INVERTER 有权
标题翻译：逆变器
公开(公告)号：US20120217320A1
公开(公告)日：2012-08-30
申请号：US13510352
申请日：2010-10-26
申请人： Guy Bernard Vauchel , Pierre Caruel , Andre Baillard , Peter Segat
发明人： Guy Bernard Vauchel , Pierre Caruel , Andre Baillard , Peter Segat
IPC分类号： B63H11/10
CPC分类号： F02K1/72 , B64D29/06 , B64D29/08 , F01D25/24 , F01D25/243 , F01D25/28 , F02C7/20 , F02K1/54 , F02K1/64 , F02K1/68 , F05D2250/34
摘要： The present invention relates to a thrust inverter for a turbojet engine nacelle (1) including at least one outer cowl (11) that is movable between a closed position and a thrust inversion position, said movable cowl also being able to be opened into a supporting position towards which said movable cowl is hinged and guided through the use of a guiding means that is suitable to said movable cowl and located substantially on a pylon, to which the nacelle is intended to be attached and at least one front frame (15) capable of being mounted downstream from an air blower housing for said turbojet engine and directly or indirectly holds at least one flow diversion means (12). Said thrust inverter is characterized in that the front frame is detachably connected to the housing in a translatable manner along at least one related guiding member (17) once said front frame is detached from the housing.
摘要翻译：本发明涉及一种用于涡轮喷气发动机机舱（1）的推力逆变器，其包括至少一个能够在关闭位置和推力倒置位置之间移动的外罩（11），所述可动罩也能够被打开成支撑所述可移动整流罩铰接并引导通过使用适于所述可移动整流罩并且基本上位于所述机舱旨在附接的塔架上的导向装置的位置，以及至少一个前框架（15）能够被安装在用于所述涡轮喷气发动机的鼓风机壳体的下游，并且直接或间接保持至少一个分流装置（12）。所述推力逆变器的特征在于，一旦所述前框架与壳体分离，前框架可沿着至少一个相关的引导构件（17）以可平移的方式可拆卸地连接到壳体。

10. 发明授权

US06379118B2 Cooled blade for a gas turbine 有权
标题翻译：用于燃气轮机的冷却叶片
公开(公告)号：US06379118B2
公开(公告)日：2002-04-30
申请号：US09758188
申请日：2001-01-12
申请人： Ewald Lutum , Klaus Semmler , Jens Wolfersdorf
发明人： Ewald Lutum , Klaus Semmler , Jens Wolfersdorf
IPC分类号： F01D518
CPC分类号： F01D5/187 , F01D5/186 , F05D2250/34 , F05D2260/202 , F05D2260/22141
摘要： In a cooled blade for a gas turbine, a cooling fluid, preferably cooling air, flows for convective cooling through internal cooling passages located close to the wall and is subsequently deflected for external film cooling through film-cooling holes onto the blade surface. The fluid flow is directed in at least some of the internal cooling passages in counterflow to the hot-gas flow flowing around the blade. Homogeneous cooling in the radial direction is achieved by providing a plurality of internal cooling passages and film-cooling holes arranged one above the other in the radial direction in the blade in such a way that the discharge openings of the film-cooling holes in each case lie so as to be offset from the internal cooling passages, and in particular the discharge openings lie between the internal cooling passages.
摘要翻译：在用于燃气轮机的冷却叶片中，冷却流体（优选冷却空气）通过位于靠近壁的内部冷却通道流动以进行对流冷却，随后通过薄膜冷却孔偏转到叶片表面上的外部薄膜冷却。流体流动被引导到至少一些内部冷却通道中，与流过叶片的热气流逆流。通过在叶片的径向方向设置多个内部冷却通路和薄膜冷却孔而沿径向方向设置多个冷却方式，使得各个薄膜冷却孔的排出口以便从内部冷却通道偏移，特别是排出口位于内部冷却通道之间。

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