公开(公告)号：EP3093453B1

公开(公告)日：2018-10-03

申请号：EP16159915.4

申请日：2016-03-11

申请人： United Technologies Corporation

发明人： PETERS, Donald W. ,  PLACE, Emma J.

IPC分类号： F01D25/16 ,  F02K1/80

CPC分类号： F02K1/80 ,  F01D25/168 ,  F02K1/1223 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2260/231 ,  F05D2300/434 ,  F05D2300/44 ,  F05D2300/603 ,  F05D2300/614 ,  F16C29/001 ,  F16C29/02 ,  F16C33/201 ,  Y02T50/672

摘要： A composite wear pad (300, 306; 520) for being coupled to a slider block (204; 510) of a convergent nozzle of a gas turbine engine (100) includes a high heat capacity composite (301; 505) having a resin (602) and a plurality of carbon fibers (600) bonded together by the resin (602). The composite wear pad (300, 306; 520) also includes a first/second rod (404/405) coupled to the high heat capacity composite (301; 505) at a first/second axial end (460/463) of the composite wear pad (300, 306; 520) such that the first axial end (460) and the second axial end (463) of the composite wear pad (300, 306; 520) each have an end thickness (452) that is greater than a middle thickness of the composite wear pad (300, 306; 520).

公开(公告)号：EP3290679A1

公开(公告)日：2018-03-07

申请号：EP17188302.8

申请日：2017-08-29

申请人： The Boeing Company

发明人： GAW, Kevin O'Brien ,  JONES, Dylan E ,  LARSON, Michael H ,  SHIVASHANKRA, Belur N ,  GROVE, Randy J ,  BARENE, David John ,  LINGELBACH, Jeston ,  SHAFFER, Kory ,  FOUTCH, David W

IPC分类号： F02K1/70 ,  B29C65/00

CPC分类号： F02K1/70 ,  B29C65/02 ,  B29C65/48 ,  B29C66/7254 ,  B29L2031/7504 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2230/60 ,  F05D2250/283 ,  F05D2260/96 ,  F05D2300/432 ,  F05D2300/433 ,  F05D2300/434 ,  F05D2300/436

摘要： A blocker door assembly for use in a gas turbine engine includes a facesheet including a plurality of openings to facilitate noise attenuation and a body portion coupled to the facesheet. The body portion includes a backsheet integrally formed with a honeycomb core, wherein the body portion is molded from a thermoplastic material.

摘要翻译： 用于燃气涡轮发动机的阻挡门组件包括：面板，其包括多个开口以促进噪音衰减;以及主体部分，其耦合到面板。 主体部分包括与蜂窝芯整体形成的底片，其中主体部分由热塑性材料模制而成。

公开(公告)号：EP2971559A4

公开(公告)日：2017-01-25

申请号：EP13878065

申请日：2013-12-20

申请人： UNITED TECHNOLOGIES CORP

发明人： MURDOCK JAMES R ,  HUI KWAN

IPC分类号： F01D5/30

CPC分类号： F01D5/3092 ,  F01D5/147 ,  F01D5/3007 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/30 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/434 ,  F05D2300/6012

摘要： A blade assembly comprises a blade (120) and one or more wear pads (170, 172). The blade has an airfoil (122) having a leading edge (126), a trailing edge (128), a pressure side (130), a suction side (132), and extending from an inboard end to a tip (125). The blade further includes an attachment root (124). The one or more wear pads are along the attachment root. The one or more wear pads have a plurality of slits (228, 230 242).

公开(公告)号：EP3105447A2

公开(公告)日：2016-12-21

申请号：EP14883805.5

申请日：2014-12-11

申请人： United Technologies Corporation

发明人： TURNER, Matthew A. ,  ALARCON, Andrew G. ,  BUGAJ, Shari L.

IPC分类号： F02K3/06 ,  F01D5/02

CPC分类号： F01D11/008 ,  F01D25/005 ,  F02K3/06 ,  F04D29/329 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2230/20 ,  F05D2230/31 ,  F05D2230/80 ,  F05D2240/80 ,  F05D2300/434 ,  F05D2300/436 ,  F05D2300/603 ,  Y02T50/672

摘要： A fan assembly for a gas turbine engine is disclosed. The fan assembly may include a rotor, a plurality of airfoils extending radially from the rotor, and a platform surrounding the rotor and including a surface that defines a flow path between the plurality of airfoils. The platform may be configured to be disposable during a life of the gas turbine engine.

公开(公告)号：EP2935951A4

公开(公告)日：2016-07-27

申请号：EP13864840

申请日：2013-11-06

申请人： UNITED TECHNOLOGIES CORP

发明人： BOGUE WILLIAM ,  PRIHAR RON I P E

IPC分类号： F16J15/14 ,  B21K3/04 ,  B23P6/00 ,  C23C4/02 ,  F01D5/00 ,  F01D5/08 ,  F23R3/00

CPC分类号： B05D7/22 ,  B23P6/007 ,  B23P2700/06 ,  B23P2700/13 ,  C23C4/02 ,  F01D5/005 ,  F01D5/288 ,  F05D2230/42 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2300/434 ,  F23R3/002 ,  F23R2900/00016 ,  F23R2900/00019

摘要： A method for filling cooling holes in a component of a gas turbine engine is disclosed. The component may include a plurality of first cooling holes extending through the wall of the component. The method may comprise the steps of exposing the outer surface of the component, filling the plurality of first cooling holes with a polyimide, curing the polyimide to block the passage of cooling fluid through the plurality of first cooling holes, and applying a thermal bather coating over the outer surface of the component. The method may further include the step of installing a second plurality of cooling holes in the wall of the component wherein the plurality of second cooling holes penetrate the thermal barrier coating and the wall of the component and allow cooling fluid to pass therethrough.

公开(公告)号：EP1368611B1

公开(公告)日：2005-11-02

申请号：EP02709829.2

申请日：2002-03-13

申请人： RAYTHEON COMPANY

发明人： FACCIANO, Andrew, B. ,  LEHNER, Paul ,  ANDERSON, Wayne, N.

IPC分类号： F42B10/66 ,  F02K9/90

CPC分类号： F42B10/665 ,  F02K9/90 ,  F02K9/974 ,  F05C2225/08 ,  F05D2230/90 ,  F05D2300/21 ,  F05D2300/224 ,  F05D2300/433 ,  F05D2300/434 ,  F05D2300/44 ,  F05D2300/603 ,  F05D2300/611 ,  F05D2300/702

摘要： A dissolvable jet vane (22/30) is a composite structure, having a support frame (38), a plug leading edge (40) connected to the forward edge (42) of the frame (38), and an insulation layer (44) on the side walls of the support frame (38). The dissolvable jet vane materials withstand the pressure and thermal loads associated with missile steering during the first few seconds of rocket boost until the missile attains sufficient speed to use conventional external aerodynamic control fins for steering control. Once control passes to the external fins, the jet vanes rapidly and uniformly dissolve in the exhaust stream. The dissolvable jet vane provides a lightweight, reliable means of removing steering jet vanes from the exhaust stream of a solid rocket motor nozzle.

公开(公告)号：EP1270876A3

公开(公告)日：2004-10-20

申请号：EP02254256.7

申请日：2002-06-18

申请人： GENERAL ELECTRIC COMPANY

发明人： Turnquist, Norman Arnold ,  Aksit, Mahmut Faruk ,  Ghasripoor, Farshad ,  Chupp, Raymond Edward

IPC分类号： F01D11/12 ,  F16J15/32

CPC分类号： F01D11/122 ,  F05C2201/0466 ,  F05D2240/56 ,  F05D2260/30 ,  F05D2300/224 ,  F05D2300/43 ,  F05D2300/434 ,  F05D2300/44 ,  F05D2300/614 ,  F05D2300/702 ,  F16J15/3288 ,  F16J15/445

摘要： The present invention provides, in one embodiment, an annular turbine seal for disposition in a turbine between a rotatable component (110) having an axis of rotation and a turbine housing (120) about the same axis of rotation. The turbine seal has a plurality of arcuate seal carrier segments (140) that have an abradable portion (150) secured to the seal carrier segments (140). In addition, at least one spring (185) is disposed on the seal carrier segment (140) to exert a force and maintain the seal carrier segment (140) adjacent to the rotatable component.

公开(公告)号：EP3093453A1

公开(公告)日：2016-11-16

申请号：EP16159915.4

申请日：2016-03-11

申请人： United Technologies Corporation

发明人： PETERS, Donald W. ,  PLACE, Emma J.

IPC分类号： F01D25/16 ,  F02K1/80

CPC分类号： F02K1/80 ,  F01D25/168 ,  F02K1/1223 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2260/231 ,  F05D2300/434 ,  F05D2300/44 ,  F05D2300/603 ,  F05D2300/614 ,  F16C29/001 ,  F16C29/02 ,  F16C33/201 ,  Y02T50/672

摘要： A composite wear pad (300, 306; 520) for being coupled to a slider block (204; 510) of a convergent nozzle of a gas turbine engine (100) includes a high heat capacity composite (301; 505) having a resin (602) and a plurality of carbon fibers (600) bonded together by the resin (602). The composite wear pad (300, 306; 520) also includes a first/second rod (404/405) coupled to the high heat capacity composite (301; 505) at a first/second axial end (460/463) of the composite wear pad (300, 306; 520) such that the first axial end (460) and the second axial end (463) of the composite wear pad (300, 306; 520) each have an end thickness (452) that is greater than a middle thickness of the composite wear pad (300, 306; 520).

摘要翻译： 用于连接到燃气涡轮发动机（100）的会聚喷嘴的滑块（204; 510）的复合耐磨垫（300,306; 520）包括具有树脂的高热容复合材料（301; 505） 602）和通过树脂（602）结合在一起的多个碳纤维（600）。 复合耐磨垫（300,306; 520）还包括在复合材料的第一/第二轴向端（460/463）处耦合到高热容复合材料（301; 505）的第一/第二杆（404/405） 磨损垫（300,306; 520），使得复合耐磨垫（300,306; 520）的第一轴向端（460）和第二轴向端（463）各自具有大于 复合耐磨垫（300,306; 520）的中间厚度。

公开(公告)号：EP2837773B1

公开(公告)日：2016-11-16

申请号：EP14180628.1

申请日：2014-08-12

申请人： Rolls-Royce plc

发明人： Bottome, Kristofer ,  Lee, James ,  Mason, Paul ,  Thompson, Ewan

IPC分类号： F01D11/00

CPC分类号： F01D11/008 ,  F05D2220/36 ,  F05D2260/95 ,  F05D2300/434 ,  F05D2300/603

公开(公告)号：EP3051073A1

公开(公告)日：2016-08-03

申请号：EP16152568.8

申请日：2016-01-25

申请人： United Technologies Corporation

发明人： GUO, Changsheng ,  EASTMAN, Scott

IPC分类号： F01D11/12 ,  C08J9/00

CPC分类号： F01D11/122 ,  B29C44/02 ,  B29K2079/085 ,  B29K2105/04 ,  B29K2995/0037 ,  B29L2031/265 ,  C08J9/0066 ,  C08J9/0085 ,  C08J2201/026 ,  C08J2333/24 ,  C08J2379/08 ,  F04D19/002 ,  F04D29/321 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2240/11 ,  F05D2240/20 ,  F05D2240/55 ,  F05D2300/2261 ,  F05D2300/2281 ,  F05D2300/2282 ,  F05D2300/434 ,  F05D2300/5024 ,  F05D2300/601 ,  F05D2300/612 ,  F05D2300/615 ,  F16J15/16

摘要： An abradable seal material comprises: a polyimide foam matrix; and a thermal conductivity-enhancing filler in the matrix.

摘要翻译： 耐磨密封材料包括：聚酰亚胺泡沫基体; 和基质中的热导率增强填料。