公开(公告)号：US20150132110A1

公开(公告)日：2015-05-14

申请号：US14400648

申请日：2013-06-14

申请人： United Technologies Corporation ,  GKN Aerospace Sweden AB

发明人： Daryl B. Mountz ,  Theodore W. Kapustka ,  Glenn Levasseur ,  Marcus Borg ,  Joakim Berglund ,  Anders Svahn ,  Johan Ockborn ,  Bengt Pettersson

IPC分类号： F01D25/24 ,  F02C9/18

CPC分类号： F01D25/005 ,  F01D21/045 ,  F01D25/162 ,  F01D25/24 ,  F01D25/30 ,  F02C9/18 ,  F02K1/386 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/232 ,  F05D2230/25 ,  F05D2230/54 ,  F05D2260/941 ,  F05D2300/175 ,  F05D2300/176 ,  F05D2300/177 ,  F05D2300/502

摘要： A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.

公开(公告)号：US20140272344A1

公开(公告)日：2014-09-18

申请号：US13841371

申请日：2013-03-15

申请人： GENERAL ELECTRIC COMPANY

发明人： Julin Wan ,  Milivoj Konstantin Brun ,  Peter Joel Meschter ,  Reza Sarrafi-Nour ,  Don Mark Lipkin

IPC分类号： C09D5/08 ,  C23C16/42 ,  C23C16/34 ,  B05D7/00

CPC分类号： C09D5/084 ,  B05D7/52 ,  C04B41/009 ,  C04B41/5066 ,  C04B41/52 ,  C04B41/87 ,  C04B41/89 ,  C23C28/044 ,  C23C28/048 ,  C23C28/42 ,  F01D5/288 ,  F05D2230/90 ,  F05D2300/177 ,  Y10T428/2495 ,  C04B35/565 ,  C04B35/806 ,  C04B35/584 ,  C04B35/58085 ,  C04B41/4529 ,  C04B41/5071

摘要： An article includes a substrate and a coating provided on a surface of the substrate. The coating includes at least one metal silicide layer consisting essentially of MoSi2 or WSi2 or (Mo, W)Si2 or a platinum group metal silicide and at least one layer consisting essentially of Si3N4.

摘要翻译： 一种制品包括基材和设置在基材表​​面上的涂层。 涂层包括至少一个金属硅化物层，其基本上由MoSi 2或WSi 2或（Mo，W）Si 2或铂族金属硅化物和至少一个由Si 3 N 4组成的层组成。

公开(公告)号：US20140090399A1

公开(公告)日：2014-04-03

申请号：US13672124

申请日：2012-11-08

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Timothy J. McAlice ,  Carlos G. Figueroa

IPC分类号： F02C7/20

CPC分类号： F02C7/20 ,  F01D25/14 ,  F01D25/28 ,  F02K1/80 ,  F02K1/82 ,  F05D2220/32 ,  F05D2230/232 ,  F05D2230/642 ,  F05D2240/54 ,  F05D2240/55 ,  F05D2250/42 ,  F05D2260/30 ,  F05D2300/174 ,  F05D2300/177 ,  F05D2300/5021 ,  F16B5/065 ,  F23R3/002 ,  F23R3/60

摘要： A support hanger is provided for a turbine engine. The support hanger includes a pin with a pin head, a retainer and a flexible seal. The retainer is pivotally connected to the pin head. The retainer includes a seal bearing surface facing towards the pin head. The seal includes a retainer bearing surface sealingly engaging the seal bearing surface.

摘要翻译： 为涡轮发动机提供支撑架。 支撑架包括具有销头，保持器和柔性密封件的销。 保持器枢转地连接到销头。 保持器包括面向销头的密封件支承表面。 密封件包括密封地接合密封件支承表面的保持器支承表面。

公开(公告)号：US20130280049A1

公开(公告)日：2013-10-24

申请号：US13454295

申请日：2012-04-24

申请人： Benjamin T. Fisk ,  Tracy A. Propheter-Hinckley

发明人： Benjamin T. Fisk ,  Tracy A. Propheter-Hinckley

IPC分类号： F01D5/20 ,  B23P17/00

CPC分类号： F01D11/122 ,  B23P15/02 ,  F01D1/02 ,  F01D5/147 ,  F01D5/20 ,  F01D9/04 ,  F05D2220/32 ,  F05D2240/307 ,  F05D2240/55 ,  F05D2250/283 ,  F05D2300/177 ,  Y10T29/49337

摘要： A blade includes an airfoil having a base and a free, tip end. The tip end includes at least one porous, abradable element.

摘要翻译： 叶片包括具有基部和自由的尖端的翼型件。 尖端包括至少一个多孔的可磨损元件。

公开(公告)号：US20100037588A1

公开(公告)日：2010-02-18

申请号：US12442547

申请日：2006-10-12

申请人： Constantine Baltas ,  Amr Ali

发明人： Constantine Baltas ,  Amr Ali

IPC分类号： F02K3/02 ,  F01D17/00

CPC分类号： F01D17/14 ,  B64C9/38 ,  F01D5/02 ,  F01D9/02 ,  F01D17/105 ,  F01D25/24 ,  F02C3/04 ,  F02K1/08 ,  F02K1/085 ,  F02K1/12 ,  F02K1/1207 ,  F02K1/386 ,  F02K3/00 ,  F02K3/04 ,  F02K3/06 ,  F02K3/075 ,  F03G7/065 ,  F05D2220/36 ,  F05D2240/128 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2260/606 ,  F05D2300/174 ,  F05D2300/177 ,  F05D2300/505

摘要： A gas turbine engine (10) includes a fan (14), a nacelle (28) arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage (30) downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow (1) from the fan. A nozzle (40) associated with the fan bypass passage is operative to control the bypass airflow. The nozzle includes a shape memory material having a first solid state phase that corresponds to a first nozzle position and a second solid state phase that corresponds to a second nozzle position.

摘要翻译： 燃气涡轮发动机（10）包括风扇（14），围绕风扇布置的机舱（28）和至少部分地在机舱内的发动机核心。 在机舱和燃气涡轮发动机之间的风扇下游的风扇旁路通道（30）从风扇传送旁路气流（1）。 与风扇旁路通道相关联的喷嘴（40）可操作以控制旁路气流。 喷嘴包括具有对应于第一喷嘴位置的第一固态相和对应于第二喷嘴位置的第二固态相的形状记忆材料。

公开(公告)号：US11834963B2

公开(公告)日：2023-12-05

申请号：US17672107

申请日：2022-02-15

申请人： Raytheon Technologies Corporation

发明人： Mark T. Ucasz

IPC分类号： F01D5/28 ,  C23C30/00 ,  C23C28/04 ,  C23C28/00 ,  C23C28/02 ,  F01D25/00 ,  F01D5/02 ,  F01D9/04 ,  F01D1/08 ,  F01D11/08

CPC分类号： F01D5/288 ,  C23C28/028 ,  C23C28/048 ,  C23C28/3215 ,  C23C28/345 ,  C23C30/00 ,  F01D1/08 ,  F01D5/02 ,  F01D9/041 ,  F01D25/007 ,  F05D2220/32 ,  F05D2230/90 ,  F05D2240/35 ,  F05D2260/95 ,  F05D2300/171 ,  F05D2300/177 ,  F05D2300/611 ,  Y02T50/60

摘要： A coated article includes a substrate and an MCrAlY coating supported on the substrate. The M includes at least one of nickel, cobalt, and iron, Cr is chromium, Al is aluminum, and Y is yttrium. The composition of the MCrAlY coating varies in an amount of at least one of Cr, Al, and Y by location on the substrate with respect to localized property requirements. In one example, the coated article is an article of a gas turbine engine.

公开(公告)号：US20190194789A1

公开(公告)日：2019-06-27

申请号：US16230377

申请日：2018-12-21

申请人： Mitsubishi Hitachi Power Systems, Ltd.

发明人： Shigeru TANAKA ,  Takeshi IZUMI ,  Akira YOSHINARI

IPC分类号： C22F1/10 ,  C22C19/05 ,  F01D5/28

CPC分类号： C22F1/10 ,  C22C19/03 ,  C22C19/056 ,  F01D5/28 ,  F05D2300/177

摘要： There is provided a regenerated member of a nickel-based alloy member for use in a turbine. The nickel-based alloy member is a used member having been operated for a predetermined period of time in the turbine. The regenerated member is a nickel-based alloy unidirectional solidification article or single crystalline solidification article including a γ phase as a matrix and a γ′ phase precipitating in the γ phase in a volume fraction of 30 volume % or more in an operational environment of the turbine. In a microstructure of the regenerated member, no recrystallized grains of the γ phase are present. And, when a rocking curve of a predetermined crystal face of the γ phase crystal grain of the used member undergone the solution/non-recrystallization heat treatment step is measured by an XRD technique, a FWHM of the rocking curve is within a range from 0.25° to 0.30°.

公开(公告)号：US20180320706A1

公开(公告)日：2018-11-08

申请号：US15586662

申请日：2017-05-04

申请人： General Electric Company

发明人： Nitesh Jain ,  Sujana Chandrasekar ,  Ramkrishna Maripalli ,  Nicholas Joseph Kray ,  Wendy Wenling Lin

IPC分类号： F04D29/38 ,  B32B5/02 ,  B32B37/14 ,  F02C3/04 ,  F04D29/32

CPC分类号： F04D29/388 ,  B32B5/02 ,  B32B37/14 ,  B32B2262/103 ,  B32B2262/106 ,  B32B2305/076 ,  B32B2605/18 ,  F02C3/04 ,  F04D29/325 ,  F05D2220/32 ,  F05D2300/171 ,  F05D2300/174 ,  F05D2300/177 ,  F05D2300/6032

摘要： A laminated composite airfoil assembly includes a first lamina formed of a pre-preg material including metal fibers, and at least a second lamina formed of a pre-preg material including at least one of metal fibers intermixed with carbon fibers, only metal fibers, only carbon fibers, a substrate including metal fibers, a substrate including carbon fibers, and combinations thereof.

公开(公告)号：US10077665B2

公开(公告)日：2018-09-18

申请号：US15009328

申请日：2016-01-28

申请人： United Technologies Corporation

发明人： Charles Thistle ,  Mohamed Hassan

IPC分类号： F01D5/30 ,  F01D5/14 ,  F01D5/02 ,  F01D5/18

CPC分类号： F01D5/147 ,  F01D5/02 ,  F01D5/081 ,  F01D5/18 ,  F01D5/3007 ,  F05D2220/32 ,  F05D2230/20 ,  F05D2240/81 ,  F05D2260/20 ,  F05D2300/133 ,  F05D2300/174 ,  F05D2300/177 ,  Y02T50/676

摘要： The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a base, a first side, and a second side, a rail extending from the base of the load beam between the first side and the second side, a tooth running parallel to the longitudinal axis disposed on the first side of the load beam. The rail may comprise at least one of, a convex sidewall having a convex curvature, a concave sidewall having a concave curvature, or a vertical sidewall extending perpendicular to the base. The rail may comprise a sidewall comprising a sidewall step wherein the sidewall has a step cut into a portion of the rail. The rail may comprise a tapered sidewall wherein the tapered sidewall extends at an angle to the base.

公开(公告)号：US20180243866A1

公开(公告)日：2018-08-30

申请号：US15444934

申请日：2017-02-28

申请人： General Electric Company

发明人： Dheepa Srinivasan ,  Madhusudan Kulkarni

IPC分类号： B23P6/00 ,  B22F3/00 ,  B22F7/06 ,  B33Y10/00 ,  B33Y50/02 ,  B22F5/04 ,  B23K26/342 ,  B23K26/03 ,  F01D5/00 ,  F01D5/12 ,  F01D9/04 ,  F01D25/24

CPC分类号： B23P6/007 ,  B22F3/008 ,  B22F5/04 ,  B22F7/062 ,  B22F2007/068 ,  B23K26/032 ,  B23K26/342 ,  B23K2101/001 ,  B23K2103/04 ,  B23K2103/05 ,  B23K2103/08 ,  B33Y10/00 ,  B33Y50/02 ,  F01D5/005 ,  F01D5/12 ,  F01D9/04 ,  F01D25/243 ,  F05D2220/31 ,  F05D2230/30 ,  F05D2230/80 ,  F05D2300/171 ,  F05D2300/177

摘要： Various embodiments include approaches for repairing a turbine component. In some cases, a method includes: removing a turbine component from a turbine rotor assembly; identifying at least one flaw in the turbine component; and direct metal laser melting (DMLM) or direct metal laser depositing (DMLD) a fill material to fill the at least one flaw in the turbine component, forming a repaired turbine component.