公开(公告)号：EP3030752A1

公开(公告)日：2016-06-15

申请号：EP14752731.1

申请日：2014-08-06

申请人： General Electric Company

发明人： TUERTSCHER, Michael Ray ,  SENILE, Darrell Glenn ,  PHELPS, Greg

IPC分类号： F01D9/04 ,  F01D5/28

CPC分类号： F01D9/041 ,  F01D5/282 ,  F01D5/284 ,  F01D9/042 ,  F01D25/246 ,  F05D2220/32 ,  F05D2220/3212 ,  F05D2230/237 ,  F05D2240/128 ,  F05D2260/30 ,  F05D2300/10 ,  F05D2300/20 ,  F05D2300/518 ,  F05D2300/6033

摘要： A turbine nozzle (10) includes: an arcuate inner band (12) having opposed flowpath and back sides, and an aft flange (22) extending outward from the back side; an arcuate outer band (14) having opposed flowpath and back sides; an airfoil-shaped turbine vane (16) extending between the flowpath sides of the inner and outer bands, wherein the inner and outer bands and the vane (16) comprise a ceramic low-ductility material; and a metallic collar (34) surrounding the aft flange (22).

摘要翻译： 涡轮喷嘴包括具有相对的流路和后侧的弓形内带和从后侧向外延伸的后凸缘; 具有相对的流路和背面的弓形外带; 在所述内带和外带的流路侧之间延伸的翼型涡轮叶片，其中所述内带和外带和所述叶片包括陶瓷低延展性材料; 以及围绕后缘的金属套环。

公开(公告)号：EP2971589A4

公开(公告)日：2016-06-08

申请号：EP14770119

申请日：2014-03-10

申请人： UNITED TECHNOLOGIES CORP

发明人： MILLER JONATHAN LOGAN ,  SHUAIB NASR A

IPC分类号： F01D11/00 ,  F02C7/28

CPC分类号： F02C7/28 ,  F01D11/003 ,  F01D25/186 ,  F02C3/04 ,  F05D2240/55 ,  F05D2260/30 ,  F16J15/3456

摘要： A turbine engine includes a main shaft bearing compartment seal. The seal includes at least an approximately circular seal portion and a seal carrier disposed about the approximately circular seal portion. A plurality of anti-rotation pins maintain the seal carrier in position relative to a housing and are received in an anti-rotation slot of the seal carrier.

公开(公告)号：EP3022424A1

公开(公告)日：2016-05-25

申请号：EP14826793.3

申请日：2014-06-17

申请人： United Technologies Corporation

发明人： CHANG, Hoyt Y.

IPC分类号： F02C7/24 ,  F01D25/08 ,  C04B35/00

CPC分类号： F23R3/002 ,  C04B35/80 ,  F01D25/145 ,  F01D25/30 ,  F02C7/24 ,  F02K1/78 ,  F02K1/80 ,  F02K1/822 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/60 ,  F05D2240/128 ,  F05D2240/35 ,  F05D2260/231 ,  F05D2260/30 ,  F05D2300/5023 ,  F05D2300/6033 ,  F23R3/007 ,  F23R3/60 ,  F23R2900/00017 ,  Y02T50/672 ,  Y02T50/675

摘要： A gas turbine engine ceramic panel assembly includes a ceramic liner that has a slot and includes a hole. An insert is received in the slot and provides a female fastening element aligned with the hole. A method of manufacturing a ceramic panel assembly includes the steps of forming a ceramic liner with a slot, installing an insert into the slot, and securing the ceramic liner to a structure using a fastening assembly.

摘要翻译： 燃气涡轮发动机陶瓷面板组件包括具有狭槽并且包括孔的陶瓷衬套。 插入件容纳在槽中并提供与孔对准的阴紧固元件。 制造陶瓷面板组件的方法包括以下步骤：形成具有槽的陶瓷衬套，将插入件安装到所述槽中，以及使用紧固组件将所述陶瓷衬套固定到结构上。

公开(公告)号：EP3004598A2

公开(公告)日：2016-04-13

申请号：EP14836013.4

申请日：2014-05-22

申请人： United Technologies Corporation

发明人： CIGAL, Brian P. ,  OTTO, John R.

IPC分类号： F02C7/20 ,  F01D25/28

CPC分类号： F02C7/36 ,  F01D25/164 ,  F02C3/107 ,  F02K3/04 ,  F05D2230/60 ,  F05D2260/30 ,  F05D2260/36 ,  F05D2260/40 ,  F05D2260/40311 ,  F16H57/02 ,  F16H57/025

摘要： A gear assembly support for a gas turbine engine includes a spline ring configured to fit into a case of the gas turbine engine and a flex support. The flex support includes splines for engaging the spline ring and an inner portion attachable to a portion the gear assembly.

公开(公告)号：EP2901083A4

公开(公告)日：2016-04-06

申请号：EP13843014

申请日：2013-03-15

申请人： UNITED TECHNOLOGIES CORP ,  JAUSE JONATHAN M ,  LOW KEVIN JOSEPH ,  DUHAMEL DENNIS JOHN

发明人： JAUSE JONATHAN M ,  LOW KEVIN JOSEPH ,  DUHAMEL DENNIS JOHN

IPC分类号： F01D25/24 ,  F01D5/08 ,  F02C3/04 ,  F02C7/12 ,  F02C7/20 ,  F23R3/50 ,  F23R3/60

CPC分类号： F23R3/60 ,  F01D5/082 ,  F01D25/243 ,  F02C3/04 ,  F02C7/12 ,  F02C7/20 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/55 ,  F05D2260/30 ,  F05D2260/31 ,  F23R3/50 ,  F23R2900/00017 ,  Y02T50/676 ,  Y10T29/49346

摘要： A combustor assembly for a gas turbine engine includes a combustor shell, a TOBI, a case, and a joint for securing the combustor shell, TOBI and case together. The joint has a combustor flange integral to the combustor shell. A TOBI flange is integral to the TOBI and a case flange is integral to the case. The combustor flange, the TOBI flange and the case flange are secured together.

公开(公告)号：EP2710229B1

公开(公告)日：2016-03-30

申请号：EP12728670.6

申请日：2012-05-14

申请人： SNECMA

发明人： CHATENET, Luc, Henri ,  LE QUELLEC, John

IPC分类号： F01D5/30 ,  F04D29/02 ,  F01D5/32

CPC分类号： F01D5/326 ,  B23P15/006 ,  F01D5/3038 ,  F01D5/3092 ,  F01D5/323 ,  F04D29/023 ,  F04D29/322 ,  F05D2260/30 ,  F05D2300/505 ,  Y02T50/671 ,  Y10T29/49332

公开(公告)号：EP2951398A4

公开(公告)日：2016-02-24

申请号：EP13873325

申请日：2013-01-30

申请人： UNITED TECHNOLOGIES CORP

发明人： SANDOVAL JONATHAN PERRY ,  HUMMEL RAYMOND S ,  VIRKLER SCOTT D

IPC分类号： F01D5/30

CPC分类号： F01D5/3015 ,  F01D5/082 ,  F01D11/001 ,  F02C3/04 ,  F02C7/28 ,  F04D29/321 ,  F05D2260/30 ,  F05D2260/36 ,  Y02T50/676

公开(公告)号：EP2977547A1

公开(公告)日：2016-01-27

申请号：EP15177951.9

申请日：2015-07-22

申请人： United Technologies Corporation

发明人： WEISSE, Michael A.

IPC分类号： F01D5/02 ,  F01D5/30

CPC分类号： F01D5/3007 ,  F01D5/02 ,  F01D5/025 ,  F01D5/3092 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/30 ,  F05D2260/30 ,  F05D2260/96 ,  F05D2300/431

摘要： A blade (40) for use in a gas turbine engine (10), the blade having an airfoil portion (46) and a dovetail root portion (48), wherein the dovetail root portion is dimensioned and configured to enable the blade to rotate within a shaped slot (44) formed in a supporting hub (42) of the engine about a center of rotation that extends parallel to a central axis of the hub in response to an impact force (F) on the airfoil portion of the blade.

摘要翻译： 一种用于燃气涡轮发动机（10）的叶片（40），所述叶片具有翼型部分（46）和燕尾根部（48），其中所述燕尾根部的尺寸和构造使得所述叶片能够在 形成在发动机的支撑轮毂（42）中的成形槽（44），其围绕围绕叶片的翼型部分的冲击力（F）平行于毂的中心轴线延伸的旋转中心。

公开(公告)号：EP2971616A1

公开(公告)日：2016-01-20

申请号：EP14778227.0

申请日：2014-03-06

申请人： United Technologies Corporation

发明人： GROGG, Gary L. ,  VDOVIAK, Garth J. ,  THAYER, Marshall

IPC分类号： F01D25/28 ,  F01D25/00 ,  F02C7/00

CPC分类号： F02C7/24 ,  F01D25/00 ,  F01D25/162 ,  F01D25/243 ,  F01D25/30 ,  F02C7/00 ,  F02C7/06 ,  F02C7/20 ,  F05D2260/30 ,  F05D2260/31

摘要： An attachment interface assembly for a gas turbine engine has a component configured for attachment to an engine static structure. A fastener has a threaded body portion and an enlarged head portion. The threaded body portion is inserted through aligned holes in the component and engine static structure. A clip has a center opening that receives the threaded body portion such that the clip is positioned between the enlarged head portion and the component.

公开(公告)号：EP2971589A1

公开(公告)日：2016-01-20

申请号：EP14770119.7

申请日：2014-03-10

申请人： United Technologies Corporation

发明人： MILLER, Jonathan Logan ,  SHUAIB, Nasr A.

IPC分类号： F01D11/08 ,  F01D11/00 ,  F02C7/28

CPC分类号： F02C7/28 ,  F01D11/003 ,  F01D25/183 ,  F01D25/186 ,  F02C3/04 ,  F02C7/06 ,  F05D2240/55 ,  F05D2250/41 ,  F05D2260/30 ,  F16J15/3456

摘要： A turbine engine includes a main shaft bearing compartment seal. The seal includes at least an approximately circular seal portion and a seal carrier disposed about the approximately circular seal portion. A plurality of anti-rotation pins maintain the seal carrier in position relative to a housing and are received in an anti-rotation slot of the seal carrier.