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1. 发明授权

EP0816637B1 Gas turbine guide vane 失效
标题翻译：燃气涡轮叶片
公开(公告)号：EP0816637B1
公开(公告)日：2004-05-12
申请号：EP97304669.1
申请日：1997-06-27
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Watson, Thomas J. , Nardone, Vincent C. , Visoskis, John A. , Anderson, Stuart A.
IPC分类号： F01D9/04 , F01D5/28 , F01D5/14 , F01D5/18 , B21C23/16 , C22C32/00
CPC分类号： F01D5/147 , F01D5/282 , F05D2230/24 , F05D2300/173 , F05D2300/603 , Y10T29/49337 , Y10T29/49339

2. 发明公开

EP2254729A1 PROCEDE DE FABRICATION D'UNE AUBE CREUSE 有权转让
标题翻译：一种用于生产空心铲
公开(公告)号：EP2254729A1
公开(公告)日：2010-12-01
申请号：EP09728172.9
申请日：2009-03-17
申请人： Snecma
发明人： BERTRAND, Françoise , DUCLOS, Guillaume , FRANCHET, Jean-Michel, Patrick, Maurice , MOLINARI, Olivier, Michaël
IPC分类号： B23P15/02 , F01D5/18 , B21H7/16 , B21J5/12 , B21C23/16 , B21K3/04
CPC分类号： B23P15/02 , B21K3/04 , F01D5/18 , F05D2230/11 , Y02T50/672 , Y02T50/676 , Y10T29/49339
摘要： The invention relates to a method for manufacturing a hollow blade (10) for a turbomachine that comprises drilling channels (24) into a blank of the blade, placing inserts into the channels (24), forging the blank, and removing the inserts by chemical dissolution, and is characterized in that the blade (10) is an aluminum alloy and the inserts are a copper alloy.

3. 发明公开

EP3302874A1 PROCÉDÉ DE FABRICATION D'UNE AUBE DE TURBOMACHINE EN TIAL 有权
标题翻译：制造涡轮机油箱的方法
公开(公告)号：EP3302874A1
公开(公告)日：2018-04-11
申请号：EP16733637.9
申请日：2016-05-26
申请人： Safran Aircraft Engines , SAFRAN
发明人： LECONTE, Gilbert , FRANCHET, Jean-Michel , SALLOT, Pierre
IPC分类号： B23P13/02 , B23P15/02 , B23K3/04 , B22F3/20 , B22F3/17 , B21C23/00 , B21C23/14 , B21C23/16 , B21C35/02
CPC分类号： B21C23/002 , B21C23/142 , B21C23/16 , B21C35/023 , B21K3/04 , B22F3/17 , B22F3/20 , B22F5/04 , B22F2998/10 , B23P13/02 , B23P15/02 , F01D5/14 , F05D2230/10 , F05D2230/24 , F05D2230/25 , F05D2240/24 , F05D2300/174 , B22F9/082 , B22F2003/247 , B22F2003/206
摘要： The present invention relates to a method for manufacturing a titanium aluminide blade of a turbine engine, comprising steps of: (E1) production of a titanium aluminide ingot, (E2) extrusion of the ingot through an opening in a die having one main arm and at least one side arm, such as to obtain a extruded ingot having the shape of a bar with a cross-section having one main arm and at least one side arm substantially perpendicular to the main arm, (E3) transverse cutting of the extruded ingot such as to obtain sections of extruded ingot, (E4) forging of each section of extruded ingot such as to obtain a turbine engine blade.

4. 发明授权

EP3815816B1 HIGH GAMMA PRIME NICKEL BASED SUPERALLOY, ITS USE, TURBINE COMPONENTS AND METHOD OF MANUFACTURING THEREOF 有权
公开(公告)号：EP3815816B1
公开(公告)日：2022-04-27
申请号：EP19215644.6
申请日：2019-12-12
发明人： Goncharov, Alexander , Liburdi, Joseph , Lowden, Paul
IPC分类号： B22F3/105 , B22F5/04 , B23K26/342 , B33Y70/00 , C22C1/04 , C22C19/05 , B22D7/00 , B22F3/24 , B22F7/06 , B22F10/25 , C22C30/00 , C22F1/10 , B21C23/16

5. 发明公开

EP2402617A2 Flared tip fan blade and method of manufacturing same 审中-公开
标题翻译： Lüfterschaufelmit ausgestellter Spitze und Herstellungsverfahrendafür
公开(公告)号：EP2402617A2
公开(公告)日：2012-01-04
申请号：EP11171437.4
申请日：2011-06-27
申请人： SPX Cooling Technologies Inc.
发明人： Lewis, Robert
IPC分类号： F04D29/38 , B21C23/16 , B21K3/04 , B23P15/02
CPC分类号： F04D29/384 , B21C23/16 , F04D29/388 , Y10T29/49336
摘要： A fan blade assembly is provided. The fan blade assembly (10) may include: a fan blade (36) having an airfoil shaped section, formed by being run lengthwise though a die and a flap portion integral with the airfoil section also run lengthwise through the die, the fan blade having a hub end and a tip end, a tapering trailing edge on a trailing edge of the fan blade defined by removing a portion of the trailing edge of the fan blade after it has been run through the die, the tapering trailing edge defining the fan blade (36) to be narrower moving from the hub end toward the tip end, and a flared portion interrupting the tapering trailing edge near the tip end, the flared portion defining the fan blade to become wider from the beginning of the flared portion to the tip end. A method for making a fan blade may also be provided.
摘要翻译：提供风扇叶片组件。风扇叶片组件（10）可以包括：风扇叶片（36），其具有翼形截面，通过纵向延伸通过模具形成，并且与翼型部分成一体的翼片部分也沿纵向延伸穿过模头，风扇叶片具有轮毂端和尖端，在风扇叶片的后缘上的锥形后缘，其通过在风扇叶片已经穿过模具之后去除风扇叶片的后缘的一部分而限定，锥形后缘限定风扇叶片（36）从轮毂端向前端移动较窄，并且扩张部分中断尖端附近的锥形后缘，限定风扇叶片的扩口部分从扩张部分的开始变宽到尖端结束。还可以提供制造风扇叶片的方法。

6. 发明授权

EP3302874B1 PROCÉDÉ DE FABRICATION D'UNE AUBE DE TURBOMACHINE EN TIAL 有权
公开(公告)号：EP3302874B1
公开(公告)日：2021-10-13
申请号：EP16733637.9
申请日：2016-05-26
发明人： LECONTE, Gilbert , FRANCHET, Jean-Michel , SALLOT, Pierre
IPC分类号： B23P13/04 , B23P15/02 , B22F3/17 , B22F3/20 , B21C23/00 , B21C23/14 , B21C23/16 , B21C35/02 , B21K3/04 , B22F5/04

7. 发明公开

EP3000546A1 METHOD OF MANUFACTURING GAS TURBINE ENGINE COMPONENT FROM A MOLYBDENUM-RICH ALLOY 有权转让
标题翻译：澳大利亚MOLYBDÄNREICHENLEGIERUNG VERFAHREN ZUR HERSTELLUNG VON GASTURBINENMOTORKOMPONENTEN AUS EINERMOLYBDÄNREICHENLEGIERUNG
公开(公告)号：EP3000546A1
公开(公告)日：2016-03-30
申请号：EP15186615.9
申请日：2015-09-24
申请人： United Technologies Corporation
发明人： John P., RIZZO
IPC分类号： B22F1/00 , B22F3/17 , B22F3/20 , C22C1/04 , F01D5/28 , B21C23/14 , B21C23/16 , B21C35/02
摘要： A method for manufacturing a gas turbine engine component from a molybdenum-rich alloy. The method includes the steps of providing a molybdenum powder of at least 50% molybdenum by weight, extruding the molybdenum powder to provide a first shape, forming the first shape to a second shape and forging the second shape to provide a third shape.
摘要翻译：一种从富钼合金制造燃气涡轮发动机部件的方法。该方法包括以下步骤：提供至少50重量％钼的钼粉末，挤出钼粉末以提供第一形状，将第一形状形成为第二形状并锻造第二形状以提供第三形状。

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