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21. 发明申请

US20160146036A1 ENGINE CASING ELEMENT 审中-公开
标题翻译：发动机组件
公开(公告)号：US20160146036A1
公开(公告)日：2016-05-26
申请号：US14948582
申请日：2015-11-23
申请人： General Electric Technology GmbH
发明人： Johannes RICHTER , Giovanni CATALDI , Nikolas WIEDEMANN , Carlos SIMON-DELGADO
IPC分类号： F01D17/10 , F01D25/08 , F01D9/06 , F01D25/24
CPC分类号： F01D17/10 , F01D9/06 , F01D11/24 , F01D25/08 , F01D25/24 , F05D2220/31 , F05D2220/32 , F05D2220/40 , F05D2240/125 , F05D2240/307 , F05D2260/221 , F05D2270/44 , Y02T50/676
摘要： An engine casing element comprises at least one clearance control cavity, the clearance control cavity being delimited by a clearance control cavity inner wall and having a clearance control cavity longitudinal extent. At least one insert member is arranged inside the clearance control cavity. The insert member is arranged and configured to effect at least one of a flow guide function and a heat transfer enhancement function.
摘要翻译：发动机壳体元件包括至少一个间隙控制腔，所述间隙控制腔由间隙控制腔内壁界定并且具有间隙控制腔纵向范围。至少一个插入构件布置在间隙控制腔内。插入构件被布置和构造成实现导流功能和传热增强功能中的至少一个。

22. 发明授权

US09328617B2 Trailing edge or tip flag antiflow separation 有权
标题翻译：后缘或尖端标志防潮隔离
公开(公告)号：US09328617B2
公开(公告)日：2016-05-03
申请号：US13424765
申请日：2012-03-20
申请人： Steven Bruce Gautschi , Brandon W. Spangler , San Quach , Dominic J. Mongillo, Jr.
发明人： Steven Bruce Gautschi , Brandon W. Spangler , San Quach , Dominic J. Mongillo, Jr.
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/122 , F05D2240/125 , F05D2240/304 , F05D2240/307 , F05D2250/314 , F05D2250/324 , F05D2260/22141 , Y02T50/676
摘要： An airfoil includes a leading edge, a trailing edge region, a suction surface, a pressure surface, a cooling passageway, and a column of flow separators. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge region, as well as radially from a root section of the airfoil to a tip section of the airfoil to define a central cavity of the airfoil. The cooling passageway is located within the central cavity at the trailing edge region. The column of flow separators is located in the cooling passageway adjacent the trailing edge and includes a first flow separator having a first longitudinal axis and a second flow separator having a second longitudinal axis. The first longitudinal axis is offset at an angle with respect to the first longitudinal axis.
摘要翻译：翼型件包括前缘，后缘区域，吸力表面，压力表面，冷却通道和流动隔板柱。吸力表面和压力表面都在前缘和后缘区域之间轴向延伸，并且从翼型的根部径向延伸到翼型的尖端部分，以限定翼型的中心腔。冷却通道位于后缘区域的中心腔内。流动分离器柱位于靠近后缘的冷却通道中，并且包括具有第一纵向轴线的第一流动分离器和具有第二纵向轴线的第二流动分离器。第一纵向轴线相对于第一纵向轴线以一定角度偏移。

23. 发明授权

US09290836B2 Crack-resistant environmental barrier coatings 有权
标题翻译：耐破坏环境屏障涂层
公开(公告)号：US09290836B2
公开(公告)日：2016-03-22
申请号：US13588051
申请日：2012-08-17
申请人： James Zhang , Herbert Chidsey Roberts , Rupak Das
发明人： James Zhang , Herbert Chidsey Roberts , Rupak Das
IPC分类号： B05D5/00 , C23C4/02 , C23C4/18 , C23C16/02 , C23C16/56 , C23C30/00 , C04B41/89 , C04B41/00 , C04B41/52 , F01D5/28
CPC分类号： C23C4/02 , C04B41/009 , C04B41/52 , C04B41/89 , C23C4/18 , C23C16/02 , C23C16/56 , C23C30/00 , F01D5/288 , F05D2240/121 , F05D2240/122 , F05D2240/125 , F05D2240/303 , F05D2240/304 , F05D2240/307 , Y10T428/24793 , C04B35/565 , C04B35/806 , C04B41/5096 , C04B41/5059 , C04B41/522 , C04B41/5066 , C04B41/5024 , C04B41/5042
摘要： Methods suitable for reducing corner cracking of environmental barrier coating systems. The methods include forming at least one layer of a first portion of the environmental barrier coating system on at least a first region of the component, performing a first heat treatment, forming at least one layer of a second portion of the environmental barrier coating system on a second region of the component, and performing a second heat treatment to the component. Edges of the first portion and edges of the second portion form an angle of at most 60° with respect to a surface of the first region of the component. During the second heat treatment, the second portion of the EBC system expands and the expansion of the second portion of the EBC system is at least partially constrained by the first portion of the EBC system to reduce tensile interfacial stresses in the EBC system.
摘要翻译：适用于减少环境屏障涂层系统的角裂纹的方法。所述方法包括在所述部件的至少第一区域上形成环境阻挡涂层系统的第一部分的至少一层，进行第一热处理，将环境阻挡涂层系统的至少一层第二部分形成在所述部件的第二区域，并且对所述部件进行第二热处理。第一部分的边缘和第二部分的边缘相对于部件的第一区域的表面形成至多60°的角度。在第二热处理期间，EBC系统的第二部分膨胀并且EBC系统的第二部分的膨胀至少部分地被EBC系统的第一部分约束，以减少EBC系统中的拉伸界面应力。

24. 发明申请

US20160032762A1 DEVICE FOR DEICING A SEPARATOR NOSE OF AN AVIATION TURBINE ENGINE 审中-公开
标题翻译：用于检测航空发动机的分离器的装置
公开(公告)号：US20160032762A1
公开(公告)日：2016-02-04
申请号：US14783263
申请日：2014-04-11
申请人： SNECMA
发明人： Benoit Jean Henri GOMANNE , Michel Gilbert, Roland BRAULT
IPC分类号： F01D25/02 , F01D25/24
CPC分类号： F01D25/02 , F01D25/24 , F02C7/047 , F05D2220/30 , F05D2230/21 , F05D2240/125 , F05D2260/607 , F05D2300/174 , Y02T50/671 , Y02T50/675
摘要： A device for deicing a separator nose of an aviation turbine engine, and including a separator nose for positioning downstream from a fan of the engine to separate annular channels for passing a primary stream and a secondary stream coming from the engine, and a casing fastened to the separator nose so as to extend it downstream, the casing having an inner shroud defining the outside of the primary stream flow passage, and including at least one air duct incorporated in the inner shroud so as to be formed integrally therewith, the air duct opening out downstream to an air feed and opening out upstream into the inside of the separator nose.
摘要翻译：一种用于对航空涡轮发动机的分离器鼻子进行除冰的装置，并且包括用于定位在发动机的风扇下游的分离器鼻部，以分离用于使主流体流过的环形通道和来自发动机的二次流，以及固定到所述分离器鼻部以便在其下游延伸，所述壳体具有限定所述主要流动通道外侧的内部护罩，并且包括结合在所述内部护罩中以与其一体形成的至少一个空气通道，所述空气管道开口在下游进入空气进料并向上游打开到分离器鼻部的内部。

25. 发明申请

US20160024955A1 Maxmet Composites for Turbine Engine Component Tips 审中-公开
标题翻译： Maxmet复合材料涡轮发动机组件提示
公开(公告)号：US20160024955A1
公开(公告)日：2016-01-28
申请号：US14775927
申请日：2013-12-16
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Shahram Amini , Christopher W Strock , Sergei F Burlatsky , Dmitri Novikov , David Ulrich Fuller
IPC分类号： F01D11/12 , F01D9/04 , B23K1/00 , B23K1/19 , C23C24/04 , B23K20/22 , B23K26/34 , B23K26/00 , C23C4/12 , F01D5/28 , B23K20/02
CPC分类号： F01D11/122 , B23K1/0006 , B23K1/19 , B23K20/02 , B23K20/22 , B23K26/0006 , B23K26/34 , B23K2103/16 , C23C4/04 , C23C4/134 , C23C24/04 , F01D5/288 , F01D9/041 , F01D11/12 , F01D11/20 , F05D2220/30 , F05D2230/236 , F05D2230/237 , F05D2230/312 , F05D2230/60 , F05D2230/90 , F05D2240/125 , F05D2240/307 , F05D2300/6032
摘要： A turbine engine system includes a turbine engine component having an airfoil portion and a tip, which turbine engine component having a MAXMET composite bonded to the tip. The MAXMET composite has MAX phases in a metal matrix.
摘要翻译：涡轮发动机系统包括具有翼型部分和尖端的涡轮发动机部件，该涡轮发动机部件具有结合到尖端的MAXMET复合材料。 MAXMET复合材料在金属基体中具有MAX相。

26. 发明申请

US20140241892A1 TURBOMACHINE BLADE AND RELATIVE PRODUCTION METHOD 有权
标题翻译：涡轮叶片和相对生产方法
公开(公告)号：US20140241892A1
公开(公告)日：2014-08-28
申请号：US14194369
申请日：2014-02-28
申请人： PIETRO ROSA T.B.M. S.r.l.
发明人： Andrea Maurizio
IPC分类号： F01D5/30 , B23P15/04
CPC分类号： F04D29/544 , B23P15/04 , F01D5/147 , F01D5/18 , F01D5/22 , F01D5/30 , F02K3/06 , F04D19/002 , F04D29/023 , F04D29/644 , F05D2220/323 , F05D2230/10 , F05D2230/232 , F05D2230/51 , F05D2240/125 , F05D2300/173 , F05D2300/174 , Y02T50/671 , Y02T50/676 , Y10T29/49337
摘要： A turbomachine blade of the type having a metal lower coupling root, a metal upper coupling head, and a metal airfoil-shaped oblong member designed to connect the coupling root rigidly to the coupling head; the airfoil-shaped oblong member having a substantially airfoil-shaped main plate-like element connected to the coupling root and to the coupling head, and which is divided into: a lower connecting fin cantilevered from and formed in one piece with the coupling root; an upper connecting fin cantilevered from and formed in one piece with the coupling head; and a center plate-like body, which is located between the lower and upper connecting fins, is shaped/designed to form an extension of the lower and upper connecting fins, and is butt-welded to, to form one piece with, the lower and upper connecting fins.
摘要翻译：一种具有金属下联结根的金属叶片，金属上连接头和金属翼型长椭圆形构件，其被设计成将联接根刚性连接到联接头; 所述翼型长椭圆形构件具有连接到所述联接根部和所述联接头的基本翼型的主板状元件，并且被分为：悬挂并与所述联接根部成一体的下连接翅片; 上连接片悬臂与联接头一体形成; 并且位于下连接翅片和上连接翅片之间的中心板状体被成形/设计成形成下连接翅片和上连接翅片的延伸部，并且被对接焊接成与下连接翅片的下部和上连接片。

27. 发明授权

US08613596B2 Vane assembly having a vane end seal 有权
标题翻译：叶片组件具有叶片端部密封
公开(公告)号：US08613596B2
公开(公告)日：2013-12-24
申请号：US12885524
申请日：2010-09-19
申请人： Theodore J. Fritsch
发明人： Theodore J. Fritsch
IPC分类号： F01D5/20
CPC分类号： F01D17/162 , F01D9/02 , F01D11/00 , F05D2240/125
摘要： One embodiment of the present invention is a unique turbomachinery device, a non-limiting example of which is a gas turbine engine. Another embodiment is a unique vane assembly for a turbomachinery device. Another embodiment is a unique seal assembly for a vane of a turbomachinery device. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for turbomachinery devices, and for vane assemblies and seal assemblies for turbomachinery devices. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
摘要翻译：本发明的一个实施例是独特的涡轮机械装置，其非限制性实例是燃气涡轮发动机。另一个实施例是用于涡轮机械装置的独特的叶片组件。另一个实施例是用于涡轮机械装置的叶片的独特的密封组件。其他实施例包括用于涡轮机械装置的装置，系统，装置，硬件，方法和组合，以及用于涡轮机械装置的叶片组件和密封组件。本申请的其他实施例，形式，特征，方面，益处和优点将从本文提供的描述和图中变得显而易见。

28. 发明申请

US20130156553A1 HONEYCOMB SEAL AND METHOD 有权
标题翻译：蜂窝密封和方法
公开(公告)号：US20130156553A1
公开(公告)日：2013-06-20
申请号：US13722973
申请日：2012-12-20
申请人： Nuovo Pignone S.P.A.
发明人： Nicola Mitaritonna , Giuseppe Vannini
IPC分类号： F01D25/00
CPC分类号： F01D25/00 , F01D11/127 , F04D29/102 , F04D29/164 , F05D2240/125 , F05D2240/55 , F05D2250/283 , F16J15/444 , Y10T29/49826
摘要： A seal for a turbo machine is provided. The seal includes a plurality of honeycomb cells, at least one circumferential groove within the plurality of honeycomb cells, and at least one swirl brake within the at least one groove.
摘要翻译：提供涡轮机的密封件。密封件包括多个蜂窝单元，多个蜂窝单元内的至少一个周向槽，以及至少一个槽内的至少一个涡流制动器。

29. 发明申请

US20130104550A1 TURBINE OF A TURBOMACHINE 有权
标题翻译：涡轮机的涡轮机
公开(公告)号：US20130104550A1
公开(公告)日：2013-05-02
申请号：US13284068
申请日：2011-10-28
申请人： Paul Kendall Smith , Gunnar Leif Siden , Craig Allen Bielek , Thomas William Vandeputte
发明人： Paul Kendall Smith , Gunnar Leif Siden , Craig Allen Bielek , Thomas William Vandeputte
IPC分类号： F02C3/04 , F01D1/00 , F01D1/04
CPC分类号： F01D5/141 , F05D2240/125 , F05D2240/307
摘要： A turbine of a turbomachine is provided and includes opposing endwalls defining a pathway for a fluid flow and a plurality of interleaved blade stages and nozzle stages arranged axially along the pathway. The plurality of the blade stages includes a last blade stage at a downstream end of the pathway and a next-to-last blade stage upstream from the last blade stage. The plurality of the nozzle stages includes a last nozzle stage between the last blade stage and the next-to-last blade stage and a next-to-last nozzle stage upstream from the next-to-last blade stage. At least one of the next-to-last blade stage and the next-to-last nozzle stage includes aerodynamic elements configured to interact with the fluid flow and to define a throat distribution producing a tip strong pressure profile in the fluid flow.
摘要翻译：提供涡轮机的涡轮机并且包括限定用于流体流动的路径的相对的端壁以及沿着该路径轴向设置的多个交错的叶片级和喷嘴级。多个叶片级在通路的下游端包括最后的叶片级，并且在最后叶片级的上游包括一个最后叶片级。多个喷嘴级包括在最后的叶片级和下一个到最后的叶片级之间的最后一个喷嘴级，以及从下一个到最后的叶片级上游的最后一个喷嘴级。下一个到最后的叶片级和下一个到最后的喷嘴级中的至少一个包括配置成与流体流相互作用并且限定喉部分布的气动元件，其产生流体流中的尖端强压力分布。

30. 发明授权

US11898450B2 Flowpath assembly for gas turbine engine 有权
公开(公告)号：US11898450B2
公开(公告)日：2024-02-13
申请号：US17323436
申请日：2021-05-18
申请人： RAYTHEON TECHNOLOGIES CORPORATION
发明人： Raymond Surace , San Quach , Bryan P. Dube
IPC分类号： F01D11/12 , F01D5/28 , F01D5/14 , F01D25/12
CPC分类号： F01D11/12 , F01D5/282 , F01D5/147 , F01D25/12 , F05D2220/323 , F05D2240/11 , F05D2240/125 , F05D2300/20 , F05D2300/6033
摘要： An assembly for a gas turbine engine includes, among other things, an end wall including a main body extending between a first end portion and a second end portion to establish a seal face. The end wall includes a first attachment portion dimensioned to fixedly attach the main body to a static structure at a first attachment point. An airfoil extends radially inwardly from the end wall relative to an assembly axis. The airfoil includes an inner cavity extending between a first end portion and a second end portion, the first end portion adjacent the end wall of the airfoil. A spar member includes a spar body extending between a first end portion and a second end portion. The spar body extends at least partially through the inner cavity. The first end portion of the end wall is cantilevered from the first attachment point.

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