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公开(公告)号：US20130051987A1
公开(公告)日：2013-02-28
申请号：US13222028
申请日：2011-08-31
申请人： Eric DUROCHER , Guy LEFEBVRE
发明人： Eric DUROCHER , Guy LEFEBVRE
CPC分类号： B22F5/009 , B22F3/004 , B22F3/12 , B22F3/225 , B22F7/06 , C22C19/03 , C22C19/07 , F01D9/02 , F01D11/08 , F01D25/24 , F05D2230/30 , F05D2240/11
摘要： A turbine shroud has a plurality of shroud segments disposed circumferentially one adjacent to another. Each segment has a flow restrictor projecting integrally from one end face thereof and overlapping a corresponding end face of a circumferentially adjacent segment. The overlap between the circumferentially adjacent segments restricts gas leakage through the inter-segment gap between adjacent shroud segments.
摘要翻译： 涡轮机护罩具有多个围绕另一个相邻设置的护罩段。 每个段具有从其一个端面一体地突出并与周向相邻的段的对应的端面重叠的限流器。 周向相邻的区段之间的重叠限制了通过相邻护罩区段之间的段间间隙的气体泄漏。
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公开(公告)号：US20110081234A1
公开(公告)日：2011-04-07
申请号：US12571909
申请日：2009-10-01
申请人： Eric DUROCHER , Guy LEFEBVRE
发明人： Eric DUROCHER , Guy LEFEBVRE
CPC分类号： F01D25/243 , F01D25/26 , F05B2260/301 , F05D2260/94 , F05D2260/941
摘要： A thermal expansion joint apparatus includes an insert extending passages passing through respective first and second components to loosely restrain the first component between the second component and an enlarged head of the insert thereby allowing thermal expansion of the respective first and second components relative to each other. The insert is secured to the second component by a fastener which can be removed, for example, when the insert is to be removed from the engine.
摘要翻译： 热膨胀接头装置包括插入件，其延伸通过相应的第一和第二部件的通道，以松散地限制第二部件和插入件的扩大头部之间的第一部件，从而允许相应的第一和第二部件相对于彼此的热膨胀。 插入件通过紧固件固定到第二部件上，该紧固件可以例如当插入件从发动机上移除时被去除。
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公开(公告)号：US20110036068A1
公开(公告)日：2011-02-17
申请号：US12858313
申请日：2010-08-17
申请人： Guy LEFEBVRE , Nicolas GRIVAS , Richard BOUCHARD , Denis LECLAIR , Eric DUROCHER
发明人： Guy LEFEBVRE , Nicolas GRIVAS , Richard BOUCHARD , Denis LECLAIR , Eric DUROCHER
IPC分类号： F02K1/38
CPC分类号： F02K1/386 , F01D9/04 , F02K1/48 , F02K1/80 , F05D2220/32 , F05D2230/642 , F05D2240/10 , F05D2240/127 , Y02T50/671
摘要： An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.
摘要翻译： 用于燃气涡轮发动机的排气混合器包括具有适于紧固到发动机壳体的上游端的环形壁和形成多个内部和外部混合器凸角的下游端。 支撑构件互连至少多个内裂片，并且包括从内裂片径向向内定位的周向延伸的加强环，以及一系列周向间隔开的从内裂纹到加强环径向延伸的混合器支柱。 混合器支柱具有至少等于限定在内部叶片和排气锥体之间的主气体通道的宽度的径向长度，使得混合器支柱完全延伸穿过主气体路径。 加强环仅被固定到混合器支柱上，以便相对于排气锥体浮动并允许它们之间的相对运动。
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公开(公告)号：US20130223982A1
公开(公告)日：2013-08-29
申请号：US13404347
申请日：2012-02-24
申请人： Eric DUROCHER , Guy LEFEBVRE
发明人： Eric DUROCHER , Guy LEFEBVRE
CPC分类号： F16B5/0241 , F16B5/04 , Y10T29/4932 , Y10T403/217
摘要： A thermal expansion joint suited for metal sheet component assemblies and method of connection is described. The expansion joint connection is formed by overlapping edge portions of components which are subject to different temperatures. Slot apertures are formed in the edge portion of a first component at predetermined locations and hole apertures are formed in the edge portion of the second component and disposed for confronting alignment with the slot apertures. A connecting sleeve is disposed in each hole aperture and projects through the hole and associated slot and a retention washer is secured over an end of the connecting sleeve on the other side of the second component. A fastener extends through the retention washer and the connecting sleeve to clampingly interconnect the overlapped edge portions of the first and second components.
摘要翻译： 描述适用于金属片组件组件的热膨胀接头和连接方法。 膨胀接头连接部由经受不同温度的部件的重叠边缘部分形成。 槽孔在第一部件的边缘部分形成在预定位置处，并且在第二部件的边缘部分中形成孔孔，并且设置成与槽孔对准。 连接套筒设置在每个孔孔中并突出穿过孔和相关联的槽，并且保持垫圈固定在第二部件另一侧的连接套筒的一端上。 紧固件延伸穿过保持垫圈和连接套筒夹紧地互连第一和第二部件的重叠的边缘部分。
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公开(公告)号：US20090110548A1
公开(公告)日：2009-04-30
申请号：US11928512
申请日：2007-10-30
申请人： Eric DUROCHER , Guy LEFEBVRE
发明人： Eric DUROCHER , Guy LEFEBVRE
IPC分类号： F04D29/08
CPC分类号： F01D11/001 , F05D2240/122 , F05D2240/304 , F05D2240/80
摘要： An abradable rim seal arrangement for a turbine stage of a gas turbine engine, which includes an abradable rim seat attached to a leading edge of an annular inner duct of a turbine exhaust case, causing a trailing edge platform of each rotor blade to overlap the abradable rim seal, and allowing rubbing with the trailing edge platform during engine operation.
摘要翻译： 一种用于燃气涡轮发动机的涡轮级的可磨损轮辋密封装置，其包括附接到涡轮机排气箱的环形内部管道的前缘的可磨损轮辋座，使得每个转子叶片的后缘平台与可磨损的 轮辋密封，并且在发动机操作期间允许与后缘平台摩擦。
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公开(公告)号：US20080060344A1
公开(公告)日：2008-03-13
申请号：US11530529
申请日：2006-09-11
申请人： Eric DUROCHER , Guy LEFEBVRE
发明人： Eric DUROCHER , Guy LEFEBVRE
IPC分类号： F02K1/38
CPC分类号： F02K1/04 , F05D2260/30
摘要： An annular exhaust duct of a gas turbine engine includes inner and outer cases co-axially disposed, and radially spaced apart by a plurality of airfoils radially extending therebetween. The outer case includes a connection apparatus for supportably connecting the exhaust duct to the gas turbine engine and the inner case includes an axial end portion at a rear end thereof for connection with a tail cone. The axial end portion bends radially and inwardly at a rear extremity thereof to stiffen the rear end of the inner ease.
摘要翻译： 燃气涡轮发动机的环形排气管包括同轴地设置的内壳体和外壳体，并且由在其间径向延伸的多个翼型件径向隔开。 外壳包括用于将排气管可支撑地连接到燃气涡轮发动机的连接装置，并且内壳在其后端包括用于与尾锥连接的轴向端部。 轴向端部在其后端处径向向内弯曲并使其内侧的后端变硬。
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公开(公告)号：US20130051989A1
公开(公告)日：2013-02-28
申请号：US13222022
申请日：2011-08-31
申请人： Eric DUROCHER , Guy LEFEBVRE
发明人： Eric DUROCHER , Guy LEFEBVRE
CPC分类号： F01D11/005 , B22F3/225 , B22F5/009 , B22F7/08 , F01D9/04 , F05D2220/32 , F05D2240/57 , Y10T29/4998
摘要： A feather seal is positioned in a mold and a shroud body is metal injection molded about a proximal end of the feather seal to provide a shroud segment with an integrated feather seal. A seal groove is provided in an opposite lateral side of the shroud body to receive the feather seal of a circumferentially adjacent shroud segment.
摘要翻译： 羽毛密封件定位在模具中，并且护罩主体围绕羽毛密封件的近端金属注射模制，以提供具有集成的羽毛密封件的护罩区段。 密封槽设置在护罩主体的相对的侧面上，以容纳周向相邻护罩区段的羽毛密封。
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公开(公告)号：US20110081238A1
公开(公告)日：2011-04-07
申请号：US12571731
申请日：2009-10-01
申请人： Eric DUROCHER , Jean Fournier
发明人： Eric DUROCHER , Jean Fournier
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F05D2230/232 , F05D2230/50 , F05D2240/12 , F05D2240/122 , F05D2240/304
摘要： A gas turbine engine stator vane has a sheet metal body with a pressure surface and a suction surface extending chordwise from a leading edge to a trailing edge. The sheet metal body has opposed pressure and suction side trailing end portions that meet at a joint upstream from the trailing edge of the airfoil. The pressure and suction surfaces of the sheet metal body are parallel to one another between the joint and the trailing edge, thereby forming a straight non-tapering trailing edge section from the joint to the trailing edge of the airfoil.
摘要翻译： 燃气涡轮发动机定子叶片具有带有压力表面的金属板体和从前缘向后缘延伸的抽吸表面。 钣金体具有与翼型件的后缘上游相接的相对的压力和吸力侧后端部。 金属板体的压力和吸力表面在接头和后缘之间彼此平行，从而形成从翼缘的接头到后缘的直的非渐缩的后缘部分。
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公开(公告)号：US20100132377A1
公开(公告)日：2010-06-03
申请号：US12325031
申请日：2008-11-28
申请人： Eric DUROCHER , John PIETROBON
发明人： Eric DUROCHER , John PIETROBON
CPC分类号： F01D9/065 , F01D9/047 , F01D25/162 , Y10T29/4932
摘要： A gas turbine engine mid turbine frame having an annular interturbine duct and vane ring assembly includes a duct having outer and inner duct walls of sheet metal interconnected by radial hollow struts of sheet metal and a vane ring is connected to the duct to provide the assembly. The interturbine duct and vane ring assembly may be provided within a mid turbine frame in a manner which is independent of a bearing load path through the mid turbine frame.
摘要翻译： 具有环形涡轮管道和叶片环组件的燃气涡轮发动机中涡轮机框架包括具有通过钣金的径向中空支柱互连的金属板的外部和内部管道壁的管道，并且叶片环连接到管道以提供组件。 涡轮管道和叶片环组件可以以不依赖于中间涡轮机框架的轴承负载路径的方式设置在中间涡轮机框架内。
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公开(公告)号：US20100272566A1
公开(公告)日：2010-10-28
申请号：US12429242
申请日：2009-04-24
IPC分类号： F01D1/02
CPC分类号： F01D25/14 , F01D5/142 , F01D5/143 , F01D5/146 , F01D9/02 , F01D9/041 , F01D9/06 , F01D17/143 , F01D25/16 , F01D25/24 , F01D25/28 , F02C7/057 , F02C9/22 , F04D29/544
摘要： A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially adjacent the strut and axially behind a leading edge of the strut, and an aerodynamic deflector located circumferentially between each strut and each vane. The aerodynamic deflector may positioned axially upstream of a flow separation point which would otherwise be caused by the strut.
摘要翻译： 燃气涡轮发动机设置有具有内管壁和外管壁的环形管道。 至少一个支柱在内管道壁和外管壁之间延伸。 支柱具有空气动力学形状。 至少一个叶片周向地邻近支柱并且轴向地在支柱的前缘之后，以及位于每个支柱和每个叶片之间周向的空气动力学偏转器。 空气动力学偏转器可以轴向位于流动分离点的上游，否则将由支柱引起。
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