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11.发明申请MEMBER FOR LOCKING RING SECTORS ON A TURBINE ENGINE CASING, INCLUDING RADIAL PASSAGES FOR GRIPPING SAME 审中-公开在涡轮发动机壳体上的锁定环部分的会员，包括用于运输的径向通道公开(公告)号：US20110056055A1
公开(公告)日：2011-03-10
申请号：US12991641
申请日：2009-05-14
IPC分类号： F16B2/24
CPC分类号： F01D25/246 , F05D2230/60 , F05D2230/70 , F16B2/245 , Y02T50/672 , Y10T24/44017
摘要： A locking member for a device used to fasten ring sectors on a casing of an aircraft turbine engine, wherein the member includes two clamping arms connected together at the rear end thereof by a connection arm extending substantially parallel to the general spacing direction between the two clamping arms. The member includes, on either side of a virtual median plane orthogonal to the circumferential direction, a passage for gripping the member, each passage being formed through the connection arm, emerging in an inter-arm space.
摘要翻译： 一种用于紧固飞机涡轮发动机的壳体上的环形部件的装置的锁定构件，其中，所述构件包括两个夹持臂，所述两个夹臂在其后端处由连接臂连接在一起，所述连接臂基本上平行于两个夹紧之间的一般间隔方向延伸 武器。 该构件在与圆周方向垂直的虚拟正中平面的任一侧上包括用于夹持构件的通道，每个通道穿过连接臂形成，并且在臂间空间中出现。
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12.发明授权Stay sector of stator shroud of the high-pressure turbine of a gas turbine engine with clearance control 有权具有间隙控制的燃气轮机的高压涡轮机的定子护罩部分公开(公告)号：US06726446B2
公开(公告)日：2004-04-27
申请号：US10204403
申请日：2002-08-27
IPC分类号： F01D2526
CPC分类号： F01D25/246 , F05D2230/642
摘要： The support spacer sector (14) minimizes functional clearances (J) between the end of the blades (3) and the ring (12) of the high-pressure turbine and the assembly clearances of the support spacer sectors (14) on the casing of the high-pressure turbine (1). Each support spacer sector (14) has a tab (20) on the upstream side one end (21) of which is supported on the inside wall (1I) of the casing of the high-pressure turbine (1) thus forming an intimate contact between the attachment parts of this support spacer sector (14) with the corresponding parts of the casing of the high-pressure turbine (1). This invention applies to turbo-machines fitted on an aircraft.
摘要翻译： 支撑间隔部分（14）最小化叶片（3）的端部与高压涡轮机的环（12）之间的功能间隙（J）和壳体上的支撑间隔件扇区（14）的组装间隙 高压涡轮机（1）。 每个支撑间隔件（14）在其上游侧具有一个突出部（20），其一端（21）支撑在高压涡轮（1）的壳体的内壁（1I）上，从而形成紧密接触 在该支撑间隔件部分（14）的附接部分与高压涡轮机（1）的壳体的相应部分之间。 本发明适用于安装在飞机上的涡轮增压机。
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13.发明授权Interface element between a blade root and a blade root housing of a turbine disc, and turbine rotor comprising an interface element 有权在叶片根部和涡轮盘的叶片根部壳体之间的界面元件，以及包括界面元件的涡轮转子公开(公告)号：US09103220B2
公开(公告)日：2015-08-11
申请号：US13643569
申请日：2011-04-20
CPC分类号： F01D5/3092 , F01D5/081 , F01D5/3007 , F05D2240/81 , F05D2250/70 , F05D2250/71 , F05D2260/20 , F05D2260/30 , F05D2260/36 , F05D2260/941 , F05D2260/96
摘要： An interface element to be mounted between a blade root and a blade root housing provided in a turbine disc of a gas turbine engine to limit wear between the root and the housing. The interface element includes: a base, configured to be aligned with a lower part of the root; and first and second upper side walls connected to the base and configured to surround the blade root up to an upper portion thereof, the first upper side wall including at least one ventilation opening to allow a flow of cooling air flowing through the rotor disc housing to flow over the upper portion of the root via the ventilation opening.
摘要翻译： 安装在叶片根部和设置在燃气涡轮发动机的涡轮盘中的叶片根部壳体之间的界面元件，以限制根部和壳体之间的磨损。 接口元件包括：基座，构造成与根部的下部对准; 以及第一和第二上侧壁，其连接到基部并且被构造成围绕叶片根部直到其上部，第一上侧壁包括至少一个通风开口，以允许流过转子盘壳体的冷却空气流动到 通过通风口流过根部的上部。
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14.发明授权Insulating a circumferential rim of an outer casing of a turbine engine from a corresponding ring sector 有权将涡轮发动机的外壳的圆周边缘与相应的环形部分隔离公开(公告)号：US08961117B2
公开(公告)日：2015-02-24
申请号：US13511021
申请日：2010-11-24
申请人： Fabrice Marcel Noel Garin , Alain Dominique Gendraud , Gilles Jeannin , Sebastien Jean Laurent Prestel
发明人： Fabrice Marcel Noel Garin , Alain Dominique Gendraud , Gilles Jeannin , Sebastien Jean Laurent Prestel
CPC分类号： F01D25/246 , F01D11/005
摘要： A turbine stage of a turbine engine, the stage including a rotor wheel mounted inside a sectorized ring carried by an outer casing, the outer casing including at least a circumferential rim housed in an annular cavity to attach a downstream end of the ring sector. A bottom wall of the annular cavity of the ring sector remains radially spaced apart from the circumferential rim of the outer casing to provide a thermally insulating space between them and includes a radial positioning mechanism acting on the circumferential rim.
摘要翻译： 涡轮发动机的涡轮级，该级包括安装在由外壳承载的扇形环内的转子轮，所述外壳至少包括容纳在环形空腔中的周缘，以附接环形部分的下游端。 环形部分的环形空腔的底壁保持与外壳的圆周边缘径向间隔开，以在它们之间提供隔热空间并且包括作用在圆周边缘上的径向定位机构。
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15.发明授权High-pressure turbine for turbomachine, associated guide vane sector and aircraft engine 有权用于涡轮机的高压涡轮机，相关导向叶片部件和飞机发动机公开(公告)号：US08858169B2
公开(公告)日：2014-10-14
申请号：US13059350
申请日：2009-08-24
CPC分类号： F02C3/045 , F01D9/042 , F01D25/246 , F05D2250/41 , F05D2270/114 , Y02T50/671
摘要： An assembling of a guide vane assembly of a turbomachine turbine, formed by an annular row of stationary flow-stabilizing vanes. An outer edge of the guide vane assembly is axially bearing on a line of an external casing of the turbine and an inner edge of the guide vane assembly is in axial sliding connection with the line of the internal casing of the turbine, the axial sliding connection allowing the inner edge to be free along the motor axis with the axial stop being achieved by the axial bearing of the outer edge of the vane.
摘要翻译： 一种涡轮机涡轮机的导叶组件的组装，由一组固定的流动稳定叶片形成。 导向叶片组件的外边缘轴向地轴承在涡轮机的外壳的一条线上，并且导向叶片组件的内边缘与涡轮机的内壳线的轴向滑动连接，轴向滑动连接 允许内边缘沿着马达轴线自由，其中轴向止动通过叶片的外边缘的轴向轴承来实现。
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16.发明申请公开(公告)号：US20120288362A1
公开(公告)日：2012-11-15
申请号：US13511021
申请日：2010-11-24
申请人： Fabrice Marcel Noel Garin , Alain Dominique Gendraud , Gilles Jeannin , Sebastien Jean Laurent Prestel
发明人： Fabrice Marcel Noel Garin , Alain Dominique Gendraud , Gilles Jeannin , Sebastien Jean Laurent Prestel
IPC分类号： F01D25/08
CPC分类号： F01D25/246 , F01D11/005
摘要： A turbine stage of a turbine engine, the stage including a rotor wheel mounted inside a sectorized ring carried by an outer casing, the outer casing including at least a circumferential rim housed in an annular cavity to attach a downstream end of the ring sector. A bottom wall of the annular cavity of the ring sector remains radially spaced apart from the circumferential rim of the outer casing to provide a thermally insulating space between them and includes a radial positioning mechanism acting on the circumferential rim.
摘要翻译： 涡轮发动机的涡轮级，该级包括安装在由外壳承载的扇形环内的转子轮，所述外壳至少包括容纳在环形空腔中的周缘，以附接环形部分的下游端。 环形部分的环形空腔的底壁保持与外壳的圆周边缘径向间隔开，以在它们之间提供隔热空间并且包括作用在圆周边缘上的径向定位机构。
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公开(公告)号：US08133018B2
公开(公告)日：2012-03-13
申请号：US12038604
申请日：2008-02-27
IPC分类号： F01D9/00
CPC分类号： F01D25/246 , F01D9/042
摘要： A high-pressure turbine of a turbomachine, including at least one upstream guide vane element and an impeller mounted so as to rotate inside ring sectors attached to an annular support which is suspended from an outer casing, the upstream guide vane element including, at its radially inner end, a mechanism for attachment to an inner casing and, at its radially outer end, a mechanism for pressing axially on a fixed element of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.
摘要翻译： 涡轮机的高压涡轮机，包括至少一个上游引导叶片元件和叶轮，其安装成在附接到从外壳悬挂的环形支撑件的环形部分内旋转，所述上游引导叶片元件包括在其上 径向内端，用于附接到内壳体的机构，并且在其径向外端处具有用于轴向地按压在涡轮机的固定元件上的机构，所述机构与所述环形支撑件独立于所述环形支撑件悬挂， 。
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18.发明申请UNIT FOR LOCKING RING SECTORS ON A TURBOMACHINE CASING, COMPRISING RADIAL PASSAGES FOR GRIPPING IT 有权用于在涡轮机壳体上锁定环部的装置，包括用于运送的径向通道公开(公告)号：US20110121150A1
公开(公告)日：2011-05-26
申请号：US12990913
申请日：2009-05-14
CPC分类号： F01D25/246 , F05D2230/60 , F05D2230/70 , F16B2/245 , Y02T50/672
摘要： A unit locking a ring sector attachment device onto an aircraft turbomachine casing, the unit including two clamping arms connected to each other at their aft ends by a connecting arm extending approximately parallel to the general direction between the two clamping arms. The unit also includes a passage enabling gripping of the unit on each side of a fictitious median plane orthogonal to the circumferential direction, each passage being formed in the connecting arm, extending along a direction line approximately parallel to the direction between the arms.
摘要翻译： 单元将环形部分附接装置锁定到飞行器涡轮机壳体上，该单元包括两个夹持臂，它们的后端通过大致平行于两个夹紧臂之间的大致方向延伸的连接臂连接。 该单元还包括能够在垂直于圆周方向的虚拟中间平面的每侧上夹持单元的通道，每个通道形成在连接臂中，沿着大致平行于臂之间的方向的方向线延伸。
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公开(公告)号：US20080267768A1
公开(公告)日：2008-10-30
申请号：US12038604
申请日：2008-02-27
IPC分类号： F01D5/02
CPC分类号： F01D25/246 , F01D9/042
摘要： High-pressure turbine of a turbomachine A high-pressure turbine (10) of a turbomachine, comprising at least one upstream guide vane element (16) and an impeller (18) mounted so as to rotate inside ring sectors (20) attached to an annular support (24) which is suspended from an outer casing (22), the upstream guide vane element comprising, at its radially inner end, means of attachment to an inner casing and, at its radially outer end, means (102, 104) for pressing axially on a fixed element (90) of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.
摘要翻译： 涡轮机的高压涡轮机涡轮机的高压涡轮机（10），包括至少一个上游引导叶片元件（16）和叶轮（18），所述至少一个上游引导叶片元件（16）和叶轮（18）安装成在环形部分（20）内旋转， 环形支撑件（24），其从外壳（22）悬挂，所述上游引导叶片元件在其径向内端包括附接到内壳的装置，并且在其径向外端处包括装置（102,104） 用于轴向地压在涡轮机的固定元件（90）上，所述固定元件（90）独立于环形支撑件从外壳悬挂以附接环形部分。
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公开(公告)号：US09080463B2
公开(公告)日：2015-07-14
申请号：US13255436
申请日：2010-03-01
申请人： Franck Roger Denis Denece , Alain Dominique Gendraud , Georges Habarou , Hubert Illand , Damien Bonneau
发明人： Franck Roger Denis Denece , Alain Dominique Gendraud , Georges Habarou , Hubert Illand , Damien Bonneau
CPC分类号： F01D25/246 , D03D25/005 , F01D9/04 , F01D11/08 , F05D2230/642 , F05D2240/11 , F05D2260/30 , F05D2300/21 , F05D2300/603 , Y02T50/67 , Y02T50/672
摘要： A turbine ring assembly includes a ring support structure and a plurality of ring sectors, each including a single piece of ceramic matrix composite material. Each ring sector includes a first portion forming an annular base with an inside face defining an inside face of the turbine ring and an outside face from which there extends two tab-forming portions including ends that are engaged in housings in the ring support structure. The ring sectors present a section that is substantially π-shaped and the ends of the tabs are held without radial clearance by the ring support structure. The tabs can have a free length in meridian section that is not less than three times their mean width.
摘要翻译： 涡轮环组件包括环支撑结构和多个环形部分，每个环形部分包括单片陶瓷基体复合材料。 每个环形部分包括形成环形基部的第一部分，其中限定了涡轮机环的内侧面的内侧面和外表面，两个突出部形成部分从该外侧面延伸，该突出部形成部分包括接合在环形支撑结构中的壳体中的端部。 环形部分呈现出基本上形状的部分，并且突片的端部由环形支撑结构保持而没有径向间隙。 翼片可以在子午线部分具有不小于平均宽度的三倍的自由长度。
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