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公开(公告)号：US07008190B2
公开(公告)日：2006-03-07
申请号：US10346134
申请日：2003-01-17
IPC分类号： F01D5/02
摘要： In a succession of rotor disks, only the end disks are connected to a main structure by bolted extensions and the intermediate disks are suspended from rigid spacer pieces by centering and anti-rotation connections. The end disks are interconnected to clamp the assembly in the axial direction. There is no bolted connection between the successive disks. Assembly is very easy. The disks and the spacer pieces are stacked together in alternately, and the assembly is torsionally very rigid because of the use of a high number of claw-coupling teeth formed by protruding ends of the blade roots forming teeth that engage in spacer piece end rims.
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2.发明授权Turbojet venting pipe, method for mounting one such pipe and turbojet provided with one such pipe 有权涡轮喷气通风管，一个这种管道的安装方法和一个这样的管道的涡轮喷气发动机公开(公告)号：US09322293B2
公开(公告)日：2016-04-26
申请号：US13636802
申请日：2011-03-28
CPC分类号： F01D25/18 , F05D2230/64 , F05D2230/642 , F05D2240/61 , F05D2260/30 , F05D2260/602 , F05D2260/6022 , F16L21/08 , F16L37/14 , Y10T29/49826
摘要： A venting pipe used to guide a gas stream in a turbojet including at least one hollow rotary shaft inside which the pipe is mounted, the pipe extending generally along an axis. The pipe includes at least two pipe segments configured to be aligned longitudinally and assembled to one another while retaining a degree of freedom in relative translation thereof, at least one of the segments including a deformable mechanism configured to deform radially as the pipe segments are tightened against one another in the shaft of the turbojet, to bear on the shaft. The pipe structure facilitates mounting of the pipe.
摘要翻译： 用于引导涡轮喷气机中的气流的排气管，其包括至少一个中空旋转轴，管内安装有管，管通常沿轴线延伸。 管道包括至少两个管段，其构造成纵向对齐并且彼此组装，同时保持其相对平移的自由度，所述段中的至少一个包括可变形机构，所述可变形机构构造成随着管段被紧固而径向变形 在涡轮喷气发动机的轴上彼此相依，承担在轴上。 管道结构便于安装管道。
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公开(公告)号：US07491031B2
公开(公告)日：2009-02-17
申请号：US11405457
申请日：2006-04-18
IPC分类号： F01D5/02
CPC分类号： F01D5/027 , F05B2260/301 , F05D2260/30 , F16F15/34
摘要： A device for balancing a turbomachine rotor includes at least one counterweight fitted to the rotor, wherein the counterweight includes two radial bearing surfaces oriented in two opposite radial directions, the said surfaces interacting with two radial bearing surfaces made on the rotor, the counterweight being held against the rotor by an axial retention device. In particular, the axial retention device can be a bolt with a nut, the bolt holding the counterweight against a coupling flange fixed ly attached to the rotor, including an axial bearing surface and the radial bearing surfaces.
摘要翻译： 用于平衡涡轮机转子的装置包括装配到转子的至少一个配重，其中所述配重包括沿两个相对的径向定向的两个径向支承面，所述表面与在所述转子上形成的两个径向支承表面相互作用，所述配重被保持 通过轴向保持装置抵靠转子。 特别地，轴向保持装置可以是具有螺母的螺栓，螺栓将配重保持固定地连接到转子的联接凸缘，包括轴向支承表面和径向支承表面。
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4.发明申请公开(公告)号：US20080112805A1
公开(公告)日：2008-05-15
申请号：US11940795
申请日：2007-11-15
IPC分类号： F01D9/00
CPC分类号： F02K3/072 , F01D25/162 , F01D25/243 , F05D2230/64 , Y02T50/671
摘要： The invention relates to the field of free turbines mounted on a gas turbine engine. It provides a fastener device for fastening a free turbine stator on a gas generator casing that shares a common axis with the turbine stator, the fastener device comprising a flange carrying a plurality of assembly parts providing a first releasable connection between the turbine stator and the gas generator casing, the flange providing first centering of the turbine stator on the casing. The fastener device further comprises a second releasable connection between the turbine stator and the gas generator casing that is axially offset from the flange towards the gas generator and that provides second centering of the turbine stator on the casing.
摘要翻译： 本发明涉及安装在燃气涡轮发动机上的自由涡轮机领域。 它提供了一种用于将自由涡轮机定子紧固在与涡轮机定子共享公共轴线的气体发生器壳体上的紧固件装置，该紧固件装置包括一个凸缘，该凸缘承载多个组件，该组件部件提供在涡轮机定子和气体之间的第一可释放连接 发电机壳体，凸缘提供壳体上的涡轮机定子的第一定心。 紧固件装置还包括在涡轮机定子和气体发生器壳体之间的第二可释放连接，其从凸缘朝向气体发生器轴向偏移并且提供涡轮机定子在壳体上的第二对中。
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公开(公告)号：US20200095890A1
公开(公告)日：2020-03-26
申请号：US16580823
申请日：2019-09-24
摘要： A turbine engine comprising a fan comprising a first shaft driven in rotation via a reduction gear, the first shaft being guided in rotation with respect to a support of a fixed structure via an upstream bearing and a downstream bearing, the downstream bearing guiding in rotation the first shaft with respect to a downstream branch of the support, the first shaft and the support together defining an enclosure, the reduction gear comprising a ring gear fixed to the structure via a shell, the turbine engine comprising lubricator composed of at least one pipe for conveying a liquid lubricant, wherein the pipe is located in the enclosure, the pipe passing through an orifice made in the shell and an opening made in the downstream branch.
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公开(公告)号：US07568336B2
公开(公告)日：2009-08-04
申请号：US12037499
申请日：2008-02-26
申请人： Michel Gilbert Roland Brault , Stephane Rousselin , Nicolas Jerome Jean Tantot , Roxane Carmelle Jeanne Yvonne Touret
发明人： Michel Gilbert Roland Brault , Stephane Rousselin , Nicolas Jerome Jean Tantot , Roxane Carmelle Jeanne Yvonne Touret
IPC分类号： F02K3/02
CPC分类号： F02C7/143 , F02K3/115 , F05D2220/326 , F05D2220/327 , F05D2260/205 , F05D2260/211 , Y02T50/675
摘要： An aeroengine includes a primary air circuit; a high-pressure compressor fed by the primary air; and a secondary air circuit. The engine further includes at least one heat exchanger mounted in the primary air circuit upstream from the high-pressure compressor, the heat exchanger including a cold secondary circuit and a hot primary circuit, the hot primary circuit being fed with air from the primary air circuit and the cold secondary circuit being fed with air from the secondary air circuit. The cold circuit of the heat exchanger is fed by pipes that open out into the secondary air circuit.
摘要翻译： 航空发动机包括一次空气回路; 由一次空气供给的高压压缩机; 和二次空气回路。 发动机还包括安装在高压压缩机上游的一次空气循环中的至少一个热交换器，该热交换器包括一个冷二次回路和一个热一次回路，该热一次回路由一次空气回路供给空气 并且冷二次回路从二次空气回路供给空气。 热交换器的冷回路由通向二次风回路的管道供给。
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7.发明授权Turbomachine with a decoupling device common to first and second bearings of its drive shaft, compressor comprising the decoupling device and decoupling device 有权涡轮机具有与其驱动轴的第一和第二轴承共同的去耦装置，压缩机包括去耦装置和去耦装置公开(公告)号：US07195444B2
公开(公告)日：2007-03-27
申请号：US11281377
申请日：2005-11-18
申请人： Michel Gilbert Roland Brault , Patrick Charles Georges Morel , Zoltan Zsiga , Gael Bouchy , Pierre Bruno Pandelakis
发明人： Michel Gilbert Roland Brault , Patrick Charles Georges Morel , Zoltan Zsiga , Gael Bouchy , Pierre Bruno Pandelakis
IPC分类号： F01D21/00
CPC分类号： F01D21/045 , F01D25/16
摘要： The invention relates to a turbomachine comprising a rotor with a drive shaft centered on the axis of the turbomachine by a first bearing and a second bearing which bearings are supported respectively by a first-bearing-support piece and a second-bearing-support piece which are secured to one another and connected to the turbomachine fixed structure by a decoupling device.This turbomachine comprises means designed to collaborate with at least one element of the turbomachine fixed structure in order to perform a dual function, that of preventing the bearing supports, from rotating and that of radially retaining the drive shaft in the event of the bearings becoming decoupled.
摘要翻译： 涡轮机技术领域本发明涉及一种涡轮机，其特征在于，具有转子，所述转子具有通过第一轴承以所述涡轮机的轴线为中心的驱动轴，所述第二轴承分别由第一轴承支撑件和第二轴承支撑件支承， 彼此固定并通过去耦装置连接到涡轮机固定结构。
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8.发明授权Gas turbine high pressure compressor fluid return and reinjection including an annular air bleeding manifold 有权燃气轮机高压压缩机流体回流和再注入，包括环形排气歧管公开(公告)号：US08959926B2
公开(公告)日：2015-02-24
申请号：US12994782
申请日：2009-05-19
CPC分类号： F02C9/18 , F04D27/0207 , F04D27/0215 , F04D27/023 , F04D27/0238 , F04D29/563 , F05D2270/101
摘要： A turbomachine including an intermediate casing including, fastened to the end thereof, an outer casing of a high pressure compressor, and an air bleed mechanism bleeding air downstream from the stream through the compressor and including an outlet connected to an air reinjection mechanism reinjecting air upstream from the compressor via an annular manifold surrounding the inner wall of the intermediate casing and situated radially between the inner wall and an outer wall defining a secondary flow stream of the turbomachine.
摘要翻译： 一种包括中间壳体的涡轮机，包括紧固在其端部的高压压缩机的外壳，以及排气机构，使来自流体的下游的空气通过压缩机排出，并且包括连接到再注入空气的空气再注入机构的出口 通过围绕中间壳体的内壁的环形歧管从压缩机中径向地位于内壁和限定涡轮机的二次流动流的外壁之间。
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公开(公告)号：US07364402B2
公开(公告)日：2008-04-29
申请号：US11412995
申请日：2006-04-28
CPC分类号： F01D5/027 , F01D5/066 , F05B2260/301 , F05D2230/60 , F05D2260/34
摘要： A turbine module for a gas turbine engine includes at least one turbine disk and a disk-shaped component mounted on the turbine disk upstream relative to the gas flow. The module can be assembled to the compressor of the engine, wherein the component is preassembled to the turbine disk, before the module is assembled to the compressor, by bolting to an attachment flange fixedly attached to the turbine disk.
摘要翻译： 用于燃气涡轮发动机的涡轮模块包括至少一个涡轮盘和相对于气流安装在涡轮盘上游的盘形部件。 模块可以组装到发动机的压缩机，其中在模块组装到压缩机之前，组件被预先组装到涡轮盘，通过螺栓连接到固定地附接到涡轮盘的附接凸缘。
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10.发明申请TURBOJET VENTING PIPE, METHOD FOR MOUNTING ONE SUCH PIPE AND TURBOJET PROVIDED WITH ONE SUCH PIPE 有权涡轮喷油管，安装一个这样的管道和一个这样的管道提供的涡轮的方法公开(公告)号：US20130008550A1
公开(公告)日：2013-01-10
申请号：US13636802
申请日：2011-03-28
CPC分类号： F01D25/18 , F05D2230/64 , F05D2230/642 , F05D2240/61 , F05D2260/30 , F05D2260/602 , F05D2260/6022 , F16L21/08 , F16L37/14 , Y10T29/49826
摘要： A venting pipe used to guide a gas stream in a turbojet including at least one hollow rotary shaft inside which the pipe is mounted, the pipe extending generally along an axis. The pipe includes at least two pipe segments configured to be aligned longitudinally and assembled to one another while retaining a degree of freedom in relative translation thereof, at least one of the segments including a deformable mechanism configured to deform radially as the pipe segments are tightened against one another in the shaft of the turbojet, to bear on the shaft. The pipe structure facilitates mounting of the pipe.
摘要翻译： 用于引导涡轮喷气机中的气流的排气管，其包括至少一个中空旋转轴，管内安装有管，管通常沿轴线延伸。 管道包括至少两个管段，其构造成纵向对齐并且彼此组装，同时保持其相对平移的自由度，所述段中的至少一个包括可变形机构，所述可变形机构构造成随着管段被紧固而径向变形 在涡轮喷气发动机的轴上彼此相依，承担在轴上。 管道结构便于安装管道。
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