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公开(公告)号：US20120073259A1
公开(公告)日：2012-03-29
申请号：US13259941
申请日：2010-03-12
IPC分类号： F23R3/50
CPC分类号： F23R3/60 , F01D9/023 , F01D25/243 , F23R3/50 , Y02T50/671
摘要： A turbomachine including an annular combustion chamber, the combustion chamber presenting a connection flange at its downstream end for connection to an outer casing. The connection flange bears axially against the outer casing and is blocked in an axial direction by the upstream end of an inner casing of a high pressure turbine.
摘要翻译： 一种包括环形燃烧室的涡轮机，所述燃烧室在其下游端具有连接凸缘以连接到外壳。 连接法兰轴向抵靠外壳，并通过高压汽轮机内壳的上游端沿轴向阻塞。
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公开(公告)号：US20110113789A1
公开(公告)日：2011-05-19
申请号：US12997266
申请日：2009-06-10
CPC分类号： F23R3/283
摘要： A gas turbine engine combustion chamber including at least one deflector mounted on the chamber end wall and including an opening for a carburetted air supply device. The deflector includes an opening, corresponding to the chamber end wall opening, with an annular cylindrical part for attachment to the wall, the cylindrical part including a mechanical attachment mechanism collaborating with a complementary attachment mechanism on a metal sleeve secured to the wall and a cylindrical centering cup fixed by one end to the sleeve and housed inside the cylindrical part of the deflector.
摘要翻译： 一种燃气涡轮发动机燃烧室，包括安装在室端壁上的至少一个偏转器，并且包括用于碳化空气供应装置的开口。 偏转器包括对应于室端壁开口的开口，具有用于附接到壁的环形圆柱形部分，圆柱形部分包括与固定到壁上的金属套筒上的互补附接机构协作的机械附接机构，以及圆柱形 定心杯由一端固定到套筒上并容纳在偏转器的圆柱形部分内。
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公开(公告)号：US07614234B2
公开(公告)日：2009-11-10
申请号：US12199116
申请日：2008-08-27
IPC分类号： F02C3/00
摘要： The invention relates to a turbomachine combustion chamber having an inner wall, an outer wall surrounding the inner wall so as to co-operate therewith to define a space forming a combustion area, a transverse wall interconnecting the inner and outer walls, and fuel injection systems. The inner wall has a plurality of inner steps each extending radially towards the outside of the inner wall, the circumferential spacing between two adjacent inner steps defining an inner cavity. The outer wall includes a plurality of outer steps each extending radially towards the inside of the outer wall, the circumferential spacing between two adjacent inner steps defining an outer cavity. At least some of the inner and outer cavities are fed with air from outside the combustion chamber in a common direction that is circumferential, and with fuel in a direction that is radial.
摘要翻译： 本发明涉及一种涡轮机燃烧室，其具有内壁，围绕内壁的外壁，以便与其配合以限定形成燃烧区域的空间，互连内壁和外壁的横向壁和燃料喷射系统 。 内壁具有多个内部台阶，每个内部台阶径向朝向内壁的外侧延伸，两个相邻的内部台阶之间的圆周间隔限定了内部空腔。 外壁包括多个外径，每个外径向径向朝向外壁的内侧延伸，两个相邻的内台阶之间的圆周间隔限定一外腔。 至少一些内腔和外腔在燃烧室的外侧沿着周向的共同方向和在径向方向上的燃料供给空气。
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公开(公告)号：US20080141678A1
公开(公告)日：2008-06-19
申请号：US11780225
申请日：2007-07-19
申请人： Antoine Robert Alain BRUNET , Jean-Christophe Leininger , David Locatelli , Romain Nicolas Lunel
发明人： Antoine Robert Alain BRUNET , Jean-Christophe Leininger , David Locatelli , Romain Nicolas Lunel
CPC分类号： F01D25/12 , F01D5/046 , F01D5/081 , F04D29/284 , F04D29/584 , F05D2260/20 , Y02T50/671 , Y02T50/676
摘要： A system for cooling the impeller of a centrifugal compressor in a turbomachine, this compressor (10) supplying an annular diffuser (12) comprising an end-piece (26) that extends downstream and along the impeller of the compressor and that is covered on the upstream side by an annular metal sheet (90) that delimits, with the impeller of the compressor, a first annular passageway (39) to carry away the air taken from the outlet of the compressor and, with the end-piece of the diffuser, a second annular passageway (98) to carry away a portion of the air flow coming out of the diffuser.
摘要翻译： 一种用于冷却涡轮机中的离心式压缩机的叶轮的系统，该压缩机（10）供应环形扩散器（12），该环形扩散器（12）包括沿着压缩机的下游和沿着叶轮延伸的端部件（26） 上游侧通过环形金属板（90），其与压缩机的叶轮限定第一环形通道（39），以便携带从压缩机的出口获取的空气，并且与扩散器的端件一起， 第二环形通道（98），用于携带从扩散器出来的一部分空气流。
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25.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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公开(公告)号：US08516830B2
公开(公告)日：2013-08-27
申请号：US12544423
申请日：2009-08-20
CPC分类号： F23R3/283
摘要： A turbomachine combustion chamber including a substantially L-shaped fuel injector and a device for mounting and fastening the injector in an orifice of the casing of the chamber, is disclosed. The device includes an outer collar carried by the injector and a removable annular spacer surrounding the injector and designed to be interposed between the collar of the injector and the casing.
摘要翻译： 公开了一种涡轮机燃烧室，其包括基本上L形的燃料喷射器和用于将喷射器安装并紧固在腔室壳体的孔中的装置。 该装置包括由注射器承载的外部轴环和围绕注射器的可移除的环形间隔件，并被设计成插入在注射器的套环和套管之间。
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27.发明申请FUEL MIXING DEVICE FOR TURBINE ENGINE COMBUSTION CHAMBER COMPRISING IMPROVED AIR FEED MEANS 有权用于涡轮发动机燃烧室的燃料混合装置，包括改进的空气进料装置公开(公告)号：US20120204567A1
公开(公告)日：2012-08-16
申请号：US13503737
申请日：2010-11-03
CPC分类号： F23R3/14 , F23R3/286 , Y02T50/675
摘要： A fuel mixing device for an annular combustion chamber of a turbine engine, including a member for centering a turbine engine injector head, at least one air intake ring including blades allowing swirling of air, a bowl including an annular row of air intake orifices, an annular cavity communicating with the air intake orifices, and channels arranged through the blades to feed air to the annular cavity.
摘要翻译： 一种用于涡轮发动机的环形燃烧室的燃料混合装置，包括用于使涡轮发动机喷射器头定心的构件，包括允许空气旋转的叶片的至少一个进气环，包括空气吸入孔的环形排的碗， 与进气口连通的环形空腔，以及通过叶片布置的通道，以将空气送入环形空腔。
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公开(公告)号：US08142148B2
公开(公告)日：2012-03-27
申请号：US12361878
申请日：2009-01-29
IPC分类号： F01D1/02
CPC分类号： F04D29/444 , F01D11/005 , F04D29/083 , F04D29/441 , F05D2230/642 , F05D2240/12 , F05D2250/52 , Y02T50/67
摘要： A diffuser-nozzle assembly mounted at the outlet from a centrifugal compressor is disclosed. The assembly includes a plurality of vanes carried by a radially inner wall forming a surface of revolution and surrounded by an outer casing, elastically deformable devices interposed between the radially outer ends of the vanes of the nozzle and the outer casing. The elastically deformable devices prevent air from passing between the outer casing and the radially outer ends of the vanes.
摘要翻译： 公开了一种安装在离心式压缩机出口处的扩散器 - 喷嘴组件。 组件包括多个叶片，其由形成旋转表面的径向内壁承载并被外壳包围，插入在喷嘴的叶片的径向外端和外壳之间的可弹性变形的装置。 可弹性变形的装置防止空气在外壳和叶片的径向外端之间通过。
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29.发明申请公开(公告)号：US20120055164A1
公开(公告)日：2012-03-08
申请号：US13255772
申请日：2010-03-15
CPC分类号： F23R3/10
摘要： Annular combustion chamber (10) to be fitted on a turbomachine and comprising a chamber end wall (22), a plurality of air and fuel injection systems (32) circumferentially distributed around an axis (34) of the combustion chamber (10) and mounted on said chamber end wall (22), and, an air manifold (100) associated with each injection system (32), comprising at least one wall (96, 98) mounted on the chamber end wall (22) and projecting in the upstream direction to form an obstacle to a circumferential airflow around the axis (34) of the combustion chamber (10), and an air inlet opening (88) formed at the upstream end of the air manifold (100) and opening radially outwards from an axis (44) of said injection system.
摘要翻译： 安装在涡轮机上的环形燃烧室（10），包括腔室端壁（22），围绕燃烧室（10）的轴线（34）周向分布的多个空气和燃料喷射系统（32），并安装 在所述腔室端壁（22）上，以及与每个注射系统（32）相关联的空气歧管（100）包括安装在腔室端壁（22）上并在上游侧突出的至少一个壁（96,98） 形成围绕燃烧室（10）的轴线（34）的圆周气流的障碍物，以及形成在空气歧管（100）的上游端并从轴线径向向外开口的空气入口（88） （44）。
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公开(公告)号：US20110097204A1
公开(公告)日：2011-04-28
申请号：US12993949
申请日：2009-05-20
IPC分类号： F04D29/44
CPC分类号： F02C3/08 , F01D9/045 , F01D25/246 , F04D29/023 , F04D29/444 , F05D2230/90 , F05D2250/52 , Y02T50/67 , Y02T50/671
摘要： A turbomachine including an annular combustion chamber; a centrifugal compressor; an annular diffuser with a radially oriented upstream portion presenting diffusion passages connected to the outlet of the compressor; a curved intermediate portion; and a downstream portion having a series of circularly spaced-apart deflector vanes. The turbomachine also includes an outer casing externally surrounding the combustion chamber and the downstream portion. The zone of the outer casing that is situated facing the deflector vanes is covered in a coating of abradable material, and the flow passage through the downstream portion is defined on the outside by the outer casing and by the coating.
摘要翻译： 包括环形燃烧室的涡轮机; 离心式压缩机; 具有径向定向的上游部分的环形扩散器，其具有连接到压缩机出口的扩散通道; 弯曲的中间部分; 以及具有一系列圆形间隔开的偏转叶片的下游部分。 涡轮机还包括外部围绕燃烧室和下游部分的外壳。 外壳的面向偏转器叶片的区域被可磨损材料的涂层覆盖，并且通过下游部分的流动通道由外壳和涂层限定在外部。
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