公开(公告)号：US06675585B2

公开(公告)日：2004-01-13

申请号：US10161662

申请日：2002-06-05

申请人： Gwénaëlle Calvez ,  Eric Conete ,  Alexandre Forestier ,  Didier Hernandez

发明人： Gwénaëlle Calvez ,  Eric Conete ,  Alexandre Forestier ,  Didier Hernandez

IPC分类号： F02C720

CPC分类号： F23R3/60 ,  F05B2230/606 ,  F23R3/007

摘要： A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, a composite material annular combustion chamber, and an nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a flange-forming metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means firstly to the composite material combustion chamber and secondly to one end of a composite material wall whose other end forms a bearing plane for a sealing element secured to the nozzle and providing sealing for the gas stream between the combustion chamber and the nozzle.

摘要翻译： 涡轮机具有金属材料的内外环形壳体，其在气体流动方向F上包含燃料喷射器组件，复合材料环形燃烧室和形成高压涡轮机的固定刀片入口级的金属材料喷嘴 。 通过多个柔性金属片将燃烧室保持在内外金属环形壳体之间的位置，其多个柔性金属片，其第一端由法兰形成金属环互相连接，该金属环通过第一固定装置 第二固定装置的第二端首先固定到复合材料燃烧室，其次是复合材料壁的一端，复合材料壁的另一端形成用于固定到喷嘴上的密封元件的支承平面，并为气流提供密封 燃烧室和喷嘴。

公开(公告)号：US06823676B2

公开(公告)日：2004-11-30

申请号：US10161805

申请日：2002-06-05

申请人： Eric Conete ,  Alexandre Forestier ,  Didier Hernandez

发明人： Eric Conete ,  Alexandre Forestier ,  Didier Hernandez

IPC分类号： F02C720

CPC分类号： F23R3/60 ,  F05B2230/606

摘要： In a turbomachine comprising a metal material shell containing in a gas flow direction F: a fuel injection assembly; a composite material combustion chamber; and a metal material sectorized nozzle forming the inlet stage with fixed blades of a high pressure turbine, provision is made for the combustion chamber to be held by a sectorized flexible sleeve of metal material having one end fixed to the combustion chamber by first fixing means and a flange-forming opposite end fixed to the shell by second fixing means. The first fixing means also serve to connect the combustion chamber to the sectorized nozzle.

摘要翻译： 在包括在气体流动方向F中包含的金属材料壳的涡轮机中：燃料喷射组件; 复合材料燃烧室; 以及金属材料扇形喷嘴，其形成具有高压涡轮机的固定叶片的入口台，提供燃烧室由金属材料的扇形柔性套筒保持，其一端通过第一固定装置固定到燃烧室， 通过第二固定装置固定在壳体上的法兰形成相对端。 第一固定装置还用于将燃烧室连接到扇形喷嘴。

公开(公告)号：US06732532B2

公开(公告)日：2004-05-11

申请号：US10162189

申请日：2002-06-05

申请人： Pierre Camy ,  Benoît Carrere ,  Eric Conete ,  Alexandre Forestier ,  Georges Habarou ,  Didier Hernandez

发明人： Pierre Camy ,  Benoît Carrere ,  Eric Conete ,  Alexandre Forestier ,  Georges Habarou ,  Didier Hernandez

IPC分类号： F02C720

CPC分类号： F23R3/60 ,  F05B2230/606 ,  F23R3/007

摘要： In a turbomachine comprising an annular shell of metal material containing in a gas flow direction F: a fuel injection assembly; an annular combustion chamber of composite material; and an annular nozzle of metal material forming the inlet stage with fixed blades of a high pressure turbine, provision is made for the combustion chamber to be held in position inside the annular metal shell by a plurality of flexible metal tongues each comprising three branches connected together in a star configuration, the ends of two of these three branches being fixed securely to a downstream end of the combustion chamber via respective first and second fixing means, and the end of the third branch being fixed securely to the annular shell via third fixing means.

摘要翻译： 在包括金属材料的环形壳体的涡轮机中，其包含气体流动方向F：燃料喷射组件; 复合材料的环形燃烧室; 以及形成具有高压涡轮机的固定叶片的入口台的金属材料的环形喷嘴，使燃烧室通过多个柔性金属舌保持在环形金属壳内的适当位置，每个柔性金属舌片包括连接在一起的三个分支 在星形结构中，这三个分支中的两个的端部经由相应的第一和第二固定装置牢固地固定到燃烧室的下游端，并且第三分支的端部经由第三固定装置牢固地固定到环形壳体 。

公开(公告)号：US06708495B2

公开(公告)日：2004-03-23

申请号：US10162385

申请日：2002-06-05

申请人： Gwénaëlle Calvez ,  Eric Conete ,  Alexandre Forestier ,  Didier Hernandez

发明人： Gwénaëlle Calvez ,  Eric Conete ,  Alexandre Forestier ,  Didier Hernandez

IPC分类号： F02C720

CPC分类号： F23R3/60 ,  F05B2230/606 ,  F23R3/007

摘要： A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, an annular combustion chamber of composite material, and an annular nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means on a ring of composite material fixed securely to said composite material combustion chamber, the flexibility of said metal fixing tongues allowing expansion to take place freely in a radial direction at high temperatures between said composite material combustion chamber and said metal annular shells.

摘要翻译： 涡轮机具有金属材料的内外环形壳体，其在气体流动方向F上包含燃料喷射器组件，复合材料的环形燃烧室和金属材料的环形喷嘴，其形成高度的固定刀片入口级 压力涡轮机。 通过多个柔性金属片将燃烧室保持在内外金属环形外壳之间的位置，其多个柔性金属片具有通过第一固定装置将金属环互相牢固固定在每个环形壳上的第一端， 端部通过第二固定装置固定在牢固地固定到所述复合材料燃烧室的复合材料环上，所述金属固定舌的柔性允许膨胀在所述复合材料燃烧室和所述金属之间的高温下在径向方向上自由发生 环形壳。

公开(公告)号：US06679062B2

公开(公告)日：2004-01-20

申请号：US10162384

申请日：2002-06-05

申请人： Eric Conete ,  Alexandre Forestier ,  Didier Hernandez

发明人： Eric Conete ,  Alexandre Forestier ,  Didier Hernandez

IPC分类号： F02C720

CPC分类号： F23R3/007 ,  F23M2900/05002 ,  F23R3/50 ,  F23R3/60

摘要： A turbomachine comprises an annular shell of metal material containing in a gas flow direction F a fuel injection assembly, an annular combustion chamber of composite material, and an annular nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine, said nozzle being supported by the annular shell and being fixed thereto by first releasable fixing means, and provision being made for the combustion chamber to be mounted in floating manner inside the annular shell and held in position solely by the nozzle to which it is fixed in resilient manner by second releasable fixing means.

摘要翻译： 涡轮机包括金属材料的环形壳体，其包含气体流动方向F，燃料喷射组件，复合材料的环形燃烧室和形成高压涡轮机的固定叶片入口级的金属材料的环形喷嘴，所述 喷嘴由环形壳体支撑并且通过第一可释放固定装置固定在其上，并且为燃烧室设置为以浮动方式安装在环形壳体内并且仅通过被固定在其上的喷嘴保持就位 方式是通过第二可释放固定装置。

公开(公告)号：US06668559B2

公开(公告)日：2003-12-30

申请号：US10161782

申请日：2002-06-05

申请人： Gwénaëlle Calvez ,  Didier Hernandez ,  Alexandre Forestier

发明人： Gwénaëlle Calvez ,  Didier Hernandez ,  Alexandre Forestier

IPC分类号： F02C720

CPC分类号： F23R3/06 ,  F05B2230/606 ,  F23R3/007 ,  F23R3/60 ,  Y02T50/675

摘要： In a turbomachine comprising inner and outer annular shells of metal material containing, in a gas flow direction F: a fuel injection assembly; an annular combustion chamber of composite material having a plurality of air feed orifices in a primary zone and/or in a dilution zone; and an annular nozzle of metal material forming the inlet stage with fixed blades for a high pressure turbine, provision is made for the combustion chamber to be held in position between the inner and outer annular metal shells by means of a plurality of flexible metal tongues having first ends interconnected by respective metal rings fixed securely to said inner and outer annular shells by first fixing means, and second ends fixed securely to the composite material combustion chamber at it air feed orifices by second fixing means.

公开(公告)号：US06647729B2

公开(公告)日：2003-11-18

申请号：US10161653

申请日：2002-06-05

申请人： Gwénaëlle Calvez ,  Alexandre Forestier ,  Didier Hernandez

发明人： Gwénaëlle Calvez ,  Alexandre Forestier ,  Didier Hernandez

IPC分类号： F23R360

CPC分类号： F23R3/60 ,  F23D2211/00 ,  F23R3/007

摘要： In an annular combustion chamber having inner and outer axially-extending side walls of composite material and an end wall of metal material, provision is made to hold the end wall in position between the side walls of the annular combustion chamber by means of a plurality of flexible metal tongues fixed firstly to said side walls by fixing means and secondly to said end wall by brazing or welding, said end wall further comprising means for providing sealing between said end wall and said side walls.

公开(公告)号：US20060032237A1

公开(公告)日：2006-02-16

申请号：US11153356

申请日：2005-06-16

申请人： Caroline Aumont ,  Eric Conete ,  Mario De Sousa ,  Didier Hernandez

发明人： Caroline Aumont ,  Eric Conete ,  Mario De Sousa ,  Didier Hernandez

IPC分类号： F23R3/42

CPC分类号： F01D25/246 ,  F01D9/023 ,  F01D9/041 ,  F05D2230/642 ,  F23R3/007 ,  F23R3/60 ,  Y02T50/672 ,  Y02T50/675

摘要： The high pressure turbine nozzle is mechanically connected to a downstream end portion of the combustion chamber and inner and outer connection ferrules connect the combustion chamber and turbine nozzle assembly to inner and outer metal shrouds in order to hold said assembly between the shrouds. Locking members are provided to prevent the turbine nozzle from turning about its axis relative to at least one of the metal shrouds so as to prevent the forces that are exerted on the turbine nozzle vanes by the flow of gas coming from the chamber being taken up by the portions of the connection ferrules that extend between the combustion chamber and turbine nozzle assembly and the metal shrouds.

摘要翻译： 高压涡轮喷嘴机械地连接到燃烧室的下游端部分，并且内部和外部连接套管将燃烧室和涡轮喷嘴组件连接到内部和外部金属罩，以将所述组件保持在护罩之间。 提供锁定构件以防止涡轮喷嘴相对于金属罩中的至少一个绕其轴线转动，以便防止通过来自腔室的气体的流动被来自腔室的气体吸收的作用在涡轮喷嘴叶片上的力被 连接套管的在燃烧室和涡轮喷嘴组件之间延伸的部分和金属罩。

公开(公告)号：US20060032236A1

公开(公告)日：2006-02-16

申请号：US11153354

申请日：2005-06-16

申请人： Caroline Aumont ,  Eric Conete ,  Mario De Sousa ,  Didier Hernandez

发明人： Caroline Aumont ,  Eric Conete ,  Mario De Sousa ,  Didier Hernandez

IPC分类号： F23R3/42

CPC分类号： F01D9/042 ,  F01D9/023 ,  Y02T50/672 ,  Y02T50/675

摘要： The downstream end portions of the inner and outer walls of the combustion chamber of the gas turbine are pressed against the inner and outer platforms respectively of the vanes of the high pressure turbine nozzle and they extend thereover substantially to the downstream end of the platforms, and the means for mechanically connecting the turbine nozzle to the downstream end portions of the combustion chamber walls are formed by connection screws implanted in the airfoils of the vanes of the turbine nozzle, passing through holes formed in the end portions of the combustion chamber walls. Thus, the downstream end portions of the combustion chamber walls contribute to preventing leakage from the gas stream at the interface between the chamber and the nozzle, and also along the nozzle.

摘要翻译： 燃气轮机的燃烧室的内壁和外壁的下游端部分别压靠在高压涡轮喷嘴的叶片的内平台和外平台上，并且它们基本延伸到平台的下游端，并且 用于将涡轮喷嘴机械地连接到燃烧室壁的下游端部的装置通过注入在涡轮喷嘴的叶片的翼型中的连接螺钉形成，通过形成在燃烧室壁的端部中的孔。 因此，燃烧室壁的下游端部有助于防止在腔室和喷嘴之间的界面处以及沿着喷嘴的气流的泄漏。

公开(公告)号：US20060032235A1

公开(公告)日：2006-02-16

申请号：US11153353

申请日：2005-06-16

申请人： Caroline Aumont ,  Eric Conete ,  Mario De Sousa ,  Didier Hernandez

发明人： Caroline Aumont ,  Eric Conete ,  Mario De Sousa ,  Didier Hernandez

IPC分类号： F23R3/42

CPC分类号： F23R3/60 ,  F05C2203/08 ,  F23R3/007

摘要： The annular combustion chamber having ceramic matrix composite material walls is mounted inside a metal casing by linking members fastened to the chamber by brazing. The linking members comprise a plurality of inner linking tabs and a plurality of outer linking tabs connecting the chamber to the inner and outer metal shrouds of the casing, each linking tab has a first portion fastened to the outside surface of a wall of the combustion chamber by brazing, the first portions of the linking tabs being spaced apart from one another circumferentially so that the brazed connections between the chamber and the linking members occupy a set of limited zones that are spaced apart from one another.

摘要翻译： 具有陶瓷基复合材料壁的环形燃烧室通过钎焊连接构件固定在金属外壳内。 连接构件包括多个内连接突片和将腔室连接到壳体的内外金属罩的多个外连接突片，每个连接突片具有固定到燃烧室壁的外表面的第一部分 通过钎焊，连接凸片的第一部分周向地间隔开，使得腔室和连接构件之间的钎焊连接占据彼此间隔开的一组限制区域。