-
1.发明授权Mounting for a CMC combustion chamber of a turbomachine by means of flexible connecting sleeves 有权通过柔性连接套筒安装涡轮机的CMC燃烧室公开(公告)号：US06823676B2
公开(公告)日：2004-11-30
申请号：US10161805
申请日：2002-06-05
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。
-
2.发明授权Resilient mount for a CMC combustion chamber of a turbomachine in a metal casing 有权用于金属外壳中涡轮机的CMC燃烧室的弹性支架公开(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：US06675585B2
公开(公告)日：2004-01-13
申请号：US10161662
申请日：2002-06-05
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。
-
4.发明授权公开(公告)号：US06708495B2
公开(公告)日：2004-03-23
申请号：US10162385
申请日：2002-06-05
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
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
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
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.
-
8.发明授权Multiple flow turbojet engine with an outer ring of the fan outlet shrunk onto the case 失效具有风扇出口外圈的多流量涡轮喷气发动机收缩到壳体上
公开(公告)号：US4940386A
公开(公告)日：1990-07-10
申请号：US152337
申请日：1988-02-04
CPC分类号： F01D9/04 , F01D9/041 , F01D9/042 , F04D29/542 , Y02T50/672
摘要： The cartridge of a fan outlet for a multiple flow turbojet engine is made of composite material and includes two thick lateral strips (8a, 8b) positioned in the interior of the outer case and a narrow central band pierced with slots (10) in which guide vanes (5), provided with an in-molded cover, come to be fixed. The outer cartridge can be integral with the support of soundproofing panels (7 and 9) and support the abradable part (6) facing fan (3).
摘要翻译： 用于多流量涡轮喷气发动机的风扇出口的盒由复合材料制成，并且包括位于外壳内部的两个厚的侧向条（8a，8b）和穿过狭槽（10）的窄的中心带，导向件 设置有模制外壳的叶片（5）固定。 外筒可与隔音板（7和9）的支撑件成一体，并支撑面向风扇（3）的可磨损部分（6）。
-
公开(公告)号：US4494909A
公开(公告)日：1985-01-22
申请号：US446625
申请日：1982-12-03
申请人： Alexandre Forestier
发明人： Alexandre Forestier
CPC分类号： F01D5/22 , F01D11/008 , Y10S416/50
摘要： A damping device for the turbojet engine fan blades which includes a wedge placed between the platforms of the blades, the shanks of the blades, and the disc. The wedge consists of a hollow, bellows-shaped body fitted with an axial stop member, the body being inflated after mounting so that it takes up all the space between the platforms of the blades, the blade shanks and the teeth of the disc. The invention is used for damping device of turbojet engine blades.
摘要翻译： 一种用于涡轮喷气发动机风扇叶片的阻尼装置，其包括设置在叶片的平台，叶片的柄部和盘之间的楔子。 楔形件由装有轴向止动构件的中空的波纹管体组成，主体在安装之后被充气，从而占据叶片平台，叶片柄和盘齿之间的所有空间。 本发明用于涡轮喷气发动机叶片的阻尼装置。
-
10.发明授权Apparatus for attaching a pre-atomization bowl to a gas turbine engine combustion chamber 失效用于将预成型管连接到气体涡轮发动机燃烧室的装置
公开(公告)号：US5172545A
公开(公告)日：1992-12-22
申请号：US710112
申请日：1991-06-04
申请人： Alexandre Forestier
发明人： Alexandre Forestier
摘要： An apparatus is disclosed for temporarily attaching a pre-atomization bowl to a wall of a generally annular combustion chamber during assembly of the combustion chamber with the fuel injector assembly. The attachment apparatus holds each of the pre-atomization bowls in a position so as to minimize the stress imparted to the fuel injectors during assembly of the engine components. The apparatus utilizes a magnetic attachment device to hold the pre-atomization bowls in their assembly positions. The force of the magnetic attachment device is sufficient to hold the pre-atomization bowls in these positions against the effect of gravity, but is insufficient to prevent the radial movement of the pre-atomization bowls relative to the combustion chamber once the turbojet engine has been assembled. Thus, the device does not inhibit the radial play of the pre-atomization bowls once the engine has been asssembled.
摘要翻译： 公开了一种用于在将燃烧室与燃料喷射器组件组装期间临时将预雾化碗附接到大致环形的燃烧室的壁上的装置。 附接装置将每个预雾化碗保持在一个位置，以便最小化在发动机部件组装过程中赋予燃料喷射器的应力。 该装置利用磁性附着装置将预雾化碗保持在其组装位置。 磁性附着装置的力足以在不影响重力的情况下将预雾化碗保持在这些位置，但是一旦涡轮喷气发动机已经被使用，不足以防止预雾化碗相对于燃烧室的径向移动 组装 因此，一旦发动机被组装，该装置不会抑制预雾化碗的径向游隙。
-
-
-
-
-
-
-
-
-
搜索结果
22 条记录 (耗时 0.019 秒)
