公开(公告)号：US20100126183A1

公开(公告)日：2010-05-27

申请号：US12594874

申请日：2008-04-08

申请人： Eric Conete ,  Benoît Carrere ,  Laurent Baroumes

发明人： Eric Conete ,  Benoît Carrere ,  Laurent Baroumes

IPC分类号： F02C7/20 ,  F01B25/00

CPC分类号： F02K1/386 ,  F02K1/48 ,  F05D2300/21 ,  F05D2300/2261 ,  F05D2300/501 ,  F05D2300/603 ,  Y02T50/672

摘要： The invention relates to a mixer (100) for a separate-stream nozzle of a turbojet, the mixer being designed to mix a hot inner stream from the combustion chamber of the turbojet with a cold outer stream from the fan of the turbojet. The mixer comprises an inner shroud (120) defining a flow channel for said hot inner stream, an outer shroud (110) disposed around the inner shroud (120) and co-operating therewith to define a flow channel for said cold outer stream, and a lobed structure (130) having lobes (1321, 1322) extending longitudinally from the trailing edges (110a, 120a) of said shrouds. The lobed structure (130) is made of a ceramic matrix composite material and is attached to the outer shroud (110) by flexible fastener tabs (140).

摘要翻译： 本发明涉及一种用于涡轮喷气发动机的分流喷嘴的混合器（100），该混合器设计成将来自涡轮喷气发动机的燃烧室的热内流与来自涡轮喷气发动机的风扇的冷外流混合。 混合器包括限定用于所述热内流的流动通道的内护罩（120），围绕内护罩（120）设置并与之配合的外护罩（110），以与所述内护罩配合以限定所述冷外流的流动通道，以及 具有从所述护罩的后缘（110a，120a）纵向延伸的裂片（1321,1322）的裂片结构（130）。 叶状结构（130）由陶瓷基质复合材料制成，并通过柔性紧固片（140）附接到外护罩（110）。

公开(公告)号：US06398483B1

公开(公告)日：2002-06-04

申请号：US09589806

申请日：2000-06-09

申请人： Eric Conete ,  François Marie Paul Marlin

发明人： Eric Conete ,  François Marie Paul Marlin

IPC分类号： F01D2100

CPC分类号： F01D17/162

摘要： A protection device for protecting a control mechanism of inlet guide-vanes of a turbojet engine includes a narrowed section on a connecting rod. The connecting rod is for transmitting the movement of a spindle of a piston of the control mechanism or actuator to a control ring that directs all of the inlet guide-vanes. The narrowed section of the connecting rod is a frangible part.

摘要翻译： 用于保护涡轮喷气发动机的入口导向叶片的控制机构的保护装置包括在连接杆上的狭窄部分。 连杆用于将控制机构或致动器的活塞的主轴的运动传递到引导所有入口导向叶片的控制环。 连杆的狭窄部分是一个易碎部分。

公开(公告)号：US08919136B2

公开(公告)日：2014-12-30

申请号：US13062617

申请日：2009-09-08

申请人： Eric Conete

发明人： Eric Conete

IPC分类号： F02K1/04 ,  F02K1/80

CPC分类号： F02K1/80 ,  F02K1/04 ,  F05D2230/642

摘要： An after-body assembly for an aeroengine, the assembly comprising an annular part (60) made of metallic material secured to the aeroengine and an after-body part (20) made of ceramic matrix composite material, the after-body part (20) being mounted on the annular part (60) by resiliently flexible fastener tabs (70) and having a first end (71) fastened to the annular part (60) and a second end (72) fastened to the upstream portion of the after-body part (20). Each fastener tab (70) includes an axial abutment element (720) that extends radially from the second end (72) of the tab and having at least a portion thereof facing the first end (71). The fastener tab (70) also includes a radial abutment element (721) at the second end (72) of the tab, the radial abutment element (721) at least partially overlying the first end (71).

摘要翻译： 一种用于航空发动机的后体组件，所述组件包括由固定到所述航空发动机的金属材料制成的环形部分（60）和由陶瓷基体复合材料制成的后体部分（20），所述后体部分（20） 通过弹性柔性的紧固件突片（70）安装在环形部分（60）上，并且具有紧固到环形部分（60）的第一端（71）和紧固到后身体的上游部分的第二端（72） 第（20）部分。 每个紧固件突片（70）包括从突片的第二端（72）径向延伸并且其至少一部分面向第一端（71）的轴向邻接元件（720）。 紧固件突片（70）还包括在突片的第二端（72）处的径向邻接元件（721），径向抵靠元件（721）至少部分地覆盖在第一端（71）上。

公开(公告)号：US20080115484A1

公开(公告)日：2008-05-22

申请号：US11664043

申请日：2005-09-28

申请人： Eric Conete ,  Eric Philippe ,  Laurent Baroumes

发明人： Eric Conete ,  Eric Philippe ,  Laurent Baroumes

IPC分类号： F02K1/48 ,  F02K1/38

CPC分类号： F02K1/80 ,  F02K1/48 ,  F05D2230/642 ,  F05D2260/30 ,  Y02T50/672

摘要： A mixer for a separate-stream turbojet nozzle, the mixer comprising along a longitudinal axis (X-X′) both a fastener shroud (10) for connecting said mixer to the exhaust casing of the nozzle, and a lobe structure (20) presenting a succession of inner and outer lobes (22 and 21) distributed circumferentially around the longitudinal axis (X-X′) of the mixer. The lobe structure (20) is made of a ceramic matrix composite material and further comprises a stiffener ring (30) that forms a connection between at least some of the lobes of said structure. Thus, the major portion of the mixer, i.e. the lobe structure, is made of a ceramic matrix composite material, thereby significantly reducing the weight of the mixer, and consequently reducing the weight of the nozzle.

摘要翻译： 一种用于独立涡轮喷气喷嘴的混合器，所述混合器包括沿着纵向轴线（X-X'），包括用于将所述混合器连接到喷嘴的排气壳体的紧固件护罩（10）和提供 沿着混合器的纵向轴线（X-X'）周向分布的一系列内和外波瓣（22和21）。 凸角结构（20）由陶瓷基复合材料制成，并且还包括在所述结构的至少一些凸角之间形成连接的加强环（30）。 因此，混合器的主要部分（即凸角结构）由陶瓷基复合材料制成，从而显着地降低了混合器的重量，从而减小了喷嘴的重量。

公开(公告)号：US20060010879A1

公开(公告)日：2006-01-19

申请号：US11153349

申请日：2005-06-16

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

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

IPC分类号： F23R3/42

CPC分类号： F01D9/044 ,  F01D9/023 ,  F05D2300/6033 ,  F23R3/60 ,  Y02T50/672 ,  Y02T50/675

摘要： The gas turbine comprises an annular combustion chamber having inner and outer walls made of ceramic matrix composite material, and a high pressure turbine nozzle secured to a downstream end of the combustion chamber and comprising a plurality of stationary airfoils extending between the inner and outer walls of an annular flow path through the nozzle for the gas stream coming from the combustion chamber. The turbine nozzle is made of ceramic matrix composite material and it is connected to the downstream end of the combustion chamber by brazing.

摘要翻译： 燃气轮机包括环形燃烧室，其具有由陶瓷基复合材料制成的内壁和外壁，以及固定到燃烧室下游端的高压涡轮喷嘴，并且包括多个固定翼型件，其在内壁和外壁之间延伸 通过喷嘴的环形流路，用于来自燃烧室的气流。 涡轮喷嘴由陶瓷基复合材料制成，并通过钎焊连接到燃烧室的下游端。

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：US5367874A

公开(公告)日：1994-11-29

申请号：US162879

申请日：1993-12-08

申请人： Didier L. C. Auffret ,  Gerard C. L. Berger ,  Eric Conete ,  Frederic Delage ,  Gerard E. A. Jourdain ,  Christophe J. F. Thorel

发明人： Didier L. C. Auffret ,  Gerard C. L. Berger ,  Eric Conete ,  Frederic Delage ,  Gerard E. A. Jourdain ,  Christophe J. F. Thorel

IPC分类号： F23R3/20 ,  F02K3/10

CPC分类号： F23R3/20

摘要： An integral, one-piece afterburner structure for a turbojet engine is disclosed which is formed of composite material. The afterburner structure has an outer casing formed as a body of revolution about a central axis, an inner casing also formed as a body of revolution about the central axis, which casings are integrally joined by a plurality of connecting arms extending between the inner and outer casing. The connecting arms are also formed of a composite material and are integrally molded with both the inner and outer casings. The afterburner structure also has a plurality of secondary support arms formed of composite material which extend either from the outer, or the inner casing in a generally radial direction relative to the central axis. Integrally formed with the plurality of secondary support arms is at least one annular flameholder ring which extends around the central axis and is supported by the secondary support arms.

摘要翻译： 公开了一种由复合材料形成的用于涡轮喷气发动机的整体式一体式加力结构。 所述加力结构具有外围壳体，所述外壳围绕中心轴线形成为旋转体，内壳体还围绕所述中心轴线形成为旋转体，所述壳体通过在所述内部和外部之间延伸的多个连接臂一体地连接 套管。 连接臂也由复合材料形成，并与内壳和外壳整体模制。 再加力结构还具有由复合材料形成的多个辅助支撑臂，其从外壳或内壳沿相对于中心轴线的大致径向方向延伸。 与多个第二支撑臂一体地形成有至少一个围绕中心轴线延伸并由第二支撑臂支撑的环形火焰支架环。

公开(公告)号：US20070039327A1

公开(公告)日：2007-02-22

申请号：US11024732

申请日：2004-12-30

申请人： Stephane Blanchard ,  Stephane Touchaud ,  Thierry Pancou ,  Eric Conete ,  Pierre Camy ,  Georges Habarou

发明人： Stephane Blanchard ,  Stephane Touchaud ,  Thierry Pancou ,  Eric Conete ,  Pierre Camy ,  Georges Habarou

IPC分类号： F02K3/10

CPC分类号： F02K3/10 ,  F23R3/18

摘要： A support arm (13) is intended to be installed in a radial position in an afterburner device of a bypass turbojet. The device comprises first and second inner annular casings defining a passage for a primary flow and an outer annular casing defining together with the first inner annular casing a passage for a secondary flow. The arm (13) comprises a monobloc structure made of composite material including two integral walls (14, 15), on the one hand, designed to define a groove (16) having a substantially V-shaped profile and, on the other hand, including first end parts (17) joined together and adapted to define a foot (18) and second end parts (19) adapted each to define at least one flange (20, 21) intended to be positively connected to the outer annular casing.

摘要翻译： 支撑臂（13）旨在安装在旁路涡轮喷气发动机的后燃器装置中的径向位置。 该装置包括限定用于主流的通道的第一和第二内部环形壳体以及与第一内部环形壳体一起限定用于二次流动的通道的外部环形壳体。 臂（13）包括由复合材料制成的整体结构，其包括两个整体壁（14,15），一方面设计成限定具有大致V形轮廓的凹槽（16），另一方面， 包括连接在一起并适于限定足部（18）的第一端部部分（17）和适于各自限定至少一个凸缘（20,21）的第二端部（19），所述至少一个凸缘（20,21）被确定地连接到所述外部环形壳体。

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。