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41. 发明申请

US20120308391A1 LAYOUT OF A BLISK 有权
标题翻译：布置布局
公开(公告)号：US20120308391A1
公开(公告)日：2012-12-06
申请号：US13520433
申请日：2011-01-11
申请人： Fabrice Marcel Noel Garin , Romain Nicolas Lunel , Bruno Andre Jean Varin , Clement Roussille
发明人： Fabrice Marcel Noel Garin , Romain Nicolas Lunel , Bruno Andre Jean Varin , Clement Roussille
IPC分类号： F04D29/34
CPC分类号： F01D5/3084 , F01D5/3092 , F05D2230/60 , F05D2250/71 , F05D2260/30
摘要： A layout of a blisk includes two inserts housed between the bulb of the blade and the wall of a groove in a disk to compensate for variations in inclination between the overhanging faces of the groove and the upper faces of the bulb at their central part. This construction makes it possible to select blades for which upper faces of the bulb are slightly inclined relative to the radial direction, which facilitates their construction from a composite material.
摘要翻译：叶片的布局包括容纳在叶片的灯泡和盘之间的槽的壁之间的两个插入件，以补偿槽的悬垂面和灯泡的中心部分的上表面之间的倾斜度的变化。这种结构使得可以选择灯泡的上表面相对于径向稍微倾斜的刀片，这有助于它们从复合材料构造。

42. 发明申请

US20120160933A1 STRUCTURING ASSEMBLY FOR AN EXHAUST NOZZLE 审中-公开
标题翻译：用于排气喷嘴的结构装配
公开(公告)号：US20120160933A1
公开(公告)日：2012-06-28
申请号：US13394250
申请日：2010-08-31
申请人： Guy Bernard Vauchel , Eric Conete
发明人： Guy Bernard Vauchel , Eric Conete
IPC分类号： F02K1/44
CPC分类号： F02K1/827 , F05D2250/283 , F05D2300/603 , Y02T50/672
摘要： The invention relates to a structuring assembly (13) for an exhaust nozzle, including the following main elements: (a) an outer skin (22) including a non-acoustic portion (33); (b) an inner structuring skin (23); (c) an acoustic structure (21) including cells (27) having a cellular core, said acoustic structure being arranged between the outer skin (22) and the inner structuring skin (23), at least one of said main elements being made of a composite material, and the acoustic structure (21) being supported between the outer skin (22) and inner structuring skin (23) by linking means (31; 41) attached to the inner structuring skin (23) and to the non-acoustic portion (33) of the outer skin (22) so as to transfer the stresses onto the inner structuring skin (23) and the non-acoustic portion (33) of the outer skin (22). The invention also relates to an exhaust nozzle for a nacelle, comprising such a structuring assembly (13), as well as to a nacelle.
摘要翻译：本发明涉及一种用于排气喷嘴的结构组件（13），其包括以下主要元件：（a）包括非声部分（33）的外皮（22）; （b）内部构造皮肤（23）; （c）包括具有多孔芯的电池（27）的声学结构（21），所述声学结构布置在外皮（22）和内结构皮肤（23）之间，所述主要元件中的至少一个由复合材料，并且通过连接到内部结构化皮肤（23）上的连接装置（31; 41）和与非内部构造皮肤（23）连接的外壳（22）和内部结构皮肤（23）之间的声学结构（21）（22）的部分（33），以将应力转移到外皮（22）的内结构皮肤（23）和非声部（33）上。本发明还涉及一种用于机舱的排气喷嘴，其包括这种结构组件（13）以及机舱。

43. 发明授权

US08205453B2 Method for assembling end to end two parts having different thermal expansion coefficients and assembly thus obtained 有权
标题翻译：用于组装具有不同热膨胀系数和如此获得的组装的端部到两端的方法
公开(公告)号：US08205453B2
公开(公告)日：2012-06-26
申请号：US12531516
申请日：2008-04-03
申请人： Eric Conete
发明人： Eric Conete
IPC分类号： F02C1/00
CPC分类号： F02K1/80 , F01D25/243 , F01D25/246 , F05D2260/30 , F05D2300/21 , F05D2300/603 , F23R3/007 , F23R3/60 , Y02T50/672 , Y10T29/49947
摘要： In order to assemble together two parts (154, 162) of materials having different coefficients of expansion via mutually engaged edge portions (154a, 162a), tongues (170) are formed in the thinned edge of one of the parts, the tongues being separated by slots (172) obtained by cutting or machining the material of the part, and the parts are assembled together by fastening (174) via the tongues. The edge portions are mutually engaged in such a manner as to be in substantially leaktight contact at the high temperatures encountered in operation. The method is applicable in particular to assembling together parts made respectively of metal and of ceramic composite material, in particular in an aviation gas turbine, for example, upstream and downstream secondary nozzles.
摘要翻译：为了通过相互接合的边缘部分（154a，162a）将具有不同膨胀系数的两个部件（154,162）组装在一个部件的薄化边缘中，舌部被分离通过切割或加工该部件的材料获得的槽（172），并且通过舌片通过紧固（174）将部件组装在一起。边缘部分以在操作中遇到的高温基本上密封接触的方式相互接合。该方法特别适用于组装分别由金属和陶瓷复合材料制成的零件，特别是在航空燃气轮机中，例如上游和下游二次喷嘴。

44. 发明授权

US08146372B2 Gas turbine combustion chamber having inner and outer walls subdivided into sectors 有权
标题翻译：燃气轮机燃烧室具有细分为扇区的内壁和外壁
公开(公告)号：US08146372B2
公开(公告)日：2012-04-03
申请号：US12416418
申请日：2009-04-01
申请人： Benoit Carrere , Georges Habarou , Patrick Spriet , Pierre Camy
发明人： Benoit Carrere , Georges Habarou , Patrick Spriet , Pierre Camy
IPC分类号： F23R3/50
CPC分类号： F23R3/002 , F23R3/007 , F23R3/50 , F23R3/60 , F23R2900/00005
摘要： An annular combustion chamber has an inner wall and an outer wall of ceramic matrix composite material, together with a chamber end wall that is connected to the inner and outer walls. Elastically-deformable link elements connect the inner wall and the outer chamber walls to inner and outer metal casings. Each of the inner and outer chamber walls is subdivided circumferentially into adjacent sectors along longitudinal edges, each sector extending continuously from the end wall to the opposite end of the chamber and being folded outwards from the chamber at each of its longitudinal edges to form a portion having a U-shaped cross-section terminated by a folded-back margin that is spaced apart from the outer face of the corresponding chamber wall. The link elements are connected to the inner and outer chamber walls by being fastened to the sector margins.
摘要翻译：环形燃烧室具有陶瓷基体复合材料的内壁和外壁，以及连接到内壁和外壁的腔室端壁。可弹性变形的连接元件将内壁和外部室壁连接到内部和外部金属外壳。每个内室壁和外室壁沿着纵向边缘沿圆周方向细分成相邻扇区，每个扇形区从端壁连续延伸到腔室的相对端，并且在其每个纵向边缘处从腔室向外折叠以形成一部分具有由与相应室壁的外表面间隔开的折回边缘终止的U形横截面。连接元件通过紧固到扇形边缘而连接到内室和外室壁。

45. 发明申请

US20120027605A1 TURBOMACHINE BLADE, A ROTOR, A LOW PRESSURE TURBINE, AND A TURBOMACHINE FITTED WITH SUCH A BLADE 有权
标题翻译：涡轮叶片，转子，低压涡轮机和配有这种叶片的涡轮机
公开(公告)号：US20120027605A1
公开(公告)日：2012-02-02
申请号：US13190809
申请日：2011-07-26
申请人： Damien CORDIER , Jean-Luc Soupizon , Julien Mateo , Georges Habarou
发明人： Damien CORDIER , Jean-Luc Soupizon , Julien Mateo , Georges Habarou
IPC分类号： F01D5/30
CPC分类号： F01D5/284 , F01D5/282 , F01D5/326
摘要： The invention relates to a turbomachine blade made of composite material and presenting a root with a bulb-shaped end suitable for engaging in a slot of a rotor disk. In characteristic manner, the end of the root of the blade is provided, beside one of its front faces, with a projecting portion having two symmetrical fins about the axial midplane of the root, each fin having a bearing face suitable for limiting tilting of the blade relative to the rotor disk about the axial direction.
摘要翻译：本发明涉及一种由复合材料制成的涡轮机叶片，其具有适于接合转子盘的狭槽的灯泡形端的根部。以特征方式，刀片的根部的端部在其前表面之一处设置有具有围绕根部的轴向中平面的两个对称翅片的突出部分，每个翅片具有适于限制刀片相对于转子盘绕轴向方向。

46. 发明申请

US20110311368A1 COMPOSITE MATERIAL TURBINE ENGINE VANE, AND METHOD FOR MANUFACTURING SAME 有权
标题翻译：复合材料涡轮发动机叶片及其制造方法
公开(公告)号：US20110311368A1
公开(公告)日：2011-12-22
申请号：US13131285
申请日：2009-11-26
申请人： Dominique Coupe , Clément Roussille , Jonathan Goering , Julien Mateo , Nicolas Eberling-Fux , Guillaume Renon
发明人： Dominique Coupe , Clément Roussille , Jonathan Goering , Julien Mateo , Nicolas Eberling-Fux , Guillaume Renon
IPC分类号： F01D5/14
CPC分类号： F01D5/282 , B29B11/16 , B29C70/222 , B29C70/24 , B29L2031/08 , C04B35/571 , C04B35/62868 , C04B35/62873 , C04B35/62884 , C04B35/62894 , C04B35/62897 , C04B2235/5244 , C04B2235/5256 , C04B2235/616 , D03D25/005 , F05D2300/21 , F05D2300/6033 , F05D2300/614 , F05D2300/702 , Y02T50/67 , Y02T50/672
摘要： A method of fabricating a turbomachine blade out of a composite material including fiber reinforcement densified by a matrix, the method including making a one-piece fiber blank by three-dimensional weaving; shaping the fiber blank to obtain a one-piece fiber preform having a first portion forming a blade airfoil and root preform and at least one second portion forming a preform for an inner or outer blade platform; and densifying the preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, fowling a single part with incorporated inner and/or outer platform.
摘要翻译：一种由包括由基体致密化的纤维增强材料的复合材料制造涡轮机叶片的方法，该方法包括通过三维编织制造单件纤维坯料; 成形纤维毛坯以获得具有形成叶片翼型和根部预制件的第一部分和形成用于内部或外部叶片平台的预制件的至少一个第二部分的单件式纤维预制件; 并用矩阵致密化预成型件，以获得具有纤维增强材料的复合材料刀片，该纤维增强材料由预成型件构成并由基体致密化，使单个部件与内部和/或外部平台结合在一起。

47. 发明申请

US20110293828A1 METHOD FOR MANUFACTURING A COMPLEXLY SHAPED COMPOSITE MATERIAL PART 有权
标题翻译：复合材料复合材料制造方法
公开(公告)号：US20110293828A1
公开(公告)日：2011-12-01
申请号：US13131320
申请日：2009-11-26
申请人： Nicolas Eberling-Fux , Eric Bouillon , Clément Roussille , Stéphane Otin , Dominique Coupe
发明人： Nicolas Eberling-Fux , Eric Bouillon , Clément Roussille , Stéphane Otin , Dominique Coupe
IPC分类号： C23C16/02
CPC分类号： B29B11/16 , B29B11/02 , C04B35/52 , C04B35/565 , C04B35/6286 , C04B35/62868 , C04B35/62873 , C04B35/62897 , C04B35/806 , C04B35/83 , C04B2235/5244 , C04B2235/5252 , C04B2235/614 , C04B2235/94 , D03D25/005 , F01D5/282 , F01D17/20 , F05D2300/601 , F05D2300/6012 , F05D2300/614 , Y02T50/672 , Y10S427/10
摘要： A method of fabricating a complex part out of composite material including three-dimensional woven fiber reinforcement densified by a matrix, the method including three-dimensionally weaving a continuous fiber strip including a succession of fiber blanks for preforms of a plurality of parts that are to be fabricated; subsequently cutting individual fiber blanks out from the strip, each blank being a one-piece blank; shaping a cut-out blank to obtain a one-piece fiber preform having a shape that is close to the shape of a part that is to be fabricated; consolidating the preform in the desired shape; and densifying the consolidated preform by forming a matrix by chemical vapor infiltration.
摘要翻译：一种由复合材料制成复合材料的方法，包括由基体致密化的三维编织纤维增强材料，该方法包括三维编织连续的纤维条，该连续纤维条包括一系列纤维毛坯，用于多个零件的预制件被制造随后从条带中切割出单根纤维毛坯，每个坯料为一片坯料; 成形切割坯料以获得具有接近要制造的部件的形状的形状的一体式纤维预制件; 将预成型件固结成所需的形状; 并通过化学气相渗透形成基质来致密化固结的预成型体。

48. 发明授权

US08039053B2 Method for making a part of composite material with ceramic matrix and resulting part 有权
标题翻译：用陶瓷基体制成复合材料的一部分的方法和结果部分
公开(公告)号：US08039053B2
公开(公告)日：2011-10-18
申请号：US11884899
申请日：2006-02-22
申请人： Eric Philippe , Sébastien Bertrand , Eric Bouillon , Alain Caillaud , Jean-Christophe Ichard , Robert Bagat
发明人： Eric Philippe , Sébastien Bertrand , Eric Bouillon , Alain Caillaud , Jean-Christophe Ichard , Robert Bagat
IPC分类号： C23C16/00
CPC分类号： C04B35/62873 , C04B35/565 , C04B35/571 , C04B35/6286 , C04B35/62863 , C04B35/62868 , C04B35/62884 , C04B35/62894 , C04B35/62897 , C04B35/806 , C04B2235/465 , C04B2235/5244 , C04B2235/80 , C04B2235/96 , Y10T428/265
摘要： An interphase coating is formed by chemical vapor infiltration (CVI) on the fibers constituting a fiber preform, the interphase coating comprising at least an inner layer in contact with the fibers for embrittlement relief to the composite material, and an outer layer for bonding with the ceramic matrix. The fiber preform is then kept in its shape by the fibers provided with the interphase coating and is consolidated by being impregnated with a liquid composition containing a ceramic precursor, and by transforming the precursor into a ceramic matrix consolidation phase. The consolidated preform is then densified by an additional ceramic matrix phase. No support tooling is needed for forming the interphase coating by CVI or for densification after consolidation using the liquid technique.
摘要翻译：通过化学气相渗透（CVI）在构成纤维预成型体的纤维上形成间期涂层，所述界面层至少包含与纤维接触的内层，用于复合材料的脆化释放，外层用于与陶瓷基体。然后将纤维预成型体通过具有相间涂层的纤维保持其形状，并通过浸渍含有陶瓷前体的液体组合物，并将前体转化为陶瓷基体固结相来固化。然后将固结的预制件通过另外的陶瓷基体相致密化。不需要支撑工具，用于通过CVI形成相间涂层或使用液体技术进行固结后的致密化。

49. 发明申请

US20110203255A1 FLEXIBLE ABUTMENT LINKS FOR ATTACHING A PART MADE OF CMC 有权
标题翻译：用于连接CMC部件的灵活连接
公开(公告)号：US20110203255A1
公开(公告)日：2011-08-25
申请号：US13062617
申请日：2009-09-08
申请人： Eric Conete
发明人： Eric Conete
IPC分类号： F02K1/80 , F02K1/04
CPC分类号： F02K1/80 , F02K1/04 , F05D2230/642
摘要： An after-body assembly for an aeroengine, the assembly including, in an axial direction, an annular part made of metallic material secured to the aeroengine and an after-body part made of ceramic matrix composite material presenting the form of a body of revolution at least in its upstream portion, the after-body part being mounted on the annular part by resiliently flexible fastener tabs, each fastener tab having a first end fastened to the annular part and a second end fastened to the upstream portion of the after-body part, wherein each fastener tab includes an axial abutment element extending radially from the second end of the tab, the axial abutment element facing the first end and a radial abutment element at the second end of the tab, the radial abutment element overlying the first end in a radial direction.
摘要翻译：一种用于航空发动机的后体组件，所述组件包括在轴向方向上由固定到所述航空发动机的金属材料制成的环形部分和由呈现旋转体形式的陶瓷基体复合材料制成的后身部分至少在其上游部分中，后身体部分通过弹性柔性紧固件突片安装在环形部分上，每个紧固件突片具有紧固到环形部分的第一端和固定到身体后部分的上游部分的第二端，其中每个紧固件突片包括从所述突片的第二端径向延伸的轴向抵靠元件，所述轴向抵靠元件面向所述第一端，并且在所述突片的第二端处具有径向抵靠元件，所述径向抵靠元件覆盖所述第一端径向。

50. 发明申请

US20100015428A1 METHOD OF FABRICATING A THERMOSTRUCTURAL COMPOSITE MATERIAL PART, AND A PART OBTAINED THEREBY 有权
标题翻译：制备热结构复合材料部件的方法及其获得的部件
公开(公告)号：US20100015428A1
公开(公告)日：2010-01-21
申请号：US12501648
申请日：2009-07-13
申请人： Eric Philippe , Eric Bouillon
发明人： Eric Philippe , Eric Bouillon
IPC分类号： B32B18/00 , C23C16/30 , C23C16/34
CPC分类号： C04B35/80 , C04B35/571 , C04B35/6286 , C04B35/62865 , C04B35/62873 , C04B35/62884 , C04B35/62894 , C04B35/62897 , C04B35/83 , C04B2235/5224 , C04B2235/5244 , C04B2235/5248 , C04B2235/5252 , C04B2235/5256 , C04B2235/614 , C04B2235/616 , Y10S427/10 , Y10T428/24975 , Y10T428/249928 , Y10T428/25 , Y10T428/265
摘要： The method comprises:using chemical vapor infiltration to form a first continuous interphase on the fibers of a fiber structure made of refractory fibers, the interphase having a thickness of no more than 100 nanometers;impregnating the fiber structure with a consolidation composition comprising a carbon or ceramic precursor resin;forming a fiber preform that is consolidated by shaping the impregnated fiber structure and using pyrolysis to transform the resin into a discontinuous solid residue of carbon or ceramic;using chemical vapor infiltration to form a second continuous interphase layer; anddensifying the preform with a refractory matrix.This preserves the capacity of the fiber structure to deform so as to enable a fiber preform to be obtained that is of complex shape, while nevertheless guaranteeing the presence of a continuous interphase between the fibers and the matrix.
摘要翻译：该方法包括：使用化学气相渗透在由耐火纤维制成的纤维结构的纤维上形成第一连续相间，相间的厚度不超过100纳米; 用包含碳或陶瓷前体树脂的固化组合物浸渍纤维结构; 形成纤维预成型件，其通过成形浸渍的纤维结构并使用热解将树脂转变成碳或陶瓷的不连续的固体残余物来固结; 使用化学气相渗透形成第二连续相间层; 并用耐火基体致密化预制件。这保持了纤维结构变形的能力，以便能够获得具有复杂形状的纤维预制件，同时保证在纤维和基质之间存在连续的相间。

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