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1.发明授权Method of manufacturing a gas turbine casing out of composite material, and a casing as obtained thereby 有权从复合材料制造燃气轮机壳体的方法以及由此获得的壳体公开(公告)号：US08322971B2
公开(公告)日：2012-12-04
申请号：US12033624
申请日：2008-02-19
申请人： Dominique Coupe , Bruno Jacques Gerard Dambrine , Francois Marie Paul Marlin , Olivier Michael Molinari , Antoine Phelippeau , Philippe Verseux
发明人： Dominique Coupe , Bruno Jacques Gerard Dambrine , Francois Marie Paul Marlin , Olivier Michael Molinari , Antoine Phelippeau , Philippe Verseux
IPC分类号： F01D21/00
CPC分类号： F01D21/045 , B29C70/24 , B29C70/443 , F05D2240/11 , F05D2300/603 , Y02T50/672
摘要： A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.
摘要翻译： 特别是用于燃气轮机风扇的不同厚度的复合材料壳体通过形成纤维增强物并用基体致密化而制成。 纤维增强件通过将纤维织构的叠层卷绕到心轴上而形成，该纹理由具有变化厚度的三维编织制成。
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2.发明申请METHOD OF MANUFACTURING A GAS TURBINE CASING OUT OF COMPOSITE MATERIAL, AND A CASING AS OBTAINED THEREBY 有权制造复合材料的气体涡轮机的方法及其获得的试验公开(公告)号：US20080206048A1
公开(公告)日：2008-08-28
申请号：US12033624
申请日：2008-02-19
申请人： Dominique Coupe , Bruno Jacques Gerard Dambrine , Francois Marie Paul Marlin , Olivier Michael Molinari , Antoine Phelippeau , Philippe Verseux
发明人： Dominique Coupe , Bruno Jacques Gerard Dambrine , Francois Marie Paul Marlin , Olivier Michael Molinari , Antoine Phelippeau , Philippe Verseux
CPC分类号： F01D21/045 , B29C70/24 , B29C70/443 , F05D2240/11 , F05D2300/603 , Y02T50/672
摘要： A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.
摘要翻译： 特别是用于燃气轮机风扇的不同厚度的复合材料壳体通过形成纤维增强物并用基体致密化而制成。 纤维增强件通过将纤维织构的叠层卷绕到心轴上而形成，该纹理由具有变化厚度的三维编织制成。
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公开(公告)号：US08424921B2
公开(公告)日：2013-04-23
申请号：US12333467
申请日：2008-12-12
CPC分类号： B29C70/545 , B29C70/00 , B29C70/08 , B29C70/32 , B29C70/34 , B29C70/342 , B29C70/345 , B29C2793/009 , B29K2277/10 , B29K2707/04 , B29K2709/08 , B29L2031/24 , F16L47/14
摘要： A coupling made of composite material including a polymer matrix reinforced by a fiber structure is disclosed. The coupling includes a structural portion reinforced by a main fiber structure, and a first machining portion reinforced by a first fiber structure that is distinct from the main fiber structure. The matrices of the structural portion and of the first machining portion are identical. The first machining portion is situated on at least a fraction of the main face of the structural portion and is machined in a first machining surface, and there is no intersection between the first machining surface and the fibers of the main fiber structure.
摘要翻译： 公开了一种由包括由纤维结构增强的聚合物基体的复合材料制成的联接器。 联接器包括由主纤维结构增强的结构部分和由与主纤维结构不同的第一纤维结构增强的第一加工部分。 结构部分和第一加工部分的矩阵是相同的。 第一加工部分位于结构部分的主面的至少一部分上，并且在第一加工表面中加工，并且第一加工表面和主纤维结构的纤维之间没有交叉。
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公开(公告)号：US08061967B2
公开(公告)日：2011-11-22
申请号：US12329919
申请日：2008-12-08
IPC分类号： H02C7/05
CPC分类号： F01D21/045 , F02C7/047 , F02K3/06 , F05D2300/603 , Y02T50/672
摘要： A panel for supporting abradable material in a turbojet, the panel comprising a rigid support for fastening to an inside wall of a fan casing and having one face covered in a laminated structure carrying a layer of abradable material, the laminated structure comprising sheets of fibers embedded in a polymer, and comprising an upstream portion covered by the abradable material and a downstream portion that extends beyond the abradable material, the thickness of the downstream portion being greater than the thickness of the upstream portion and being capable of withstanding ice impacts.
摘要翻译： 一种用于在涡轮喷气发动机中支撑耐磨材料的面板，所述面板包括用于紧固到风扇壳体的内壁的刚性支撑件，并且具有覆盖在承载有可磨损材料层的层压结构中的一个面，所述层压结构包括嵌入的纤维片 在聚合物中，并且包括由可磨损材料覆盖的上游部分和延伸超过可磨损材料的下游部分，下游部分的厚度大于上游部分的厚度并且能够承受冰撞击。
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公开(公告)号：US20090200700A1
公开(公告)日：2009-08-13
申请号：US12333467
申请日：2008-12-12
CPC分类号： B29C70/545 , B29C70/00 , B29C70/08 , B29C70/32 , B29C70/34 , B29C70/342 , B29C70/345 , B29C2793/009 , B29K2277/10 , B29K2707/04 , B29K2709/08 , B29L2031/24 , F16L47/14
摘要： The invention relates to a coupling made of composite material comprising a polymer matrix reinforced by a fiber structure. The coupling comprises a structural portion reinforced by a main fiber structure, and a first machining portion reinforced by a first fiber structure that is distinct from the main fiber structure, the matrices of the structural portion and of the first machining portion being identical, the first machining portion being situated on at least a fraction of the main face of the structural portion and being machined in a first machining surface, there being no intersection between the first machining surface and the fibers of the main fiber structure.
摘要翻译： 本发明涉及由复合材料制成的耦合体，其包括由纤维结构增强的聚合物基体。 联轴器包括由主纤维结构增强的结构部分和由与主纤维结构不同的第一纤维结构增强的第一加工部分，结构部分和第一加工部分的基体相同，第一 所述加工部位于所述结构部的主面的至少一部分上，并且在第一加工面加工，所述第一加工面与所述主纤维结构的纤维之间不相交。
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公开(公告)号：US08075246B2
公开(公告)日：2011-12-13
申请号：US12028994
申请日：2008-02-11
CPC分类号： F01D17/105 , F02C9/18 , F02K3/075 , F04D27/023 , F04D29/522 , Y02T50/672
摘要： The relief device is designed to divert a portion of a main flow toward a by-pass flow in a turbojet that includes a main flow stream, a by-pass flow stream and an intermediate casing. The relief device includes inner openings of the inner shroud, outer openings of the outer shroud, a relief circuit connecting the inner openings to the outer openings, and a blanking device capable of opening and closing the relief circuit. The relief circuit includes upstream holes of the intermediate casing, downstream holes of the intermediate casing, and an annular channel defined between the intermediate casing, the outer shroud and a connecting partition. The connecting partition rests on the intermediate casing so as to encompass the downstream holes of the intermediate casing in the annular channel and resting on the outer shroud so as to encompass the outer openings of the outer shroud in the annular channel.
摘要翻译： 溢流装置被设计成在包括主流动流，旁通流动流和中间壳体的涡轮喷气机中将主流体的一部分转向旁通流。 救生装置包括内护罩的内部开口，外护罩的外部开口，将内部开口连接到外部开口的释放电路，以及能够打开和关闭救生电路的冲裁装置。 释放电路包括中间壳体的上游孔，中间壳体的下游孔和限定在中间壳体，外护罩和连接隔板之间的环形通道。 连接分隔件搁置在中间壳体上，以便包围环形通道中的中间壳体的下游孔并且搁置在外护罩上，以便围绕环形通道中的外护罩的外部开口。
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公开(公告)号：US20080193279A1
公开(公告)日：2008-08-14
申请号：US12028994
申请日：2008-02-11
CPC分类号： F01D17/105 , F02C9/18 , F02K3/075 , F04D27/023 , F04D29/522 , Y02T50/672
摘要： The relief device is designed to divert a portion (94) of a main flow (90) toward a by-pass flow (92) in a turbojet that comprises a main flow stream (10), a by-pass flow stream (14) and an intermediate casing (20).The relief device comprises: inner openings (26) of the inner shroud (16), outer openings (28) of the outer shroud (18), a relief circuit (32, 34, 36, 52, 56) connecting said inner openings (26) to said outer openings (28), blanking means (58, 60, 62, 64, 66) capable of opening and closing said relief circuit and wherein the relief circuit (32, 34, 36, 52, 56) comprises upstream holes (32) of the intermediate casing (20), downstream holes (34) of the intermediate casing (20), an annular channel (52) defined between the intermediate casing (20), the outer shroud (18) and a connecting partition (54), said connecting partition (54) resting on the intermediate casing (20) so as to encompass the downstream holes (34) of the latter in said annular channel (52) and resting on the outer shroud (18) so as to encompass the outer openings (28) of the latter in said annular channel (52).
摘要翻译： 溢流装置被设计成在包括主流体流（10），旁通流动流（14）的涡轮喷气机中将主流（90）的一部分（94）转向旁通流（92） 和中间壳体（20）。 救护装置包括：内护罩（16）的内部开口（26），外护罩（18）的外部开口（28），连接所述内部开口（18）的释放回路（32,34,36,52,56） 26）到能够打开和关闭所述释放电路的所述外部开口（28），冲切装置（58,60,62,64,66），并且其中所述释放电路（32,34,36,52,56）包括上游孔 中间壳体（20）的下游孔（34），中间壳体（20）的下游孔（34），限定在中间壳体（20），外护罩（18）和连接分隔件 54），所述连接隔板（54）搁置在中间壳体（20）上，以便在所述环形通道（52）中包围其中的下游孔（34）并且搁置在外护罩（18）上，以便包围 后者在所述环形通道（52）中的外部开口（28）。
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8.发明授权De-icing device for turbojet inlet guide wheel vane, vane provided with such a de-icing device, and aircraft engine equipped with such vanes 有权用于涡轮喷气进口导向轮叶片的除冰装置，具有这种除冰装置的叶片，以及配备有这种叶片的飞机发动机公开(公告)号：US07055304B2
公开(公告)日：2006-06-06
申请号：US10883699
申请日：2004-07-06
IPC分类号： F02G3/00
CPC分类号： F01D5/146 , F01D17/162 , F02C7/047 , Y02T50/672 , Y02T50/673
摘要： The de-icing device is intended for the vane (10) of the inlet guide wheel (4) of a turbojet (2), comprising a fixed part (12) arranged on the upstream side and a mobile flap (18) arranged on the downstream side, in which said fixed part (12) comprises a trailing edge (16) substantially in the shape of a “U”, with one of the branches (162) being located on the intrados side (I) and the other branch (164) being located on the extrados side (E). It comprises at least one emission window (202), oriented substantially along an upstream-downstream direction, and arranged along the branch (162) of the “U” located on the intrados side (I) of the trailing edge (16).The inlet guide wheel (4) vane (10) is equipped with at least such a de-icing device.The aircraft engine (2) comprises at least one vane (10) equipped with such a de-icing device.
摘要翻译： 除冰装置用于涡轮喷气发动机（2）的入口引导轮（4）的叶片（10），包括设置在上游侧的固定部分（12）和布置在上游侧的活动挡板（18） 下游侧，其中所述固定部分（12）包括基本上为“U”形的后缘（16），其中一个分支（162）位于内侧（I）和另一分支 164）位于引渡侧（E）上。 它包括基本上沿着上游 - 下游方向定向并沿着位于后缘（16）的内侧（I）的“U”的分支（162）布置的至少一个发射窗口（202）。 入口导向轮（4）叶片（10）至少装有这样的除冰装置。 飞机发动机（2）包括配备有这样的除冰装置的至少一个叶片（10）。
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公开(公告)号：US09441494B2
公开(公告)日：2016-09-13
申请号：US14115513
申请日：2012-05-04
CPC分类号： F01D5/3038 , F01D5/323 , F01D11/008 , F04D29/322 , F05D2220/36
摘要： A rotor of a turbomachine, such as a multi-flow turbojet engine fan, has a disc including, on the rim thereof, substantially axial slots with a dovetailed cross-section, and blades mounted individually in the slots, an axial wedge positioned between the root of the blades and the bottom of the slots, and a transverse lock providing upstream axial immobilization of the blades in the slot thereof. The lock is guided in radial notches formed in the flanks of the slots and radially supported against the wedge. The axial wedge is immobilised in the upstream direction, butting up against a transverse annular component secured to the disc.
摘要翻译： 涡轮机的转子，例如多流量涡轮喷气发动机风扇，具有一个圆盘，其圆盘包括在其边缘上具有燕尾形横截面的基本上轴向的狭槽，以及分别安装在槽中的叶片，位于 叶片的根部和槽的底部，以及横向锁，其提供叶片在其狭槽中的上游轴向固定。 锁定在形成在槽的侧面中的径向槽口中被引导并且径向地支撑在楔形件上。 轴向楔固定在上游方向，与固定在盘上的横向环形部件对接。
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10.发明授权Soundproofing panel for turbomachine and turbomachine comprising such a panel 有权包括这种面板的涡轮机和涡轮机的隔音面板公开(公告)号：US08544598B2
公开(公告)日：2013-10-01
申请号：US13588669
申请日：2012-08-17
申请人： Florian Gaudry , Romain Plante , Noel Robin , Georges Jean Xavier Riou , Jacky Novi Mardjono , Francois Marie Paul Marlin
发明人： Florian Gaudry , Romain Plante , Noel Robin , Georges Jean Xavier Riou , Jacky Novi Mardjono , Francois Marie Paul Marlin
IPC分类号： B64D33/02
CPC分类号： F02C7/045 , B64D33/02 , B64D2033/0206 , F01D25/243 , F05D2250/283 , F05D2260/30 , F05D2260/962 , Y02T50/672 , Y10T29/49236
摘要： A one-piece soundproofing panel which is attached within an circumferential air blower casing of a turbomachine, with an axis, in which circulates an airflow from upstream to downstream, is disclosed. The panel includes a circumferential rigid seat with a longitudinal cylindrical part, arranged to axially extend with respect to the axis A of the turbomachine, having an outside surface, intended to come to extend facing with an internal surface of the air blower casing, and an internal surface to which is applied a soundproofing coating; and an annular fastening flange, formed at the upstream end of the longitudinal cylindrical part, radially outwardly extending, the fastening flange being arranged to cooperate with a fastening flange of the air blower casing.
摘要翻译： 公开了一种连接在涡轮机的周向鼓风机壳体内的一体式隔音板，其具有从上游到下游循环气流的轴线。 面板包括具有纵向圆柱形部分的圆周刚性座，该圆周刚性座被布置为相对于涡轮机的轴线A轴向延伸，具有外表面，旨在面向鼓风机壳体的内表面延伸，并且 内表面应用隔音涂层; 以及形成在所述纵向圆柱形部分的上游端处的径向向外延伸的环形紧固凸缘，所述紧固凸缘被布置成与所述鼓风机壳体的紧固凸缘配合。
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