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1. 发明授权

US08951017B2 Turbomachine blade, a rotor, a low pressure turbine, and a turbomachine fitted with such a blade 有权
标题翻译：涡轮机叶片，转子，低压涡轮机和装有这种叶片的涡轮机
公开(公告)号：US08951017B2
公开(公告)日：2015-02-10
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 , F01D5/28 , F01D5/32
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。

2. 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。

3. 发明申请

US20100092281A1 TURBINE RING ASSEMBLY FOR GAS TURBINE 有权
标题翻译：用于气体涡轮机的涡轮环组件
公开(公告)号：US20100092281A1
公开(公告)日：2010-04-15
申请号：US12531115
申请日：2008-03-14
申请人： Georges Habarou , Julien Mateo , Eric Bouillon
发明人： Georges Habarou , Julien Mateo , Eric Bouillon
IPC分类号： F02C7/00
CPC分类号： F01D11/08 , F01D11/125 , F05D2250/232 , F05D2260/30 , F05D2300/5021 , F05D2300/603 , F05D2300/614 , Y02T50/67 , Y02T50/672
摘要： A turbine ring assembly for a gas turbine comprises a one-piece split ring (10) of ceramic matrix composite (CMC) material, a CMC wedge-shaped part (20) having flanks in contact with the ends of the ring, on either side of the split, so as to close the ring, and an annular metal support structure (40) surrounding the CMC ring and in contact therewith over the major fraction of its outline, the CMC ring being mounted with prestress in the metal structure, at least one element (26) exerting a resilient return force on the wedge-shaped part to keep it in contact with the ends of the CMC ring when the split opens under the effect of differential expansion between the annular metal structure and the CMC ring, and at least one element for preventing the CMC ring from turning about its axis.
摘要翻译：一种用于燃气轮机的涡轮环组件包括陶瓷基体复合材料（CMC）材料的一体式开口环（10），具有与环的端部相接触的侧面的CMC楔形部分（20）以及围绕所述CMC环的环形金属支撑结构（40），并且在其轮廓的主要部分上与其接触，所述CMC环至少安装有金属结构中的预应力一个元件（26）在楔形部件上施加弹性的返回力，以在分离在环形金属结构和CMC环之间的不同膨胀的作用下打开时保持其与CMC环的端部接触，并且在至少一个用于防止CMC环转动其轴的元件。

4. 发明授权

US08257029B2 Turbine ring assembly for gas turbine 有权
标题翻译：燃气轮机的涡轮环组件
公开(公告)号：US08257029B2
公开(公告)日：2012-09-04
申请号：US12531115
申请日：2008-03-14
申请人： Georges Habarou , Julien Mateo , Eric Bouillon
发明人： Georges Habarou , Julien Mateo , Eric Bouillon
IPC分类号： F01D11/00
CPC分类号： F01D11/08 , F01D11/125 , F05D2250/232 , F05D2260/30 , F05D2300/5021 , F05D2300/603 , F05D2300/614 , Y02T50/67 , Y02T50/672
摘要： A turbine ring assembly for a gas turbine includes a one-piece split ring (10) of ceramic matrix composite (CMC) material, a CMC wedge-shaped part (20) having flanks in contact with the ends of the ring, on either side of the split, so as to close the ring, and an annular metal support structure (40) surrounding the CMC ring and in contact therewith over the major fraction of its outline, the CMC ring being mounted with prestress in the metal structure, at least one element (26) exerting a resilient return force on the wedge-shaped part to keep it in contact with the ends of the CMC ring when the split opens under the effect of differential expansion between the annular metal structure and the CMC ring, and at least one element for preventing the CMC ring from turning about its axis.
摘要翻译：一种用于燃气轮机的涡轮环组件包括陶瓷基体复合材料（CMC）材料的一体式开口环（10），具有与环的端部接触的侧面的CMC楔形部分（20）以及围绕所述CMC环的环形金属支撑结构（40），并且在其轮廓的主要部分上与其接触，所述CMC环至少安装有金属结构中的预应力一个元件（26）在楔形部件上施加弹性的返回力，以在分离在环形金属结构和CMC环之间的不同膨胀的作用下打开时保持其与CMC环的端部接触，并且在至少一个用于防止CMC环转动其轴的元件。

5. 发明申请

US20100111678A1 TURBINE RING ASSEMBLY FOR GAS TURBINE 有权
标题翻译：用于气体涡轮机的涡轮环组件
公开(公告)号：US20100111678A1
公开(公告)日：2010-05-06
申请号：US12531113
申请日：2008-03-14
申请人： Georges Habarou , Julien Mateo , Eric Bouillon
发明人： Georges Habarou , Julien Mateo , Eric Bouillon
IPC分类号： F01D11/08 , D04H18/00
CPC分类号： F01D9/04 , F01D11/08 , F05D2240/11 , F05D2300/21 , F05D2300/603 , Y02T50/67 , Y02T50/672
摘要： A turbine ring assembly for a gas turbine, the assembly comprising a complete ring (10) forming a single piece of ceramic matrix composite material (CMC), a metal structure for supporting the CMC ring having metal annular supports (20, 30) between which the CMC ring is placed while allowing differential expansion at least in a radial direction between the CMC ring and the annular supports, means (40-42) for centering the CMC ring, and at least one element for preventing turning of the CMC ring about its axis.
摘要翻译：一种用于燃气轮机的涡轮环组件，该组件包括形成单片陶瓷基复合材料（CMC）的完整环（10），用于支撑具有金属环形支撑件（20,30）的CMC环的金属结构 CMC环被放置，同时至少在CMC环和环形支撑件之间的径向方向上进行不同的膨胀，用于使CMC环对中的装置（40-42）以及用于防止CMC环绕其旋转的至少一个元件轴。

6. 发明授权

US08496431B2 Turbine ring assembly for gas turbine 有权
标题翻译：燃气轮机的涡轮环组件
公开(公告)号：US08496431B2
公开(公告)日：2013-07-30
申请号：US12531113
申请日：2008-03-14
申请人： Georges Habarou , Julien Mateo , Eric Bouillon
发明人： Georges Habarou , Julien Mateo , Eric Bouillon
IPC分类号： F01D9/04
CPC分类号： F01D9/04 , F01D11/08 , F05D2240/11 , F05D2300/21 , F05D2300/603 , Y02T50/67 , Y02T50/672
摘要： A turbine ring assembly for a gas turbine, the assembly having a complete ring forming a single piece of ceramic matrix composite material (CMC), a metal structure for supporting the CMC ring having metal annular supports between which the CMC ring is placed while allowing differential expansion at least in a radial direction between the CMC ring and the annular supports, an arrangement for centering the CMC ring, and at least one element for preventing turning of the CMC ring about its axis.
摘要翻译：一种用于燃气轮机的涡轮环组件，该组件具有形成单片陶瓷基体复合材料（CMC）的完整环，用于支撑具有金属环形支撑的CMC环的金属结构，CMC环之间放置有CMC环，同时允许差动至少在CMC环和环形支撑件之间的径向方向上的膨胀，用于使CMC环对中的装置以及用于防止CMC环绕其轴线转动的至少一个元件。

7. 发明申请

US20070039327A1 MONOBLOC FLAMEHOLDER ARM FOR AN AFTERBURNER DEVICE OF A BYPASS TURBOJET 有权
标题翻译：用于旁路涡轮机燃烧器装置的MONOBLOC FLAMEHOLDER ARM
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。

8. 发明授权

US07249462B2 Mounting a turbine nozzle on a combustion chamber having CMC walls in a gas turbine 有权
标题翻译：将涡轮喷嘴安装在燃气轮机中具有CMC壁的燃烧室上
公开(公告)号：US07249462B2
公开(公告)日：2007-07-31
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： F23R3/60
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。

9. 发明授权

US06988369B2 Combustion chamber sealing ring, and a combustion chamber including such a ring 有权
标题翻译：燃烧室密封环和包括这种环的燃烧室
公开(公告)号：US06988369B2
公开(公告)日：2006-01-24
申请号：US10460736
申请日：2003-06-12
申请人： Eric Conete , Francis Mirambeau , Georges Habarou , Didier Hernandez , Christophe Pieussergues
发明人： Eric Conete , Francis Mirambeau , Georges Habarou , Didier Hernandez , Christophe Pieussergues
IPC分类号： F02C7/20
CPC分类号： F23R3/007 , F05B2230/606 , F23M2900/05004 , F23R3/50 , F23R3/60 , F23R2900/03042 , Y02T50/67 , Y02T50/675
摘要： The present invention provides a fixing or sealing ring for maximizing cooling at the end of a combustion chamber wall. For this purpose, the ring is constituted by a sleeve which is fixed around the end of a wall of the combustion chamber by means of a plurality of orifices for receiving fasteners or by means of any other system for connecting the ring to the wall. The sleeve includes at least one recess in its face facing the wall of the combustion chamber, thereby reducing the area of the sleeve that presses against the wall, and co-operating with said wall to form an open cavity in which a cooling air stream can flow.
摘要翻译：本发明提供一种用于使燃烧室壁的端部处的冷却最大化的固定或密封环。为此，环由套筒构成，该套筒通过用于接收紧固件的多个孔或通过用于将环连接到壁的任何其它系统固定在燃烧室的壁的端部周围。该套筒在其面向燃烧室的壁的面上包括至少一个凹槽，从而减小了压靠在壁上的套筒的面积，并且与所述壁配合以形成开放的空腔，其中冷却气流可以流。

10. 发明授权

US5348598A Method of manufacturing a gun barrel provided with a lining 失效
标题翻译：制造具有内衬的枪管的方法
公开(公告)号：US5348598A
公开(公告)日：1994-09-20
申请号：US892179
申请日：1992-06-02
申请人： Michel Vives , Pierre Taveau , Georges Habarou , Francois Bognandi
发明人： Michel Vives , Pierre Taveau , Georges Habarou , Francois Bognandi
IPC分类号： F41A21/02 , B65H81/00
CPC分类号： F41A21/02
摘要： A gun barrel lining made of composite material having refractory fiber reinforcement and a ceramic matrix, the fiber reinforcement comprises a cylindrical inner portion constituted by a three-dimensional fiber texture and a cylindrical outer portion surrounding the inner portion and having the same axis, the outer portion being constituted by a strip wound around the inner portion, and the inner and outer portions being codensified by the ceramic matrix.
摘要翻译：由具有耐火纤维增强材料和陶瓷基体的复合材料制成的枪管衬套，所述纤维增强材料包括由三维纤维织构构成的圆柱形内部部分和围绕所述内部部分并具有相同轴线的圆柱形外部部分，所述外部所述部分由围绕所述内部部分缠绕的条带构成，并且所述内部和外部部分由所述陶瓷基体编码。

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