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1. 发明授权

US09518472B2 Turbine engine stator wheel and a turbine or a compressor including such a stator wheel 有权
标题翻译：涡轮发动机定子轮和包括这种定子轮的涡轮或压缩机
公开(公告)号：US09518472B2
公开(公告)日：2016-12-13
申请号：US14234268
申请日：2012-07-18
申请人： Olivier Belmonte , Antoine Jean-Philippe Beaujard
发明人： Olivier Belmonte , Antoine Jean-Philippe Beaujard
IPC分类号： F01D9/04 , F01D25/24
CPC分类号： F01D9/04 , F01D9/042 , F01D25/246 , F05D2300/21 , F05D2300/222 , F05D2300/603 , F05D2300/6033 , Y02T50/672 , Y02T50/673
摘要： A turbine nozzle comprises a plurality of composite material vanes, each vane comprising an inner platform, an outer platform with attachment tabs on the outside, and at least one airfoil extending between the inner and outer platforms and secured thereto. The attachment tabs of the vanes are engaged on a metal assembly ring supporting all of the vanes, extending continuously along the outer platforms of adjacent vanes, and forming a distinct assembly part between the vanes and a turbine casing.
摘要翻译：涡轮喷嘴包括多个复合材料叶片，每个叶片包括内平台，在外部具有附接凸片的外平台以及在内平台和外平台之间延伸并固定到其上的至少一个翼型件。叶片的附接突片接合在支撑所有叶片的金属组件环上，沿着相邻叶片的外平台连续延伸，并且在叶片和涡轮壳体之间形成不同的组件部分。

2. 发明授权

US09284041B2 Stationary actuator device for controlling the pitch of fan blades of a turboprop 有权
标题翻译：用于控制涡轮螺旋桨发生器风扇叶片间距的固定致动器装置
公开(公告)号：US09284041B2
公开(公告)日：2016-03-15
申请号：US13375024
申请日：2010-04-16
申请人： Olivier Belmonte , Franck Emmanuel Bosco
发明人： Olivier Belmonte , Franck Emmanuel Bosco
IPC分类号： F01D7/00 , B64C11/32 , B64C11/48 , B64D27/02
CPC分类号： B64C11/32 , B64C11/48 , B64D2027/026 , F01D7/00 , F05D2260/79
摘要： A device for controlling pitch of fan blades of a turboprop including at least one set of variable-pitch fan blades constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade coupled for pitch adjustment to a synchronization ring. A turntable is mounted via a rotary connection to a rod of an actuator that is secured to a stationary structural element of the turboprop, the turntable being mechanically connected to the synchronization ring by a plurality of connection arms hinge-mounted on the turntable and connected to the synchronization ring such that a longitudinal movement of the turntable under drive from the actuator causes the synchronization ring to turn about the longitudinal axis.
摘要翻译：一种用于控制涡轮螺旋桨飞机的风扇叶片间距的装置，包括至少一组可变桨距风扇叶片，其被限制为以纵向轴线为中心并机械地连接到涡轮机转子的旋转环旋转，每个叶片被耦合用于俯仰调节到同步环转盘通过旋转连接安装到致动器的杆上，致动器的杆被固定到涡轮螺旋桨发生器的固定结构元件上，转盘通过铰链安装在转台上的多个连接臂机械连接到同步环上，并连接到所述同步环使得在来自致动器的驱动下的转台的纵向运动导致同步环围绕纵向轴线转动。

3. 发明授权

US08932020B2 Low-pressure turbine 有权
标题翻译：低压涡轮机
公开(公告)号：US08932020B2
公开(公告)日：2015-01-13
申请号：US13322027
申请日：2010-05-21
申请人： Olivier Belmonte , Gregory Nicolas Gerald Gillant
发明人： Olivier Belmonte , Gregory Nicolas Gerald Gillant
IPC分类号： F01D1/24 , F04D13/12 , F01D5/06
CPC分类号： F01D5/066 , F05D2250/712 , Y02T50/671
摘要： A low-pressure turbine for a turbomachine including turbine disks with festooned annular flanges for fastening to a festooned annular flange of a drive cone connecting the turbine disks to a turbine shaft, solid portions of the festooned annular flanges of the turbine disks and of the drive cone being connected to peripheries of the turbine disks and of the drive cone, respectively, via concave filets that are asymmetrical.
摘要翻译：一种用于涡轮机的低压涡轮机，包括具有带有环形凸缘的涡轮盘，其具有用于紧固到将涡轮盘连接到涡轮轴的驱动锥的花键环形凸缘，涡轮盘的花式环形凸缘和驱动器的实心部分锥体分别通过不对称的凹形盘连接到涡轮盘和驱动锥的周边。

4. 发明申请

US20140147264A1 TURBINE ENGINE STATOR WHEEL AND A TURBINE OR A COMPRESSOR INCLUDING SUCH A STATOR WHEEL 有权
标题翻译：涡轮发动机定子轮和涡轮机或包括这种定子轮的压缩机
公开(公告)号：US20140147264A1
公开(公告)日：2014-05-29
申请号：US14234268
申请日：2012-07-18
申请人： Olivier Belmonte , Antoine Jean-Philippe Beaujard
发明人： Olivier Belmonte , Antoine Jean-Philippe Beaujard
IPC分类号： F01D9/04
CPC分类号： F01D9/04 , F01D9/042 , F01D25/246 , F05D2300/21 , F05D2300/222 , F05D2300/603 , F05D2300/6033 , Y02T50/672 , Y02T50/673
摘要： A turbine nozzle comprises a plurality of composite material vanes, each vane comprising an inner platform, an outer platform with attachment tabs on the outside, and at least one airfoil extending between the inner and outer platforms and secured thereto. The attachment tabs of the vanes are engaged on a metal assembly ring supporting all of the vanes, extending continuously along the outer platforms of adjacent vanes, and forming a distinct assembly part between the vanes and a turbine casing.
摘要翻译：涡轮喷嘴包括多个复合材料叶片，每个叶片包括内平台，在外部具有附接凸片的外平台以及在内平台和外平台之间延伸并固定到其上的至少一个翼型件。叶片的附接突片接合在支撑所有叶片的金属组件环上，沿着相邻叶片的外平台连续延伸，并且在叶片和涡轮壳体之间形成不同的组件部分。

5. 发明授权

US08616853B2 Stator vane for 3D composite blower 有权
标题翻译：三维复合风机定子叶片
公开(公告)号：US08616853B2
公开(公告)日：2013-12-31
申请号：US13003436
申请日：2009-07-09
申请人： Olivier Belmonte , Jean Noel Mahieu , Xavier Millier
发明人： Olivier Belmonte , Jean Noel Mahieu , Xavier Millier
IPC分类号： F04D29/38 , F01D5/14
CPC分类号： B29C70/24 , B29B11/16 , B29C70/443 , B29C70/48 , B29L2031/08 , D03D25/005 , D10B2505/02 , F01D5/28 , F04D29/023 , F04D29/542 , F04D29/646 , F05D2230/20 , F05D2240/12 , F05D2240/80 , F05D2300/6012 , F05D2300/603 , Y10T29/49321 , Y10T29/49336 , Y10T29/49337
摘要： A method of fabricating a guide vane. The method produces a fiber preform by 3D weaving a single piece, the preform including a first portion extending along the longitudinal axis and constituting the preform for an airfoil of the vane, and at a longitudinal end of the first portion, a second portion constituting the preform for the platform of the vane, the second portion being produced as a first layer and a second layer facing the first layer and separated from the first layer by unlinking without cutting while producing the preform; folding the first and second layers such that each of them lies in a plane perpendicular to the longitudinal axis, substantially symmetrically to each other relative to the first portion, and such that a first region of the first layer covers a second region of the second layer in front of a front edge of the first portion; conforming the preform in a mold; and densifying the preform with a polymer matrix.
摘要翻译：一种制造导向叶片的方法。该方法通过3D编织单件来生产纤维预成型件，预型件包括沿着纵向轴线延伸的第一部分，并且构成用于叶片翼型的预成型件，并且在第一部分的纵向端部处构成第二部分预制件用于叶片的平台，第二部分被制造为第一层，第二层面向第一层，并且在制造预制件的同时通过解除连接而与第一层分离; 折叠第一和第二层，使得它们中的每一个位于垂直于纵向轴线的平面中，相对于第一部分基本上彼此对称，并且使得第一层的第一区域覆盖第二层的第二区域在第一部分的前边缘的前面; 使预成型件在模具中保持一致; 并用聚合物基质致密预成型体。

6. 发明申请

US20130133194A1 METHOD OF FABRICATING A TURBINE ENGINE DRUM 有权
标题翻译：制造涡轮发动机气缸的方法
公开(公告)号：US20130133194A1
公开(公告)日：2013-05-30
申请号：US13814375
申请日：2011-07-20
申请人： Olivier Belmonte , Lionel Rene, Henri Weller
发明人： Olivier Belmonte , Lionel Rene, Henri Weller
IPC分类号： B23P19/00
CPC分类号： B23P19/00 , B23K20/129 , B23K2101/001 , B23K2103/26 , B23P15/006 , F01D5/063 , F05D2230/232 , Y02T50/673 , Y10T29/49229
摘要： A method of fabricating a turbine engine drum including at least two rotor disks, the method including: positioning the two disks on a common axis spaced apart from each other and in a predetermined angular position relative to each other; placing a wall forming a body of revolution between the two disks coaxially about their common axis; driving the wall in rotation about its axis; and moving the disks axially towards the wall so as to put the disks into contact with ends of the wall and thus welding the disks to the wall by inertial friction welding.
摘要翻译：一种制造包括至少两个转子盘的涡轮引擎鼓的方法，所述方法包括：将所述两个盘彼此间隔开并且相对于彼此以预定的角度位置定位在公共轴上; 将两个盘之间的旋转体在它们的公共轴线上同轴地放置成一个壁; 驱动围绕其轴旋转的壁; 并且将盘向轴向移动到壁上，以便将盘与壁的端部接触，从而通过惯性摩擦焊接将盘焊接到壁上。

7. 发明申请

US20110255983A1 DEVICE FOR ATTACHING HAMMER CLAMP BLADES, ASSOCIATED COMPRESSOR HUB, COMPRESSOR AND TURBINE ENGINE 有权
标题翻译：用于连接HAMMER夹紧刀片，相关压缩机座，压缩机和涡轮发动机的装置
公开(公告)号：US20110255983A1
公开(公告)日：2011-10-20
申请号：US13141586
申请日：2009-12-01
申请人： Olivier Belmonte , Franck Emmanuel Bosco
发明人： Olivier Belmonte , Franck Emmanuel Bosco
IPC分类号： F01D5/30
CPC分类号： F01D5/3038 , F01D5/32 , Y02T50/673
摘要： The invention relates to a locking device for enabling the circular locking of a set of blades provided with a hammer base (5) on the rim of a turbine engine compressor hub (3), said rim comprising a peripheral groove (4) on the outer surface thereof for receiving the bases (5) of the blades of said set and two shoulders (7) framing said groove with surfaces which form bearings for holding said blades, said rim also comprising a cut-out (8) provided in at least one of said shoulders (7) to enable the bases (5) of the blades to be inserted in said groove (4), said device comprising a means (10) for translatably immobilising the blades in said groove, suitable for being positioned in said groove (4) between two consecutive blades and in turn translatably held in said groove by an attachment means, characterised in that said carrier is shaped so as to fit into said cut-out (8) and to rest circumferentially on at least one engagement surface (9a, 9b) of said shoulder (7).
摘要翻译：本发明涉及一种锁定装置，用于能够在涡轮发动机压缩机毂（3）的轮辋上设置有锤槌基座（5）的一组叶片的圆形锁定，所述轮辋包括在外侧的周向槽（4）用于接收所述组件的叶片的基部（5）的表面和两个肩部（7），所述两个肩部（7）用形成用于保持所述叶片的轴承的表面构成所述凹槽，所述边缘还包括切口（8），设置在至少一个的所述肩部（7）上以使得所述刀片的基部（5）能够插入所述凹槽（4）中，所述装置包括用于可移动地固定所述凹槽中的刀片的装置（10），适于定位在所述凹槽（4），并且通过附接装置可转动地保持在所述凹槽中，其特征在于，所述托架成形为适合于所述切口（8）并且周向地搁置在至少一个接合表面（ 9a，9b）。

8. 发明申请

US20110223008A1 TURBINE ENGINE FAN COMPRISING A BALANCING SYSTEM WITH BLIND HOLES FOR ACCOMMODATING MASSES 有权
标题翻译：涡轮发动机风扇，包含用于容纳质量的带有盲孔的平衡系统
公开(公告)号：US20110223008A1
公开(公告)日：2011-09-15
申请号：US13131500
申请日：2009-12-09
申请人： Olivier Belmonte , Lionel Rene Henri Weller
发明人： Olivier Belmonte , Lionel Rene Henri Weller
IPC分类号： F01D25/04
CPC分类号： F02C7/04 , F01D5/027 , F04D29/662 , F05D2200/00 , Y02T50/671 , Y02T50/673
摘要： A fan for an aircraft turbine engine, including an intake cone including a balancing system including a plurality of mass accommodation holes and at least one balancing mass mounted in one of the holes. The balancing system further includes an attachment mechanism exerting pressure that flattens the balancing mass against the bottom of its mass accommodation hole, the accommodation hole being made blind in the intake cone, so as to open out inside the intake cone.
摘要翻译：一种用于飞机涡轮发动机的风扇，包括进气锥体，该进气锥体包括平衡系统，该平衡系统包括多个质量容纳孔和安装在其中一个孔中的至少一个平衡块。平衡系统还包括施加压力的附接机构，所述压力使平衡块相对于其质量容纳孔的底部平坦化，所述容纳孔在进气锥体中被制成盲形，以便在进气锥体内部打开。

9. 发明申请

US20110110787A1 STATOR VANE FOR 3D COMPOSITE BLOWER 有权
标题翻译：三维复合鼓风机定子槽
公开(公告)号：US20110110787A1
公开(公告)日：2011-05-12
申请号：US13003436
申请日：2009-07-09
申请人： Olivier Belmonte , Jean Noel Mahieu , Xavier Millier
发明人： Olivier Belmonte , Jean Noel Mahieu , Xavier Millier
IPC分类号： B64C27/46 , B23P15/04
CPC分类号： B29C70/24 , B29B11/16 , B29C70/443 , B29C70/48 , B29L2031/08 , D03D25/005 , D10B2505/02 , F01D5/28 , F04D29/023 , F04D29/542 , F04D29/646 , F05D2230/20 , F05D2240/12 , F05D2240/80 , F05D2300/6012 , F05D2300/603 , Y10T29/49321 , Y10T29/49336 , Y10T29/49337
摘要： A method of fabricating a guide vane. The method produces a fiber preform by 3D weaving a single piece, the preform including a first portion extending along the longitudinal axis and constituting the preform for an airfoil of the vane, and at a longitudinal end of the first portion, a second portion constituting the preform for the platform of the vane, the second portion being produced as a first layer and a second layer facing the first layer and separated from the first layer by unlinking without cutting while producing the preform; folding the first and second layers such that each of them lies in a plane perpendicular to the longitudinal axis, substantially symmetrically to each other relative to the first portion, and such that a first region of the first layer covers a second region of the second layer in front of a front edge of the first portion; conforming the preform in a mold; and densifying the preform with a polymer matrix.
摘要翻译：一种制造导向叶片的方法。该方法通过3D编织单件来生产纤维预成型件，预型件包括沿着纵向轴线延伸的第一部分，并且构成用于叶片翼型的预成型件，并且在第一部分的纵向端部处构成第二部分预制件用于叶片的平台，第二部分被制造为第一层，第二层面向第一层，并且在制造预制件的同时通过解除连接而与第一层分离; 折叠第一和第二层，使得它们中的每一个位于垂直于纵向轴线的平面中，相对于第一部分基本上彼此对称，并且使得第一层的第一区域覆盖第二层的第二区域在第一部分的前边缘的前面; 使预成型件在模具中保持一致; 并用聚合物基质致密预成型体。

10. 发明申请

US20080075588A1 DEVICE FOR ATTACHING A STATOR VANE TO A TURBOMACHINE ANNULAR CASING, TURBOJET ENGINE INCORPORATING THE DEVICE AND METHOD FOR MOUNTING THE VANE 有权
标题翻译：用于将定位翼连接到涡轮机环形壳体的装置，装有该装置的涡轮发动机和用于安装风门的方法
公开(公告)号：US20080075588A1
公开(公告)日：2008-03-27
申请号：US11861873
申请日：2007-09-26
申请人： Olivier BELMONTE
发明人： Olivier BELMONTE
IPC分类号： F01D1/02 , B23P11/00 , F04D29/54
CPC分类号： F01D9/042 , F04D29/542 , F04D29/644 , Y02T50/672 , Y10T29/49321 , Y10T29/49947
摘要： The present invention relates to a device for attaching a turbomachine stator vane in an annular casing (20) of the turbomachine, the vane comprising a tip formed of a platform (14) with two edges (141, 142), one of them forming an upstream edge (141) and the other forming a downstream edge (142), an airfoil (11) and a root (13), the annular casing (20) comprising a circumferential groove (23) formed in its interior wall with an upstream flank (21) and a downstream flank (22), the vane being held by engagement of the platform (14) in the groove (23), the upstream edge against the upstream flank (21) and the downstream edge (142) against the downstream flank (22) of the groove (23), the downstream flank (22) of the groove (23) being in the form of a slot (22) opening axially in the upstream direction, the downstream edge of the platform (23) being engaged in said downstream flank (22) and a fastening means (40) being attached in order to hold the platform (14) in the groove on the upstream side, wherein the vane comprises a portion of platform (14) between the airfoil (11) and the upstream edge, this portion being pierced with a through-hole (17) designed to accept said fastening means (40).
摘要翻译：本发明涉及一种用于将涡轮机定子叶片附接在涡轮机的环形壳体（20）中的装置，该叶片包括由具有两个边缘（141,142）的平台（14）形成的尖端，其中一个形成一个上游边缘（141），另一个形成下游边缘（142），机翼（11）和根部（13），所述环形壳体（20）包括在其内壁中形成有周向凹槽（23）（21）和下游侧翼（22），所述叶片通过所述平台（14）在所述凹槽（23）中的接合而保持，所述上游边缘抵抗所述上游侧面（21）和所述下游边缘（142）抵靠所述下游侧槽（23）的侧面（22），槽（23）的下游侧面（22）为沿上游方向轴向开口的槽（22）的形式，平台（23）的下游边缘为接合在所述下游侧面（22）中，并且紧固装置（40）被连接以便于安装 d在上游侧的凹槽中的平台（14），其中叶片包括在翼型件（11）和上游边缘之间的一部分平台（14），该部分用通孔（17）刺穿，该通孔设计成接受所述紧固装置（40）。

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