专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

US20230133871A1 AIRCRAFT TURBINE ENGINE WITH AN OFF-AXIS PROPELLER 有权
公开(公告)号：US20230133871A1
公开(公告)日：2023-05-04
申请号：US17932934
申请日：2022-09-16
申请人： Paul Ghislain Albert LEVISSE , Julien Fabien Patrick BECOULET , Guillaume Pierre MOULY , Patrice Jocelyn Francis GEDIN , Olivier BELMONTE
发明人： Paul Ghislain Albert LEVISSE , Julien Fabien Patrick BECOULET , Guillaume Pierre MOULY , Patrice Jocelyn Francis GEDIN , Olivier BELMONTE
IPC分类号： F02C7/36
摘要： An aircraft turbine engine includes a turbine shaft having a first axis of rotation, a propulsion propeller having a second axis of rotation parallel to and spaced from the first axis, and a mechanical reduction gear coupled to the turbine shaft and rotating the propeller. The reduction gear has a sun gear connected to the turbine shaft, a ring gear, and at least two planet gears, each including a first external toothing that is meshed with an external toothing of the sun gear. A second external toothing is located within the ring gear and is meshed with an internal toothing of the ring gear.

2. 发明申请

US20080226457A1 TURBOMACHINE ROTOR DISK 有权
标题翻译：涡轮转子盘
公开(公告)号：US20080226457A1
公开(公告)日：2008-09-18
申请号：US12048726
申请日：2008-03-14
申请人： Olivier BELMONTE
发明人： Olivier BELMONTE
IPC分类号： F01D5/02
CPC分类号： F04D29/322 , F01D5/3007 , F01D5/3092 , F01D5/323 , F04D29/644
摘要： A turbomachine rotor disk (32) comprising inter-blade platforms (44) fixed to ribs (16) delimited by cavities (14) in which blade roots (20) are retained, and protective liners (30) mounted between the flanks of the cavities (14) of the disk (32) and the blade roots (20), wherein the protective liners (30) have a C-shaped cross section so that they can be fitted translationally and retained radially on the ribs (16) of the disk (32) and constitute means of locking the platforms (44) on the ribs (16) of the disk (32).
摘要翻译：涡轮机转子盘（32），其包括固定到由空腔（14）限定的肋（16）的刀片间平台（44），叶片根部（20）保持在其中;以及保护衬套（30），其安装在所述腔（32）的叶片（14）和叶根（20），其中保护衬垫（30）具有C形横截面，使得它们可以平移地并且径向地保持在盘的肋（16）上（32），并且构成将平台（44）锁定在盘（32）的肋（16）上的装置。

3. 发明申请

US20090004017A1 SPACER INTERPOSED BETWEEN A BLADE ROOT AND THE BOTTOM OF A SLOT IN THE DISK IN WHICH THE BLADE IS MOUNTED 有权
标题翻译：叶片与刀片之间的间隙与刀片底部之间的间隙
公开(公告)号：US20090004017A1
公开(公告)日：2009-01-01
申请号：US12144974
申请日：2008-06-24
申请人： Olivier BELMONTE , Jean-Luc Christian Yvon GOGA , Jean-Noel MAHIEU
发明人： Olivier BELMONTE , Jean-Luc Christian Yvon GOGA , Jean-Noel MAHIEU
IPC分类号： F01D5/30 , F01D5/02
CPC分类号： F01D5/303 , F01D5/3092 , F04D29/322 , F04D29/666 , F04D29/668
摘要： Wedging blades attached to the disk of a rotor having slots. According to the invention, each wedging spacer is made of an elastically deformable material and at least one longitudinal segment of the spacer presents a transverse profile of arcuate shape to define two lateral contact zones.
摘要翻译：附接到具有槽的转子盘的楔形叶片。根据本发明，每个楔形间隔件由可弹性变形的材料制成，并且间隔件的至少一个纵向段呈现弓形形状的横向轮廓以限定两个横向接触区域。

4. 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）。

5. 发明申请

US20100046868A1 BEARING SUPPORT JOURNAL AND ASSEMBLY OF SUCH A JOURNAL AND A SEALING SLEEVE 有权
标题翻译：轴承支持期刊和这样一个日记和一个密封套
公开(公告)号：US20100046868A1
公开(公告)日：2010-02-25
申请号：US12478281
申请日：2009-06-04
申请人： Olivier BELMONTE , Franck Emmanuel Bosco , Dimitri Alain Fauron , Lionel Rene Henri Weller
发明人： Olivier BELMONTE , Franck Emmanuel Bosco , Dimitri Alain Fauron , Lionel Rene Henri Weller
IPC分类号： F16C33/10
CPC分类号： F01D25/24 , F02C7/28
摘要： A bearing support journal (100) for an internal shaft of a gas turbine engine comprising a means of retaining a sealing sleeve surrounding said shaft, the retaining means comprising: a full radial annular flange (132) formed upstream on an axial cylindrical part (130) of the journal (100), said full flange (132) being intended to butt axially against a radial annular flange of the sealing sleeve, and tangential means (135) of immobilizing the sealing sleeve with respect to the journal (100), these being created downstream on the axial cylindrical part (130) of the journal (100). The invention also relates to assembly of a journal (100) and of a sealing sleeve.
摘要翻译：一种用于燃气涡轮发动机的内轴的轴承支撑轴颈（100），其包括保持围绕所述轴的密封套筒的装置，所述保持装置包括：形成在轴向圆柱形部件（130）上游的全径向环形凸缘（132）），所述完整凸缘（132）旨在与所述密封套筒的径向环形凸缘轴向对接，以及相对于所述轴颈（100）固定所述密封套筒的切向装置（135），这些在轴颈（100）的轴向圆柱形部分（130）上形成下游。本发明还涉及轴颈（100）和密封套筒的组装。

6. 发明申请

US20090028717A1 FAN BLADE 有权
标题翻译：风机叶片
公开(公告)号：US20090028717A1
公开(公告)日：2009-01-29
申请号：US12055615
申请日：2008-03-26
申请人： Olivier BELMONTE , Amadou Lamine M'Bengue
发明人： Olivier BELMONTE , Amadou Lamine M'Bengue
IPC分类号： F01D5/14
CPC分类号： F04D19/022 , F01D5/146 , F01D5/147 , F05D2220/326 , F05D2220/327 , Y02T50/671 , Y02T50/673
摘要： The present invention relates to the field of blades, particularly fan blades, intended for turbojets, particularly of the aeronautical type.Its objective is to provide a fan blade the features of which will enable the number of fan blades to be reduced while at the same time providing satisfactory performance.According to the invention, the fan blade comprises a plurality of aerodynamic parts which are superposed in a radial direction Z and the number of aerodynamic profiles varies from one aerodynamic part to the other.
摘要翻译：本发明涉及用于涡轮喷气发动机，特别是航空类型的叶片领域，特别是风扇叶片领域。其目的是提供一种风扇叶片，其特征在于能够减少风扇叶片的数量，同时提供令人满意的性能。根据本发明，风扇叶片包括多个空气动力部件，它们沿径向Z重叠，并且空气动力学轮廓的数量从一个空气动力部分变化到另一个。

7. 发明申请

US20110239661A1 ROTOR FOR A GAS TURBINE ENGINE COMPRISING A ROTOR SPOOL AND A ROTOR RING 有权
标题翻译：用于包含转子和转子环的气体涡轮发动机的转子
公开(公告)号：US20110239661A1
公开(公告)日：2011-10-06
申请号：US13077033
申请日：2011-03-31
申请人： Olivier BELMONTE , Lionel René Henri Weller
发明人： Olivier BELMONTE , Lionel René Henri Weller
IPC分类号： F02C7/20
CPC分类号： F01D5/06 , F01D5/34
摘要： A one-piece rotor spool (20) for a gas turbine engine extending along the axis of the engine, the spool comprising an upstream portion (20A) and a downstream portion (20B) that are radially offset relative to one another, the radially outer portion (20B) comprising a plurality of housings (24) for rotor blades formed in the outer surface of said radially outer portion (20B), the spool (20) being characterized in that the radially inner portion (20A) comprises attachment means (23) designed to interact with a rotor ring (30) in order to prevent a tangential movement of the rotor ring (30) relative to the radially inner portion (20A).
摘要翻译：一种用于沿着发动机轴线延伸的燃气涡轮发动机的一体式转子线轴（20），所述线轴包括相对于彼此径向偏移的上游部分（20A）和下游部分（20B）部分（20B）包括形成在所述径向外部部分（20B）的外表面中的用于转子叶片的多个壳体（24），所述卷轴（20）的特征在于，所述径向内部部分（20A）包括附接装置）设计成与转子环（30）相互作用，以便防止转子环（30）相对于径向内部部分（20A）的切向运动。

8. 发明申请

US20110058942A1 BALANCING DEVICE AND METHOD 有权
标题翻译：平衡装置和方法
公开(公告)号：US20110058942A1
公开(公告)日：2011-03-10
申请号：US12876716
申请日：2010-09-07
申请人： Olivier BELMONTE , Lucie Galons
发明人： Olivier BELMONTE , Lucie Galons
IPC分类号： F01D25/00 , F16B37/00 , F16B33/00 , G01M1/00
CPC分类号： F16F15/34 , F01D5/027 , F16F15/322 , G01M1/04 , G01M1/34 , Y10T29/49948
摘要： The invention relates to a balancing device comprising a nut 15 having an internal thread, and a countersunk collar 17 integral with said nut 15, said countersunk collar 17 having a through-hole 23 with a diameter greater than the diameter of the internal thread of the nut 15. Said countersunk collar comprises a balancing weight 19. The invention also relates to a method for balancing a rotating part 1 with such a device, and a rotating part 1 balanced by such a device.
摘要翻译：本发明涉及一种平衡装置，其包括具有内螺纹的螺母15和与所述螺母15成一体的埋头圈17，所述埋头圈17具有直径大于所述内螺纹直径的通孔23 螺母15.所述埋头圈包括平衡重物19.本发明还涉及一种用于将旋转部件1与这种装置平衡的方法以及由这种装置平衡的旋转部件1。

9. 发明申请

US20090087313A1 AIRCRAFT TURBOMACHINE FAN COMPRISING A BALANCING FLANGE CONCEALED BY THE INLET CONE 有权
标题翻译：飞机涡轮风扇包含入口锥度所限定的平衡法兰
公开(公告)号：US20090087313A1
公开(公告)日：2009-04-02
申请号：US12193886
申请日：2008-08-19
申请人： Olivier BELMONTE , Jean-Luc Christian Yvon Goga
发明人： Olivier BELMONTE , Jean-Luc Christian Yvon Goga
IPC分类号： F01D5/10
CPC分类号： F04D29/662 , B64C11/14 , F01D5/027 , F02C7/04 , F05D2220/36 , F05D2250/232 , F05D2260/96 , Y02T50/671 , Y02T50/673
摘要： The present invention relates to an aircraft turbomachine fan (1) comprising a turbomachine inlet cone (20) that has an exterior surface (19) intended to be closely followed by a flow section (22) of the turbomachine, an annular balancing flange (34) that rotates as one with a fan disk (4) about an axis of rotation (2) and is equipped with a plurality of weight-fixing holes (24), the fan also comprising one or more balancing weights (26) mounted fixedly on said annular balancing flange. Furthermore, the annular balancing flange (34) is positioned inside the inlet cone (20) in such a way that its weight-fixing holes (24) are isolated from the flow section (22). According to the invention, the flange (34) is produced as a single piece with a fan blade retaining ring (16).
摘要翻译：本发明涉及一种包括涡轮机入口锥体（20）的飞行器涡轮机风扇（1），其具有旨在紧接着涡轮机的流动部分（22）的外表面（19），环形平衡凸缘（34）），其围绕旋转轴线（2）与风扇盘（4）一体旋转，并且配备有多个重量固定孔（24），该风扇还包括固定地安装在其上的一个或多个平衡重块（26）所述环形平衡法兰。此外，环形平衡法兰（34）位于入口锥体（20）的内部，使得其重量固定孔（24）与流动部分（22）隔离。根据本发明，凸缘（34）被制成具有风扇叶片保持环（16）的单件。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式