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1. 发明申请

US20050005607A1 System for sealing the secondary flow at the inlet to a nozzle of a turbomachine having a post-combustion chamber 有权
标题翻译：用于将具有后燃烧室的涡轮机的喷嘴的入口处的二次流密封的系统
公开(公告)号：US20050005607A1
公开(公告)日：2005-01-13
申请号：US10847864
申请日：2004-05-19
申请人： Guy Lapergue , Guillaume Sevi , Jacques Roche
发明人： Guy Lapergue , Guillaume Sevi , Jacques Roche
IPC分类号： F02C7/28 , F02C7/12 , F02C7/18 , F02C7/24 , F02K1/80 , F02K1/82 , F16J15/08 , F02K1/00
CPC分类号： F02K1/805 , F02K1/822 , F05D2260/10 , F16J15/0887 , Y02T50/675
摘要： The invention relates to an aviation turbomachine comprising, downstream from the turbine, a post-combustion chamber extended by at least one nozzle, said chamber being defined radially by a thermal protection lining disposed inside a casing, said casing and said lining together defining an annular channel in which, in operation, there flows a secondary flow, an annular diaphragm secured to said casing being disposed at the downstream end of said channel, said nozzle comprising a plurality of flaps hinged to the upstream end of said casing, each flap being fitted on its inside face with a thermal protection plate co-operating with said flap to define a passage for being fed with cooling air delivered by said diaphragm, wherein the feed of cooling air to said passages is provided by an annular duct defined on the outside by a first flexible annular gasket retained, in operation, pressed in sliding contact against the downstream inside face of the casing and against the upstream inside faces of the flaps under urging from the pressure of the secondary flow, and defined on the inside by a second flexible annular gasket whose upstream end is fixed to the radially inner zone of the diaphragm, and whose downstream end is pressed in sliding contact against the upstream inside face of the protection plates.
摘要翻译：本发明涉及一种航空涡轮机，包括在涡轮的下游，由至少一个喷嘴延伸的后燃烧室，所述室由设置在壳体内部的热保护衬套径向地限定，所述壳体和所述衬套一起限定环形通道，其中在操作中流动二次流动，固定到所述壳体的环形隔膜设置在所述通道的下游端，所述喷嘴包括铰接到所述壳体的上游端的多个翼片，每个翼片装配在其内表面上具有与所述翼片配合的热保护板，以限定用于供给由所述隔膜输送的冷却空气的通道，其中向所述通道供应的冷却空气由外部限定的环形管道在操作中保持第一柔性环形垫圈，以与壳体的下游内表面滑动接触并抵靠在f的上游内侧在二次流动的压力作用下，翼片的侧面由第二柔性环形垫片限定在内侧，第二柔性环形垫片的上游端固定在隔膜的径向内部区域，并且其下游端被压靠在隔膜保护板的上游内侧面。

2. 发明授权

US06966189B2 System for sealing the secondary flow at the inlet to a nozzle of a turbomachine having a post-combustion chamber 有权
标题翻译：用于将具有后燃烧室的涡轮机的喷嘴的入口处的二次流密封的系统
公开(公告)号：US06966189B2
公开(公告)日：2005-11-22
申请号：US10847864
申请日：2004-05-19
申请人： Guy Lapergue , Guillaume Sevi , Jacques Roche
发明人： Guy Lapergue , Guillaume Sevi , Jacques Roche
IPC分类号： F02C7/28 , F02C7/12 , F02C7/18 , F02C7/24 , F02K1/80 , F02K1/82 , F16J15/08 , F02K1/12
CPC分类号： F02K1/805 , F02K1/822 , F05D2260/10 , F16J15/0887 , Y02T50/675
摘要： A turbomachine comprising, downstream from the turbine, a post-combustion chamber defined by a thermal protection lining inside a casing defining an annular channel for a secondary flow, an annular diaphragm secured at the downstream end of said channel, said nozzle comprising a plurality of flaps hinged to the upstream end of said casing, each flap fitted on its inside face with a thermal protection plate to define a passage for cooling air delivered by said diaphragm, wherein the cooling air is provided by an annular duct defined by a first flexible annular gasket in sliding contact against the downstream inside face of the casing and against the upstream inside faces of the flaps under the pressure of the secondary flow, and defined on the inside by a second flexible annular gasket whose upstream end is fixed to the radially inner zone of the diaphragm, and whose downstream end is in sliding contact against the upstream inside face of the protection plates.
摘要翻译：一种涡轮机，包括在涡轮下游的由燃烧室内限定的用于二次流的环形通道限定的后燃烧室，固定在所述通道的下游端的环形隔膜，所述喷嘴包括多个翼片铰接到所述壳体的上游端，每个翼片在其内表面上安装有热保护板，以限定用于冷却由所述隔膜输送的空气的通道，其中所述冷却空气由第一柔性环形衬垫与壳体的下游内表面滑动接触，并且在二次流动的压力下抵靠翼片的上游内表面，并且通过第二柔性环形垫圈限定在内侧，第二柔性环形垫圈的上游端固定到径向内部区域并且其下游端与保护板的上游内表面滑动接触。

3. 发明授权

US07520135B2 Variable-section turbomachine nozzle 有权
标题翻译：可变截面涡轮机喷嘴
公开(公告)号：US07520135B2
公开(公告)日：2009-04-21
申请号：US11248330
申请日：2005-10-13
申请人： Mathieu Dakowski , Guy Lapergue , Romain Lunel , Guillaume Sevi
发明人： Mathieu Dakowski , Guy Lapergue , Romain Lunel , Guillaume Sevi
IPC分类号： F02K1/12
CPC分类号： F02K1/1207
摘要： A variable-section turbomachine nozzle comprises a plurality of moving flaps, and a moving flap control system comprising control levers each associated with a respective moving flap, the control levers comprising both controlled levers that are actuated directly by actuators, and follower levers that are actuated by the controlled levers via transmission links. When the nozzle is at rest, the flaps associated with the follower levers present a radial offset relative to the flaps associated with the controlled levers.
摘要翻译：可变截面涡轮机喷嘴包括多个移动翼片，以及包括各自与相应的活动翼片相关联的控制杆的移动翼片控制系统，所述控制杆包括由致动器直接致动的受控杆和致动器的从动杆通过控制杆通过传输链路。当喷嘴处于静止状态时，与从动杆相关联的翼片相对于与受控杆相关的翼片呈现径向偏移。

4. 发明申请

US20060090470A1 Variable-section turbomachine nozzle 有权
公开(公告)号：US20060090470A1
公开(公告)日：2006-05-04
申请号：US11248330
申请日：2005-10-13
申请人： Mathieu Dakowski , Guy Lapergue , Romain Lunel , Guillaume Sevi
发明人： Mathieu Dakowski , Guy Lapergue , Romain Lunel , Guillaume Sevi
IPC分类号： F02K1/12
CPC分类号： F02K1/1207
摘要： A variable-section turbomachine nozzle comprises a plurality of moving flaps, and a moving flap control system comprising control levers each associated with a respective moving flap, the control levers comprising both controlled levers that are actuated directly by actuators, and follower levers that are actuated by the controlled levers via transmission links. When the nozzle is at rest, the flaps associated with the follower levers present a radial offset relative to the flaps associated with the controlled levers.

5. 发明授权

US07322181B2 Turbofan engine with the fan fixed to a drive shaft supported by a first and a second bearing 有权
标题翻译：涡轮风扇发动机，其风扇固定到由第一和第二轴承支撑的驱动轴上
公开(公告)号：US07322181B2
公开(公告)日：2008-01-29
申请号：US11041996
申请日：2005-01-26
申请人： Guy Lapergue , Regis Servant , Gael Bouchy
发明人： Guy Lapergue , Regis Servant , Gael Bouchy
IPC分类号： F02K3/02
CPC分类号： F01D21/04 , F01D25/16
摘要： The turbojet includes a fixed structure, a fan rotor fixed to a drive shaft supported by a first bearing and a second bearing. The second bearing is mounted on the fixed structure through a bearing support part. The first bearing is mounted on the fixed structure of the turbojet through a device enabling it to be decoupled from the fixed structure. The second bearing is mounted on the bearing support part through a link acting as a ball joint. The turbojet also allows axial displacements of the second bearing with respect to the fixed structure of the turbojet if the first bearing should be decoupled. The centering function of the second bearing after decoupling of the first bearing is thus provided without introducing excessive stresses in the bearing.
摘要翻译：涡轮喷气发动机包括固定结构，固定到由第一轴承和第二轴承支撑的驱动轴的风扇转子。第二轴承通过轴承支撑部件安装在固定结构上。第一轴承通过装置安装在涡轮喷气发动机的固定结构上，使其能够与固定结构分离。第二轴承通过作为球窝接头的连杆安装在轴承支撑部件上。涡轮喷气发动机还允许第二轴承相对于涡轮喷气发动机的固定结构的轴向位移，如果第一轴承应该被分离。因此，在第一轴承解耦之后第二轴承的定中心功能不会在轴承中引入过大的应力。

6. 发明申请

US20050247526A1 Device for lubricating a component in an assembly of parts 有权
标题翻译：用于润滑部件组件中的部件的装置
公开(公告)号：US20050247526A1
公开(公告)日：2005-11-10
申请号：US11113049
申请日：2005-04-25
申请人： Regis Servant , Gael Bouchy , Guy Lapergue
发明人： Regis Servant , Gael Bouchy , Guy Lapergue
IPC分类号： F01D25/16 , F02C7/06 , F16N7/22 , F16C1/24
CPC分类号： F01D25/18 , F16C19/06 , F16C33/6659 , F16C33/6677 , F16C35/042 , F16C2360/23
摘要： A device for lubricating a component in an assembly of parts comprises a lubricant distribution chamber arranged in the vicinity of the component and formed by an annular setback in a ring mounted on a part of the assembly, said setback being closed automatically when the ring is mounted by means of a corresponding surface of the part into which there open out channels or ducts formed in the part and feeding the setback with lubricant and/or connecting the setback to means for taking lubricant to the component.
摘要翻译：用于润滑部件组件中的部件的装置包括布置在部件附近并由安装在组件的一部分上的环中的环形挫折形成的润滑剂分配室，当安装环时，所述挫折被自动关闭通过部件的对应表面，其中打开形成在部件中的通道或管道，并将润滑剂供给挫折和/或将挫折连接到用于将润滑剂用于部件的装置。

7. 发明申请

US20050060984A1 Convergent-divergent turbojet nozzle 有权
标题翻译：收敛发散型涡轮喷嘴
公开(公告)号：US20050060984A1
公开(公告)日：2005-03-24
申请号：US10915446
申请日：2004-08-11
申请人： Jackie Prouteau , Raphael Curtelin , Guy Lapergue , Didier Feder
发明人： Jackie Prouteau , Raphael Curtelin , Guy Lapergue , Didier Feder
IPC分类号： F02C7/18 , F02K1/12 , F02K1/82 , F02K1/06
CPC分类号： F02K1/1223 , F02K1/822 , Y02T50/675
摘要： The present invention relates to a convergent-divergent turbojet nozzle (1) comprising driven divergent flaps (4a), follower divergent flaps (4b) interposed between the driven flaps, and means (32) for supplying cooling air to the follower flaps (4b), said follower flaps (4b) having a box structure and having lateral openings for delivering cooling air towards the inner face of said driven flaps (4a), in such a way as to limit the heating up of these flaps when the turbojet is in operation.
摘要翻译：本发明涉及一种会聚发散涡轮喷嘴（1），包括被驱动的发散翼片（4a），介于驱动翼片之间的从动发散翼片（4b）和用于向随动翼片（4b）供应冷却空气的装置（32）所述随动翼片（4b）具有盒结构，并且具有用于将冷却空气朝向所述从动翼片（4a）的内表面传送的侧向开口，以便当涡轮喷气发动机运行时限制这些翼片的加热。

8. 发明授权

US07340882B2 Turbomachine with means for axial retention of the rotor 有权
标题翻译：涡轮机具有用于轴向保持转子的装置
公开(公告)号：US07340882B2
公开(公告)日：2008-03-11
申请号：US11149214
申请日：2005-06-10
申请人： Guy Lapergue , Regis Servant , Gael Bouchy , Alain Baum
发明人： Guy Lapergue , Regis Servant , Gael Bouchy , Alain Baum
IPC分类号： F02C7/06
CPC分类号： F01D21/045 , F01D25/16
摘要： The turbomachine of the invention extends longitudinally along an axis, and includes a rotor attached to drive shaft, arranged to rotate around an axis, supported by at least a first bearing, mounted on the fixed structure of the turbomachine by a bearing support element. The turbomachine is characterised by the fact that it includes a stop ring, mounted on the fixed structure of the turbomachine, to cooperate with the support element of the first bearing and, in the event of displacement of the rotor in relation to the fixed structure, to perform a function of axial retention of the rotor in an even manner, with no angle effect between the axis of the turbomachine and the axis of the drive shaft.
摘要翻译：本发明的涡轮机器沿着轴线纵向延伸，并且包括附接到驱动轴的转子，该转子被布置为通过轴承支撑元件围绕安装在涡轮机的固定结构上的至少第一轴承支承的轴旋转。涡轮机的特征在于它包括安装在涡轮机的固定结构上的止动环，以与第一轴承的支撑元件配合，并且在转子相对于固定结构移位的情况下，以均匀的方式执行转子的轴向保持的功能，在涡轮机的轴线和驱动轴的轴线之间没有角度影响。

9. 发明授权

US07296397B2 Ventilation system for a convergent divergent exhaust nozzle 有权
标题翻译：用于收敛发散排气喷嘴的通风系统
公开(公告)号：US07296397B2
公开(公告)日：2007-11-20
申请号：US10945917
申请日：2004-09-22
申请人： Raphael Curtelin , Marc Doussinault , Guy Lapergue , Didier Durand
发明人： Raphael Curtelin , Marc Doussinault , Guy Lapergue , Didier Durand
IPC分类号： F02K1/12 , F02K1/82
CPC分类号： F01D9/065 , F01D9/06 , F02K1/1223 , F02K1/30 , F02K1/80 , F02K1/822 , Y02T50/675
摘要： The invention relates to a ventilation system for a convergent divergent exhaust nozzle in a bypass turbojet comprising an afterburn chamber surrounded by an annular passage through which circulates a stream of cooling air, a convergent divergent axisymmetric nozzle arranged downstream of said afterburn chamber, each circle of flaps comprising alternately a plurality of controlled flaps, and a plurality of follower flaps, a circle of cold flaps arranged radially outside said nozzle and hinged at their upstream end to a conical shell linked to the downstream part of the casing. The means of cooling the divergent flaps comprise an annular plenum chamber delimited downstream by said conical shell and fed with cooling air through drillings made in a boundary wall between said plenum chamber and the downstream end of said annular passage, a plurality of distribution cells surrounding the plenum chamber and linked to the latter, said cells being delimited downstream by said conical shell and being arranged around the X axis in the planes of symmetry of the follower flaps and telescopic pipelines each linking a cell to the follower divergent flap situated in the same plane of symmetry as said cell.
摘要翻译：本发明涉及一种用于旁路涡轮喷气发动机中的会聚发散排气喷嘴的通风系统，其包括由环形通道围绕的再燃烧室，循环冷却空气流，位于所述再燃烧室下游的会聚发散轴对称喷嘴，交替地包括多个受控翼片的翼片和多个从动翼片，一排冷却翼片，其径向设置在所述喷嘴的外侧，并在其上游端铰接到与壳体的下游部分连接的锥形壳体。冷却发散板的装置包括一个由所述锥形壳体在下游限定的环形增压室，并且通过在所述增压室和所述环形通道的下游端之间的边界壁中形成的钻孔供给冷却空气，所述细胞在所述锥形壳体的下游被限定在下游，并且在随动翼片和伸缩管线的对称平面中绕X轴布置，每个将细胞连接到位于同一平面中的从动发散片的对称性作为所述细胞。

10. 发明授权

US07213393B2 Device for supplying cooling air to exhaust nozzle flaps 有权
标题翻译：用于向排气喷嘴襟翼供应冷却空气的装置
公开(公告)号：US07213393B2
公开(公告)日：2007-05-08
申请号：US11025910
申请日：2005-01-03
申请人： Guy Lapergue , Raphael Curtelin , Didier Feder
发明人： Guy Lapergue , Raphael Curtelin , Didier Feder
IPC分类号： F02K1/12
CPC分类号： F02K1/1223 , F02K1/822 , F05D2260/20 , Y02T50/675
摘要： A device for supplying cooling air to a hollow flap of an exhaust nozzle in a turbojet engine. The device includes a tube connecting the hollow flap to a cooling air source. The tube comprises at least one telescopic portion and at least one ball-joint connection.
摘要翻译：一种用于向涡轮喷气发动机的排气喷嘴的中空翼片供给冷却空气的装置。该装置包括将中空翼片连接到冷却空气源的管子。该管包括至少一个伸缩部分和至少一个球形接头连接。

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