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1. 发明授权

US4543039A Stator assembly for an axial compressor 失效
标题翻译：轴向压缩机定子总成
公开(公告)号：US4543039A
公开(公告)日：1985-09-24
申请号：US547711
申请日：1983-11-01
申请人： Jean-Pierre Ruis , Marcel R. Soligny
发明人： Jean-Pierre Ruis , Marcel R. Soligny
IPC分类号： F01D9/04 , F01D11/24 , F01D25/26 , F04D29/54 , F04D29/58
CPC分类号： F01D25/26 , F01D11/24 , F01D9/041 , F04D29/542
摘要： A device for attaching the stator vanes of an axial compressor to an external housing is disclosed. The attachment utilizes an inner casing, having the vanes mounted on it, and an outer casing surrounding the inner casing in such a manner that differential thermal expansion between the various elements is minimized. This allows more accurate control of the clearances between the rotor and the stator.
摘要翻译：公开了一种用于将轴向压缩机的定子叶片连接到外部壳体的装置。该附件利用具有安装在其上的叶片的内壳和围绕内壳的外壳，使得各种元件之间的不同热膨胀最小化。这允许更精确地控制转子和定子之间的间隙。

2. 发明授权

US4821758A Turbine plant intake housing 失效
标题翻译：涡轮机植入物室
公开(公告)号：US4821758A
公开(公告)日：1989-04-18
申请号：US124604
申请日：1987-11-24
申请人： Jean-Pierre Ruis
发明人： Jean-Pierre Ruis
IPC分类号： F01D17/16 , F02C7/04
CPC分类号： F01D17/162 , Y10T137/0536
摘要： A turbine plant intake housing includes an outer shell supporting radially extending arms which include a fixed part and a movable flap associated therewith. Each arm is provided with a metal tie rod having its radially outer end fixed between two forks supported by the outer shell, and its radially inner end co-operating with a metal insert embedded in layers of coiled filaments of composite material forming a floating hub supported by the tie rods. The radially inner end of each rod is attached to the insert of the hub by use of a nut which effects a prestressing clamping of the tie rod on assembly.
摘要翻译：涡轮机进口壳体包括支撑径向延伸的臂的外壳，其包括固定部分和与其相关联的活动翼片。每个臂设置有金属拉杆，其金属拉杆的径向外端固定在由外壳支撑的两个叉之间，并且其径向内端与镶嵌有复合材料的卷绕长丝的金属嵌件配合，形成浮动毂，通过拉杆。每个杆的径向内端通过使用在组合件上实现拉杆的预应力夹紧的螺母连接到轮毂的插入件上。

3. 发明申请

US20060236676A1 Swivelling exhaust nozzle for an aircraft engine 有权
公开(公告)号：US20060236676A1
公开(公告)日：2006-10-26
申请号：US11409087
申请日：2006-04-24
申请人： Philippe Bouiller , Michel Franchet , Jean-Pierre Ruis
发明人： Philippe Bouiller , Michel Franchet , Jean-Pierre Ruis
IPC分类号： F02K1/00
CPC分类号： F02K1/006 , F02K1/80 , F05D2300/501 , Y02T50/671
摘要： Swivelling nozzle for an aircraft engine, the nozzle 10 being pivotally mounted about a transverse yaw axis by means of two elastically deformable one-piece articulations 24 mounted on two external pivots 22 of the nozzle and housed in engine case elements, the nozzle being caused to pivot by an actuator 46 mounted on the engine case and connected by a link 50 to a pivot 22 of the nozzle.

4. 发明授权

US06767187B2 Electrohydraulic device for varying the pitch of the blades of a machine rotor 有权
标题翻译：用于改变机器转子叶片间距的电动液压装置
公开(公告)号：US06767187B2
公开(公告)日：2004-07-27
申请号：US10277750
申请日：2002-10-23
申请人： Michel Franchet , Daniel Kettler , Jean-Pierre Ruis
发明人： Michel Franchet , Daniel Kettler , Jean-Pierre Ruis
IPC分类号： F01D700
CPC分类号： F01D7/00 , B64C11/305 , B64C11/38 , B64C11/44 , F04D29/323 , F05D2220/36 , F05D2260/74 , F05D2260/76 , Y02T50/671
摘要： An electrohydraulic device for varying the pitch of the blades of a machine rotor, the blades being mounted on a hub rotated by a drive shaft of the machine, and each blade having a root capable of pivoting about a longitudinal axis of the blade, the drive shaft itself being rotated relative to a stationary structure of the machine, the device comprising firstly a hydraulic actuator whose piston is secured to a control and synchronization ring in which off-center wrist pins are engaged, each fixed in register with one of said blade roots, and having a cylinder closed by a cover that includes a high pressure hydraulic pump feeding hydraulic fluid to both faces of said piston via channels integrated in said cylinder of the actuator, and secondly an electric motor controlled and powered by an electricity generator comprising an inductor secured to said stationary structure of the machine and an armature secured to said drive shaft of the machine.
摘要翻译：一种电动液压装置，用于改变机器转子的叶片的间距，所述叶片安装在由所述机器的驱动轴旋转的轮毂上，并且每个叶片具有能够围绕所述叶片的纵向轴线枢转的根部，所述驱动装置轴本身相对于机器的静止结构旋转，该装置首先包括液压致动器，其活塞被固定到控制和同步环，在该环中偏心中心腕销接合，每个固定与所述叶片根部中的一个对准并且具有由盖封闭的气缸，所述盖包括高压液压泵，其通过集成在所述致动器的所述气缸中的通道将所述活塞的两个面供给到所述活塞的两个面，其次由由发电机控制和供电的电动机，所述发电机包括电感器固定到机器的所述固定结构上，以及固定在机器的所述驱动轴上的电枢。

5. 发明授权

US06164563A Converging exhaust nozzle fitted with translating cold flaps 有权
标题翻译：融合排气喷嘴配有翻转冷襟翼
公开(公告)号：US06164563A
公开(公告)日：2000-12-26
申请号：US356321
申请日：1999-07-16
申请人： Philippe Pierre Vincent Bouiller , Pierre-Yves Bourquin , Fabrice Michel Olivier Cot , Daniel Kettler , Jean-Pierre Ruis
发明人： Philippe Pierre Vincent Bouiller , Pierre-Yves Bourquin , Fabrice Michel Olivier Cot , Daniel Kettler , Jean-Pierre Ruis
IPC分类号： F02K1/11 , F02K1/82 , B05B12/00
CPC分类号： F02K1/11 , F02K1/825 , F05D2250/323 , F05D2250/34
摘要： A gas-flow exhaust assembly for a jet propulsion system of an aircraft in which a converging exhaust nozzle (4) is fitted with translating cold flaps (21, 22). The primary exhaust nozzle (4) comprises two hot-flaps (5, 6) situated beyond a primary duct (1) enclosed by an aircraft fairing (2). The fairing (2) is extended by a secondary exhaust nozzle (20) which is supported by the primary duct (1) and which is translatable by a control mechanism (27a, 27b). The secondary exhaust nozzle (20) comprises cold flaps (21, 22) which are driven by another control mechanism (29a, 29b) independently of the angular positions of the hot flaps (5, 6). Preferably, there are two eyelid-shaped cold-flaps (21, 22) hinging and supported on horizontal transverse shafts (23a, 23b). The shafts (23a, 23b) are preferably affixed on two lateral slides (24a, 24b) which slide on the primary duct (1) and are displaceable by the control mechanism (27a, 27b) which translates the secondary exhaust nozzle (20).
摘要翻译：一种用于飞行器的喷射推进系统的气体流动排气组件，其中会聚的排气喷嘴（4）装配有平移的冷襟翼（21,22）。主排气喷嘴（4）包括位于由飞行器整流罩（2）包围的主管道（1）之外的两个热襟翼（5,6）。整流罩（2）由辅助排气喷嘴（20）延伸，二次排气喷嘴（20）由主管道（1）支撑，并可由控制机构（27a，27b）平移。二次排气喷嘴（20）包括与另一个控制机构（29a，29b）驱动的冷襟翼（21,22），独立于热襟翼（5,6）的角位置。优选地，在水平横向轴（23a，23b）上铰接并支撑有两个眼睑形冷舌片（21,22）。轴（23a，23b）优选地固定在两个横向滑动件（24a，24b）上，滑动件（24a，24b）在主导管（1）上滑动，并可通过使辅助排气喷嘴（20）平移的控制机构（27a，27b）移动。

6. 发明授权

US5934564A Variable geometry turbojet engine exhaust nozzle 失效
标题翻译：可变几何涡轮喷气发动机排气喷嘴
公开(公告)号：US5934564A
公开(公告)日：1999-08-10
申请号：US874507
申请日：1997-06-13
申请人： Philippe Pierre Vincent Bouiller , Pierre Yves Bourquin , Gerard Ernest Andre Jourdain , Jean-Pierre Ruis
发明人： Philippe Pierre Vincent Bouiller , Pierre Yves Bourquin , Gerard Ernest Andre Jourdain , Jean-Pierre Ruis
IPC分类号： F02K1/12 , B05B12/00
CPC分类号： F02K1/1292
摘要： A variable geometry exhaust nozzle is disclosed for a turbojet engine having a rear portion, the nozzle having an outer flap ring with a plurality of driven outer flaps and a plurality of outer interlock flaps, each outer flap being pivotally connected to the rear portion of the turbojet engine, and an inner flap ring having a plurality of inner forward driven flaps and a plurality of inner forward interlock flaps, each having a forward portion pivotally attached to the rear portion of the turbojet engine, the inner flap ring also having a plurality of inner rear driven flaps and a plurality of inner rear interlock flaps, each inner rear flap having a front edge portion pivotally connected to a rear edge portion of a corresponding inner forward flap. The inner and outer flap rings are radially spaced apart and are arranged symmetrically about an axis of symmetry, with a drive collar located in the space between the inner and outer flaps that is movable between forwardmost and rearmost positions in a direction substantially parallel to the axis of symmetry of the nozzle. A plurality of translating levers are each pivotally attached to the drive collar and to one of the inner forward driven flaps. A plurality of interlock levers are each pivotally connected to one of the translating levers and to one of the inner rear driven flaps. Each interlock lever is connected to one of the outer driven flaps by a link rod pivotally connected to the interlock lever and to the outer driven flaps. Actuators are connected to the rear portion of the turbojet engine and to the translating levers to move the drive collar between its forwardmost and rearmost positions, such movement causing the inner flap ring to move between a converging-diverging configuration and a converging--converging configuration. Thus, the nozzle is suitable for both subsonic and supersonic aircraft operation.
摘要翻译：公开了一种用于具有后部的涡轮喷气发动机的可变几何形状排气喷嘴，该喷嘴具有带有多个从动外侧翼片的外侧翼环和多个外部互锁翼片，每个外部翼片可枢转地连接到涡轮喷气发动机和具有多个内部向前驱动翼片和多个内部向前互锁翼片的内翼片环，每个翼片环具有可枢转地附接到涡轮喷气发动机的后部的前部，内翼片环还具有多个内部后驱动翼片和多个内部后互锁翼片，每个内后翼片具有可枢转地连接到相应内部前翼片的后边缘部分的前边缘部分。内侧翼片环和外侧翼片环径向间隔开并且围绕对称轴线对称地布置，其中驱动套环位于内侧翼片和外部翼片之间的空间中，其可以在基本上平行于轴线的方向上在最前方和最后方向的位置之间移动喷嘴的对称性。多个平移杆各自枢转地附接到驱动轴环和内部向前驱动的挡板中的一个。多个互锁杠杆各自枢转地连接到平移杆中的一个和内部后驱动翼片中的一个。每个互锁杆通过连杆与连接杆连接到一个外驱动挡板上，该连杆与联动杆和外驱动挡板枢转连接。致动器连接到涡轮喷气发动机的后部和平移杆，以使驱动套环在其最前面和最后面的位置之间移动，这样的运动使得内翼片环在会聚发散构型和会聚会聚构型之间移动。因此，喷嘴适用于亚音速和超音速飞行器操作。

7. 发明授权

US07555894B2 Swivelling exhaust nozzle for an aircraft engine 有权
标题翻译：用于飞机发动机的旋转排气喷嘴
公开(公告)号：US07555894B2
公开(公告)日：2009-07-07
申请号：US11409087
申请日：2006-04-24
申请人： Philippe Pierre Vincent Bouiller , Michel Francois Raymond Franchet , Jean-Pierre Ruis
发明人： Philippe Pierre Vincent Bouiller , Michel Francois Raymond Franchet , Jean-Pierre Ruis
IPC分类号： F02K1/00
CPC分类号： F02K1/006 , F02K1/80 , F05D2300/501 , Y02T50/671
摘要： Swivelling nozzle for an aircraft engine, the nozzle 10 being pivotally mounted about a transverse yaw axis by means of two elastically deformable one-piece articulations 24 mounted on two external pivots 22 of the nozzle and housed in engine case elements, the nozzle being caused to pivot by an actuator 46 mounted on the engine case and connected by a link 50 to a pivot 22 of the nozzle.
摘要翻译：用于飞行器发动机的旋转喷嘴，喷嘴10通过安装在喷嘴的两个外部枢轴22上并容纳在发动机壳体元件中的两个可弹性变形的单件铰接24围绕横向偏转轴线枢转地安装，由安装在发动机壳体上的致动器46枢转，并通过连杆50连接到喷嘴的枢轴22。

8. 发明授权

US07040082B2 Assistance and emergency drive for electrically-driven accessories 有权
标题翻译：电动附件的辅助和应急驱动
公开(公告)号：US07040082B2
公开(公告)日：2006-05-09
申请号：US10617656
申请日：2003-07-14
申请人： Philippe Bouiller , Michel Franchet , Jean-Pierre Ruis
发明人： Philippe Bouiller , Michel Franchet , Jean-Pierre Ruis
IPC分类号： F02C7/32
CPC分类号： F02C7/32 , F01D15/08 , F01D15/10 , F02C6/08 , Y02T50/671
摘要： The invention relates to a system for driving an accessory, such as a fuel pump or an oil pump in a turboengine, said system comprising an electric motor and further comprising an air turbine associated with said electric motor. Said air turbine is suitable for being fed with a flow of air taken from a compressor of said turboengine and contributing to driving the accessory. The system also includes a valve for controlling the flow of air taken from the compressor, which valve is in the closed position while the turboengine is starting.
摘要翻译：本发明涉及一种用于驱动诸如涡轮发动机中的燃料泵或油泵的附件的系统，所述系统包括电动机，并且还包括与所述电动机相关联的空气涡轮机。所述空气涡轮机适用于从所述涡轮发动机的压缩机中取出的空气流供给并有助于驱动附件。该系统还包括用于控制从压缩机获取的空气流的阀，该阀在涡轮发动机起动时处于关闭位置。

9. 发明授权

US06179225B2 Turbo jet engine exhaust nozzle with masked gas jet 有权
标题翻译：涡轮喷气发动机排气喷嘴与掩蔽气体喷射
公开(公告)号：US06179225B2
公开(公告)日：2001-01-30
申请号：US09356362
申请日：1999-07-19
申请人： Philippe Pierre Bouiller , Pierre-Yves Bourquin , Daniel Kettler , Jean-Pierre Ruis
发明人： Philippe Pierre Bouiller , Pierre-Yves Bourquin , Daniel Kettler , Jean-Pierre Ruis
IPC分类号： B63H2546
CPC分类号： F02K1/825 , F02K1/11
摘要： An axially symmetric turbojet engine exhaust-nozzle includes a system for masking the exhaust jet, such system including inner hot flaps (7), hinging on a conical shell (4) and driven by a first control ring (10) powered by linear actuators (11), and outer cold flaps (20) hinging on an annular assembly (12) and driven by a second control ring (22) powered by linear actuators (23) to vary the angle of the cold flaps. The annular assembly (12) is axially displaceable by a third set of linear actuators (30). Each cold flap (20) comprises an inner skin (40) fitted with orifices (43) and hinging on the annular assembly(12) and an outer skin (41) spaced radially away of the inner skin (40) to define an air flow channel between the skins. When the annular assembly (12) is moved downstream by the third set of linear actuators (30), the outer skins (41) form a scoop introducing fresh air into the cold flaps (20), and said air is injected into the hot gas flow through the orifices (43) in the inner skin and other orifices (44) at the trailing edge (42) of the cold flaps to reduce the exhaust signature.
摘要翻译：轴向对称的涡轮喷气发动机排气喷嘴包括用于遮蔽排气射流的系统，该系统包括铰接在锥形壳体（4）上并由第一控制环（10）驱动的内部热襟翼（7），该第一控制环由线性致动器以及铰链在环形组件（12）上并由由线性致动器（23）供电的第二控制环（22）驱动的外部冷襟翼（20），以改变冷襟翼的角度。环形组件（12）可被第三组线性致动器（30）轴向移动。每个冷翼（20）包括装配有孔（43）并铰接在环形组件（12）上的内表皮（40）和径向远离内表皮（40）的外表皮（41），以限定空气流皮肤之间的通道。当环形组件（12）由第三组线性致动器（30）向下游移动时，外表面（41）形成将新鲜空气引入冷襟翼（20）中的勺子，并将所述空气注入到热气体流过冷皮瓣后缘（42）的内皮和其他孔（44）中的孔（43），以减少排气特征。

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