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。

2. 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。

3. 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。

4. 发明申请

US20120055137A1 FAN BLADES WITH CYCLIC SETTING 有权
标题翻译：风扇叶片与循环设置
公开(公告)号：US20120055137A1
公开(公告)日：2012-03-08
申请号：US13203353
申请日：2010-02-25
申请人： Philippe Pierre Vincent Bouiller , Stephane Rousselin
发明人： Philippe Pierre Vincent Bouiller , Stephane Rousselin
IPC分类号： F02K3/02
CPC分类号： F02K3/06 , F01D7/00 , F04D29/323 , F04D29/362 , F05D2220/36 , F05D2260/74 , Y02T50/671 , Y02T50/673
摘要： A fan portion of a dual flow turbojet engine including a plurality of fan blades, a disk supporting the blades and configured to be rotated relative to a stator portion of the fan, along a longitudinal axis of the fan, and a system for setting the angle of attack associated with each fan blade, the systems configured such that the angle of attack of each blade varies according to a same setting law according to the angular position of the blade relative to the stator portion, along the longitudinal axis, the same setting law being periodic with a period of P=360°/n, where n is an integer at least equal to 1.
摘要翻译：双流涡轮喷气发动机的风扇部分，其包括多个风扇叶片，支撑叶片并构造成相对于风扇的定子部分沿着风扇的纵向轴线旋转的盘，以及用于设定角度的系统与每个风扇叶片相关的攻击的系统，被配置为使得每个叶片的迎角根据相对于叶片相对于定子部分的角位置沿着纵向轴线的相同设定规律而变化，相同的设定定律周期性地具有P = 360°/ n的周期，其中n是至少等于1的整数。

5. 发明授权

US07855483B2 Turbomachine with integral generator/starter 有权
标题翻译：涡轮机与集成发电机/启动器
公开(公告)号：US07855483B2
公开(公告)日：2010-12-21
申请号：US12547554
申请日：2009-08-26
申请人： Philippe Pierre Vincent Bouiller , Anthony Lorand , Stephane Rousselin
发明人： Philippe Pierre Vincent Bouiller , Anthony Lorand , Stephane Rousselin
IPC分类号： H02K15/00 , H02K11/00 , F01D15/12
CPC分类号： H02K7/14 , F01D9/065 , F01D15/10 , F02C7/268 , F02C7/275 , F05D2220/76 , F05D2260/85 , H02K5/225
摘要： A turbomachine such as an aircraft turbojet including an electrical generator/starter that can be mounted and dismounted by axial translation in an upstream enclosure of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables which extend inside the structural arms of the intermediate casing of the turbomachine.
摘要翻译：一种涡轮机，例如包括发电机/起动器的飞行器涡轮喷气发动机，其可以通过在低压压缩机和高压压缩机之间的涡轮机的上游外壳中的轴向平移来安装和拆卸，并且耦合到在内部延伸的电缆涡轮机的中间套管的结构臂。

6. 发明申请

US20090309432A1 TURBOMACHINE WITH INTEGRAL GENERATOR/STARTER 有权
标题翻译：具有集成发电机/起动机的涡轮机
公开(公告)号：US20090309432A1
公开(公告)日：2009-12-17
申请号：US12547554
申请日：2009-08-26
申请人： Philippe Pierre Vincent Bouiller , Anthony Lorand , Stephane Rousselin
发明人： Philippe Pierre Vincent Bouiller , Anthony Lorand , Stephane Rousselin
IPC分类号： H02K11/00 , H02K9/19
CPC分类号： H02K7/14 , F01D9/065 , F01D15/10 , F02C7/268 , F02C7/275 , F05D2220/76 , F05D2260/85 , H02K5/225
摘要： A turbomachine such as an aircraft turbojet including an electrical generator/starter that can be mounted and dismounted by axial translation in an upstream enclosure of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables which extend inside the structural arms of the intermediate casing of the turbomachine.
摘要翻译：一种涡轮机，例如包括发电机/起动器的飞行器涡轮喷气发动机，其可以通过在低压压缩机和高压压缩机之间的涡轮机的上游外壳中的轴向平移来安装和拆卸，并且耦合到在内部延伸的电缆涡轮机的中间套管的结构臂。

7. 发明授权

US09322293B2 Turbojet venting pipe, method for mounting one such pipe and turbojet provided with one such pipe 有权
标题翻译：涡轮喷气通风管，一个这种管道的安装方法和一个这样的管道的涡轮喷气发动机
公开(公告)号：US09322293B2
公开(公告)日：2016-04-26
申请号：US13636802
申请日：2011-03-28
申请人： Michel Gilbert Roland Brault , Philippe Pierre Vincent Bouiller
发明人： Michel Gilbert Roland Brault , Philippe Pierre Vincent Bouiller
IPC分类号： F01D25/18 , F16L37/14 , F16L21/08
CPC分类号： F01D25/18 , F05D2230/64 , F05D2230/642 , F05D2240/61 , F05D2260/30 , F05D2260/602 , F05D2260/6022 , F16L21/08 , F16L37/14 , Y10T29/49826
摘要： A venting pipe used to guide a gas stream in a turbojet including at least one hollow rotary shaft inside which the pipe is mounted, the pipe extending generally along an axis. The pipe includes at least two pipe segments configured to be aligned longitudinally and assembled to one another while retaining a degree of freedom in relative translation thereof, at least one of the segments including a deformable mechanism configured to deform radially as the pipe segments are tightened against one another in the shaft of the turbojet, to bear on the shaft. The pipe structure facilitates mounting of the pipe.
摘要翻译：用于引导涡轮喷气机中的气流的排气管，其包括至少一个中空旋转轴，管内安装有管，管通常沿轴线延伸。管道包括至少两个管段，其构造成纵向对齐并且彼此组装，同时保持其相对平移的自由度，所述段中的至少一个包括可变形机构，所述可变形机构构造成随着管段被紧固而径向变形在涡轮喷气发动机的轴上彼此相依，承担在轴上。管道结构便于安装管道。

8. 发明授权

US07766607B2 Device for ventilating turbine disks in a gas turbine engine 有权
标题翻译：用于在燃气涡轮发动机中通风涡轮盘的装置
公开(公告)号：US07766607B2
公开(公告)日：2010-08-03
申请号：US11551560
申请日：2006-10-20
申请人： Gilles Alain Marie Charier , Stephane Rousselin , Philippe Pierre Vincent Bouiller
发明人： Gilles Alain Marie Charier , Stephane Rousselin , Philippe Pierre Vincent Bouiller
IPC分类号： F04D29/38
CPC分类号： F02C7/12 , F01D5/082 , F05D2220/3212 , F05D2260/60
摘要： A device for ventilating turbine components in a gas turbine engine which includes first and second turbine rotors mechanically independent of each other, the first turbine rotor includes an HP turbine disk and the second turbine rotor includes an LP turbine disk and with a first circuit for ventilating the LP turbine is disclosed. The device includes an air compression wheel arranged downstream of the HP turbine disk between the HP turbine disk and LP turbine disk in order to assist the circulation of the air in the first circuit.
摘要翻译：一种用于在燃气涡轮发动机中通风涡轮机部件的装置，其包括彼此机械独立的第一和第二涡轮转子，所述第一涡轮转子包括HP涡轮盘，并且所述第二涡轮转子包括LP涡轮盘，并具有用于通风的第一回路公开了LP涡轮机。该装置包括空气压缩轮，其布置在HP涡轮盘和LP涡轮盘之间的HP涡轮盘的下游，以帮助第一回路中的空气循环。

9. 发明授权

US06276126B1 Axisymmetric, directable and adjustable turbojet-engine exhaust nozzle 有权
标题翻译：轴对称，可直接和可调节的涡轮喷气发动机排气喷嘴
公开(公告)号：US06276126B1
公开(公告)日：2001-08-21
申请号：US09523465
申请日：2000-03-10
申请人： Philippe Pierre Vincent Bouiller , Gilles Alain Marie Charier , Gérard Ernest André Jourdain , Daniel Germain Alexis Kettler , Gérard Marcel François Mandet , Jackie Raymond Julien Prouteau
发明人： Philippe Pierre Vincent Bouiller , Gilles Alain Marie Charier , Gérard Ernest André Jourdain , Daniel Germain Alexis Kettler , Gérard Marcel François Mandet , Jackie Raymond Julien Prouteau
IPC分类号： F02K100
CPC分类号： F02K1/15 , F02K1/008 , F02K1/1292 , Y02T50/671 , Y02T50/677
摘要： An axially symmetric turbojet-engine exhaust nozzle which is directable as a unit. The exhaust nozzle is situated downstream of an exhaust duct (1) fitted with a spherical wall (5). A single control ring (12) driven by linear actuators (30) allows regulation of the nozzle cross section and direction. Converging flaps (7) are guided on an upstream side by the spherical wall (5) and are supported at a downstream side by a control lever (13) which hinges on the control ring (12) and rests upstream on an external surface (16) of the spherical wall (5). Diverging flaps (10) hinge on the converging flaps (7) to form an inner ring of hot flaps. The diverging flaps (10) are situated downstream in an extension of the converging flaps (7) and further hinge on an outer ring of cold flaps (11), which in turn hinge on the control ring (12). A synchronizing system connects upstream ends of the control levers (13) to the control ring (12) and ensures self-centering of the control ring (12), the outer ring of cold flaps (11) and the inner ring of hot flaps relative to the spherical wall (5).
摘要翻译：轴向对称的涡轮喷气发动机排气喷嘴，其可作为一个单元定向。排气喷嘴位于装配有球形壁（5）的排气管（1）的下游。由线性致动器（30）驱动的单个控制环（12）允许调节喷嘴横截面和方向。汇流襟翼（7）在上游侧由球形壁（5）引导，并通过控制杆（13）支撑在下游侧，控制杆（13）铰接在控制环（12）上并在外表面（16））的球形壁（5）。折叠翼片（10）铰接在会聚翼片（7）上以形成热襟翼的内圈。发散的翼片（10）位于会聚翼片（7）的延伸部的下游，并进一步铰接在冷襟翼（11）的外环上，冷襟翼（11）又在控制环（12）上铰接。同步系统将控制杆（13）的上游端连接到控制环（12），并确保控制环（12）的自定心，冷襟翼（11）的外环和热襟翼的内圈相对到球形壁（5）。

10. 发明申请

US20130008550A1 TURBOJET VENTING PIPE, METHOD FOR MOUNTING ONE SUCH PIPE AND TURBOJET PROVIDED WITH ONE SUCH PIPE 有权
标题翻译：涡轮喷油管，安装一个这样的管道和一个这样的管道提供的涡轮的方法
公开(公告)号：US20130008550A1
公开(公告)日：2013-01-10
申请号：US13636802
申请日：2011-03-28
申请人： Michel Gilbert Roland Brault , Philippe Pierre Vincent Bouiller
发明人： Michel Gilbert Roland Brault , Philippe Pierre Vincent Bouiller
IPC分类号： F16L11/00 , B23P11/00
CPC分类号： F01D25/18 , F05D2230/64 , F05D2230/642 , F05D2240/61 , F05D2260/30 , F05D2260/602 , F05D2260/6022 , F16L21/08 , F16L37/14 , Y10T29/49826
摘要： A venting pipe used to guide a gas stream in a turbojet including at least one hollow rotary shaft inside which the pipe is mounted, the pipe extending generally along an axis. The pipe includes at least two pipe segments configured to be aligned longitudinally and assembled to one another while retaining a degree of freedom in relative translation thereof, at least one of the segments including a deformable mechanism configured to deform radially as the pipe segments are tightened against one another in the shaft of the turbojet, to bear on the shaft. The pipe structure facilitates mounting of the pipe.
摘要翻译：用于引导涡轮喷气机中的气流的排气管，其包括至少一个中空旋转轴，管内安装有管，管通常沿轴线延伸。管道包括至少两个管段，其构造成纵向对齐并且彼此组装，同时保持其相对平移的自由度，所述段中的至少一个包括可变形机构，所述可变形机构构造成随着管段被紧固而径向变形在涡轮喷气发动机的轴上彼此相依，承担在轴上。管道结构便于安装管道。

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