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1. 发明授权

US07488112B2 Assembly arrangement between a bearing inner race and a journal, race and journal suitable for such an arrangement, and turbomachine fitted therewith 有权
标题翻译：轴承内圈和适合于这种布置的轴颈，座圈和轴颈之间的装配布置以及与其配合的涡轮机
公开(公告)号：US07488112B2
公开(公告)日：2009-02-10
申请号：US11402974
申请日：2006-04-13
申请人： Philippe Pierre Vincent Bouiller , Gilles Alain Marie Charier , Daniel Georges Plona
发明人： Philippe Pierre Vincent Bouiller , Gilles Alain Marie Charier , Daniel Georges Plona
IPC分类号： F16C43/04 , F16C13/04
CPC分类号： F01D25/16 , F02C7/06 , F05D2260/30 , F16C19/26 , F16C33/58 , F16C33/6651 , F16C33/6677 , F16C35/063 , F16C2360/23
摘要： An assembly arrangement between an inner race of a bearing and a journal supported in rotation in this bearing includes a journal annular groove and a race annular groove which interact to form an annular channel when they are placed opposite one another. The assembly further includes a retaining ring placed in the annular channel, which prevents a relative movement in translation between the journal and the inner race. The assembly also includes at least one recess of the journal and at least one tooth of the inner race, which interact to prevent a relative movement in rotation between the journal and the inner race.
摘要翻译：在轴承的内圈和在该轴承中旋转支承的轴颈之间的组装装置包括轴颈环形凹槽和套圈环形槽，当它们彼此相对放置时相互作用以形成环形通道。组件还包括设置在环形通道中的保持环，其防止在轴颈和内圈之间平移的相对移动。组件还包括轴颈的至少一个凹部和内圈的至少一个齿，其相互作用以防止在轴颈和内圈之间的相对运动。

2. 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。

3. 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）。

4. 发明授权

US07390167B1 Compressor with centripetal air takeoff 有权
标题翻译：压缩机带向心空气起飞
公开(公告)号：US07390167B1
公开(公告)日：2008-06-24
申请号：US11461592
申请日：2006-08-01
申请人： Philippe Pierre Vincent Bouiller , Gilles Alain Marie Charier , Didier Rene Andre Escure , Stephane Rousselin
发明人： Philippe Pierre Vincent Bouiller , Gilles Alain Marie Charier , Didier Rene Andre Escure , Stephane Rousselin
IPC分类号： F01D5/08
CPC分类号： F02C6/08 , F04D27/023 , F04D29/321
摘要： A compressor with a centripetal air takeoff system that includes pipes installed between an outer collar and an inner collar. Each pipe is fitted in a hole in the outer collar and in a hole in the inner collar. The system further includes a locking mechanism between the pipe and the inner collar.
摘要翻译：具有向心空气起飞系统的压缩机，其包括安装在外部套环和内部套环之间的管道。每根管子都装在外圈的一个孔中，在内圈的一个孔中。该系统还包括在管和内套环之间的锁定机构。

5. 发明授权

US07651317B2 Multistage turbomachine compressor 有权
标题翻译：多级涡轮机压缩机
公开(公告)号：US07651317B2
公开(公告)日：2010-01-26
申请号：US11476113
申请日：2006-06-28
申请人： Gilles Alain Marie Charier , Franck Christian Conan , Thomas Julien Roland Earith , Marc Leandri
发明人： Gilles Alain Marie Charier , Franck Christian Conan , Thomas Julien Roland Earith , Marc Leandri
IPC分类号： F01D11/14
CPC分类号： F04D29/164
摘要： A multistage compressor for a turbomachine, in particular an airplane turboprop or turbojet, the compressor comprising a double-walled casing having an inner wall made up of shrouds surrounding respective annular rows of moving blades and annular rows of straightening stator vanes, said shrouds being connected to the outer wall of the casing by independent suspension means enabling the radial clearances between the outer ends of the moving blades and the shrouds of the inner wall of the casing to be adjusted independently from one compression stage to another.
摘要翻译：一种用于涡轮机，特别是飞机涡轮螺旋桨或涡轮喷气发动机的多级压缩机，该压缩机包括双壁壳体，该双壁壳体具有由围绕相应的环形行动叶片和环形排矫正定子叶片的护罩构成的内壁，所述护罩连接通过独立的悬挂装置将壳体的外壁附着到壳体的外壁之间的径向间隙，从而能够独立于一个压缩级到另一个压缩级。

6. 发明授权

US07618232B2 Compressor comprising a plurality of cells reconstituting an annular volume of separation of flows in a turbine engine 有权
标题翻译：压缩机包括在涡轮发动机中重构流动的环形体积的多个单元
公开(公告)号：US07618232B2
公开(公告)日：2009-11-17
申请号：US11465998
申请日：2006-08-21
申请人： Eric Stephan Bil , Gilles Alain Marie Charier
发明人： Eric Stephan Bil , Gilles Alain Marie Charier
IPC分类号： F01D1/04
CPC分类号： F02K3/06 , F01D5/22 , F02K3/072 , F04D29/526 , F05D2220/36 , F05D2240/40 , F05D2300/603
摘要： This turbine engine compressor comprises a separating nose extended by inner and outer annular walls defining in cooperation an annular volume (V) of separation of a primary flow (F1) and a secondary flow (F2). This volume (V) comprises a plurality of annular segments in the form of cells separated in pairs by blades of a first fan, these blades passing through both the primary flow (F1) and the secondary flow (F2). These cells are fixed to an upstream annular collar and a downstream annular collar driven rotationally by the aforementioned blades.
摘要翻译：该涡轮发动机压缩机包括由内部和外部环形壁延伸的分离鼻，所述内部和外部环形壁协同地限定主流（F1）和次流（F2）的分离的环形体积（V）。该体积（V）包括以第一风扇的叶片成对分离的细胞形式的多个环形段，这些叶片通过主流（F1）和次流（F2）。这些电池被固定到由上述叶片旋转地驱动的上游环形环和下游环形环。

7. 发明授权

US07553126B2 Device for varying the section of the throat in a turbine nozzle 有权
标题翻译：用于改变涡轮喷嘴中喉部的部分的装置
公开(公告)号：US07553126B2
公开(公告)日：2009-06-30
申请号：US11355884
申请日：2006-02-17
申请人： Gilles Alain Marie Charier , Claude Daniel Nottin , Stephane Rousselin
发明人： Gilles Alain Marie Charier , Claude Daniel Nottin , Stephane Rousselin
IPC分类号： F01D9/00
CPC分类号： F01D17/141 , F01D17/14 , F05D2300/50212
摘要： A device for varying the section of the throat of a turbine nozzle, the nozzle being formed by a plurality of stationary vanes extending radially between outer and inner annular platforms and spaced apart from one another in order to define a throat presenting a minimum flow section. The device comprises an annular element having a coefficient of expansion that is less than that of the platforms of the nozzle, the annular element being secured to the outer platform and being capable of taking up two positions: one position corresponding to no expansion of the platforms, in which the element provides continuity for the profile of the flow passage; and another position corresponding to the platforms having expanded, in which position the element projects into the flow passage so as to reduce its section.
摘要翻译：一种用于改变涡轮喷嘴喉部的部分的装置，该喷嘴由多个固定叶片形成，该固定叶片在外环形平台和内环形平台之间径向延伸并且彼此间隔开，以便限定呈现最小流动部分的喉部。该装置包括具有比喷嘴平台的膨胀系数小的膨胀系数的环形元件，环形元件固定到外平台并且能够占据两个位置：对应于不平台的膨胀的一个位置，其中所述元件为所述流动通道的轮廓提供连续性; 并且对应于已经膨胀的平台的另一位置，元件在该位置突出到流动通道中以便减小其截面。

8. 发明申请

US20090304498A1 MULTISTAGE TURBOMACHINE COMPRESSOR 有权
标题翻译：多功能涡轮压缩机
公开(公告)号：US20090304498A1
公开(公告)日：2009-12-10
申请号：US11476113
申请日：2006-06-28
申请人： Gilles Alain Marie Charier , Franck Christian Conan , Thomas Julien Roland Earith , Marc Leandri
发明人： Gilles Alain Marie Charier , Franck Christian Conan , Thomas Julien Roland Earith , Marc Leandri
IPC分类号： F01D11/08
CPC分类号： F04D29/164
摘要： A multistage compressor for a turbomachine, in particular an airplane turboprop or turbojet, the compressor comprising a double-walled casing having an inner wall made up of shrouds surrounding respective annular rows of moving blades and annular rows of straightening stator vanes, said shrouds being connected to the outer wall of the casing by independent suspension means enabling the radial clearances between the outer ends of the moving blades and the shrouds of the inner wall of the casing to be adjusted independently from one compression stage to another.
摘要翻译：一种用于涡轮机，特别是飞机涡轮螺旋桨或涡轮喷气发动机的多级压缩机，该压缩机包括双壁壳体，该双壁壳体具有由围绕相应的环形行动叶片和环形排矫正定子叶片的护罩构成的内壁，所述护罩连接通过独立的悬挂装置将壳体的外壁附着到壳体的外壁之间的径向间隙，从而能够独立于一个压缩级到另一个压缩级。

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