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1. 发明申请

US20060291953A1 DEVICE FOR ROTATIONALLY LOCKING A CLAMPING NUT FOR A COMPONENT ON A SHAFT, CLAMPING NUT AND SHAFT COMPRISING IT, AND AIRCRAFT ENGINE EQUIPPED THEREWITH 有权
标题翻译：用于旋转锁定用于组件的夹紧螺母的装置，包括其的夹紧螺母和轴以及装备的飞机发动机
公开(公告)号：US20060291953A1
公开(公告)日：2006-12-28
申请号：US11425540
申请日：2006-06-21
申请人： Jacques Bart , Laurent Michel Berbiguier
发明人： Jacques Bart , Laurent Michel Berbiguier
IPC分类号： F16D1/072
CPC分类号： F01D25/162 , F05B2260/301 , F05D2230/64 , F05D2250/182 , F16B39/06 , F16C35/067 , Y10T403/49
摘要： The device for rotationally locking a clamping nut (6) for a component (4) on an end of a hollow shaft (2), said clamping nut (6) being screwed inside said shaft (2) and having a free end, comprises: at least one shaft cutout (28) on the radially outer periphery of said end of the shaft (2), at least one nut cutout (68) on the radially inner periphery of an end of said clamping nut (6), and a locking plug (8) intended to be placed in a locking hole (682) formed by bringing a shaft cutout (28) into coincidence with a nut cutout (680). Application to the clamping of a bearing outer race.
摘要翻译：用于将空心轴（2）的端部上的部件（4）的夹紧螺母（6）旋转地锁定的装置，所述夹紧螺母（6）旋入所述轴（2）内并具有自由端，包括：在所述轴（2）的所述端部的径向外周上的至少一个轴切口（28），在所述夹紧螺母（6）的端部的径向内周上的至少一个螺母切口（68）插头（8）将被放置在通过使轴切口（28）与螺母切口（680）重合而形成的锁定孔（682）中。应用于轴承外圈的夹紧。

2. 发明申请

US20060251520A1 Turbine module for a gas-turbine engine with rotor that includes a monoblock body 有权
标题翻译：用于具有转子的燃气涡轮发动机的涡轮机模块，其包括整体主体
公开(公告)号：US20060251520A1
公开(公告)日：2006-11-09
申请号：US11229676
申请日：2005-09-20
申请人： Jacques Bart
发明人： Jacques Bart
IPC分类号： B64C11/04
CPC分类号： F01D5/063 , F01D25/246
摘要： The invention concerns a turbine module for a gas-turbine engine with a turbine rotor composed of four disks at least supporting blades at their periphery, and where two of the said disks form a monoblock body. The module is characterised by the fact that the said monoblock body includes two lateral inter-disk ferrules, the said ferrules being bolted on the disks of the two rotors adjacent to the monoblock body. The invention applies in particular to turbine modules composed of 4 to 6 turbine stages.
摘要翻译：本发明涉及一种用于燃气涡轮发动机的涡轮机模块，其具有涡轮转子，涡轮转子由四个圆盘组成，至少在其周边支撑叶片，并且其中两个所述圆盘形成整体主体。该模块的特征在于所述整体主体包括两个横向盘间套圈，所述套圈螺栓连接在与整体主体相邻的两个转子的盘上。本发明尤其适用于由4至6个涡轮级组成的涡轮机组。

3. 发明申请

US20070028590A1 SEALING SYSTEM FOR THE REAR LUBRICATING CHAMBER OF A JET ENGINE 有权
标题翻译：喷气发动机后部润滑室密封系统
公开(公告)号：US20070028590A1
公开(公告)日：2007-02-08
申请号：US11461614
申请日：2006-08-01
申请人： Jacques Bart , Stephane Rousselin
发明人： Jacques Bart , Stephane Rousselin
IPC分类号： F02C7/06
CPC分类号： F01D25/18 , F01D25/16 , F01D25/183 , F05D2240/56 , F05D2260/602 , F05D2260/6022 , Y02T50/671
摘要： Recovery of oil around the lubricating chamber of the rear rolling bearing of the shaft of a jet engine. According to the invention the shaft (14) is supported by a rolling bearing (20) situated in a lubricating chamber (24) surrounded by a single recovery chamber (26) having a seal (48) situated downstream from the rotor of the turbine (12) driving the shaft.
摘要翻译：在喷气发动机的轴的后滚动轴承的润滑室周围回收油。根据本发明，轴（14）由位于由单个回收室（26）围绕的润滑室（24）中的滚动轴承（20）支撑，所述单个回收室具有位于涡轮转子下游的密封件（48） 12）驱动轴。

4. 发明申请

US20050089399A1 Low-pressure turbine of a turbomachine 有权
标题翻译：涡轮机的低压涡轮机
公开(公告)号：US20050089399A1
公开(公告)日：2005-04-28
申请号：US10910635
申请日：2004-08-04
申请人： Jacques Bart , Bruno Beutin , Philippe Bouiller
发明人： Jacques Bart , Bruno Beutin , Philippe Bouiller
IPC分类号： F01D5/06 , F01D25/00 , F01D25/16 , F02C7/06 , F02C7/28 , F02C7/36 , F01D5/00
CPC分类号： F02C7/36 , F01D5/06 , F01D25/16 , F02C7/06 , F05D2230/70
摘要： A low-pressure turbine of a turbomachine, the turbomachine comprising a high-pressure turbine disposed upstream from the low-pressure turbine, and an exhaust casing disposed downstream from the low-pressure turbine, the low-pressure turbine comprising a rotor secured on a low-pressure trunnion, a low-pressure shaft, a first rolling bearing disposed on said low-pressure shaft and supporting a high-pressure trunnion having fastened thereon a rotor of the high-pressure turbine, a second rolling bearing disposed on said low-pressure trunnion downstream from said first rolling bearing and enabling said low-pressure trunnion to be centered relative to said exhaust casing, and a system of fluting for enabling said low-pressure trunnion to drive said low-pressure shaft, said system of fluting being disposed between said first and second rolling bearings.
摘要翻译：一种涡轮机的低压涡轮机，包括设置在低压涡轮机上游的高压涡轮机的涡轮机和设置在低压涡轮机下游的排气壳体，该低压涡轮机包括固定在低压涡轮机低压耳轴，低压轴，设置在所述低压轴上的第一滚动轴承，并且支撑高压耳轴，所述高压耳轴紧固在所述高压涡轮机的转子上;第二滚动轴承，所述第一滚动轴承下游的压力耳轴，并且使所述低压耳轴相对于所述排气壳体居中;以及用于使所述低压耳轴驱动所述低压轴的凹槽系统，所述凹槽系统被布置在所述第一和第二滚动轴承之间。

5. 发明授权

US07097415B2 Low-pressure turbine of a turbomachine 有权
标题翻译：涡轮机的低压涡轮机
公开(公告)号：US07097415B2
公开(公告)日：2006-08-29
申请号：US10910635
申请日：2004-08-04
申请人： Jacques Bart , Bruno Beutin , Philippe Bouiller
发明人： Jacques Bart , Bruno Beutin , Philippe Bouiller
IPC分类号： F01D25/16
CPC分类号： F02C7/36 , F01D5/06 , F01D25/16 , F02C7/06 , F05D2230/70
摘要： A low-pressure turbine of a turbomachine, the turbomachine comprising a high-pressure turbine disposed upstream from the low-pressure turbine, and an exhaust casing disposed downstream from the low-pressure turbine, the low-pressure turbine comprising a rotor secured on a low-pressure trunnion, a low-pressure shaft, a first rolling bearing disposed on said low-pressure shaft and supporting a high-pressure trunnion having fastened thereon a rotor of the high-pressure turbine, a second rolling bearing disposed on said low-pressure trunnion downstream from said first rolling bearing and enabling said low-pressure trunnion to be centered relative to said exhaust casing, and a system of fluting for enabling said low-pressure trunnion to drive said low-pressure shaft, said system of fluting being disposed between said first and second rolling bearings.
摘要翻译：一种涡轮机的低压涡轮机，包括设置在低压涡轮机上游的高压涡轮机的涡轮机和设置在低压涡轮机下游的排气壳体，该低压涡轮机包括固定在低压涡轮机低压耳轴，低压轴，设置在所述低压轴上的第一滚动轴承，并且支撑高压耳轴，所述高压耳轴紧固在所述高压涡轮机的转子上;第二滚动轴承，所述第一滚动轴承下游的压力耳轴，并且使所述低压耳轴相对于所述排气壳体居中;以及用于使所述低压耳轴驱动所述低压轴的凹槽系统，所述凹槽系统被布置在所述第一和第二滚动轴承之间。

6. 发明申请

US20070231133A1 Turbine module for a gas-turbine engine 有权
标题翻译：用于燃气涡轮发动机的涡轮机模块
公开(公告)号：US20070231133A1
公开(公告)日：2007-10-04
申请号：US11229726
申请日：2005-09-20
申请人： Jacques Bart
发明人： Jacques Bart
IPC分类号： F04D29/54
CPC分类号： F01D11/001 , F01D5/06 , F01D25/246
摘要： The invention concerns a turbine module for a gas turbine engine that includes at least an annular distributor and a turbine rotor inside a casing, where the annular distributor includes a variety of elements in the form of a ring sector, of which a first part supports fixed blades positioned radially towards the turbine axis, and a second part forms a sealing resource with the tips of the turbine rotor blades. The module is characterised by the fact that the said elements in the form of a ring sector are held inside the casing by attachment resources. The invention applies in particular to modules that include 3 to 6 turbine stages.
摘要翻译：本发明涉及一种用于燃气涡轮发动机的涡轮机模块，其包括壳体内的至少一个环形分配器和涡轮转子，其中环形分配器包括环形部分形式的各种元件，第一部件支撑固定叶片径向朝向涡轮机轴线定位，并且第二部分与涡轮机转子叶片的尖端形成密封资源。该模块的特征在于，环形部件形式的所述元件通过附接资源保持在壳体内。本发明尤其适用于包括3至6个涡轮级的模块。

7. 发明申请

US20050198941A1 Turbojet architecture with two fans at the front 有权
标题翻译： Turbojet架构在前面有两个风扇
公开(公告)号：US20050198941A1
公开(公告)日：2005-09-15
申请号：US11041998
申请日：2005-01-26
申请人： Jacques Bart , Bruno Beutin , Yann Lebret
发明人： Jacques Bart , Bruno Beutin , Yann Lebret
IPC分类号： F02C7/04 , F01D25/16 , F02C7/06 , F02K3/04 , F02K3/06 , F02K3/065 , F02K3/072 , F04D29/04 , F04D29/056 , F04D29/059 , F04D29/32
CPC分类号： F04D29/0563 , F01D25/162 , F02C7/06 , F02K3/04 , F02K3/065 , F04D29/059 , F04D29/321 , Y02T50/671
摘要： The invention relates to a turbojet having a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. Said compressor is disposed under the rear fan and has a downstream ring of rotor blades connecting the rear fan to the drive shaft of the rear fan, an upstream rotor blade ring that is connected to the drive shaft of the front fan and at least one ring of stator blades that is disposed between the rings of rotor blades and inside an outer stator that is supported by a second intermediate casing. Bearings are interposed respectively between the two intermediate casings and the two shafts.
摘要翻译：本发明涉及一种涡轮喷气发动机，其具有低压压缩机和在中间壳体前部的两个风扇，风扇由两个独立的轴驱动。所述压缩机设置在所述后风扇下方，并且具有将所述后风扇连接到所述后风扇的驱动轴的转子叶片的下游环，连接到所述前风扇的驱动轴的上游转子叶片环和至少一个环的定子叶片，其设置在转子叶片的环之间并且在由第二中间壳体支撑的外部定子内部。轴承分别插在两个中间壳体和两个轴之间。

8. 发明申请

US20050172610A1 Turbojet having two counter-rotatable fans secured to a counter-rotatable low-pressure compressor 审中-公开
标题翻译：涡轮喷气发动机具有固定到可逆转的低压压缩机上的两个可反向旋转的风扇
公开(公告)号：US20050172610A1
公开(公告)日：2005-08-11
申请号：US11054559
申请日：2005-02-10
申请人： Jacques Bart , Fabienne Lacorre , Yann Lebret , Vanessa Le Rousseau , Patrick Morel
发明人： Jacques Bart , Fabienne Lacorre , Yann Lebret , Vanessa Le Rousseau , Patrick Morel
IPC分类号： F04D29/32 , F01D5/03 , F02C3/067 , F02K3/072 , F02K3/04
CPC分类号： F02C3/067 , F01D5/03 , F02K3/072 , F04D19/024
摘要： The invention relates to a turbojet having two counter-rotatable fans (3, 5) at the front of an intermediate casing (2), said fans being secured to a counter-rotatable low-pressure compressor (7). The blades (14) of the rear fan (5) extend into the by-pass air flow (F2) from a wheel (15) that surrounds the outer rotor (20) of the low-pressure compressor (7). The distance (L) between the blades (10) of the front fan (3) and the blades (14) of the rear fan (5) is not less than twice the length (l) of the projection onto the axis of the cord-line of the blades (10) of the front fan (3).
摘要翻译：本发明涉及一种涡轮喷气发动机，其具有在中间壳体（2）前部的两个可逆转风扇（3,5），所述风扇固定在可逆转的低压压缩机（7）上。后风扇（5）的叶片（14）从围绕低压压缩机（7）的外转子（20）的轮（15）延伸到旁通气流（F 2）。前风扇（3）的叶片（10）和后风扇（5）的叶片（14）之间的距离（L）不小于在帘线轴线上的突起的长度（l）的两倍 - 前风扇（3）的叶片（10）。

9. 发明授权

US07412819B2 Turbojet architecture with two fans at the front 有权
标题翻译： Turbojet架构在前面有两个风扇
公开(公告)号：US07412819B2
公开(公告)日：2008-08-19
申请号：US11041998
申请日：2005-01-26
申请人： Jacques Bart , Bruno Beutin , Yann Lebret
发明人： Jacques Bart , Bruno Beutin , Yann Lebret
IPC分类号： F02K3/065 , F02K3/072
CPC分类号： F04D29/0563 , F01D25/162 , F02C7/06 , F02K3/04 , F02K3/065 , F04D29/059 , F04D29/321 , Y02T50/671
摘要： A turbojet has a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. The compressor is disposed under the rear fan and has a downstream ring of rotor blades connecting the rear fan to the drive shaft of the rear fan, an upstream rotor blade ring that is connected to the drive shaft of the front fan and at least one ring of stator blades that is disposed between the rings of rotor blades and inside an outer stator that is supported by a second intermediate casing. Bearings are interposed respectively between the two intermediate casings and the two shafts.
摘要翻译：涡轮喷气发动机在中间壳体的前部具有低压压缩机和两个风扇，风扇由两个独立的轴驱动。压缩机设置在后风扇下方，并且具有将后风扇连接到后风扇的驱动轴的转子叶片的下游环，连接到前风扇的驱动轴的上游转子叶片环和至少一个环的定子叶片，其设置在转子叶片的环之间并且在由第二中间壳体支撑的外部定子内部。轴承分别插在两个中间壳体和两个轴之间。

10. 发明授权

US07299621B2 Three-spool by-pass turbojet with a high by-pass ratio 有权
标题翻译：具有高旁路比率的三线路旁路涡轮喷气发动机
公开(公告)号：US07299621B2
公开(公告)日：2007-11-27
申请号：US11045365
申请日：2005-01-31
申请人： Jacques Bart , Fabienne Lacorre , Yann Lebret , Vanessa Le Rousseau , Patrick Morel
发明人： Jacques Bart , Fabienne Lacorre , Yann Lebret , Vanessa Le Rousseau , Patrick Morel
IPC分类号： F02K3/065 , F02K3/072
CPC分类号： F02K3/072 , F01D17/162 , F02C3/067 , Y02T50/671
摘要： The invention relates to aerodynamically matching the rear fan of a turbojet having two fans and a low-pressure compressor at the front of the intermediate casing, said fans being driven by two independent shafts. Said compressor is disposed between the blades of the two fans and includes at least one ring of rotor blades around the periphery of a wheel driven by the drive shaft for the front fan, and at least two grids of stator vanes disposed on either side of the ring of rotor blades and inside a grid carrier ring. A stationary outer grid and a stator of variable pitch connect the ring to the fan casing.
摘要翻译：本发明涉及空气动力学匹配具有两个风扇的涡轮喷气发动机的后风扇和在中间壳体前部的低压压缩机，所述风扇由两个独立的轴驱动。所述压缩机设置在两个风扇的叶片之间，并且包括围绕由用于前风扇的驱动轴驱动的轮的周边的至少一个转子叶片环，以及设置在该风扇两侧的至少两个定子叶片格栅转子叶片环和电网载体环内。固定外格栅和可变节距的定子将环连接到风扇外壳。

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