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公开(公告)号：US06938407B2
公开(公告)日：2005-09-06
申请号：US10284181
申请日：2002-10-31
CPC分类号： F02K3/075 , F01D9/065 , F01D17/105 , F04D29/522 , Y02T50/671
摘要： This object is achieved by the bleed-off means comprising means for tapping air from the primary duct which are arranged upstream of the intermediate casing and means for evacuating the air tapped into the secondary duct downstream of the support arms, these means comprising conduits arranged around the intermediate casing under the platforms.
摘要翻译： 该目的是通过排放装置实现的，该排放装置包括用于从主管道排出空气的装置，该装置布置在中间壳体的上游，以及用于抽空在支撑臂下游排入第二管道的空气的装置，这些装置包括围绕 平台下的中间套管。
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公开(公告)号：US20060183593A1
公开(公告)日：2006-08-17
申请号：US11333506
申请日：2006-01-18
申请人： Bruno Beutin , Jeremy Fert
发明人： Bruno Beutin , Jeremy Fert
IPC分类号： F16H57/08
CPC分类号： F02C7/36 , F05D2220/323 , F05D2260/40311 , Y02T50/671
摘要： The twin turbo-shaft engine according to the invention comprises a high pressure rotor and a low pressure rotor, at least one accessory gearbox driven by mechanical transmission means, main drive pinion means, on each rotor, driving power transmission means each associated with an input to a differential, the output of which drives a drive shaft of the accessory gearbox. It is characterised by the fact that the power transmission means extend in two different structural arms, the power transmission means of one of the rotors being connected to a power transfer box fulfilling two functions, firstly transmission of power to an input to the differential, and secondly modification of the transmission speed. The required space in each arm is thus reduced and the efficiency of the accessory gearbox is high.
摘要翻译： 根据本发明的双涡轮轴发动机包括高压转子和低压转子，由机械传动装置驱动的至少一个附件齿轮箱，每个转子上的主驱动小齿轮装置，每个转子与输入 到差速器，其输出驱动附件齿轮箱的驱动轴。 其特征在于，动力传递装置在两个不同的结构臂中延伸，一个转子的动力传递装置连接到实现两个功能的动力传送箱，首先将功率传输到差速器的输入，以及 二是修改传输速度。 因此，每个臂中的所需空间减小，并且附件齿轮箱的效率高。
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公开(公告)号：US07430852B2
公开(公告)日：2008-10-07
申请号：US11042052
申请日：2005-01-26
IPC分类号： F02K3/02
CPC分类号： F02K1/68 , F01D5/22 , F02C7/20 , F05D2240/14
摘要： A turbojet comprises at least a fan, a compressor, a combustion chamber, a turbine, and a rigid substantially-cylindrical jacket fastened at its upstream end to an intermediate casing and at its downstream end to an exhaust casing, the jacket serving to transmit forces between the intermediate casing and the exhaust casing.
摘要翻译： 涡轮喷气发动机包括至少一个风扇，压缩机，燃烧室，涡轮机和刚性的大致圆柱形的套管，其紧固在其上游端到中间壳体，并且在其下游端处连接到排气罩，所述护套用于传递力 在中间壳体和排气壳体之间。
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4.发明申请Turbojet designed to be fixed onto the AFT part of the fuselage of an aircraft, in upper position 有权Turbojet旨在固定在飞机机身的AFT部分，位于上位公开(公告)号：US20050178887A1
公开(公告)日：2005-08-18
申请号：US10986004
申请日：2004-11-12
申请人： Bruno Beutin , Didier Yvon , Georges Mazeaud , Fabien Burdin
发明人： Bruno Beutin , Didier Yvon , Georges Mazeaud , Fabien Burdin
摘要： The turbojet according to the invention is designed to be fixed onto the upper part of the aft section of the fuselage of an aircraft using at least one coat hanger, the turbojet comprising a fan, a forward casing, an aft casing, accessories arranged around the periphery of the forward casing, the forward casing comprising attachment points, for the coat hanger. The attachment points are arranged so that the turbojet can be installed indifferently on either side of the aircraft fuselage, accessories being arranged on the casing so that they are accessible from the outside of the fuselage regardless of which side the installation is done.
摘要翻译： 根据本发明的涡轮喷气发动机被设计成使用至少一个衣架固定到飞行器机身的后部的上部，涡轮喷气发动机包括风扇，前壳，后壳，围绕 前壳体的周边，前部壳体包括用于衣架的附接点。 附接点被布置成使得涡轮喷气发动机可以无差别地安装在飞行器机身的任一侧上，附件被布置在壳体上，使得它们可以从机身的外部接近，而不管安装的哪一方。
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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
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。
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公开(公告)号：US20060226282A1
公开(公告)日：2006-10-12
申请号：US11386740
申请日：2006-03-23
申请人： Bruno Beutin , Jeremy Fert
发明人： Bruno Beutin , Jeremy Fert
IPC分类号： B64C29/00
摘要： Deflection system for a gas stream 11 in an exhaust nozzle 10 of a flying craft, comprising fixed structural housings 18,20 which extend perpendicularly to the gas stream 11 and which are fed with deflection gas through one of their ends external to the nozzle 10, these housings 18,20 containing in their side walls 22,28 gas injection slits 23,30 oriented in oblique directions 24,26 relative to the gas stream 11, and controlled means for the adjustable closure of these slits 23,30.
摘要翻译： 飞行器的排气喷嘴10中的气流11的偏转系统，包括垂直于气流11延伸的固定结构壳体18,20，并且通过喷嘴10外部的一个端部供给偏转气体， 这些壳体18,20在其侧壁22,28中包含相对于气流11在倾斜方向24,26上取向的气体注入狭缝23,30，以及用于这些狭缝23,30的可调节闭合的受控装置。
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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。
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公开(公告)号：US20060230744A1
公开(公告)日：2006-10-19
申请号：US11402952
申请日：2006-04-13
申请人： Bruno Beutin , Jeremy Fert
发明人： Bruno Beutin , Jeremy Fert
IPC分类号： F02K1/28
摘要： Exhaust nozzle 14 for an engine of a flying craft, comprising a tubular body with two outlet ducts 16, 18 and boxes 26, 28 for injecting gas into the outlet ducts for the purpose of thrust vectoring, these boxes having windows 38 aligned with slots 39 formed in the outlet ducts, and controlled means for adjusting the outflow of gas injected into the outlet ducts.
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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。
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公开(公告)号：US20050172609A1
公开(公告)日：2005-08-11
申请号：US11042052
申请日：2005-01-26
CPC分类号： F02K1/68 , F01D5/22 , F02C7/20 , F05D2240/14
摘要： A turbojet comprises at least a fan, a compressor, a combustion chamber, a turbine, and a rigid substantially-cylindrical jacket fastened at its upstream end to an intermediate casing and at its downstream end to an exhaust casing, the jacket serving to transmit forces between the intermediate casing and the exhaust casing.
摘要翻译： 涡轮喷气发动机包括至少一个风扇，压缩机，燃烧室，涡轮机和刚性的大致圆柱形的套管，其紧固在其上游端到中间壳体，并且在其下游端处连接到排气罩，所述护套用于传递力 在中间壳体和排气壳体之间。
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