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公开(公告)号：US20070177935A1
公开(公告)日：2007-08-02
申请号：US11627625
申请日：2007-01-26
Applicant: Jean Pierre Galivel , Regis Eugene Henri Servant
Inventor： Jean Pierre Galivel , Regis Eugene Henri Servant
IPC: F16B7/18
CPC classification number: F02C7/32 , F01D5/026 , F02C7/36 , F02K3/02 , F05D2260/40 , F05D2260/4031 , Y10T403/32598
Abstract: The invention relates to a system for attaching the end of a shaft (14) of a gas turbine engine engaged inside a coupling (15) supported by a bearing (3). Said system comprising a nut (16) is characterized in that the nut (16) comprises a first thread (16f1) by which it is screwed into said shaft (14) and a second thread (16f2) by which it is screwed to said coupling (15). Advantageously, the screw pitches of the two threads (16f1, 16f2) of the nut (16) are reversed relative to one another so as to form an adjusting nut.
Abstract translation: 本发明涉及一种用于连接燃气涡轮发动机的轴（14）的端部的系统，其接合在由轴承（3）支撑的联轴器（15）内部。 所述包括螺母（16）的系统的特征在于，所述螺母（16）包括第一螺纹（16f1），通过所述螺纹拧入所述轴（14）和第二螺纹（16） f 2），由此将其拧到所述联轴器（15）上。 有利地，螺母（16）的两个螺纹（16f 1，16f 2 2）的螺距相对于彼此反转，以形成调节 坚果。
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2.发明申请METHOD OF TAKING OFF AUXILIARY POWER FROM AN AIRPLANE TURBOJET, AND A TURBOJET FITTED TO IMPLEMENT SUCH A METHOD 有权从AIRPLANE涡轮机获取辅助动力的方法，以及用于实施这种方法的涡轮机公开(公告)号：US20100000223A1
公开(公告)日：2010-01-07
申请号：US12031194
申请日：2008-02-14
Applicant: Baptiste Benoit COLOTTE , Jean Pierre GALIVEL , Zoltan ZSIGA
Inventor： Baptiste Benoit COLOTTE , Jean Pierre GALIVEL , Zoltan ZSIGA
CPC classification number: F02C7/32 , F02C7/36 , F02C9/22 , F05D2270/023
Abstract: Producing the electrical power need for equipment on board an airplane. Auxiliary power is taken off by means of a shaft driven by the high pressure turbine and, when idling, the efficiency of the low pressure turbine is degraded so as to enable the high pressure turbine to operate at a speed that is sufficient for delivering the required auxiliary power.
Abstract translation: 生产飞机上设备的电力需求。 辅助动力通过由高压涡轮机驱动的轴来取下，并且当空转时，低压涡轮机的效率降低，使得高压涡轮机能够以足够的速度运行，以便传送所需的 辅助电源。
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公开(公告)号：US20120122631A1
公开(公告)日：2012-05-17
申请号：US13384111
申请日：2010-07-07
Applicant: Jean Pierre Galivel , Bruno Gaully , Julien Ricordeau
Inventor： Jean Pierre Galivel , Bruno Gaully , Julien Ricordeau
IPC: B64D31/06
CPC classification number: F02C7/268 , F01D15/10 , F02C7/275 , F02C7/32 , F02C7/36 , F05D2260/40 , F05D2260/85 , Y02T50/671 , Y10T477/33 , Y10T477/40
Abstract: A system and a method for controlling an aircraft engine starter/generator. The system includes an AGB of fixed gear ratio for coupling mechanically to a turbine shaft of the engine to enable the engine to be started, a gearbox having multiple gear ratios mechanically coupled to a gearwheel of the AGB, a starter/generator mechanically coupled to a gearwheel of the gearbox, and a controller to cause the gear ratio of the gearbox to be changed as a function of the mode of operation of the starter/generator.
Abstract translation: 一种用于控制飞机发动机起动器/发电机的系统和方法。 该系统包括AGB的固定齿轮比，用于机械地联接到发动机的涡轮机轴，以使发动机能够启动;齿轮箱具有机械耦合到AGB的齿轮的多个齿轮比;机械联接到 齿轮箱的齿轮和控制器，用于根据起动器/发电机的工作模式来改变齿轮箱的齿轮比。
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公开(公告)号：US08006501B2
公开(公告)日：2011-08-30
申请号：US11839162
申请日：2007-08-15
Applicant: Guy Frank Paul Dusserre-Telmon , Jean Pierre Galivel , Zoltan Zsiga
Inventor： Guy Frank Paul Dusserre-Telmon , Jean Pierre Galivel , Zoltan Zsiga
CPC classification number: F02C7/32 , F02C7/36 , F05B2260/3011 , F05D2220/50 , F05D2220/768 , F05D2240/54 , F16H48/12 , Y10T74/19005
Abstract: A device for driving the rotor of an auxiliary is mounted on a turbine engine auxiliaries support which includes a pinion for driving the rotor shaft. The device includes a tubular shaft driven by the pinion and supported by a first bearing (18) and a second bearing (19) which are secured to the auxiliaries support (10). The rotor shaft is coaxial with the tubular shaft and a splined coupling portion formed between the rotor shaft and the tubular shaft. By virtue of the invention, mechanical loads of the auxiliary are transmitted to a lesser extent to the rotor shaft support bearings and to the auxiliaries support gear train.
Abstract translation: 用于驱动辅助转子的装置安装在包括用于驱动转子轴的小齿轮的涡轮发动机辅助支撑件上。 该装置包括由小齿轮驱动并由第一轴承（18）和第二轴承（19）支撑的管状轴，第一轴承（18）和第二轴承（19）固定到辅助支撑件（10）上。 转子轴与管状轴同轴并且形成在转子轴和管状轴之间的花键联接部分。 凭借本发明，辅助件的机械载荷在较小程度上传递到转子轴支撑轴承和辅助支撑齿轮系。
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5.发明授权Method of taking off auxiliary power from an airplane turbojet, and a turbojet fitted to implement such a method 有权从飞机涡轮喷气发动机起飞辅助动力的方法，以及适用于实施这种方法的涡轮喷气发动机公开(公告)号：US08240124B2
公开(公告)日：2012-08-14
申请号：US12031194
申请日：2008-02-14
Applicant: Baptiste Colotte , Jean Pierre Galivel , Zoltan Zsiga
Inventor： Baptiste Colotte , Jean Pierre Galivel , Zoltan Zsiga
CPC classification number: F02C7/32 , F02C7/36 , F02C9/22 , F05D2270/023
Abstract: A method for producing the electrical power required for equipment on board an airplane is disclosed. Auxiliary power is taken off by a shaft driven by the high pressure turbine and, when idling, the efficiency of the low pressure turbine is degraded so as to enable the high pressure turbine to operate at a speed that is sufficient for delivering the required auxiliary power.
Abstract translation: 公开了一种用于生产飞机上的设备所需的电力的方法。 辅助动力由高压汽轮机驱动的轴取出，当空转时，低压汽轮机的效率降低，使得高压汽轮机能够以足够的速度运行所需的辅助动力 。
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Patent Agency Ranking
公开(公告)号：US08191686B2
公开(公告)日：2012-06-05
申请号：US12033391
申请日：2008-02-19
Applicant: Jean Pierre Galivel
Inventor： Jean Pierre Galivel
CPC classification number: F01D25/20 , F01M9/04 , F02C9/48 , F05D2260/602 , F05D2270/301 , F16N29/00 , Y02T50/671
Abstract: A method of providing a standby lubrication for an engine in the event of the failure of a main lubrication system of this engine, in which the failure is detected and, in response to the detection of this failure, at least one portion of a fuel fluid of the engine is tapped off to lubricate at least one element of the engine. A standby lubrication device includes a device for detecting a failure of a main lubrication system, a device for tapping off at least a portion of a fuel fluid of the engine in order to direct it to at least one element of the engine intended to be lubricated, and a controller connected to the tapping and detection devices, in order to carry out the standby lubrication method.
Abstract translation: 在发动机的主润滑系统发生故障的情况下为发动机提供备用润滑的方法，其中检测到故障，并且响应于该故障的检测，至少一部分燃料流体 的发动机被分流以润滑发动机的至少一个元件。 备用润滑装置包括用于检测主润滑系统故障的装置，用于抽出发动机的燃料流体的至少一部分的装置，以将其引导到待润滑的发动机的至少一个元件 ，以及连接到出料和检测装置的控制器，以便执行备用润滑方法。
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公开(公告)号：US20080196974A1
公开(公告)日：2008-08-21
申请号：US12033391
申请日：2008-02-19
Applicant: Jean Pierre GALIVEL
Inventor： Jean Pierre GALIVEL
CPC classification number: F01D25/20 , F01M9/04 , F02C9/48 , F05D2260/602 , F05D2270/301 , F16N29/00 , Y02T50/671
Abstract: The invention relates to a standby lubrication method for an engine 1 in the event of the failure of a main lubrication system 2 of this engine 1, in which said failure is detected and, in response to the detection of this failure, at least one portion of a fuel fluid of the engine 1 is tapped off to lubricate at least one element of the engine 1. The invention also relates to a standby lubrication device 6 for an engine 1 comprising a main lubrication system 2, said standby lubrication device 6 comprising means for detecting a failure of the main lubrication system 2, means 12 for tapping off at least a portion of a fuel fluid of the engine 1 in order to direct it to at least one element of the engine 1 intended to be lubricated, and control means 15 capable of being connected to said tapping and detection means 12, in order to carry out the standby lubrication method.
Abstract translation: 本发明涉及在发动机1的主润滑系统2发生故障的情况下发动机1的备用润滑方法，其中检测到所述故障，并且响应于该故障的检测，至少一部分 发动机1的燃料流体被分接以润滑发动机1的至少一个元件。 本发明还涉及一种用于发动机1的备用润滑装置6，其包括主润滑系统2，所述备用润滑装置6包括用于检测主润滑系统2的故障的装置，用于抽出主润滑系统2的至少一部分的装置12 发动机1的燃料流体，以将其引导到要被润滑的发动机1的至少一个元件，以及能够连接到所述排出和检测装置12的控制装置15，以便执行备用润滑方法 。
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8.发明授权公开(公告)号：US08979705B2
公开(公告)日：2015-03-17
申请号：US13384111
申请日：2010-07-07
Applicant: Jean Pierre Galivel , Bruno Gaully , Julien Ricordeau
Inventor： Jean Pierre Galivel , Bruno Gaully , Julien Ricordeau
CPC classification number: F02C7/268 , F01D15/10 , F02C7/275 , F02C7/32 , F02C7/36 , F05D2260/40 , F05D2260/85 , Y02T50/671 , Y10T477/33 , Y10T477/40
Abstract: A system and a method for controlling an aircraft engine starter/generator. The system includes an AGB of fixed gear ratio for coupling mechanically to a turbine shaft of the engine to enable the engine to be started, a gearbox having multiple gear ratios mechanically coupled to a gearwheel of the AGB, a starter/generator mechanically coupled to a gearwheel of the gearbox, and a controller to cause the gear ratio of the gearbox to be changed as a function of the mode of operation of the starter/generator.
Abstract translation: 一种用于控制飞机发动机起动器/发电机的系统和方法。 该系统包括AGB的固定齿轮比，用于机械地联接到发动机的涡轮机轴，以使发动机能够启动;齿轮箱具有机械耦合到AGB的齿轮的多个齿轮比;机械联接到 齿轮箱的齿轮和控制器，用于根据起动器/发电机的工作模式来改变齿轮箱的齿轮比。
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9.发明授权Method and system for determining the angular position of a turbojet engine rotor 有权用于确定涡轮喷气发动机转子的角位置的方法和系统公开(公告)号：US08497676B2
公开(公告)日：2013-07-30
申请号：US13000858
申请日：2009-06-18
Applicant: Jean-Pierre Galivel
Inventor： Jean-Pierre Galivel
IPC: G01B7/30
CPC classification number: F01D21/003 , F05D2260/80 , F05D2270/44 , G01H1/006
Abstract: A method of determining the angular position of a first rotor of a turbojet. A vibration pulse is generated during a rotation of the first rotor, each vibration pulse being generated when the first rotor passes through a given reference angular position. The vibration generated is detected. The angular position is obtained at a given instant of a second rotor of the turbojet relative to the angular position that it occupied at a reference instant representative of detecting a vibration pulse. The second rotor is coupled in rotation with the first rotor and has a speed of rotation different from the speed of rotation thereof. The angular position of the first rotor at the given instant is determined from the angular position of the second rotor.
Abstract translation: 一种确定涡轮喷气发动机的第一转子的角位置的方法。 在第一转子旋转期间产生振动脉冲，当第一转子通过给定的参考角位置时，产生每个振动脉冲。 检测到产生的振动。 在涡轮喷气发动机的第二转子的给定时刻，相对于其在表示检测振动脉冲的基准时刻占据的角位置获得角位置。 第二转子与第一转子一起旋转并且具有与其旋转速度不同的旋转速度。 在给定时刻的第一转子的角位置由第二转子的角位置确定。
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10.发明申请METHOD AND SYSTEM FOR DETERMINING THE ANGULAR POSITION OF A TURBOJET ENGINE ROTOR 有权用于确定涡轮发动机转子的角位置的方法和系统公开(公告)号：US20110109305A1
公开(公告)日：2011-05-12
申请号：US13000858
申请日：2009-06-18
Applicant: Jean-Pierre Galivel
Inventor： Jean-Pierre Galivel
IPC: G01B7/30
CPC classification number: F01D21/003 , F05D2260/80 , F05D2270/44 , G01H1/006
Abstract: The invention relates to a method of determining the angular position of a first rotor of a turbojet, the method consisting in: generating at least one vibration pulse during a rotation of the first rotor, each vibration pulse being generated when the first rotor passes through a given reference angular position; detecting the vibration generated thereby; obtaining (E30) the angular position at a given instant of a second rotor of the turbojet relative to the angular position that it occupied at a reference instant representative of detecting a vibration pulse, said second rotor being coupled in rotation with the first rotor and having a speed of rotation different from the speed of rotation thereof; and determining (E40) from the angular position of the second rotor, the angular position of the first rotor at said given instant.
Abstract translation: 本发明涉及一种确定涡轮喷气发动机的第一转子的角位置的方法，该方法包括：在第一转子旋转期间产生至少一个振动脉冲，当第一转子通过一个 给定参考角位置; 检测由此产生的振动; 在涡轮喷气发动机的第二转子的给定时刻获得（E30）相对于其在代表检测振动脉冲的基准时刻占据的角位置的角位置，所述第二转子与第一转子一起旋转并具有 旋转速度与其旋转速度不同; 以及从所述第二转子的角位置确定所述第一转子在所述给定时刻的角位置（E40）。
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