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11. 发明申请

US20070267539A1 Hinged device for doors of an aircraft nacelle and nacelle equipped with said hinged device 有权
标题翻译：用于装备有所述铰接装置的飞机机舱和机舱的门的铰接装置
公开(公告)号：US20070267539A1
公开(公告)日：2007-11-22
申请号：US11798375
申请日：2007-05-14
申请人： Guillaume Bulin
发明人： Guillaume Bulin
IPC分类号： B64D33/00
CPC分类号： B64D29/06 , B64D29/08
摘要： A hinged device for at least one door (46.1, 46.2) of an aircraft nacelle (40), whereby the door is able to block an opening (44) that is made in the fairing of the nacelle, the device including a base to which is connected at least one door, able to occupy a first retracted state in which the base is located at least in part inside the nacelle and a second extended state in which the base is located outside the fairing of the nacelle so as to be able to move, in a direction that is essentially parallel to the longitudinal axis of the nacelle, outside of the nacelle by entraining the at least one door (46.1, 46.2) to release the opening (44) at least in part.
摘要翻译：一种用于飞机机舱（40）的至少一个门（46.1,46.2）的铰接装置，由此门能够阻挡在机舱的整流罩中制造的开口（44），该装置包括基座连接至少一个门，其能够占据第一缩回状态，其中基座至少部分地位于机舱内部;第二延伸状态，其中基座位于机舱的整流罩之外，以便能够在基本上平行于所述机舱的纵向轴线的方向上，通过夹带所述至少一个门（46.1,46.2）至少部分地释放所述开口（44）而在所述机舱的外部移动。

12. 发明授权

US08890343B2 Electric generator disposed on a rotating turboprop part 有权
标题翻译：发电机设置在旋转的涡桨螺旋桨部件上
公开(公告)号：US08890343B2
公开(公告)日：2014-11-18
申请号：US13318434
申请日：2010-05-03
申请人： Guillaume Bulin , Severine Perret , Jean-Michel Rogero
发明人： Guillaume Bulin , Severine Perret , Jean-Michel Rogero
IPC分类号： B64C11/44 , F02C7/32 , H01L35/32 , B64C11/48 , F01D15/10 , B64D27/02
CPC分类号： B64C11/48 , B64D2027/026 , F01D15/10 , F02C7/32 , F28D15/02 , Y02T50/66
摘要： An electrical energy generating device for a propfan-type aircraft propulsion unit rotor. The propulsion unit includes a turbomachine that drives in rotation at least one rotor including a plurality of blades arranged around an annular crown moving with the blades, which forms with its outer wall part of an outer envelope of the propulsion unit, the outer envelope being subjected to atmospheric conditions outside the propulsion unit. The turbomachine generates a flow of hot gases that exit via an annular hot vein, which is concentric with the moving annular crown, and defined for part of its surface by an inner wall of the moving annular crown, and includes, within the moving annular part, a mechanism to transform thermal energy into electrical energy, preferably by thermal diodes. Such a device, as an example, can find application to a device for controlling a pitch of rotors of a propfan-type propulsion unit.
摘要翻译：一种用于propfan型飞机推进单元转子的电能产生装置。推进单元包括涡轮机，其旋转驱动至少一个转子，其包括围绕与叶片一起移动的环形凸台布置的多个叶片，其与推进单元的外部外壳的外壁部分形成，到推进单元外的大气条件。涡轮机产生一热气流，该热气体通过环形热静脉排出，该环形热静脉与移动的环形冠同心，并由活动的环形冠的内壁限定于其表面的一部分，并且包括在活动的环形部分内，将热能转换成电能的机制，优选地通过热二极管。作为示例，这种装置可以发现应用于用于控制丙烷型推进单元的转子的间距的装置。

13. 发明授权

US08516792B2 System for managing the heat fluxes of an aircraft 有权
标题翻译：用于管理飞机热通量的系统
公开(公告)号：US08516792B2
公开(公告)日：2013-08-27
申请号：US12565930
申请日：2009-09-24
申请人： Guillaume Bulin
发明人： Guillaume Bulin
IPC分类号： F02K99/00
CPC分类号： B64D13/06 , B64D37/34 , B64D2013/0674 , F28D1/024 , F28D21/00 , F28F27/02 , Y02T50/56
摘要： A system for managing heat fluxes of an aircraft is provided, including a fuel tank supplying a turbomachine with fuel via a fuel supply circuit; a cell cooling circuit connected to a thermal effluents source, which integrates a first heat exchanger ensuring heat transfer between a coolant circulating in the cell cooling circuit and air flow channeled into a cooling air channel extending from an air intake to an exhaust; and a second heat exchanger ensuring a heat transfer between the coolant circulating in the cell cooling circuit and the fuel. The air intake includes a blocker to open/close it. The system includes a fuel transfer circuit, which connects the fuel tank to the second heat exchanger and provides fuel to the second heat exchanger, including a valve selectively changing a fuel supply direction from the second heat exchanger between the directions of the tank and the fuel supply circuit.
摘要翻译：提供了一种用于管理飞机的热通量的系统，包括经由燃料供给回路向涡轮机供给燃料的燃料箱; 连接到热排出源的电池冷却回路，其集成了第一热交换器，其确保在电池冷却回路中循环的冷却剂之间的热传递和通向从进气口延伸到排气口的冷却空气通道的空气流; 以及确保在电池冷却回路中循环的冷却剂与燃料之间的热传递的第二热交换器。进气口包括一个打开/关闭的挡块。该系统包括燃料传输回路，其将燃料箱连接到第二热交换器并且向第二热交换器提供燃料，其包括在罐和燃料的方向之间选择性地从第二热交换器改变燃料供给方向的阀供电电路。

14. 发明申请

US20130092754A1 NACELLE FOR A POWER PLANT WITH A VARIABLE-AREA FAN NOZZLE 审中-公开
标题翻译：用于具有可变区域风扇喷嘴的发电厂的NACELLE
公开(公告)号：US20130092754A1
公开(公告)日：2013-04-18
申请号：US13554883
申请日：2012-07-20
申请人： Guillaume Bulin , Patrick Oberle , Nicolas Devienne
发明人： Guillaume Bulin , Patrick Oberle , Nicolas Devienne
IPC分类号： F02K1/09
CPC分类号： F02K1/09 , B64D33/04 , F02K1/08 , F02K3/075 , Y02T50/671
摘要： A power plant includes a nacelle with a bypass turbojet engine having a ducted fan with a low compression ratio. A secondary flow, drawn in and accelerated by the fan, is channeled through a secondary duct installed in the nacelle between the inner surface of the nacelle and the outer surface of the turbojet, toward a fan nozzle. The power plant has at least two moving parts on either side of a vertical plane of symmetry of the nacelle, at least one moving part being able to adopt one of a discrete number of positions, the moving part containing or releasing a portion of the secondary flow, depending on the moving part's position. A control unit controls a different displacement of each of the moving parts between their possible positions in order to create asymmetry of the moving parts relative to the vertical plane of symmetry.
摘要翻译：发电厂包括具有旁路涡轮喷气发动机的机舱，其具有低压缩比的管道风扇。被风扇拉入并加速的二次流通过安装在机舱的内表面和涡轮喷气发动机的外表面之间的机舱中的辅助管道朝向风扇喷嘴引导。发电厂在机舱的垂直对称平面的任一侧上具有至少两个运动部件，至少一个运动部件能够采用离散数量的位置中的一个，运动部件容纳或释放二次侧部分的一部分流动，取决于移动部件的位置。控制单元控制每个移动部件在其可能位置之间的不同位移，以便相对于垂直对称平面产生运动部件的不对称性。

15. 发明申请

US20110155846A1 ANCILLARY DEVICE WITH AN AIR TURBINE FOR TAXIING AN AIRCRAFT ON THE GROUND 有权
标题翻译：具有用于对地面进行飞机的空气涡轮机的附加装置
公开(公告)号：US20110155846A1
公开(公告)日：2011-06-30
申请号：US12990145
申请日：2009-05-04
申请人： Guillaume Bulin , Christophe Cros , Juluan Gaultier
发明人： Guillaume Bulin , Christophe Cros , Juluan Gaultier
IPC分类号： B64C25/50 , B64C25/36
CPC分类号： B64C25/405 , Y02T50/823
摘要： Device for driving at least one wheel of an aircraft landing gear, which includes at least one turbine machine incorporated into the landing gear of the aircraft. Advantageously, the turbine machine is a pneumatic turbine.
摘要翻译：用于驱动飞机起落架的至少一个车轮的装置，其包括结合到飞行器的起落架中的至少一个涡轮机。有利地，涡轮机是气动涡轮机。

16. 发明申请

US20100300066A1 TURBOJET ENGINE FOR AIRCRAFT 审中-公开
标题翻译：涡轮发动机
公开(公告)号：US20100300066A1
公开(公告)日：2010-12-02
申请号：US12665790
申请日：2008-06-18
申请人： Guillaume Bulin , Patrick Oberle
发明人： Guillaume Bulin , Patrick Oberle
IPC分类号： F02K99/00
CPC分类号： F02K7/14 , F01D9/065 , F02C7/14 , F02C7/185 , F02K3/06 , F05D2240/12 , F05D2250/32 , F05D2260/20 , F05D2260/2214 , Y02T50/67 , Y02T50/676
摘要： A turbojet engine for an aircraft that includes an engine provided in a nacelle and at least one heat exchanger for cooling down a hot fluid collected in the propulsion system of the turbojet engine before re-injecting the aforementioned partially-cooled hot flow into the aforementioned propulsion system, wherein at least one heat exchanger is a radial heat exchanger extending in the lower portion of the turbojet engine at a lower branching of the turbojet engine.
摘要翻译：一种用于飞行器的涡轮喷气发动机，其包括设置在机舱中的发动机和至少一个热交换器，用于冷却在涡轮喷气发动机的推进系统中收集的热流体，然后将上述部分冷却的热流再次注入上述推进系统，其中至少一个热交换器是在涡轮喷气发动机的较低分支处在涡轮喷气发动机的下部延伸的径向热交换器。

17. 发明申请

US20100288244A1 METHOD FOR CONTROLLING THERMAL EFFLUENTS GENERATED BY AN AIRCRAFT AND COOLING DEVICE FOR AN AIRCRAFT IMPLEMENTING SAID METHOD 有权
标题翻译：用于控制飞机生产的热效应的方法和用于实施方法的飞机的冷却装置
公开(公告)号：US20100288244A1
公开(公告)日：2010-11-18
申请号：US12742937
申请日：2008-11-12
申请人： Guillaume Bulin , Jan Dittmar
发明人： Guillaume Bulin , Jan Dittmar
IPC分类号： F02G5/00
CPC分类号： B64D37/34 , B64D33/10 , B64D2013/0614 , B64D2013/0659 , F02C7/224 , Y02T50/54 , Y02T50/671
摘要： A process for management of thermal effluents of an aircraft that includes an airframe (110) and at least one propulsion system (112), whereby the at least one propulsion system (112) includes a gas turbine engine (116) that is supplied with fuel via a fuel supply circuit (122) that extends from a reservoir (124) that is arranged at the airframe (110), whereby the airframe (110) includes at least one source of thermal effluents (134), wherein the process includes at least partially dissipating—at the level of at least one propulsion system (112)—the thermal effluents that are generated at the airframe (110) by using as coolant the fuel that is used for supplying the gas turbine engine (116).
摘要翻译：一种用于管理包括机体（110）和至少一个推进系统（112）的飞机的热排出物的过程，由此所述至少一个推进系统（112）包括燃气涡轮发动机（116），所述燃气涡轮发动机（116）被供应燃料通过从布置在机身（110）处的储存器（124）延伸的燃料供应回路（122），由此机身（110）包括至少一个热源流出源（134），其中该过程至少包括通过使用用于供应燃气涡轮发动机（116）的燃料作为冷却剂，在至少一个推进系统（112）的水平面部分地消散在机身（110）处产生的热流出物。

18. 发明授权

US07818958B2 Jet engine nacelle for an aircraft and aircraft comprising such a nacelle 有权
标题翻译：用于包括这种机舱的飞机和飞机的喷气发动机机舱
公开(公告)号：US07818958B2
公开(公告)日：2010-10-26
申请号：US12443343
申请日：2007-09-28
申请人： Guillaume Bulin , Patrick Oberle , Thierry Surply
发明人： Guillaume Bulin , Patrick Oberle , Thierry Surply
IPC分类号： F02K3/04
CPC分类号： F02K3/06 , F02K1/09 , F02K1/28 , Y02T50/671
摘要： A nacelle for an aircraft high-bypass jet engine, in which a jet engine having a longitudinal axis is mounted, the nacelle including a wall concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct for fluid inner flow, including at the downstream end of the nacelle wall a passage section of a flow outlet. The nacelle includes a displacement mechanism displacing on request a portion of the nacelle wall to modify the passage section of the flow outlet through which a major portion of the flow escapes, the displacement forming in the nacelle wall at least one opening through which a small portion of a leak flow, naturally escapes. The nacelle further includes a fluid device that uses a fluid for compelling the leak flow to flow along the outer face of the portion of the nacelle wall located downstream relative to the at least one opening.
摘要翻译：用于飞机高旁路喷气发动机的机舱，其中安装有具有纵向轴线的喷气发动机，所述机舱包括壁同心并且至少部分地围绕喷气发动机并且与后者一起限定用于流体内部流动的环形管道，包括在所述机舱壁的下游端处具有流出口的通道部分。机舱包括位移机构，根据要求移动机舱壁的一部分，以改变流出口的通道部分，流体出口的主要部分通过该通道部分排出，在机舱壁中形成至少一个开口的位移，小部分的泄漏流，自然逃脱。机舱还包括流体装置，其使用流体来迫使泄漏流沿着相对于至少一个开口下游的机舱壁的部分的外表面流动。

19. 发明申请

US20100212857A1 SYSTEM FOR COOLING AND ADJUSTING THE TEMPERATURE OF APPARATUSES IN THE PROPULSION ASSEMBLY OF AN AIRCRAFT 有权
标题翻译：飞机推进装置冷却和调节装置温度的系统
公开(公告)号：US20100212857A1
公开(公告)日：2010-08-26
申请号：US12532696
申请日：2008-03-25
申请人： Guillaume Bulin , Stephane Pugliese , Christian Fabre , Patrick Oberle
发明人： Guillaume Bulin , Stephane Pugliese , Christian Fabre , Patrick Oberle
IPC分类号： B60K11/00
CPC分类号： F02C7/224 , F02C7/14 , F05D2260/205 , Y02T50/671 , Y02T50/676
摘要： A system for cooling and adjusting the temperature of apparatuses in the propulsion assembly of an aircraft, that includes first means for heat exchange between lubrication circuits of at least two of the aforementioned apparatuses and a heat-carrier fluid contained in a closed circuit, a second means for heat exchange between the heat-carrier fluid and at least one coolant, the first heat exchange means being arranged locally at each of the aforementioned apparatuses, the second heat exchange means being remote from the aforementioned first means, the closed circuit extending between at least two of the aforementioned apparatuses and the aforementioned second means.
摘要翻译：一种用于冷却和调节飞行器推进组件中的装置的温度的系统，其包括用于至少两个上述装置的润滑回路之间的热交换的第一装置和包含在闭合回路中的热载体流体的第二装置用于在所述热载体流体和至少一个冷却剂之间进行热交换的装置，所述第一热交换装置局部地布置在每个所述装置处，所述第二热交换装置远离上述第一装置，所述闭合回路在至少两个上述装置和上述第二装置。

20. 发明申请

US20090199536A1 PROCESS FOR REVERSING THE THRUST PRODUCED BY A PROPULSION UNIT OF AN AIRCRAFT, DEVICE FOR ITS IMPLEMENTATION, NACELLE EQUIPPED WITH SAID DEVICE 审中-公开
标题翻译：用于反转由飞机的推进单元产生的扭矩的过程，用于其实施的装置，装有设备的装置
公开(公告)号：US20090199536A1
公开(公告)日：2009-08-13
申请号：US12307483
申请日：2007-06-28
申请人： Guillaume Bulin , Patrick Oberle , Thierry Surply
发明人： Guillaume Bulin , Patrick Oberle , Thierry Surply
IPC分类号： F02K3/02
CPC分类号： F02K3/06 , F02K1/09 , F02K1/28 , F02K1/30 , F02K1/32 , F02K1/34 , F02K1/70 , F02K1/72 , Y02T50/671
摘要： The object of the invention is a process whose purpose is to reduce, cancel or reverse the thrust generated by at least one air flow exiting from a propulsion unit of an aircraft by deflecting at least a portion of the flow that is able to assist the thrust, characterized in that it consists in injecting at the level of the propulsion unit a fluid called a thrust reversal fluid to deflect by an entrainment effect, from the inside of the nacelle toward the outside of the nacelle, at least a portion of the flow that is able to assist the thrust.
摘要翻译：本发明的目的是一种方法，其目的是通过使能够协助推力的至少一部分流动来减少，抵消或扭转由飞行器的推进单元离开的至少一个气流产生的推力其特征在于，其包括在所述推进单元的水平面处喷射称为推力反向流体的流体，以通过夹带效应从所述机舱的内部朝向所述机舱的外部偏转所述流动的至少一部分，能够帮助推力。

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