公开(公告)号：US08841584B2

公开(公告)日：2014-09-23

申请号：US13318616

申请日：2010-05-03

申请人： Guillaume Bulin ,  Severine Perret

发明人： Guillaume Bulin ,  Severine Perret

IPC分类号： B60L1/02 ,  B64D15/12 ,  B64C11/48 ,  B64D27/02

CPC分类号： B64D15/12 ,  B64C11/48 ,  B64D2027/026 ,  F28D15/02 ,  Y02T50/66

摘要： A deicing device for propfan-type aircraft propulsion unit blades, wherein 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 the outer envelope of the propulsion unit, the outer envelope being subjected to atmospheric conditions outside the propulsion unit, the turbomachine generating 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. The deicing device includes: a mechanism transforming thermal energy into electrical energy, within the moving annular part; a mechanism transferring the generated electrical energy towards the rotor blades; and a mechanism transforming the electrical energy into thermal energy onto at least a part of the surface of the blades.

摘要翻译： 一种用于丙烷型飞机推进单元叶片的除冰装置，其中推进单元包括涡轮机，该涡轮机旋转地驱动至少一个转子，该转子包括多个叶片，该叶片布置在与叶片一起移动的环形冠部周围，叶片的外壁部分 推进单元的外壳，外壳在推进单元外部经受大气条件，涡轮机产生通过环形热静脉排出的热气流，其与移动的环形冠同心，并被定义为部分 的表面由移动的环形冠的内壁。 除冰装置包括：在移动的环形部分内将热能转换成电能的机构; 将产生的电能转移到转子叶片的机构; 以及将电能转换成热能到机翼表面的至少一部分上的机构。

公开(公告)号：US08684299B2

公开(公告)日：2014-04-01

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

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。

公开(公告)号：US08499822B2

公开(公告)日：2013-08-06

申请号：US12532696

申请日：2008-03-25

申请人： Guillaume Bulin ,  Stephane Pugliese ,  Fabre Christian ,  Patrick Oberle

发明人： Guillaume Bulin ,  Stephane Pugliese ,  Fabre Christian ,  Patrick Oberle

IPC分类号： F01N5/02

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。

公开(公告)号：US08128022B2

公开(公告)日：2012-03-06

申请号：US12435655

申请日：2009-05-05

申请人： Guillaume Bulin

发明人： Guillaume Bulin

IPC分类号： B64D27/00 ,  B64D27/16 ,  B64D27/18

CPC分类号： B64D29/06

摘要： The object of the invention is an aircraft nacelle that comprises, on the inside, an inside pipe (56) that empties out toward the front at an air intake (58), and, on the outside, an aerodynamic wall that extends from the air intake (58) up to the rear end of the nacelle, and a hood (62) that comprises said air intake (58) as well as a cylindrical wall (64) that forms at least one portion of the aerodynamic surface of the outside of the nacelle, whereby said hood (62) can move translationally relative to a stationary part of the nacelle toward the front along slides (72), each slide (72) comprising a guide element (74) that is connected to the hood (or to the stationary part of the nacelle), whereby said guide element (74) can slide into a pipe (78) that is connected to the stationary part of the nacelle (or to a hood) and has a section that is above the section of the guide element (74) so as to allow the hood (62) to rotate in order to immobilize it in the closed position.

摘要翻译： 本发明的目的是一种飞机机舱，其在内部包括在进气口（58）向前排空的内管（56），并且在外部包括从空气延伸的空气动力学壁 进气口（58）直到机舱的后端，以及包括所述进气口（58）的罩（62）以及形成至少一部分空气动力学表面的圆柱形壁（64） 由此所述罩（62）能够相对于所述机舱的固定部分沿着滑架（72）向前移动而平移地移动，每个滑动件（72）包括连接到所述罩（或者连接到所述机罩）的引导元件（74） 机舱的固定部分），由此所述引导元件（74）可以滑入连接到所述机舱（或罩）的固定部分的管道（78），并且具有位于所述机舱 引导元件（74）以允许罩（62）旋转以便将其固定在关闭位置。

公开(公告)号：US08739516B2

公开(公告)日：2014-06-03

申请号：US12306177

申请日：2007-06-19

申请人： Guillaume Bulin ,  Patrick Oberle

发明人： Guillaume Bulin ,  Patrick Oberle

IPC分类号： F02K99/00

CPC分类号： F02K3/04 ,  F02C7/14 ,  F05D2240/14 ,  F05D2260/20 ,  Y02T50/67 ,  Y02T50/675

摘要： The invention concerns a turbojet for aircraft including engine located in nacelle, and thermal exchanger intended to cool a fluid participating in the engine propulsive system, characterized in that said thermal exchanger is located on engine external wall, an interstitial space within which air can circulate being arranged between the engine external wall and a lower wall of said thermal exchanger. The invention also concerns an aircraft provided with at least one such turbojet.

摘要翻译： 本发明涉及用于飞行器的涡轮喷气发动机，包括位于机舱中的发动机，以及用于冷却参与发动机推进系统的流体的热交换器，其特征在于，所述热交换器位于发动机外壁上，空气可以在其间循环的间隙空间 布置在发动机外壁和所述热交换器的下壁之间。 本发明还涉及具有至少一个这种涡轮喷气发动机的飞行器。

公开(公告)号：US08677755B2

公开(公告)日：2014-03-25

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： F02C7/224

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。

公开(公告)号：US20130175388A1

公开(公告)日：2013-07-11

申请号：US13635278

申请日：2011-03-16

申请人： Guillaume Bulin ,  Christophe Cros

发明人： Guillaume Bulin ,  Christophe Cros

IPC分类号： B64C25/40

CPC分类号： B64C25/405 ,  F02C7/32 ,  F05D2250/82 ,  Y02T50/54 ,  Y02T50/671 ,  Y02T50/823

摘要： The invention relates to a device for driving at least one landing gear wheel of an aircraft by means of a wheel motor, which is intended to be used in the stage when the aircraft is traveling on the ground, said aircraft having turbojet engines (1) attached to the main wing. The device comprises at least one power source (6, 8), and one power transmission line between the power source and the wheel motor. The power source (6, 8) is arranged adjacently to a turbojet engine (1) attached to the main wing of the aircraft, and comprises disengageable means (7) enabling the power source to be mechanically connected to the rotating portion of the turbojet engine (1), the power source being sufficient to act as a starter for the turbojet engine (1).

摘要翻译： 本发明涉及一种用于通过轮式电动机来驱动飞行器的至少一个起落架轮的装置，所述轮式电动机旨在在飞行器在地面上行驶的阶段中使用，所述飞行器具有涡轮喷气发动机（1） 附在主翼。 该装置包括至少一个电源（6,8）和在电源和车轮电动机之间的一个电力传输线。 电源（6,8）与安装在飞行器的主翼上的涡轮喷气发动机（1）相邻设置，并且包括能够将动力源与涡轮喷气发动机的旋转部分机械连接的可脱离装置（7） （1），电源足以用作涡轮喷气发动机（1）的起动器。

公开(公告)号：US07703716B2

公开(公告)日：2010-04-27

申请号：US11798375

申请日：2007-05-14

申请人： Guillaume Bulin

发明人： Guillaume Bulin

IPC分类号： B64D29/00 ,  B64D29/08

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。

公开(公告)号：US20090301057A1

公开(公告)日：2009-12-10

申请号：US12306177

申请日：2007-06-19

申请人： Guillaume Bulin ,  Patrick Oberle

发明人： Guillaume Bulin ,  Patrick Oberle

IPC分类号： F02K99/00

CPC分类号： F02K3/04 ,  F02C7/14 ,  F05D2240/14 ,  F05D2260/20 ,  Y02T50/67 ,  Y02T50/675

摘要： The invention concerns a turbojet for aircraft including engine located in nacelle, and thermal exchanger intended to cool a fluid participating in the engine propulsive system, characterized in that said thermal exchanger is located on engine external wall, an interstitial space within which air can circulate being arranged between the engine external wall and a lower wall of said thermal exchanger. The invention also concerns an aircraft provided with at least one such turbojet.

摘要翻译： 本发明涉及用于飞行器的涡轮喷气发动机，包括位于机舱中的发动机，以及用于冷却参与发动机推进系统的流体的热交换器，其特征在于，所述热交换器位于发动机外壁上，空气可以在其间循环的间隙空间 布置在发动机外壁和所述热交换器的下壁之间。 本发明还涉及具有至少一个这种涡轮喷气发动机的飞行器。

公开(公告)号：US20090272842A1

公开(公告)日：2009-11-05

申请号：US12435655

申请日：2009-05-05

申请人： Guillaume BULIN

发明人： Guillaume BULIN

IPC分类号： B64D27/26

CPC分类号： B64D29/06

摘要： The object of the invention is an aircraft nacelle that comprises, on the inside, an inside pipe (56) that empties out toward the front at an air intake (58), and, on the outside, an aerodynamic wall that extends from the air intake (58) up to the rear end of the nacelle, and a hood (62) that comprises said air intake (58) as well as a cylindrical wall (64) that forms at least one portion of the aerodynamic surface of the outside of the nacelle, whereby said hood (62) can move translationally relative to a stationary part of the nacelle toward the front along slides (72), each slide (72) comprising a guide element (74) that is connected to the hood (or to the stationary part of the nacelle), whereby said guide element (74) can slide into a pipe (78) that is connected to the stationary part of the nacelle (or to a hood) and has a section that is above the section of the guide element (74) so as to allow the hood (62) to rotate in order to immobilize it in the closed position.

摘要翻译： 本发明的目的是一种飞机机舱，其在内部包括在进气口（58）向前排空的内管（56），并且在外部包括从空气延伸的空气动力学壁 进气口（58）直到机舱的后端，以及包括所述进气口（58）的罩（62）以及形成至少一部分空气动力学表面的圆柱形壁（64） 由此所述罩（62）能够相对于所述机舱的固定部分沿着滑架（72）向前移动而平移地移动，每个滑动件（72）包括连接到所述罩（或者连接到所述机罩）的引导元件（74） 机舱的固定部分），由此所述引导元件（74）可以滑入连接到所述机舱（或罩）的固定部分的管道（78），并且具有位于所述机舱 引导元件（74）以允许罩（62）旋转以便将其固定在关闭位置。