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。

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。

公开(公告)号：US20100044503A1

公开(公告)日：2010-02-25

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： B64C7/02 ,  B64D29/00 ,  F02K3/02

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。

公开(公告)号：US20090277155A1

公开(公告)日：2009-11-12

申请号：US12521869

申请日：2007-12-27

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： B64C7/02 ,  F02K1/28 ,  F02K1/30 ,  F02K1/72 ,  F02K3/06 ,  F05D2260/60 ,  F05D2270/173 ,  F05D2270/18 ,  Y02T50/671

摘要： The invention relates to a nacelle, for an aircraft jet engine (10) having a high bypass ratio, in which a jet engine having a longitudinal axis (X) is mounted, the nacelle (12) including a wall (24) concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct (26) for a fluid internal flow having, at the downstream end of the nacelle wall, a flow outlet passage section, characterised in that the nacelle includes displacement means (40) for controllably displacing a portion (24b) of the nacelle wall in order to modify the section of the flow outlet passage, wherein said displacement generates in the nacelle wall at least one longitudinally extending opening (28), the nacelle including a device (30) for forming a fluid barrier (fi) extending along a portion at least of the longitudinal extent of said at least one opening (28) in order to counteract the natural exhaust through said at least one opening of a portion of the so-called trailing flow.

摘要翻译： 本发明涉及一种用于具有高旁路比的飞机喷气发动机（10）的机舱，其中安装有具有纵向轴线（X）的喷气发动机，所述机舱（12）包括壁（24），同心且位于 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的环形管道（26），其在机舱壁的下游端处具有流出口通道部分，其特征在于，所述机舱包括位移装置（40） 用于可控地移动所述机舱壁的一部分（24b）以改变所述流出口通道的所述部分，其中所述位移在所述机舱壁中产生至少一个纵向延伸的开口（28），所述机舱包括装置（30） 用于形成沿着所述至少一个开口（28）的纵向范围的至少一部分延伸的流体屏障（fi），以抵消所述自然排气通过所述尾迹的一部分的所述至少一个开口 g流。

公开(公告)号：US08596037B2

公开(公告)日：2013-12-03

申请号：US12521869

申请日：2007-12-27

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： B64C7/02 ,  F02K1/28 ,  F02K1/30 ,  F02K1/72 ,  F02K3/06 ,  F05D2260/60 ,  F05D2270/173 ,  F05D2270/18 ,  Y02T50/671

摘要： A nacelle, for an aircraft jet engine having a high bypass ratio, in which a jet engine having a longitudinal axis is mounted. The nacelle includes a wall that concentrically, and at least partially, surrounds the jet engine and together defines an annular duct. The nacelle further includes a displacement device that controllably displaces a portion of the nacelle wall in order to modify the section of the flow outlet passage and form at least one longitudinally extending opening. A device for forming a fluid barrier along the at least one longitudinally extending opening is provided to counteract the natural exhaust.

摘要翻译： 对于具有高旁路比的飞机喷气发动机，其中安装有具有纵向轴线的喷气发动机的机舱。 机舱包括同心且至少部分地围绕喷气发动机并且一起限定环形管道的壁。 机舱还包括位移装置，其可控地移动机舱壁的一部分，以便改变流出口通道的部分并形成至少一个纵向延伸的开口。 用于沿着至少一个纵向延伸的开口形成流体屏障的装置被提供以抵消自然排气。

公开(公告)号：US08925295B2

公开(公告)日：2015-01-06

申请号：US13235706

申请日：2011-09-19

申请人： Guillaume Bulin ,  Thierry Surply

发明人： Guillaume Bulin ,  Thierry Surply

IPC分类号： F02K3/075 ,  F02K1/12 ,  F02K1/70 ,  B64D29/00 ,  F02K1/82

CPC分类号： F02K1/70 ,  B64D29/00 ,  F02K1/12 ,  F02K1/827 ,  Y02T50/671

摘要： An air discharging device (20) for an aircraft turbine engine, comprising at least one door (24) displaceable between an open and a closed position of a corresponding orifice (30) and comprising two valves (26, 28), which delimit between them a conduit (68) for guiding a portion (74) of the secondary flow (76) outwards in the downstream direction, and which are integral with each other and are hinged around a pivot axis (58), so that in said open position, the upstream end of said internal valve (26) protrudes from the inner side relative to the internal surface (12), the downstream end of said external valve (28) protrudes from the external side relative to the external surface (14), and said internal valve (26) is spaced away from the fixed structure (22) so that an air passage exists downstream of said internal valve (26), between the latter and said fixed structure (22).

摘要翻译： 一种用于飞行器涡轮发动机的排气装置（20），包括至少一个门（24），所述门可在对应的孔口（30）的打开和关闭位置之间移动并且包括两个阀门（26,28），其在它们之间界定 用于沿下游方向向外引导二次流（76）的一部分（74）并彼此成一体并围绕枢转轴线（58）铰接的导管（68），使得在所述打开位置， 所述内阀（26）的上游端相对于内表面（12）从内侧突出，所述外阀（28）的下游端相对于外表面（14）从外侧突出，并且所述 内部阀（26）与固定结构（22）间隔开，使得在所述内部阀（26）的下游，后者和所述固定结构（22）之间存在空气通道。

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：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：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：US08235657B2

公开(公告)日：2012-08-07

申请号：US11766286

申请日：2007-06-21

申请人： Guillaume Bulin ,  Patrick Oberle

发明人： Guillaume Bulin ,  Patrick Oberle

IPC分类号： F01D5/08

CPC分类号： F02K3/06 ,  F01D9/065 ,  F01D25/12 ,  F02C7/14 ,  F02C7/18 ,  F02K3/115 ,  Y02T50/67 ,  Y02T50/675

摘要： A turbojet for an aircraft includes an engine housed in a nacelle and a thermal exchanger that can be traversed by a hot fluid designed to be cooled by thermal exchange with a cold fluid external to the thermal exchanger. The thermal exchanger is disposed in an internal volume of the nacelle, between an internal wall of the nacelle and an external wall of the engine, in such a way as to present two thermal exchange surfaces in the flow of the air stream from the turbojet. The disclosed embodiments also relate to an aircraft equipped with such a jet turbine engine.

摘要翻译： 用于飞行器的涡轮喷气发动机包括容纳在机舱中的发动机和热交换器，热交换器可以被设计成通过与热交换器外部的冷流体进行热交换而被冷却的热流体横穿。 热交换器设置在机舱的内部体积中，在机舱的内壁和发动机的外壁之间，以便在来自涡轮喷气发动机的气流的流动中呈现两个热交换表面。 所公开的实施例还涉及配备有这种喷气涡轮发动机的飞机。