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公开(公告)号：US10190538B2
公开(公告)日：2019-01-29
申请号：US14841407
申请日：2015-08-31
Applicant: AIRCELLE
Inventor： Patrick Boileau , Peter Segat , Pierre Caruel , Sarah Tissot
Abstract: A thrust reverser device for an aircraft turbojet engine includes: a movable cowl, translating cascades connected to the movable cowl, a mast; and a front suspension to suspend the turbojet engine. The cascades translates between a direct jet position where the cascades are retracted in a fan casing, and an indirect jet position where the cascades are brought out of the fan casing. In particular, the cascades have a sliding connection with the mast by means of at least one spacer connected to the mast downstream of the front suspension.
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Patent Agency Ranking
公开(公告)号：US09151225B2
公开(公告)日：2015-10-06
申请号：US14304555
申请日：2014-06-13
Applicant: AIRCELLE
Inventor： Nicolas Dezeustre , Pierre Caruel , Patrick Gonidec , Patrick Boileau
CPC classification number: F02C7/045 , B64D33/02 , B64D2033/0206 , B64D2033/0286
Abstract: An air intake structure for a turbojet engine nacelle includes a substantially annular main structure having an internal wall, an external wall and an air intake lip structure connecting the external and internal walls upstream. The air intake structure also includes a first acoustic attenuation structure which has a holed acoustic skin, a cellular core and a solid rear skin with which the internal wall is equipped, and a second acoustic attenuation structure having a similar architecture fitted to a part of the air intake lip substantially near a junction with the internal wall. The rear skin of the first acoustic attenuation structure is aligned with the rear skin of the second acoustic attenuation structure, both of rear skins being structural.
Abstract translation: 用于涡轮喷气发动机机舱的进气结构包括具有连接外壁和内壁上游的内壁，外壁和进气口结构的基本上环形的主结构。 进气结构还包括第一声衰减结构，该第一声衰减结构具有孔声学皮肤，多孔芯和固定的后壁，内壁装有该第一声衰减结构，以及具有类似结构的第二声衰减结构， 进气口基本上在与内壁的接合处附近。 第一声衰减结构的后表皮与第二声衰减结构的后表皮对准，两个后皮都是结构的。
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公开(公告)号：US09587583B2
公开(公告)日：2017-03-07
申请号：US14173484
申请日：2014-02-05
Applicant: AIRCELLE
Inventor： Pierre Caruel , Patrick Gonidec , Patrick Boileau
CPC classification number: F02K1/763 , F02K1/06 , F02K1/12 , F02K1/30 , F02K1/625 , F02K1/72 , F02K1/766 , Y02T50/671
Abstract: A turbojet engine nacelle has a thrust reverser device and an actuating system for said thrust reverser device, and the thrust reverser device includes a moving cowl mounted translatably alternating between a closed position and an open position, and a jet nozzle section for gases that extends the moving cowl. In particular, the jet nozzle section includes a nozzle flap mounted movable between a closed position and an open position in which the nozzle flap opens a leakage passage toward the outside of the nozzle section. The actuating system has an actuator shared with the moving cowl and the nozzle flap to activate the translational movement of the moving cowl and to pivot the nozzle flap between three following positions: an idle position, an open position of the nozzle flap and an open position of the moving cowl.
Abstract translation: 涡轮喷气发动机发动机舱具有推力反向装置和用于所述推力反向装置的致动系统，并且推力反向装置包括可在可关闭位置和打开位置之间平移地交替安装的移动整流罩，以及用于气体的喷嘴部分， 移动整流罩 特别地，喷嘴部分包括安装在关闭位置和打开位置之间的喷嘴盖，喷嘴盖打开朝向喷嘴部分外部的泄漏通道。 致动系统具有与移动整流罩和喷嘴挡板共享的致动器，以启动移动整流罩的平移运动并使喷嘴阀瓣在三个以下位置之间枢转：空转位置，喷嘴挡板的打开位置和打开位置 的移动整流罩。
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公开(公告)号：US10309340B2
公开(公告)日：2019-06-04
申请号：US15281569
申请日：2016-09-30
Applicant: AIRCELLE
Inventor： Patrick Boileau , Olivier Kerbler
Abstract: A thrust reverser of a bypass turbojet engine nacelle is disclosed, which includes movable cowls that move backwards with respect to a fixed front structure to uncover thrust reverser cascades and a variable secondary nozzle connected to the movable cowls by guide means allowing an axial sliding of the system which controls the movement of this variable secondary nozzle, wherein it includes cylinders bearing on the front structure for controlling reversal means of the displacement direction connected to the movable cowls, which move the variable secondary nozzle backwards when these cylinders output a forward stroke, as well as blocking devices which connect the secondary nozzle to the movable cowls when this nozzle is deployed.
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公开(公告)号：US10167815B2
公开(公告)日：2019-01-01
申请号：US15290115
申请日：2016-10-11
Applicant: AIRCELLE
Inventor： Patrick Boileau , Olivier Kerbler
Abstract: A thrust reverser of a turbofan pod is provided that includes movable cowlings that retract relative to stationary front structure to reveal stationary or movable thrust reverser cascades, as well as a secondary variable nozzle section connected to the movable cowlings by guiding means enabling movement controlled by actuators engaged with the front structure to apply an axial thrust. The actuators are directly connected to the secondary nozzle, and in that the thrust reverser comprises latches connected to the movable cowlings, having two positions providing, alternately, latching onto the front structure or latching onto the control of the secondary nozzle.
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公开(公告)号：US09957056B2
公开(公告)日：2018-05-01
申请号：US14716969
申请日：2015-05-20
Inventor： Patrick Boileau , Pierre Caruel , Carmen Ancuta , Bruno Beutin
Abstract: The present disclosure relates to a propulsion unit for an aircraft including a nacelle which surrounds a turbojet engine. The nacelle has an inner structure surrounding a downstream compartment of the turbojet engine, and the inner structure includes two annular half-portions. The propulsion unit also includes a rail/guide unit and to move the annular half-portions between a working position and a maintenance position. In particular, the rail/guide unit radially moves away the annular half-portions relative to a longitudinal axis of the nacelle, during a translation movement of the annular half-portions. The nacelle is provided with a connecting rod which is connected to the annular half-portions and to the turbojet engine and so that the connecting rod contributes to rotate the annular half-portions about the rail.
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