-
11.发明申请公开(公告)号：US20140131515A1
公开(公告)日：2014-05-15
申请号：US13944187
申请日：2013-07-17
Applicant: AIRCELLE
Inventor： Pierre Caruel
CPC classification number: F02K1/54 , B64D33/04 , F02K1/72 , F02K1/766 , Y02T50/671
Abstract: A thrust reverser with grids includes a jet engine pylon, a one piece cowl either directly or indirectly slidably mounted on the jet engine pylon between a direct jet position and a reverse jet position, and a system for locking this cowl on a beam. The system has a single tertiary lock, which is positioned on one side of the jet engine pylon being capable of locking a corresponding upper edge of the cowl. In addition, the tertiary lock includes a locker to lock the cowl, a blocker for blocking the locker, and a position detector in order to detect the position of the locker. The system further includes another detector to detect proper closing of the other upper edge of the cowl.
Abstract translation: 具有网格的推力反向器包括喷气式发动机塔架，直接或间接可滑动地安装在喷气发动机塔架上的直接喷射位置和反向喷射位置之间的一个整流罩，以及用于将该罩盖锁定在梁上的系统。 该系统具有单个三级锁，其位于喷气发动机塔的一侧，能够锁定整流罩的相应上边缘。 此外，三级锁包括用于锁定整流罩的储物柜，用于阻挡储物柜的阻塞器和用于检测储物柜位置的位置检测器。 该系统还包括用于检测整流罩的另一个上边缘的适当关闭的另一检测器。
-
公开(公告)号：US10532820B2
公开(公告)日：2020-01-14
申请号：US15153172
申请日：2016-05-12
Applicant: AIRCELLE
Inventor： Pierre Caruel
Abstract: A de-icing device is provided that includes a piccolo tube integrated with a front bulkhead for limiting an inner volume of a perforated front lip. The piccolo tube is in contact with a noise reduction cellular structure provided with perforations and hot air circulation channels delivered by the piccolo tube, the de-icing hot air being diffused through the perforations and channels of the cellular structure, on the perforations facing the front lip.
-
公开(公告)号：US10036348B2
公开(公告)日：2018-07-31
申请号：US14584435
申请日：2014-12-29
Applicant: AIRCELLE
Inventor： Pierre Caruel , Hervé Hurlin , Olivier Kerbler
CPC classification number: F02K1/15 , F02K1/763 , F02K9/80 , F05D2270/051
Abstract: A method for controlling a position of a variable nozzle of an aircraft includes the following steps: setting the variable nozzle in a position P(t0) at a time t0 as a preliminary step; step A in which at each instant ti with 1
-
公开(公告)号：US09777670B2
公开(公告)日：2017-10-03
申请号：US14166159
申请日：2014-01-28
Applicant: AIRCELLE
Inventor： Pierre Caruel
Abstract: The present disclosure relates to a nacelle for a dual-flow turbojet engine includes a cold airstream having a non-constant cross-section over the periphery of the nacelle, such that at least one flap is radially offset with respect to the central axis of the turbojet engine, relative to the adjacent flaps. The system for driving the radially offset flaps is suitable for ensuring that the kinematics of the flaps are offset relative to the kinematics of the flaps mounted along the remainder of the periphery of the airstream.
-
公开(公告)号：US09677502B2
公开(公告)日：2017-06-13
申请号：US14720403
申请日：2015-05-22
Applicant: AIRCELLE
Inventor： Pierre Caruel
CPC classification number: F02K1/56 , B64D29/08 , F02K1/72 , F02K1/763 , F05D2230/72 , F05D2260/36
Abstract: The present disclosure relates to a turbojet engine nacelle equipped with at least one thrust reverser. The thrust reverser includes: two half-cowls forming an outer cowl which is articulated on hinges and translates between closed and open positions, a first actuator to translationally actuate a downstream frame, a second actuator to rotationally actuate each half-cowl, and a lock capable of locking or unlocking the half-cowls relative to one another. In particular, the thrust reverser includes cascades vanes supported at their upstream end by an upstream frame and at their downstream end by the downstream frame, and a connector between the downstream frame and the external cowl. The cascade vanes are enclosed in a shroud formed by a fan casing and a fan cowl.
-
Patent Agency Ranking
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。
-
17.发明授权Aircraft turbojet engine thrust reverser with a reduced number of latches 有权飞机涡轮喷气发动机推力反向器具有减少的锁存数量公开(公告)号：US09476383B2
公开(公告)日：2016-10-25
申请号：US13944187
申请日：2013-07-17
Applicant: AIRCELLE
Inventor： Pierre Caruel
CPC classification number: F02K1/54 , B64D33/04 , F02K1/72 , F02K1/766 , Y02T50/671
Abstract: A thrust reverser with grids includes a jet engine pylon, a one piece cowl either directly or indirectly slidably mounted on the jet engine pylon between a direct jet position and a reverse jet position, and a system for locking this cowl on a beam. The system has a single tertiary lock, which is positioned on one side of the jet engine pylon being capable of locking a corresponding upper edge of the cowl. In addition, the tertiary lock includes a locker to lock the cowl, a blocker for blocking the locker, and a position detector in order to detect the position of the locker. The system further includes another detector to detect proper closing of the other upper edge of the cowl.
Abstract translation: 具有网格的推力反向器包括喷气式发动机塔架，直接或间接可滑动地安装在喷气发动机塔架上的直接喷射位置和反向喷射位置之间的一个整流罩，以及用于将该罩盖锁定在梁上的系统。 该系统具有单个三级锁，其位于喷气发动机塔的一侧，能够锁定整流罩的相应上边缘。 此外，三级锁包括用于锁定整流罩的储物柜，用于阻挡储物柜的阻塞器和用于检测储物柜位置的位置检测器。 该系统还包括用于检测整流罩的另一个上边缘的适当关闭的另一检测器。
-
公开(公告)号：US20150367946A1
公开(公告)日：2015-12-24
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.
Abstract translation: 本公开涉及一种用于飞行器的推进单元，其包括围绕涡轮喷气发动机的机舱。 机舱具有围绕涡轮喷气发动机的下游隔室的内部结构，并且内部结构包括两个环形半部分。 推进单元还包括轨道/引导单元并且使工作位置和维护位置之间的环形半部分移动。 特别地，轨道/引导单元在环形半部分的平移运动期间相对于机舱的纵向轴线径向地移动环形半部分。 机舱设置有连接到环形半部分和涡轮喷气发动机的连杆，使得连杆有助于围绕轨道旋转环形半部。
-
19.发明授权公开(公告)号：US10669971B2
公开(公告)日：2020-06-02
申请号：US14978490
申请日：2015-12-22
Applicant: AIRCELLE
Inventor： Pierre Caruel
Abstract: A thrust reverser for a turbojet engine nacelle includes movable cowls which move backward relative to a front frame under the action of an actuation system, thereby making flaps tilt, via a control mechanism, so as to substantially close the annular cold air flow path, and by opening cascades disposed around this flow path and which receive the cold air flow and return it forward. When the thrust reverser is closed, the cascades are partially integrated in the cowls, and the thrust reverser includes an actuation system which makes the cascades move backward along a stroke which is shorter than the stroke of the cowl.
-
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.
-
-
-
-
-
-
-
-
-
Search Results
28
records
(took 0.016 seconds)
