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1. 发明授权

US10036348B2 Method for controlling a variable nozzle section of an aircraft 有权
公开(公告)号：US10036348B2
公开(公告)日：2018-07-31
申请号：US14584435
申请日：2014-12-29
申请人： AIRCELLE
发明人： Pierre Caruel , Hervé Hurlin , Olivier Kerbler
IPC分类号： F02K1/15 , F02K1/76 , F02K9/80
CPC分类号： F02K1/15 , F02K1/763 , F02K9/80 , F05D2270/051
摘要： 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

2. 发明授权

US09816462B2 Integrated thrust reverser device and aircraft engine nacelle equipped therewith 有权
公开(公告)号：US09816462B2
公开(公告)日：2017-11-14
申请号：US15017931
申请日：2016-02-08
申请人： AIRCELLE
发明人： Philipe Guerin , Olivier Kerbler , Jean-Paul Rami
IPC分类号： F02K1/76 , F02K1/72 , F02K1/62 , F02K1/70 , F02K1/09 , F02K3/06
CPC分类号： F02K1/72 , F02K1/09 , F02K1/62 , F02K1/625 , F02K1/70 , F02K1/76 , F02K1/763 , F02K1/766 , F02K3/06
摘要： The present disclosure provides a thrust reverser device that is integrated in an aircraft nacelle. Blocking flaps are stored inside a mobile cowl disposed in a downstream section of the nacelle, under deflection cascade assemblies during direct-jet operation of the nacelle. Various devices are provided for executing the passage from direct-jet operation to reverse-jet operation in two stages: the mobile cowl moves in translation towards the downstream end of the nacelle; and each flap is then deployed in the main air flow path.

3. 发明申请

US20140131480A1 THRUST REVERSER DEVICE WITHOUT A CONTROL ROD IN THE STREAM 有权
标题翻译：在STREAM中没有控制杆的颠倒装置
公开(公告)号：US20140131480A1
公开(公告)日：2014-05-15
申请号：US13875863
申请日：2013-05-02
申请人： AIRCELLE
发明人： Herve Hurlin , Olivier Kerbler , Nicolas Dezeustre , Loic Le Boulicaut
IPC分类号： F02K1/56
CPC分类号： F02K1/72 , F02K1/566 , F02K1/70 , Y02T50/671
摘要： A jet engine nacelle has one thrust reverser device which includes a deflection means and one cowl translatable in a direction substantially parallel to a longitudinal axis of the nacelle. The cowl can translate between a closed position and an open position. In the open position, the cowl ensures the aerodynamic continuity of the nacelle and covers the deflection means. In the open position, the cowl opens a passage into the nacelle and uncovers the deflection means. The thrust reverser device moreover includes one blocking flap pivotably mounted by one end attached to a rear portion of the deflection means, and slidingly connected to the moving cowl. The pivoting end is also translatably connected to the rear portion of the deflection means.
摘要翻译：喷气发动机舱具有一个推力反向装置，其包括偏转装置和一个在基本上平行于机舱的纵向轴线的方向上平移的整流罩。整流罩可以在关闭位置和打开位置之间平移。在打开位置，整流罩确保机舱的空气动力学连续性并覆盖偏转装置。在打开位置，整流罩打开通向机舱的通道并且展开偏转装置。推力反向装置还包括一个阻挡片，其一端连接在偏转装置的后部，并可滑动地连接到移动整流罩上。枢转端也可平移地连接到偏转装置的后部。

4. 发明申请

US20140131479A1 AIRCRAFT TURBOJET ENGINE THRUST REVERSER WITH A LOWER NUMBER OF ACTUATORS 审中-公开
标题翻译：飞机涡轮发动机用较少数量的执行机构反相
公开(公告)号：US20140131479A1
公开(公告)日：2014-05-15
申请号：US13875856
申请日：2013-05-02
申请人： AIRCELLE
发明人： Olivier Kerbler , Nicolas Dezeustre , Herve Hurlin
IPC分类号： F02K1/56
CPC分类号： F02K1/566 , F02K1/72 , F02K1/763 , Y02T50/671
摘要： This cascade-type thrust reverser with one-piece moving cowl includes rails able to slide in guideways positioned on each side of a suspension pylon. This thrust reverser includes just two actuators positioned near the rails and able to cause this cowl to slide on the guideways between its direct-jet and reverse-jet positions. It also has means capable of compensating for forces that have a tendency to misalign the rails with respect to the guideways, thus preventing them from jamming in one another.
摘要翻译：这种具有单件式移动整流罩的级联型推力反向器包括能够在位于悬挂塔的每一侧上的导轨中滑动的轨道。该推力反向器仅包括位于轨道附近的两个致动器，并且能够使导向件在其直接喷射和反向喷射位置之间的导轨上滑动。它还具有能够补偿相对于导轨使轨道不对准的力的装置，从而防止它们彼此卡住。

5. 发明申请

US20150267643A1 THRUST REVERSER WITH PIVOTING CASCADES 审中-公开
标题翻译：扭转反转器
公开(公告)号：US20150267643A1
公开(公告)日：2015-09-24
申请号：US14464649
申请日：2014-08-20
申请人： AIRCELLE
发明人： Patrick GONIDEC , Laurent Albert Blin , Olivier Kerbler
IPC分类号： F02K1/72
CPC分类号： F02K1/72 , Y02T50/671
摘要： A cascade-type thrust reverser for an aircraft turbojet engine includes a front frame, a sliding cowl between a direct jet position and a reverse jet position, a plurality of actuating cylinders interposed between this front frame and this sliding cowl, and a plurality of cascades pivotally mounted on the front frame between the direct and reverse jet positions. In the direct jet position, the cascades are substantially parallel to the axis (A) of the thrust reverser, and in the reverse jet position, the cascades are inclined relative to the axis (A) of the thrust reverser. In particular, the cascade-type thrust reverser includes a single radial layer of cascades.
摘要翻译：用于飞行器涡轮喷气发动机的级联型推力反向器包括前框架，在直接喷射位置和反向喷射位置之间的滑动罩，插入在该前框架和该滑动罩之间的多个致动缸以及多个级联在直接和反向喷射位置之间枢转地安装在前框架上。在直接喷射位置，级联基本上平行于推力反向器的轴线（A），并且在反向喷射位置中，级联相对于推力反向器的轴线（A）倾斜。特别地，级联型推力反向器包括单个径向的级联层。

6. 发明申请

US20140255178A1 AIRCRAFT ENGINE AIR FLOW STRAIGHTENING VANE AND ASSOCIATED FLOW STRAIGHTENING STRUCTURE 有权
标题翻译：飞机发动机空气流量相关风扇和相关流量推力结构
公开(公告)号：US20140255178A1
公开(公告)日：2014-09-11
申请号：US14286666
申请日：2014-05-23
申请人： AIRCELLE
发明人： Arnaud OUDIN , Bertrand Desjoyeaux , Nicolas Dezeustre , Olivier Kerbler
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F01D25/28 , F04D29/023 , F04D29/542 , F05C2225/08 , F05D2240/12 , F05D2300/43 , F05D2300/436 , F05D2300/44 , F05D2300/603 , F05D2300/6034 , Y02T50/672
摘要： A flow straightening vane made of composite materials includes a core made up of three-dimensional woven textile rods which core is surrounded by a textile covering, this core and this covering being consolidated using a thermoset resin.
摘要翻译：由复合材料制成的流动矫直叶片包括由三维编织织物棒构成的芯，该芯由纤维覆盖层包围，该芯并且该覆盖物使用热固性树脂固结。

7. 发明授权

US10294822B2 Turbine engine nacelle fitted with a heat exchanger 有权
公开(公告)号：US10294822B2
公开(公告)日：2019-05-21
申请号：US14471323
申请日：2014-08-28
申请人： AIRCELLE
发明人： Pierre Caruel , Franck Zaganelli , Patrick Gonidec , Olivier Kerbler
IPC分类号： F01D25/24 , B64D15/04 , B64D33/10 , F02C7/047 , F02C7/12 , F02K3/06 , B64D33/02
摘要： A nacelle of a turbine engine includes an external cowling, an internal cowling, and a heat exchanger associated with at least one circulation duct for a fluid. In particular, the circulation duct forms a recirculation loop through the heat exchanger, and the recirculation loop includes at least one circulation area extending at least partially along the external cowling in contact with a wall of the external cowling so as to allow exchange of heat by conduction with the air outside the nacelle.

8. 发明授权

US10125721B2 Nacelle for a turbojet engine with a variable nozzle 有权
公开(公告)号：US10125721B2
公开(公告)日：2018-11-13
申请号：US14987302
申请日：2016-01-04
申请人： AIRCELLE
发明人： Olivier Kerbler , Olivier Gilo , Patrick Gonidec
IPC分类号： F02K1/12 , B64D29/06 , B64D33/04 , B64C15/02 , F02K1/76
摘要： The present disclosure provides a turbojet engine nacelle having a downstream section including a cowl which is ended with a hinged flap constituting a nozzle. In particular, the hinged flap is hingedly and translatably hinged to the cowl.

9. 发明授权

US10036323B2 Rear nacelle assembly for a turbojet engine 有权
公开(公告)号：US10036323B2
公开(公告)日：2018-07-31
申请号：US14200365
申请日：2014-03-07
申请人： AIRCELLE
发明人： Herve Hurlin , Nicolas Dezeustre , Olivier Kerbler
IPC分类号： F02C7/20 , B64D29/06 , B64D29/08 , F02K1/72
CPC分类号： F02C7/20 , B64D29/06 , B64D29/08 , F02K1/72 , Y02T50/671
摘要： A rear nacelle assembly for turbojet engine includes an inner structure surrounding a downstream portion of the turbojet engine. In particular, the inner structure is movable in rotation between an operating position in which it forms a downstream fairing and defines an annular stream of cold air with a thrust reverser cowl, and a maintenance position in which the inner structure moves away from the downstream portion. A suspension pylon is further provided to mount the thrust reverser cowl and the inner structure. The thrust reverser cowl slides between an opening position clearing air flow deviation grids and a closing position recovering the air flow deviation grids. Moreover, the thrust reverser cowl is mounted on the suspension pylon by a pivot connection sliding around a main axis, and the inner structure is mounted on the suspension pylon by a pivot connection around the main axis.

10. 发明授权

US09850776B2 Variable-section nozzle, and aircraft turbojet engine nacelle equipped with such a nozzle 有权
公开(公告)号：US09850776B2
公开(公告)日：2017-12-26
申请号：US14492274
申请日：2014-09-22
申请人： AIRCELLE
发明人： Hervé Hurlin , Hakim Maalioune , Olivier Kerbler
IPC分类号： F01D17/14 , F02K1/18 , F02K1/06 , F02K1/15 , F02K1/12 , F01D17/22 , F01D17/20 , F02K1/08 , F02K1/09 , F01D17/24 , F02K1/10 , F02K1/11
CPC分类号： F01D17/141 , F01D17/20 , F01D17/22 , F01D17/24 , F02K1/06 , F02K1/08 , F02K1/085 , F02K1/09 , F02K1/10 , F02K1/11 , F02K1/12 , F02K1/1207 , F02K1/1215 , F02K1/1223 , F02K1/123 , F02K1/1238 , F02K1/1246 , F02K1/1253 , F02K1/1261 , F02K1/1269 , F02K1/1276 , F02K1/1284 , F02K1/1292 , F02K1/15 , F02K1/18 , F05D2260/407 , Y02T50/672
摘要： A variable-section nozzle for an aircraft nacelle includes a deformable portion of which is movable between a narrow section position and a wide section position. In particular, the variable-section nozzle includes piezoelectric actuators and a controller to control the piezoelectric actuators in order to displace the deformable portion between the narrow and wide section positions. The piezoelectric actuators can be disposed on at least one faces of the deformable portion or be disposed end-to-end to form actuating rods.

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