公开(公告)号：US20160208738A1

公开(公告)日：2016-07-21

申请号：US14703144

申请日：2015-05-04

Applicant: AIRCELLE

Inventor： Vincent PEYRON ,  Laurent Georges VALLEROY ,  Bouziane BEHRAOUI

IPC: F02K1/54 ,  F01D25/24

CPC classification number: F02K1/54 ,  B64D29/06 ,  F01D25/24 ,  F05D2220/323 ,  F05D2260/50

Abstract: The present disclosure concerns an assembly including at least one unit assembly of a nacelle for a turbojet engine, and the assembly is movable relative to a fixed structure along at least one associated guide assembly. The guide assembly includes: at least one guiding element secured to the fixed structure; at least one guided element secured to the unit assembly, shaped so as to move along the guiding element; at least one contact surface common to said guiding and guided elements. In particular, the guided element and the guiding element present each at least one profile, and the profiles is non-complementary to each other at least at the contact surface, the profiles being shaped so as to achieve at least one plane abutment connection at least during circumferential forces of the unit assembly.

Abstract translation: 本公开涉及一种组件，其包括用于涡轮喷气发动机的机舱的至少一个单元组件，并且该组件可沿着至少一个相关联的引导组件相对于固定结构移动。 导向组件包括：固定到固定结构的至少一个引导元件; 固定到所述单元组件的至少一个被引导元件成形为沿着所述引导元件移动; 所述引导和引导元件共同的至少一个接触表面。 特别地，引导元件和引导元件至少呈现至少一个轮廓，并且轮廓至少在接触表面处彼此不互补，轮廓被成形为至少实现至少一个平面邻接连接 在单元组件的周向力期间。

公开(公告)号：US20160053720A1

公开(公告)日：2016-02-25

申请号：US14852462

申请日：2015-09-11

Applicant: AIRCELLE

Inventor： Hazem KIOUA ,  Laurent Georges VALLEROY ,  Jerome LESCURE ,  Jerome CORFA

IPC: F02K1/76 ,  F02K1/72

CPC classification number: F02K1/766 ,  F02K1/72 ,  F05D2240/90

Abstract: The present disclosure provides a thrust reverser device for a nacelle of a by-pass turbojet engine, including: a cowl moving alternately between a deployed position in which the cowl opens a passage within the nacelle and a retracted position in which the cowl closes the passage; a locking/unlocking system to lock and unlock the cowl, the locking/unlocking system moving alternately between a closed position in which a bolt cooperates with a striker so as to hold the cowl in the retracted position, and an open position in which the bolt releases the striker, so as to allow a switching of the cowl from the retracted position to the deployed position; and a device for mechanically inhibiting the cowl from a movement, holding in the retracted position. In particular, the mechanical inhibition device holds the locking/unlocking system in the closed position.

Abstract translation: 本公开内容提供了一种用于旁通涡轮喷气发动机的机舱的推力反向装置，包括：总成在交替地在展开位置之间移动，在该展开位置之间，整流罩打开机舱内的通道和缩回位置，其中整流罩关闭通道 ; 锁定/解锁系统，用于锁定和解锁整流罩，所述锁定/解锁系统交替地在关闭位置之间移动，在该位置中，螺栓与撞针协同工作，以将前罩保持在缩回位置;以及打开位置， 释放撞针，以便使整流罩从缩回位置切换到展开位置; 以及用于机械地阻止整流罩从保持在缩回位置的运动的装置。 特别地，机械抑制装置将锁定/解锁系统保持在关闭位置。

公开(公告)号：US20160245229A1

公开(公告)日：2016-08-25

申请号：US14620543

申请日：2015-02-12

Applicant: AIRCELLE

Inventor： Vincent PEYRON ,  Laurent Georges VALLEROY ,  Franck DEPOORTERE

IPC: F02K1/62 ,  F02K1/76 ,  F02K1/72

CPC classification number: F02K1/625 ,  F02K1/72 ,  F02K1/763 ,  F02K1/766

Abstract: The present disclosure relates to a cascade thrust reverser providing that when a sliding cowl and a flap are in a direct jet position, a hook is held in engagement with another hook and the flap is immobilized inside of a housing of the sliding cowl by a stem of a telescopic connecting rod subjected to pre-stress generated by a compressed spring located in the body of the connecting rod. When the sliding cowl starts to slide from the direct jet position toward the reverse jet position, the hooks disengage each other and the stem engages with an extension in the body of the connecting rod, so that the flap is rotated from the direct jet position toward the reverse jet position due to the tensile force exerted by the stem.

Abstract translation: 本发明涉及一种级联推力反向器，其特征在于，当滑动罩和挡板处于直接喷射位置时，钩与另一钩保持接合，并且所述挡板通过杆固定在所述滑动罩的壳体内部 通过位于连杆主体中的压缩弹簧产生的预应力的伸缩连杆。 当滑盖从直接喷射位置朝向反向喷射位置开始滑动时，钩彼此脱离，并且杆与连杆的主体中的延伸部接合，使得翼片从直接喷射位置转向 由于由杆施加的张力造成的反向喷射位置。

公开(公告)号：US20150300204A1

公开(公告)日：2015-10-22

申请号：US14524099

申请日：2014-10-27

Applicant: AIRCELLE

Inventor： Hazem KIOUA ,  Vincent PEYRON ,  Laurent Georges VALLEROY

IPC: F01D25/24

CPC classification number: F01D25/24 ,  B64D29/06 ,  B64D33/04 ,  F02K1/72 ,  F05D2220/30

Abstract: A turbofan engine nacelle has a downstream section which includes at least one front frame. The front frame is attached to a stationary portion of the nacelle, and the downstream section is provided with at least one rail or slide which extends in a longitudinal direction of the nacelle and is capable of engaging with at least one corresponding slide or rail of an attachment pylon of the turbofan engine. The front frame is connected to the rail or slide of the downstream section by means of at least one swiveled connecting rod.

Abstract translation: 涡轮风扇发动机舱具有包括至少一个前框架的下游部分。 前框架连接到机舱的静止部分，并且下游部分设置有至少一个轨道或滑块，其沿着机舱的纵向方向延伸并且能够与至少一个相应的滑轨或轨道接合 涡扇发动机的附件塔。 前框架通过至少一个可旋转的连接杆连接到下游部分的导轨或滑块。