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1.发明申请公开(公告)号：US20130081248A1
公开(公告)日：2013-04-04
申请号：US13644803
申请日：2012-10-04
发明人： Frédéric CHELIN , Jacques LALANE
CPC分类号： B21J15/50 , B23B47/284 , Y10T29/49726 , Y10T29/49821 , Y10T29/49822 , Y10T29/53796 , Y10T29/53909 , Y10T29/5393 , Y10T29/53996 , Y10T408/559
摘要： A method is provided for destroying a blind fastener joining at least two parts. The blind fastener includes, but is not limited to a body situated in the holes provided in the joined parts, with a head at each end thereof, and portions of which protrude above the level of the holes. The method also includes, but is not limited to withdrawing the accessible head of the fastener, and creating a hole that passes through the fastener. An insertion device is configured to restrain the remainder of the fastener in the hole, which has an elongated body having a diameter smaller than or equal to that of the hole and an expandable head at one end thereof The insertion device for restraining the remainder of the fastener being immobilised or capable of only limited movement relative to the joined parts, and expelling the remainder of the fastener from the holes.
摘要翻译： 提供一种破坏连接至少两部分的盲紧固件的方法。 盲紧固件包括但不限于位于设置在接合部分中的孔中的主体，在其每个端部具有头部，并且其一部分突出于孔的高度之上。 该方法还包括但不限于撤回紧固件的可触及的头部，并且产生穿过紧固件的孔。 插入装置构造成将紧固件的其余部分限制在孔中，该孔具有直径小于或等于孔的直径的细长主体和在其一端的可扩张头。用于限制其余部分的插入装置 紧固件被固定或仅能够相对于连接的部件有限的移动，并且将其余的紧固件从孔中排出。
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公开(公告)号：US20230340929A1
公开(公告)日：2023-10-26
申请号：US18303076
申请日：2023-04-19
摘要： A deflector provided with a spoiler for a thrust reverser of an aircraft engine nacelle. The deflector, a lateral deflector or an orbital deflector, may be in an exhaust structure of a thrust reverser and comprises a deflector plate configured to act on an aerodynamic flow. The deflector plate has a concave upstream face and a convex downstream face, as well as an intake end and an exhaust end. The deflector is fitted with a spoiler rigidly connected to the exhaust end of the deflector plate and arranged transversely in relation to the deflector plate. The spoiler endowing the deflector with specific properties to act on the aerodynamic flow.
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3.发明申请公开(公告)号：US20200340426A1
公开(公告)日：2020-10-29
申请号：US16855298
申请日：2020-04-22
IPC分类号： F02K1/62
摘要： A thrust reverser door for an aircraft propulsion unit, including a seal positioned at an upstream edge of the door. This seal includes a part that projects with respect to the upstream edge of the door and a rigid core to stiffen the projecting part. This configuration serves to reduce aerodynamic disturbances.
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公开(公告)号：US20240360802A1
公开(公告)日：2024-10-31
申请号：US18644812
申请日：2024-04-24
CPC分类号： F02K1/766 , F02K1/72 , F05D2220/323
摘要： An aircraft nacelle equipped with a thrust reversal device which comprises: at least one deflection system configured to deflect an air stream channeled in the nacelle toward a lateral opening of the nacelle, in the activated state, at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system in radial directions and toward the upstream end of the nacelle, at least one longitudinal deflector configured to orient the air stream deflected by the deflection system in at least one direction that forms an angle with a radial direction.
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公开(公告)号：US20240360801A1
公开(公告)日：2024-10-31
申请号：US18644977
申请日：2024-04-24
CPC分类号： B64D29/06 , F02K1/32 , F05D2220/323
摘要： An aircraft nacelle equipped with a thrust reversal device which comprises: at least one deflection system configured to deflect an air stream channeled in the nacelle toward a lateral opening of the nacelle, in the activated state; at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system toward the upstream end of the nacelle, at least one downstream deflector positioned at the downstream edge of the lateral opening and configured to deflect the air stream deflected by the deflection system toward the upstream end of the nacelle.
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6.发明公开公开(公告)号：US20230340928A1
公开(公告)日：2023-10-26
申请号：US18129507
申请日：2023-03-31
IPC分类号： F02K1/72
CPC分类号： F02K1/72
摘要： A deflector for an ejection structure of a thrust reverser is disclosed including a deflector plate configured to act on an aerodynamic flow, the deflector plate having a concave upstream face, a convex downstream face, an inlet end, and an outlet end. The upstream face and the downstream face of the deflector plate have different curved profiles, the deflector has a particular profile giving it properties allowing it to act effectively on the aerodynamic flow so as to enhance the performance of the thrust reverser in which it is mounted.
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