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公开(公告)号：US10336458B2
公开(公告)日：2019-07-02
申请号：US14575332
申请日：2014-12-18
发明人： Julien Guillemaut , Sébastien Alby , Jérôme Colmagro , Pascal Pome , Jonathan Blanc , Thomas Robiglio , Tobias Sjostrom
摘要： In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.
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公开(公告)号：US09656742B2
公开(公告)日：2017-05-23
申请号：US14561488
申请日：2014-12-05
CPC分类号： B64C21/04 , B64C21/08 , B64D29/04 , Y02T50/166
摘要： An air ejection device comprises an aerodynamic profile provided with a slot and an ejection nozzle. The device comprises a flexible tongue fixed flush with the aerodynamic profile in such a way as to obstruct the slot, the tongue being able to lift under the effect of a pressure differential between the air situated in the ejection nozzle and the outside air. The tongue makes it possible for the slot made in the profile to be obstructed during phases of flight during which the ejection of the air is unnecessary, and prevents external air from entering the slot. The flow of air over the aerodynamic profile is unaffected, and there is no increase in drag. Because the tongue lifts as a result of a pressure differential, it does not require any control mechanism to lift it.
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公开(公告)号：US20180327104A1
公开(公告)日：2018-11-15
申请号：US15919970
申请日：2018-03-13
CPC分类号： B64D35/08 , B64D27/10 , B64D27/14 , B64D27/20 , B64D35/02 , B64D2027/026 , F01D13/003 , F02C6/02 , F02C6/206 , F02K3/04 , F02K3/12 , F05D2220/323 , F05D2260/40311 , F05D2260/84
摘要： An aircraft propulsion assembly including a fan. It include a first engine and a second engine which are not coaxial and a mechanical energy transmission device configured to enable the fan to be conjointly rotated by the first engine and the second engine. This allows an aircraft propulsion assembly to be produced of which the fan may be positioned so as to ingest the boundary layer formed at the surface of a member of the aircraft equipped with the propulsion assembly, while allowing operating modes in the case of certain failures, and certification for commercial use of an aircraft equipped with such a propulsion assembly, to which the invention also relates.
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公开(公告)号：US09656736B2
公开(公告)日：2017-05-23
申请号：US14695731
申请日：2015-04-24
发明人： Julien Guillemaut , Esteban Martino Gonzalez , Diego Folch Cortes , Jerome Colmagro , Jonathan Blanc
摘要： In the case of an aircraft aft portion equipped with an engine mounting structure passing across the fuselage, assembly of the aft portion presents problems caused by the moving of the box structure of the mounting structure through lateral openings in the fuselage. In order to overcome these problems, a method of assembling an aircraft aft portion is proposed, in which method the box structure of the engine mounting structure is inserted into the fuselage through a top opening extending from one side of the fuselage to the other across a vertical midplane of the fuselage such that the top opening opens to the top and to the sides of the fuselage.
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5.发明申请AIRCRAFT ASSEMBLY COMPRISING A MOUNTING STRUT BUILT INTO THE NACELLE AND ARRANGED AT THE REAR SECTION OF THE FUSELAGE 审中-公开包括安装在内的飞机组件安装在NACELLE上并安装在FUSELAGE的后面部分公开(公告)号：US20150259074A1
公开(公告)日：2015-09-17
申请号：US14575332
申请日：2014-12-18
发明人： Julien Guillemaut , Sébastien Alby , Jérôme Colmagro , Pascal Pome , Jonathan Blanc , Thomas Robiglio , Tobias Sjostrom
CPC分类号： B64D27/26 , B64D27/20 , B64D2027/262
摘要： In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.
摘要翻译： 为了减少发动机变形，本文公开的主题提供了一种用于飞行器的组件，其包括飞行器后部，发动机，机舱和用于将发动机安装在后部上的安装支柱，该组件还包括安装 将发动机安装在支柱的刚性结构上，该安装件包括两个发动机支架，其被设计成反应由发动机产生的轴向推力。 根据本文公开的主题，支柱的刚性结构包括部分包围发动机的第一部分，该第一部分包括形成机舱的外部空气动力学表面的一部分的外部皮肤，并且两个发动机支架沿径向相对 彼此在刚性结构的后部附接到第一部分。
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