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公开(公告)号：US10562639B2
公开(公告)日：2020-02-18
申请号：US15381821
申请日：2016-12-16
发明人： Olivier Pautis , Jean-Michel Rogero
摘要： In order to reduce congestion of attachments between an aircraft engine and its attachments, an engine assembly is provided, the primary structure of the device of which includes a structural cover surrounding the engine and connected on a central box, the cover including an outer skin interiorly delimiting a secondary flow. A group of main mounts is provided as a group of secondary mounts laid out at the rear of the group of main mounts, the group of main mounts including a plurality of bolts distributed around the longitudinal axis of the engine and ensuring the attachment of a front end of the cover to the hub of the intermediate case, and a group of secondary mounts including a plurality of secondary mounts distributed around the axis and ensuring attachment of a rear portion of the engine to a rear end of the cover.
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公开(公告)号：US11878809B2
公开(公告)日：2024-01-23
申请号：US16355999
申请日：2019-03-18
IPC分类号： B64D33/02 , F02K3/077 , B64C7/02 , F02K3/12 , B64D29/00 , F01D25/24 , F02K3/04 , B64D33/04 , B64D27/10 , B64D27/16
CPC分类号： B64D33/02 , B64C7/02 , B64D27/10 , B64D27/16 , B64D29/00 , B64D33/04 , F01D25/24 , F02K3/04 , F02K3/077 , F02K3/12 , B64D2033/0266 , F05D2220/323
摘要： An aircraft propulsion assembly includes a first engine and a second engine that are adjacent and a nacelle in which the engines are installed. The nacelle includes a common air inlet lip for the first engine and the second engine, the air flow being divided between the first engine and the second engine by a median lip which extends, at least partly, set back from said common air inlet lip. The common are inlet lip includes, directly in line with the median lip, a bottom lobe and a top lobe extending forward of the nacelle. Such a configuration makes it possible to be able to provide a high aerodynamic form between the fairings of the engines, without the risk of generating overspeeds in the air flow.
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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：US20190291885A1
公开(公告)日：2019-09-26
申请号：US16355999
申请日：2019-03-18
摘要： An aircraft propulsion assembly includes a first engine and a second engine that are adjacent and a nacelle in which the engines are installed. The nacelle includes a common air inlet lip for the first engine and the second engine, the air flow being divided between the first engine and the second engine by a median lip which extends, at least partly, set back from said common air inlet lip. The common are inlet lip includes, directly in line with the median lip, a bottom lobe and a top lobe extending forward of the nacelle. Such a configuration makes it possible to be able to provide a high aerodynamic form between the fairings of the engines, without the risk of generating overspeeds in the air flow.
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