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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：US11708168B2
公开(公告)日：2023-07-25
申请号：US16452634
申请日：2019-06-26
发明人： Camil Negulescu
摘要： An aircraft propulsion unit includes a drive unit with a static part and a rotary part which rotates a fan situated downstream from the drive unit, an assembly of fixed blades situated downstream from the fan, and a nacelle in which the fan and the assembly of fixed blades are accommodated. The propulsion unit also includes an assembly of at least two coaxial shafts, wherein a fan shaft connects the fan to the rotary part, and a stator blading shaft connecting the assembly of fixed blades to the static part extends concentrically, and for at least part of its length in the interior of the fan shaft. This rigid and compact configuration limits the variations of distance between the end of the fan blades and a fan housing situated in the inner duct of the nacelle.
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公开(公告)号：US20200216182A1
公开(公告)日：2020-07-09
申请号：US16719020
申请日：2019-12-18
发明人： Camil Negulescu , Antoine Abele
摘要： A propulsion system for an aircraft including a fuselage and a wing assembly. The propulsion system includes a first propulsion device at the level of the rear part of the fuselage and constituted of at least one BLI propulsion unit including a fan, a second propulsion device constituted of at least one conventional propulsion unit, and a transmission device coupling the first and second propulsion devices. The second propulsion system therefore generates the energy necessary for driving in rotation the fan of the BLI propulsion unit or units. The thrust produced by the propulsion devices contributes to generating the total thrust of the aircraft. In this propulsion system at least one conventional propulsion unit constituting the second propulsion device is situated on one side of the rear part of the fuselage between the tail of the fuselage and the wing assembly of the aircraft.
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公开(公告)号：US20200002013A1
公开(公告)日：2020-01-02
申请号：US16452634
申请日：2019-06-26
发明人： Camil Negulescu
摘要： An aircraft propulsion unit includes a drive unit with a static part and a rotary part which rotates a fan situated downstream from the drive unit, an assembly of fixed blades situated downstream from the fan, and a nacelle in which the fan and the assembly of fixed blades are accommodated. The propulsion unit also includes an assembly of at least two coaxial shafts, wherein a fan shaft connects the fan to the rotary part, and a stator blading shaft connecting the assembly of fixed blades to the static part extends concentrically, and for at least part of its length in the interior of the fan shaft. This rigid and compact configuration limits the variations of distance between the end of the fan blades and a fan housing situated in the inner duct of the nacelle.
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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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