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公开(公告)号：US20220219829A1
公开(公告)日：2022-07-14
申请号：US17558213
申请日：2021-12-21
Applicant: Airbus Operations (S.A.S.)
Inventor： Alexis Courpet , Jean Geliot , Arnaud Bourhis
Abstract: A forward secondary structure for a mounting pylon for a turbomachine, the forward secondary structure extending from upstream to downstream along a longitudinal axis and having a chassis clad with an aerodynamic fairing. The aerodynamic fairing includes two adjacent cowls each having an upstream portion, where each of the cowls extends lengthwise along the longitudinal direction and includes in its upstream portion a system for articulating the cowl to the chassis, by which system the cowl can pivot with respect to the chassis about an axis of rotation normal to the longitudinal axis, between a closed position in which all of an inner face of the cowl is pressed against the chassis and an open position in which the cowl frees up an opening in the forward secondary structure.
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公开(公告)号：US11745887B2
公开(公告)日：2023-09-05
申请号：US17091604
申请日：2020-11-06
Applicant: Airbus Operations (S.A.S.)
Inventor： Alain Porte , Jacques Lalane , Arnaud Bourhis , Florent Mercat
IPC: B64D33/02 , G10K11/172 , G10K11/168
CPC classification number: B64D33/02 , G10K11/168 , G10K11/172 , B64D2033/0206
Abstract: An acoustic panel for an aircraft nacelle includes, from a central axis of the nacelle to the exterior thereof, a resistive skin perforated with sound-absorbing micro-perforations, a first attenuation stage, a septum perforated with holes, a second attenuation stage, and a back skin configured to provide the mechanical strength of the acoustic panel. The septum is a planar wall having a thickness greater than that of the resistive skin, preferably greater than 4 mm. Such a panel is configured to attenuate several frequency ranges one of which being a low-frequency range, while optimizing the weight, the cost and the air intake functions. The thickness of the septum, the dimensions of the holes in the septum, the OAR of the septum and the height of the second attenuation stage are adjusted to match the mean attenuated low frequency to the vibration frequency of the aircraft engine.
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公开(公告)号：US11591098B2
公开(公告)日：2023-02-28
申请号：US16226910
申请日：2018-12-20
Applicant: Airbus Operations S.A.S.
Inventor： Frédéric Vinches , Arnaud Bourhis , Julien Sentier , Clément Breton
Abstract: A nacelle forward part of an aircraft propulsion assembly, includes an air inlet lip at the front end, an internal structure and an external panel extending the lip, and an annular stiffening frame formed around an axis of revolution and comprising an internal peripheral edge linked to the internal structure and an external peripheral edge linked to the external panel. The stiffening frame presents an inclination relative to the axis of revolution, its slope being oriented towards the front end of the nacelle forward part. The stiffening frame is configured to deviate, outside the nacelle of the propulsion assembly, an object striking the stiffening frame. The stiffening frame so configured is capable of withstanding the impacts of objects without breaking while enabling the object striking the stiffening frame to be deviated towards the exterior of the nacelle.
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公开(公告)号：US11384688B2
公开(公告)日：2022-07-12
申请号：US16456500
申请日：2019-06-28
Applicant: AIRBUS OPERATIONS (S.A.S.)
Inventor： Arnaud Bourhis , François Pons , Alain Porte
Abstract: An air intake structure for a nacelle of an aircraft is disclosed having an air intake lip with a U-shaped section open towards the rear, an acoustic panel that extends the air intake lip towards the rear and on an inner side, an outer panel extending the air intake lip towards the rear and on an outer side, and a rear strengthening frame fixed between the outer panel and the acoustic panel, where the rear strengthening frame partly defines an inner volume that is immediately in front of the rear strengthening frame. The air intake structure comprises an impact absorber element positioned in the inner volume and the impact absorber element assumes the form of a structure that is deformable during an impact and that is at least partially filled with a fluid. The impact absorber element is a flexible shroud filled with a pressurized gas.
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Patent Agency Ranking
公开(公告)号：US20210237890A1
公开(公告)日：2021-08-05
申请号：US17091604
申请日：2020-11-06
Applicant: Airbus Operations (S.A.S.)
Inventor： Alain Porte , Jacques Lalane , Arnaud Bourhis , Florent Mercat
IPC: B64D33/02 , B64D29/00 , G10K11/162
Abstract: An acoustic panel for an aircraft nacelle includes, from a central axis of the nacelle to the exterior thereof, a resistive skin perforated with sound-absorbing micro-perforations, a first attenuation stage, a septum perforated with holes, a second attenuation stage, and a back skin configured to provide the mechanical strength of the acoustic panel. The septum is a planar wall having a thickness greater than that of the resistive skin, preferably greater than 4 mm. Such a panel is configured to attenuate several frequency ranges one of which being a low-frequency range, while optimizing the weight, the cost and the air intake functions. The thickness of the septum, the dimensions of the holes in the septum, the OAR of the septum and the height of the second attenuation stage are adjusted to match the mean attenuated low frequency to the vibration frequency of the aircraft engine.
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公开(公告)号：US20190193833A1
公开(公告)日：2019-06-27
申请号：US16226910
申请日：2018-12-20
Applicant: Airbus Operations S.A.S.
Inventor： Frédéric Vinches , Arnaud Bourhis , Julien Sentier , Clément Breton
CPC classification number: B64C7/02 , B64D29/06 , B64D33/02 , B64D2033/022 , B64D2033/0286
Abstract: A nacelle forward part of an aircraft propulsion assembly, includes an air inlet lip at the front end, an internal structure and an external panel extending the lip, and an annular stiffening frame formed around an axis of revolution and comprising an internal peripheral edge linked to the internal structure and an external peripheral edge linked to the external panel. The stiffening frame presents an inclination relative to the axis of revolution, its slope being oriented towards the front end of the nacelle forward part. The stiffening frame is configured to deviate, outside the nacelle of the propulsion assembly, an object striking the stiffening frame. The stiffening frame so configured is capable of withstanding the impacts of objects without breaking while enabling the object striking the stiffening frame to be deviated towards the exterior of the nacelle.
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公开(公告)号：US11753176B2
公开(公告)日：2023-09-12
申请号：US17558213
申请日：2021-12-21
Applicant: Airbus Operations (S.A.S.)
Inventor： Alexis Courpet , Jean Geliot , Arnaud Bourhis
CPC classification number: B64D27/26 , B64D29/06 , B64D29/08 , B64D2027/264
Abstract: A forward secondary structure for a mounting pylon for a turbomachine, the forward secondary structure extending from upstream to downstream along a longitudinal axis and having a chassis clad with an aerodynamic fairing. The aerodynamic fairing includes two adjacent cowls each having an upstream portion, where each of the cowls extends lengthwise along the longitudinal direction and includes in its upstream portion a system for articulating the cowl to the chassis, by which system the cowl can pivot with respect to the chassis about an axis of rotation normal to the longitudinal axis, between a closed position in which all of an inner face of the cowl is pressed against the chassis and an open position in which the cowl frees up an opening in the forward secondary structure.
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公开(公告)号：US11661173B2
公开(公告)日：2023-05-30
申请号：US16507470
申请日：2019-07-10
Applicant: Airbus Operations S.A.S.
Inventor： Alain Porte , Francois Pons , Arnaud Bourhis , Julien Sentier
Abstract: An aircraft nacelle air intake includes sectors each having a lip forming portion, an outer panel forming portion and an inner panel forming portion. The outer panel forming portions and lip forming portions are formed by a continuous one-piece wall. At at least one junction between two adjacent sectors, an opening and a hatch are provided between the outer panel forming portions of the sectors. The inner panel forming portions and the lip forming portions of the sectors are edge to edge and fixed to each other by fixing devices accessible from the inside of the sectors and invisible from outside of the sectors. A maintenance method in which, when a zone of a sector is damaged, the sector concerned is removed as a whole and is replaced by a new of “recycled” sector is also described.
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公开(公告)号：US20200017191A1
公开(公告)日：2020-01-16
申请号：US16507470
申请日：2019-07-10
Applicant: Airbus Operations S.A.S.
Inventor： Alain Porte , Francois Pons , Arnaud Bourhis , Julien Sentier
Abstract: An aircraft nacelle air intake includes sectors each having a lip forming portion, an outer panel forming portion and an inner panel forming portion. The outer panel forming portions and lip forming portions are formed by a continuous one-piece wall. At at least one junction between two adjacent sectors, an opening and a hatch are provided between the outer panel forming portions of the sectors. The inner panel forming portions and the lip forming portions of the sectors are edge to edge and fixed to each other by fixing devices accessible from the inside of the sectors and invisible from outside of the sectors. A maintenance method in which, when a zone of a sector is damaged, the sector concerned is removed as a whole and is replaced by a new of “recycled” sector is also described.
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