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公开(公告)号：US20220136439A1
公开(公告)日：2022-05-05
申请号：US17427563
申请日：2020-01-22
Applicant: SAFRAN NACELLES
Inventor： Sébastien Laurent, Marie Pascal , Jean-Michel Paul, Ernest Nogues , Marc Versaevel , François Chauveau
Abstract: The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake comprising an inner wall facing the axis X and an outer wall for guiding an external air flow, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall to allow the hot air flow to escape after heating the inner cavity, the ventilation orifice comprising an upstream edge, the circumferential profile of which is discontinuous in order to generate turbulences, and a downstream edge, the radial profile of which is aerodynamic in order to limit the formation of pressure fluctuations.
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公开(公告)号：US20220099023A1
公开(公告)日：2022-03-31
申请号：US17427548
申请日：2020-01-22
Applicant: SAFRAN NACELLES
Inventor： Sébastien Laurent, Marie Pascal , Jean-Michel Paul, Ernest Nogues , Marc Versaevel , François Chauveau
Abstract: The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake extending circumferentially around the axis X and comprising an inner wall, which faces the axis X in order to guide an inner air flow, and an outer wall, which is opposite the inner wall, for guiding an external air flow, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall in order to allow the hot air flow to escape after heating the internal cavity, the air intake comprising at least one disruption member of the external air flow, positioned upstream of the ventilation orifice, which extends outwardly from the outer wall.
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公开(公告)号：US12092026B2
公开(公告)日：2024-09-17
申请号：US17510803
申请日：2021-10-26
Applicant: Safran Nacelles
IPC: F02C7/045
CPC classification number: F02C7/045 , F05D2220/323 , F05D2230/60
Abstract: An air intake for a nacelle for an aircraft engine includes a front lip connecting a substantially cylindrical internal wall and a substantially cylindrical external wall, and at least one acoustic structure including acoustic cells. The acoustic structure is situated in the space delimited by the internal wall, the external wall and the front lip. The acoustic structure is an added part secured to the air intake. The acoustic cells of the acoustic structure are arranged facing a region of the internal wall or of the lip at a predetermined distance so that the acoustic cells of the acoustic structure are not in contact with the internal wall or the lip while providing an acoustic attenuation function.
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公开(公告)号：US11542865B2
公开(公告)日：2023-01-03
申请号：US16901733
申请日：2020-06-15
Applicant: Safran Nacelles
Inventor： Patrick Boileau , Caroline Coat-Lenzotti , Marc Versaevel , Virginie Emmanuelle Anne Marie Digeos , Pierre-François Behaghel
Abstract: An air inflow lip of a nacelle for a turbojet of an aircraft, including a cavity defined by a leading edge of the nacelle and by an annular wall, includes an inner wall, an acoustic treatment device, and a pneumatic de-icing device including a de-icing fluid supply device. The inner wall of the air inflow lip includes acoustic boreholes and the pneumatic de-icing device includes a honeycombed de-icing plate mounted inside the cavity on the inner wall of the air inflow lip. Also included are conduits for the circulation of a de-icing fluid and acoustic wells communicating with the acoustic boreholes.
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公开(公告)号：US12170077B2
公开(公告)日：2024-12-17
申请号：US17716089
申请日：2022-04-08
Applicant: Safran Nacelles
Inventor： Marc Versaevel , Bertrand Desjoyeaux , Mathieu Preau
IPC: G10K11/172 , B64D33/02
Abstract: An acoustic attenuation panel includes a perforated acoustic wall, a first honeycomb structure coupled to the perforated acoustic wall and including a plurality of acoustic cells defined by peripheral partitions, a second honeycomb structure including a plurality of acoustic cells defined by peripheral partitions, and a septum which includes a plurality of macro-perforations and is positioned between the first honeycomb structure and the second honeycomb structure. Each acoustic cell of the first honeycomb structure and each acoustic cell of the at least second honeycomb structure are arranged opposite a single perforation of the septum.
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Patent Agency Ranking
公开(公告)号：US11655760B2
公开(公告)日：2023-05-23
申请号：US17427565
申请日：2020-02-05
Applicant: SAFRAN NACELLES
Inventor： Sébastien Laurent Marie Pascal , Jean-Michel Paul Ernest Nogues , Marc Versaevel , François Chauveau
Abstract: The invention relates to an air intake of an aircraft turbojet engine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake comprising an inner wall and an outer wall which are connected by a leading edge and an inner partition so as to delimit an annular cavity, the air intake comprising means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall in order to allow the hot air flow to escape after heating the inner cavity, the air intake comprising at least one acoustic member positioned in the inner cavity facing the ventilation orifice so as to modify the acoustic resonance frequencies and/or to attenuate the acoustic waves formed in the inner cavity via the ventilation orifice.
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公开(公告)号：US20220162990A1
公开(公告)日：2022-05-26
申请号：US17427565
申请日：2020-02-05
Applicant: SAFRAN NACELLES
Inventor： Sébastien Laurent, Marie Pascal , Jean-Michel Paul, Ernest Nogues , Marc Versaevel , François Chauveau
Abstract: The invention relates to an air intake of an aircraft turbojet engine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake comprising an inner wall and an outer wall which are connected by a leading edge and an inner partition so as to delimit an annular cavity, the air intake comprising means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall in order to allow the hot air flow to escape after heating the inner cavity, the air intake comprising at least one acoustic member positioned in the inner cavity facing the ventilation orifice so as to modify the acoustic resonance frequencies and/or to attenuate the acoustic waves formed in the inner cavity via the ventilation orifice.
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公开(公告)号：US12264625B2
公开(公告)日：2025-04-01
申请号：US17729541
申请日：2022-04-26
Applicant: Safran Nacelles
Inventor： Pierre Caruel , Bertrand Desjoyeaux , Bertrand Leroyer , Marc Versaevel , Laurent Georges Valleroy
Abstract: An acoustic attenuation panel includes a cellular structure including a plurality of acoustic cells separated from one another by peripheral partitions, a perforated acoustic structure, the perforated acoustic structure and the cellular structure being formed in one piece in a first material, and a porous acoustic layer formed of a second material and fastened to a surface of the perforated acoustic structure by entangling the first material and the second material.
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公开(公告)号：US20240253804A1
公开(公告)日：2024-08-01
申请号：US18627959
申请日：2024-04-05
Applicant: Safran Nacelles
Inventor： Vincent DUTOT , Jean-Philippe Joret , Marc Versaevel , Vincent Lefeuvre
CPC classification number: B64D33/06 , B64D29/00 , F02K1/827 , F05D2220/323 , F05D2260/963
Abstract: An air ejection nozzle for a nacelle includes an outer aerodynamic line and an inner aerodynamic line meeting at a trailing edge. The air ejection nozzle includes at discrete positions at least one area of larger thickness that is compensated by at least one fairing to connect the aerodynamic lines to form the trailing edge. The fairing includes an outer wall and an inner wall delimiting a cavity therebetween. The inner wall provides for the continuity of the inner aerodynamic line, and the outer wall is solid and the inner wall is pierced so that the at least one fairing forms an acoustic attenuation structure.
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公开(公告)号：US11608781B2
公开(公告)日：2023-03-21
申请号：US17427563
申请日：2020-01-22
Applicant: SAFRAN NACELLES
Inventor： Sébastien Laurent Marie Pascal , Jean-Michel Paul Ernest Nogues , Marc Versaevel , François Chauveau
Abstract: The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake comprising an inner wall facing the axis X and an outer wall for guiding an external air flow, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall to allow the hot air flow to escape after heating the inner cavity, the ventilation orifice comprising an upstream edge, the circumferential profile of which is discontinuous in order to generate turbulences, and a downstream edge, the radial profile of which is aerodynamic in order to limit the formation of pressure fluctuations.
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