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1.发明公开公开(公告)号：US20240351298A1
公开(公告)日：2024-10-24
申请号：US18580668
申请日：2022-07-13
CPC分类号： B29C70/443 , B29C70/446 , B29C70/544 , B29C70/549 , B29L2031/3076
摘要： The invention relates to an assembly structure (10) for manufacturing a composite part. The structure comprises:—a skin preform (Pp) and a generally omega-shaped stiffener preform (PT) each having first and second opposing surfaces, the stiffener preform extending along and opposite the first surface of the skin preform. longitudinally and transversely in the form of a stiffener preform cross-section,—a rigid skin tooling (Op) disposed opposite the entire second surface (Sp2) of the skin preform,—a local rigid stiffener tooling (Or1, Or2) extending transversely around the stiffener preform cross-section with a transverse dimension smaller than the transverse dimension of the first surface of the skin preform.
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公开(公告)号：US20240351699A1
公开(公告)日：2024-10-24
申请号：US18637871
申请日：2024-04-17
申请人： SAFRAN NACELLES
发明人： Bertrand Léon Marie DESJOYEAUX , Mathieu François Eric PREAU , Marc VERSAEVEL , Pierre Charles CARUEL , Geneviève CLUZEAU
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0206
摘要： An acoustic panel for an aircraft turbomachine has a sandwich structure. The sandwich structure includes a cell structure with a plurality of acoustic cells, a perforated acoustic structure, and a porous acoustic structure attached to the perforated acoustic structure. The perforated acoustic structure is arranged between the cell structure and the porous acoustic structure. The porous acoustic structure is multi-layered and has a first woven textile layer and a second woven textile layer connected to the first layer. The second layer is arranged between the first layer and the perforated acoustic structure.
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公开(公告)号：US12122106B2
公开(公告)日：2024-10-22
申请号：US17843224
申请日：2022-06-17
申请人： Safran Nacelles
CPC分类号： B29C70/46 , B29C33/0033 , B29C33/485 , B29C70/54 , B29L2031/3076
摘要： Tooling for manufacture of an apertured element made of a composite material includes first and second sole plates and tooling elements. Each sole plate is configured to be placed on either side of the apertured element to be manufactured. The tooling elements are placed between the first and second sole plates. The tooling elements include at least one core and peripheral bars. The core is configured to delimit a cell of the apertured element to be manufactured. The core is movable in translation along the first and second sole plates. The peripheral bars are placed on a periphery of the core and configured to delimit the apertured element to be manufactured. At least one peripheral bar is movable in translation along the first and second sole plates.
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公开(公告)号：US12109639B2
公开(公告)日：2024-10-08
申请号：US16870391
申请日：2020-05-08
申请人： Safran Nacelles
IPC分类号： B23K20/02 , B23K1/00 , B23K20/24 , B64D29/00 , B23K101/00 , B23K101/02 , B64D27/16
CPC分类号： B23K1/0014 , B23K20/021 , B23K20/24 , B64D29/00 , B23K2101/006 , B23K2101/02 , B64D27/16
摘要： A method and a device for manufacturing a structural and/or acoustic panel for a nacelle of an aircraft propulsion assembly involves heating, by producing electromagnetic radiation, at least one skin of the structural and/or acoustic panel in such a way as to assemble this skin with a cellular structure of the structural and/or acoustic panel, by diffusion brazing or welding. This heating device can also be used to shape the skin to the cellular structure prior to assembly.
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公开(公告)号：US12104555B2
公开(公告)日：2024-10-01
申请号：US17907743
申请日：2021-03-31
申请人： SAFRAN NACELLES
摘要： This summary relates to a thrust reverser for a turbojet engine mounted on an engine nacelle pylon, comprising a fixed part, a movable part, coaxial and mounted in translation with respect to the fixed part and sealingly inserted against the fixed part by blocking an air outlet passage in a closed state whereas the air outlet passage is freed up in the extended state, and a single actuating device including a beam, a slider, and a driving device, configured to drive the movable part in translation with respect to the fixed part, wherein the beam comprises a stop taking the form of a protuberance protruding on a radially outer surface of the beam and configured to have a clearance with respect to said engine nacelle pylon.
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公开(公告)号：US20240317415A1
公开(公告)日：2024-09-26
申请号：US18574120
申请日：2022-06-27
申请人： SAFRAN NACELLES
摘要： A propulsion unit includes a fairing delimiting a flow conduit for a secondary flow. This fairing comprises includes panels, at least one of which is articulated on a mast via connecting members such as clevises.
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公开(公告)号：US12065986B2
公开(公告)日：2024-08-20
申请号：US17790048
申请日：2020-12-23
申请人： SAFRAN NACELLES , SAFRAN LANDING SYSTEMS , SAFRAN ELECTRONICS & DEFENSE , SAFRAN AIRCRAFT ENGINES
CPC分类号： F02K1/32 , B64C25/426 , B64D45/00 , G05D1/101
摘要： This system (36) for controlling an aircraft thrust reversal means comprises a reverse idle control means (38), a first detection means (31) configured to detect, when the reverse idle control is active, a condition for activation of the thrust reversal means, and an actuation means (52) configured to activate the thrust reversal means when the first detection means (31) detects a condition for activation of the thrust reversal means.
It further comprises a second detection means (42, 44, 46, 48, 49) configured to detect a condition for activation of the reverse idle control, the control means (38) being configured to activate the reverse idle control when the second detection means (42, 44, 46, 48, 49) detects a condition for activating the reverse idle control.-
公开(公告)号：US12044168B2
公开(公告)日：2024-07-23
申请号：US18247852
申请日：2021-10-01
申请人： SAFRAN NACELLES
摘要： Disclosed is an air intake of a turbine engine nacelle extending along an axis in which a flow of air circulates from upstream to downstream, the air intake extending annularly about the axis, the air intake having a movable upstream portion and a stationary downstream portion, at least one controllable movement member for moving the movable upstream portion between a retracted position and an extended position in order to enable circulation of an air flow passing between the movable upstream portion and the stationary downstream portion, at least one de-icing circuit having at least one circulation channel fluidically connecting the movable upstream portion and a hot air source, the circulation channel having at least one non-telescopic upstream pipe and at least one telescopic downstream member.
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公开(公告)号：US12037940B2
公开(公告)日：2024-07-16
申请号：US18247037
申请日：2021-10-01
申请人： SAFRAN NACELLES
CPC分类号： F02C7/047 , F05D2220/80
摘要： A supersonic air intake of an aircraft propulsion assembly comprises: •⋅ pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, •⋅ a speed reducer fixedly mounted inside the pipe along the longitudinal axis, •⋅ at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and •⋅ at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.
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公开(公告)号：US20240191673A1
公开(公告)日：2024-06-13
申请号：US18470590
申请日：2023-09-20
申请人： SAFRAN NACELLES
摘要： A guide assembly for an aircraft propulsion unit, the guide assembly having a first element and at least one guide element attached to the first element. The guide element includes a bottom wall, two lateral walls connected together by the bottom wall, and an opening defined between the bottom wall and the lateral walls. The opening is configured to receive at least partly a second element configured to move relative to the guide element. The guide element can further include at least one pair of gripping tongues cooperating with holding members of the first element to retain the guide element on the first element.
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