-
1.发明公开公开(公告)号：US20240316894A1
公开(公告)日：2024-09-26
申请号：US18578231
申请日：2022-07-05
申请人： SAFRAN
CPC分类号： B32B3/12 , B32B3/266 , B32B27/08 , B32B27/281 , B32B27/285 , B32B27/288 , B32B27/38 , B32B2307/102 , F02K1/827 , F05D2260/96
摘要： A method for manufacturing an acoustic attenuation structure including the following steps: making a complex acoustic multi-element panel including a plurality of hollow complex acoustic elements and a plurality of partitions forming acoustic cavities, each complex acoustic element being housed in an acoustic cavity so as to form an acoustic cell, making a first skin, piercing a plurality of perforations on the first skin at determined locations to form a multi-perforated acoustic skin, assembling the complex acoustic multi-element panel with the multi-perforated acoustic skin. The multi-perforated acoustic skin including on its assembly face a plurality of positioning studs configured to cooperate with a hollow complex acoustic element or an acoustic cavity during the assembly of the complex acoustic multi-element panel with the multi-perforated acoustic skin.
-
公开(公告)号：US12065985B2
公开(公告)日：2024-08-20
申请号：US18030151
申请日：2021-10-04
申请人： SAFRAN CERAMICS
发明人： Thierry Guy Xavier Tesson , Christophe Jean François Thorel , Christophe Paul Aupetit , Thierry Jacques Albert Le Docte , Philippe Avenel
CPC分类号： F02K1/04 , F01D25/30 , F02K1/805 , F02K1/827 , F05D2240/55 , F05D2260/96
摘要： The present invention relates to an assembly for a turbomachine turbine extending along an axis (X), comprising: —an ejection cone (100) comprising a radially outer annular wall (102) defining a flow duct for a flow of hot gases and a sound box radially arranged inside the outer annular wall (102), the sound box comprising a radially inner annular wall (104), —a connecting member (106) intended to be axially inserted between the exhaust housing and the ejection cone (100), the connecting member (106) comprising an upstream annular flange (108) intended to be attached to the exhaust housing and a plurality of downstream securing tabs (110) connected to the inner annular wall (104), —an annular sealing shroud (112) comprising an upstream portion surrounding the securing tabs (110) of the connecting member (106) so as to cover the spaces circumferentially located between the securing tabs (110) and axially located between the upstream annular flange (108) of the connecting member (106) and the radially inner annular wall (104).
-
公开(公告)号：US20240263565A1
公开(公告)日：2024-08-08
申请号：US18618081
申请日：2024-03-27
CPC分类号： F01D25/04 , F01D5/141 , F01D5/145 , F01D5/18 , F01D9/041 , F02K1/827 , G10K11/16 , B64D2033/0226 , F05D2240/121 , F05D2250/184 , F05D2260/96 , F05D2260/961
摘要： An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.
-
公开(公告)号：US20240254944A1
公开(公告)日：2024-08-01
申请号：US18560510
申请日：2022-05-13
申请人： SAFRAN NACELLES
摘要： A thrust reverser for an aircraft propulsion unit, including a fixed structure, at least one cowl and a plurality of cascades of deflection vanes, the cowl and the cascades of vanes forming a system capable of translational movement relative to the fixed structure along a longitudinal central axis, the mobile system further including at least one rear cascade-support structure to which a rear end of the cascades of vanes is fixed, the rear structure extending in a circumferential direction of the reverser. The rear structure incorporates an acoustic-absorption device including an array of cells and a skin covering the cells, the skin having a first surface arranged facing the cells, and a second surface bounding part of a secondary flow path.
-
公开(公告)号：US20240217150A1
公开(公告)日：2024-07-04
申请号：US18092759
申请日：2023-01-03
申请人： Rohr, Inc.
发明人： Jennifer Davis
IPC分类号： B29C45/14
CPC分类号： B29C45/14811 , F02K1/827 , F05D2230/20 , F05D2260/963 , F05D2300/43 , F05D2300/603
摘要： A method is provided for manufacturing. This method includes: providing a first skin; providing a second skin; overmolding a cellular core onto the first skin; and joining the second skin to the cellular core to form a blocker door panel for an aircraft thrust reverser system. The blocker door panel includes a plurality of acoustic chambers and a face skin. Each of the acoustic chambers extends through the cellular core from the first skin to the second skin. Each of the acoustic chambers is fluidly coupled with one or more perforations through the face skin. The face skin includes one of the first skin or the second skin.
-
公开(公告)号：US11965425B2
公开(公告)日：2024-04-23
申请号：US17828112
申请日：2022-05-31
CPC分类号： F01D25/04 , F01D5/141 , F01D5/145 , F01D5/18 , F01D9/041 , F02K1/827 , G10K11/16 , B64D2033/0226 , F05D2240/121 , F05D2250/184 , F05D2260/96 , F05D2260/961
摘要： An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.
-
公开(公告)号：US11927133B2
公开(公告)日：2024-03-12
申请号：US16158524
申请日：2018-10-12
IPC分类号： F02C7/045 , B64C1/40 , B64C23/00 , B64D33/02 , D06N3/00 , F02C7/24 , F02K1/82 , F02K3/06 , G10K11/16 , G10K11/162
CPC分类号： F02C7/045 , B64C23/00 , B64D33/02 , F02K1/827 , F02K3/06 , G10K11/16 , G10K11/161 , G10K11/162 , B64C1/40 , B64D2033/0206 , D06N3/0006 , D06N2209/025 , F02C7/24 , F05D2220/323 , F05D2260/96 , F05D2300/514 , F05D2300/611
摘要： An acoustic attenuation liner includes
a porous coating with a mesh structure,
an acoustically absorbent material covered with the porous coating and having a first volume, and
at least one cavity created between the acoustically absorbent material and the porous coating and which has a second volume, such as Vcav>3%,
wherein the mesh structure has wires separating between them openings passing through the structure, some of which have, when flat, a minimum elementary surface area.-
公开(公告)号：US20230398646A1
公开(公告)日：2023-12-14
申请号：US18250345
申请日：2021-10-25
IPC分类号： B23P6/00 , F02C7/045 , F02K1/82 , B33Y10/00 , B33Y50/02 , B22F5/00 , B22F10/85 , B22F10/28 , B22F10/30 , B29C64/118 , B29C64/393
CPC分类号： B23P6/007 , F02C7/045 , F02K1/827 , B33Y10/00 , B33Y50/02 , B22F5/009 , B22F10/85 , B22F10/28 , B22F10/30 , B29C64/118 , B29C64/393 , F05D2220/323 , F05D2230/80 , F05D2260/96 , B22F2998/10 , B22F2301/052 , B29K2077/10
摘要： A method for repairing a part for an aircraft turbine engine, the part including a lower panel, an upper panel and a core having a honeycomb structure arranged between the lower panel and the upper panel, the part having an unimpaired portion and an at least partially impaired portion, the repair method including the following steps: (a) removing at least one portion of the lower panel or the upper panel from an area to be repaired; (b) removing at least one portion of the core from the area to be repaired; (c) reforming the core in the area to be repaired directly on the part by additive manufacturing; (d) reforming the lower panel or the upper panel in the area to be repaired, directly on the part.
-
公开(公告)号：US11676567B2
公开(公告)日：2023-06-13
申请号：US16722264
申请日：2019-12-20
CPC分类号： G10K11/168 , B29D24/008 , B29D99/0021 , B32B3/08 , B32B3/12 , F02C7/045 , F02K1/827 , G10K11/16
摘要： A method for manufacturing a sound absorption structure comprising a cellular panel, a porous layer positioned on a cellular panel first face, a reflective layer positioned on a cellular panel second face and a plurality of acoustic elements positioned in the cellular panel. The method comprises the steps of producing, for each acoustic element, a recess in the cellular panel opening out onto the first and second faces of the cellular panel, inserting the acoustic elements into their recesses, laying an anchoring layer on the second cellular panel face, curing or polymerization at a first pressure to connect each acoustic element to the cellular panel and/or to the anchoring layer, putting in place the porous layer and the reflective layer, and curing or polymerization at a second pressure to connect the porous layer and the reflective layer to the cellular panel.
-
公开(公告)号：US20190219000A1
公开(公告)日：2019-07-18
申请号：US15869223
申请日：2018-01-12
申请人： The Boeing Company
发明人： Jonathan Joseph REED
CPC分类号： F02K1/827 , B32B3/12 , B32B2305/024 , B32B2307/102 , B32B2605/18 , B64D33/02 , B64D2033/0206 , B64D2033/0273 , F02K1/72
摘要： An engine nacelle structure including a fan duct having a fan duct wall. The fan duct wall including a latticed frame having circumferentially extending frame members and longitudinally extending frame members, the circumferentially extending frame members and longitudinally extending frame members form a plurality of bays therebetween, and a plurality of acoustic attenuation panels, each acoustic attenuation panel being removably coupled to the latticed frame within a respective one of the plurality of bays so that the acoustic attenuation panel is configured to be coupled to and removed from the latticed frame independent of other ones of the plurality of acoustic panels.
-
-
-
-
-
-
-
-
-
搜索结果
549 条记录 (耗时 0.027 秒)
