公开(公告)号：US20190084261A1

公开(公告)日：2019-03-21

申请号：US15708573

申请日：2017-09-19

申请人： The Boeing Company

发明人： Eric Herrera ,  John Scott Bauman ,  Peter James Oberst

IPC分类号： B29D99/00 ,  B29D24/00 ,  B29C65/04 ,  B29C65/08 ,  B29C65/10 ,  B32B3/12 ,  G10K11/16 ,  F02C7/045 ,  F02K1/82 ,  E04B1/82

CPC分类号： B29D99/001 ,  B29C65/04 ,  B29C65/08 ,  B29C65/10 ,  B29C66/431 ,  B29C66/4326 ,  B29C66/49 ,  B29C66/729 ,  B29C66/8322 ,  B29D24/005 ,  B29D99/0089 ,  B29L2031/38 ,  B29L2031/608 ,  B29L2031/7724 ,  B32B3/12 ,  B32B2307/10 ,  B64D29/00 ,  B64D33/02 ,  B64D2033/0206 ,  B64F5/10 ,  E04B1/82 ,  E04B2001/748 ,  E04B2001/8245 ,  F02C7/045 ,  F02K1/827 ,  F05D2230/23 ,  F05D2250/283 ,  F05D2260/96 ,  G10K11/16 ,  G10K11/172 ,  G10K2210/1281

摘要： A method and system for manufacturing a conical shaped acoustic structure. A sheet of acoustical material is cut to form individual pieces using a cutter system. Each individual piece in the individual pieces has a flat pattern for the conical shaped acoustic structure. An individual piece is positioned around a mandrel with a conical shape using an actuator system. Two edges of the individual piece are positioned for joining. The two edges of the individual piece positioned around the mandrel are joined to form the conical shaped acoustic structure.

公开(公告)号：US20190054999A1

公开(公告)日：2019-02-21

申请号：US15681031

申请日：2017-08-18

申请人： Rohr, Inc.

发明人： Sreenivas Narayanan Nampy ,  David M. Adams

IPC分类号： B64C1/40 ,  B64D29/00

CPC分类号： B64C1/40 ,  B64D29/00 ,  B64D2033/0206

摘要： A structural panel is provided that includes a first core structure and a second core structure. The second core structure includes a plurality of core components, which components includes a corrugated ribbon, a first wall and a second wall. The corrugated ribbon includes a plurality of baffles and a plurality of porous septums. The baffles and the porous septums are laterally between and connected to the first wall and the second wall. Each of the porous septums are longitudinally between a respective adjacent pair of the baffles. A first of the core components projects longitudinally into and/or along the first core structure at a splice joint between the first core structure and the second core structure.

公开(公告)号：US20180363558A1

公开(公告)日：2018-12-20

申请号：US15626913

申请日：2017-06-19

申请人： Rohr, Inc.

发明人： Luby Weaver ,  Charles M. Biset ,  Jeffrey Woods ,  David M. Adams

IPC分类号： F02C7/24 ,  F02C7/045 ,  F02K1/82 ,  G10K11/172 ,  E04B1/84

CPC分类号： F02C7/24 ,  B64D2033/0206 ,  E04B1/8409 ,  E04B1/86 ,  E04B2001/8471 ,  F02C7/045 ,  F02K1/827 ,  F05D2260/96 ,  G10K11/168 ,  G10K11/172

摘要： A panel is provided for attenuating noise. This panel includes a perforated first skin, a second skin, an array of corrugations, a first channel, a second channel, a plurality of first sidewalls and a plurality of second sidewalls. The array of corrugations includes a first corrugation and a second corrugation. Each of the corrugations includes a baffle and a septum. The first channel is formed by the baffle of the first corrugation, the septum of the first corrugation and the first skin. The second channel is formed by the baffle of the second corrugation, the septum of the first corrugation and the second skin. The first sidewalls divide the first channel into a plurality of first chambers. The second sidewalls divide the second channel into a plurality of second chambers. A first of the second chambers is fluidly coupled with a subset of the first chambers through perforations in the septum of the first corrugation.

公开(公告)号：US20180339785A1

公开(公告)日：2018-11-29

申请号：US15604697

申请日：2017-05-25

申请人： THE BOEING COMPANY

发明人： John C. Waldrop, III ,  Zachary Benjamin Renwick ,  Matthew Scott Thompson ,  Michael William Hayes

IPC分类号： B64D33/02 ,  B32B3/12 ,  B32B7/08 ,  B32B37/00 ,  B64D27/16

CPC分类号： B64D33/02 ,  B32B3/12 ,  B32B7/08 ,  B32B7/12 ,  B32B27/08 ,  B32B27/12 ,  B32B27/285 ,  B32B27/286 ,  B32B27/288 ,  B32B27/34 ,  B32B37/0076 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2262/0269 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2305/024 ,  B32B2307/102 ,  B32B2307/724 ,  B32B2307/726 ,  B32B2605/18 ,  B64D27/16 ,  B64D2033/0206

摘要： A composite structure assembly and method of forming a composite structure assembly is provided. The composite structure assembly includes a composite core including a first cell layer having a plurality of first cells and a second cell layer having a plurality of second cells. The first cell layer is adjacent to the second cell layer. The plurality of first cells are fluidly interconnected with the plurality of second cells.

公开(公告)号：US20180258788A1

公开(公告)日：2018-09-13

申请号：US15452627

申请日：2017-03-07

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Bruce L. Morin ,  Daniel L. Gysling ,  Mani Sadeghi

IPC分类号： F01D25/06 ,  B64D33/02

CPC分类号： F01D25/06 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/045 ,  F02K1/827 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/14 ,  F05D2260/96 ,  F05D2260/963 ,  G10K11/172 ,  Y02T50/672

摘要： Disclosed is flutter damper including a first cavity having a radially inner side in fluid communication with a flow path, and a second cavity having a radially inner side in fluid communication with a radially outer side of the first cavity, and the flutter damper having an impedance characteristic at one or more target frequencies defined as ftarget=fS,ND+Ω·ND wherein fS,ND is a resonance frequency corresponding to a structural mode of a rotating component, ND is a nodal diameter count of the structural mode, and Ω is a rotational speed of the rotating component, and wherein the flutter damper has the following impedance characteristic at the one or more targeted frequencies R≥2ρc −3ρc≤X≤−0.6ρc wherein R is the real part of the impedance characteristic, X is the imaginary part of the impedance characteristic, ρ is air density, and c is speed of sound.

公开(公告)号：US20180257196A1

公开(公告)日：2018-09-13

申请号：US15779433

申请日：2016-11-22

申请人： SHORT BROTHERS PLC

发明人： Derek SIMPSON ,  Tony MILLAR

IPC分类号： B24C1/04 ,  B32B3/12 ,  B32B3/26 ,  B32B7/12 ,  B64D33/02

CPC分类号： B24C1/04 ,  B32B3/12 ,  B32B3/266 ,  B32B5/024 ,  B32B5/26 ,  B32B7/05 ,  B32B7/12 ,  B32B15/08 ,  B32B15/12 ,  B32B15/14 ,  B32B15/20 ,  B32B29/02 ,  B32B2250/03 ,  B32B2250/04 ,  B32B2250/40 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2262/02 ,  B32B2262/0269 ,  B32B2262/101 ,  B32B2262/103 ,  B32B2262/106 ,  B32B2307/102 ,  B32B2307/732 ,  B32B2605/00 ,  B32B2605/10 ,  B32B2605/18 ,  B64D33/02 ,  B64D2033/0206 ,  G10K11/172

摘要： Noise attenuating devices and methods, precursors and abrasive blasting masks for manufacturing noise attenuating devices are disclosed. An exemplary method disclosed herein includes bonding a facing sheet of the noise attenuating device to a cellular core and then perforating the facing sheet. Perforating the facing sheet may be performed by abrasive blasting using a mask configured to prevent the abrasive blasting of an underlying structure.

公开(公告)号：US20180201387A1

公开(公告)日：2018-07-19

申请号：US15847207

申请日：2017-12-19

申请人： Airbus (S.A.S.) ,  Airbus Operations (S.A.S.)

发明人： Alain Porte ,  Eric Haramburu ,  Patrick Oberle ,  Grégory Albet ,  Vincent Billerot ,  Frédéric Piard ,  Franck Oundjian

IPC分类号： B64D33/02 ,  F02C7/045 ,  F02C7/047

CPC分类号： B64D33/02 ,  B64D2033/0206 ,  B64D2033/0233 ,  B64D2033/0286 ,  F02C7/045 ,  F02C7/047 ,  F05D2220/323 ,  F05D2250/75 ,  F05D2260/83 ,  F05D2260/96 ,  Y02T50/672

摘要： An aircraft nacelle air intake structure including an air intake lip with a U-shaped section to ensure air is shared between an inner face and an outer face. An acoustic panel is on the intake lip rear on the side of the inner face level with a first assembly point. An outer panel is on the intake lip rear on the side of the outer face level with a second assembly point. A front reinforcing frame on the intake lip inside is fixed to the air intake lip on the side of the inner face level with a first fixing point and on the side of the outer face level with a second fixing point. The length of the chord between the stop point and each fixing point is between ⅓ and ⅙ of the total chord between the stop point and the assembly point.

公开(公告)号：US10017261B2

公开(公告)日：2018-07-10

申请号：US14650143

申请日：2013-12-02

申请人： ALENIA AERMACCHI S.P.A.

发明人： Marco Francesco Vercellesi

IPC分类号： H05B3/16 ,  B64D15/12 ,  H05B3/22 ,  H05K1/02 ,  F02K1/82 ,  H05B3/14 ,  H05B3/34 ,  B64D33/02

CPC分类号： B64D15/12 ,  B64D2033/0206 ,  B64D2033/0233 ,  F02K1/827 ,  H05B3/145 ,  H05B3/22 ,  H05B3/34 ,  H05B3/342 ,  H05B2203/007 ,  H05B2203/013 ,  H05B2203/014 ,  H05B2203/037 ,  H05B2214/02 ,  H05K1/0212 ,  H05K1/0296 ,  H05K1/0298 ,  H05K2201/09681 ,  H05K2201/0979 ,  Y02T50/672

摘要： An electronic circuit allows at least one current to flow between at least two points of the same circuit. The electronic circuit is in contact with a structure (P) and includes at least one graph (2) including a plurality of nodes (24) and a plurality of connections or branches (22) between the nodes (24) that create at least one mesh (M) of interconnections. The at least one mesh (M) includes interconnections that are configured at least two interconnections between two nodes (24) created by the plurality of connections or branches (22).

公开(公告)号：US20180105281A1

公开(公告)日：2018-04-19

申请号：US15730954

申请日：2017-10-12

申请人： Airbus Operations SAS

发明人： Alain PORTE ,  Frédéric VINCHES

IPC分类号： B64D33/02 ,  B64C7/02

CPC分类号： B64D33/02 ,  B64C7/02 ,  B64D29/00 ,  B64D2033/0206 ,  B64D2033/0273 ,  B64D2033/0286 ,  F02C7/045 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2230/70 ,  F05D2260/30 ,  F05D2260/31 ,  F05D2260/963 ,  Y02T50/672

摘要： An aircraft nacelle including a conduit rigidly connected to an air inlet and a conduit rigidly connected to an engine, a link between the conduit rigidly connected to the air inlet and the conduit rigidly connected to the engine. The link includes a sleeve that receives one end of a first conduit and is rigidly connected to a second conduit, and linking elements that link the sleeve and the first conduit and that are distributed about the entire circumference of the nacelle, each linking element having a threaded stem oriented in a radial direction and being configured to enable tightening from inside the first conduit.

公开(公告)号：US20180066545A1

公开(公告)日：2018-03-08

申请号：US15683881

申请日：2017-08-23

申请人： Safran Aero Boosters SA

发明人： Benoit Meys ,  Alain Lacroix

IPC分类号： F01D25/28 ,  G10K11/178 ,  F02C7/045 ,  B64C1/40

CPC分类号： F01D25/285 ,  B64C1/40 ,  B64D2033/0206 ,  B64F1/26 ,  F01D21/003 ,  F02C7/045 ,  F02K1/44 ,  F02K1/827 ,  F05D2260/12 ,  F05D2260/962 ,  F05D2270/333 ,  F05D2270/81 ,  G01M15/12 ,  G01M15/14 ,  G10K11/178 ,  G10K11/17857 ,  G10K2210/121 ,  G10K2210/1281

摘要： a test bench for turbomachine comprising: an installation zone for turbomachine; an active system for attenuating the noise emissions produced by the turbomachine. The active system includes an attenuation zone with emitters such as loudspeakers; a first microphone placed downstream of the turbomachine; and a second microphone placed downstream of the attenuation zone. The system reduces the turbomachine waves on the basis of the measurements from the first microphone and from the second microphone. The invention also proposes a method for attenuating the noise emissions from the turbomachine tested in the test bench.