公开(公告)号：US20240343413A1

公开(公告)日：2024-10-17

申请号：US18301397

申请日：2023-04-17

申请人： The Boeing Company

发明人： Thomas Karl Tsotsis

IPC分类号： B64F5/10 ,  B33Y10/00 ,  B33Y80/00

CPC分类号： B64F5/10 ,  B33Y10/00 ,  B33Y80/00 ,  B64D33/02 ,  B64D2033/0206

摘要： Present systems and apparatuses and their methods of manufacture are directed to acoustic core that can be made from metal alloys or thermoplastic materials and formed into single-piece, net-shaped core details possessing one or more of the following features: varying cell size, varying cell-wall thickness, varying cell shape, varying core thickness, incorporation of wall perforations, incorporation of septums, edge closeouts, and non-vertical and/or curved cell walls.

公开(公告)号：US12116930B2

公开(公告)日：2024-10-15

申请号：US18254775

申请日：2021-11-24

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Paco Maurer ,  Julien Fabien Patrick Becoulet ,  Serge Rene Morreale ,  Nicolas Stoliaroff-Pepin

IPC分类号： F02C7/042 ,  B64D33/02 ,  F02C7/18 ,  F02K1/70

CPC分类号： F02C7/042 ,  B64D33/02 ,  F02C7/18 ,  F02K1/70

摘要： A scoop for an aircraft turbine engine, this scoop including a body which is movable between at least two positions, including a first position in which it is configured to capture part of a first air stream flowing in a first direction, wherein the body is movable into a second position in which it is configured to capture part of a second air stream flowing in a second direction which is opposite to the first direction, and wherein the body is mounted to move freely between the at least two positions so as to automatically adopt the first position when the first air stream flows, and to automatically adopt the second position when the second air stream flows.

公开(公告)号：US12104526B2

公开(公告)日：2024-10-01

申请号：US17166826

申请日：2021-02-03

申请人： Safran Nacelles

发明人： Audrey Riquet

IPC分类号： F02C7/047 ,  B23K26/00 ,  B23K26/0622 ,  B23K26/352 ,  B23K103/16 ,  B29C59/16 ,  B64D15/04 ,  B64D29/00 ,  B64D33/02

CPC分类号： F02C7/047 ,  B23K26/0006 ,  B23K26/0624 ,  B23K26/355 ,  B23K26/3584 ,  B29C59/16 ,  B64D15/04 ,  B64D33/02 ,  B23K2103/16 ,  B29C59/165 ,  B64D29/00 ,  B64D2033/0233 ,  F05D2300/512 ,  Y02T50/60

摘要： A method for the anti-icing treatment of a surface of an aircraft part made of an organic matrix composites includes a texturing step in which the surface is irradiated with femtosecond laser pulses so as to render the surface superhydrophobic.

公开(公告)号：US12077309B2

公开(公告)日：2024-09-03

申请号：US18571073

申请日：2022-06-10

申请人： SAFRAN NACELLES

发明人： Patrick Gonidec ,  Albin Lafont ,  Virginie Emmanuelle Anne-Marie Digeos ,  Stuart Hardyman

IPC分类号： B64D33/02 ,  F02C7/045 ,  G10K11/168

CPC分类号： B64D33/02 ,  F02C7/045 ,  B64D2033/0206 ,  F05D2220/323 ,  F05D2250/283 ,  F05D2260/96 ,  G10K11/168

摘要： An acoustic treatment panel intended to be disposed on at least one wall of an aircraft propulsion unit in contact with a fluidic flow, the panel including a first, acoustically reflective skin, a second, acoustically porous skin intended to be in contact with the fluidic flow, and a honeycomb structure extending between the first skin and the second skin and having a plurality of cavities. The panel includes at least one acoustically transparent reinforcing wall passing through a plurality of cavities of the honeycomb structure and extending from the second skin to the first skin, forming a non-orthogonal angle with the first and second skins.

公开(公告)号：US20240262523A1

公开(公告)日：2024-08-08

申请号：US18405712

申请日：2024-01-05

申请人： RTX CORPORATION

发明人： Neil J. Terwilliger ,  Joseph B. Staubach

IPC分类号： B64D33/02 ,  B64D33/04

CPC分类号： B64D33/02 ,  B64D33/04 ,  B64D2033/0286

摘要： A propulsion system for an aircraft includes a gas generating core engine, a propulsor that is driven by an exhaust gas flow that is generated by the core engine, and an inlet assembly where an inlet airflow is communicated to the core engine. The inlet assembly is disposed aft of the core engine and includes a turning duct that directs inlet air into the core engine, and a particle exhaust outlet that directs particulates away from the core engine.

公开(公告)号：US20240254894A1

公开(公告)日：2024-08-01

申请号：US18428881

申请日：2024-01-31

申请人： Rohr, Inc.

发明人： Pratap Mallampati

IPC分类号： F01D25/02 ,  B64D33/02 ,  F02C7/057

CPC分类号： F01D25/02 ,  B64D33/02 ,  F02C7/057 ,  B64D2033/0233 ,  F05D2220/323

摘要： An anti-icing system for an aircraft nacelle structure is provided that includes a controllable PRSOV, a circumferentially extending duct, a bleed air duct segment, at least one PRV, and a controller. The PRSOV may be disposed in a closed or an open configuration. The PRV is disposed downstream of the PRSOV and in fluid communication with the bleed air duct segment. The PRV may be disposed in a closed or in an open configuration. The controller is in communication with a memory storing instructions. The instructions when executed cause the system controller to control the PRSOV to maintain bleed air within the anti-icing system within a predetermined range of operating pressures by selectively controlling the PRSOV into at least one of the one or more PRV open configurations, and control the PRV to open to maintain the bleed air below the maximum pressure.

公开(公告)号：US20240253803A1

公开(公告)日：2024-08-01

申请号：US18425129

申请日：2024-01-29

申请人： Airbus SAS ,  Airbus Operations SAS

发明人： François PONS ,  Laurent CAZEAUX ,  Arnulfo CARAZO MENDEZ ,  Florent MERCAT ,  Alexandre BELLANGER ,  Laurent PRESSEQ ,  Maxime GAUTHIER ,  Manuel TEIGNE ,  Philippe WESSEL ,  Joelle BONNEFONT

IPC分类号： B64D33/02

CPC分类号： B64D33/02 ,  B64D2033/0206

摘要： An alveolar structure of an acoustic damping panel which is configured for damping at least one sound wave of a sound frequency, wherein the alveolar structure comprises at least one attached element, separate from partitions, and configured for vibrating at a frequency substantially equal to the sound frequency of the sound wave to be damped. Also a method for producing such an alveolar structure, an acoustic damping panel comprising at least one such alveolar structure, and an aircraft comprising at least one such acoustic damping panel.

公开(公告)号：US20240229713A1

公开(公告)日：2024-07-11

申请号：US18368948

申请日：2023-09-15

申请人： Rohr, Inc.

发明人： Timothy Gormley

IPC分类号： F02C7/042 ,  B64D27/14 ,  B64D33/02 ,  F02K1/12

CPC分类号： F02C7/042 ,  B64D27/14 ,  B64D33/02 ,  F02K1/12 ,  B64D2033/0286

摘要： An assembly is provided for an aircraft propulsion system. This assembly includes a variable area inlet, and the variable area inlet includes an inlet structure, an inlet lip, an inlet orifice and an inlet passage extending within the variable area inlet from the inlet orifice. The inlet lip is configured to pivot about a pivot axis between a first position and a second position. The inlet orifice is formed by and between the inlet structure and the inlet lip. The inlet orifice has a first area when the inlet lip is in the first position. The inlet orifice has a second area when the inlet lip is in the second position. The second area is different than the first area.

公开(公告)号：US20240228053A1

公开(公告)日：2024-07-11

申请号：US18235311

申请日：2023-08-17

申请人： JETOPTERA, INC.

发明人： Andrei Evulet

IPC分类号： B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C39/02 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  B64U30/00 ,  B64U30/10 ,  F02C3/04 ,  F02C6/04 ,  F02K1/00 ,  F02K1/36

CPC分类号： B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C23/005 ,  B64C39/024 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  F02C3/04 ,  F02C6/04 ,  F02K1/002 ,  F02K1/36 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/16 ,  B64D2033/0273 ,  B64U30/00 ,  B64U30/10 ,  F05D2220/90 ,  Y02T50/10 ,  Y02T50/30 ,  Y02T50/40

摘要： A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

公开(公告)号：US20240217667A1

公开(公告)日：2024-07-04

申请号：US18571073

申请日：2022-06-10

申请人： SAFRAN NACELLES

发明人： Patrick GONIDEC ,  Albin LAFONT ,  Virginie Emmanuelle Anne-Marie DIGEOS ,  Stuart HARDYMAN

IPC分类号： B64D33/02 ,  F02C7/045 ,  G10K11/168

CPC分类号： B64D33/02 ,  F02C7/045 ,  B64D2033/0206 ,  F05D2220/323 ,  F05D2250/283 ,  F05D2260/96 ,  G10K11/168

摘要： An acoustic treatment panel intended to be disposed on at least one wall of an aircraft propulsion unit in contact with a fluidic flow, the panel including a first, acoustically reflective skin, a second, acoustically porous skin intended to be in contact with the fluidic flow, and a honeycomb structure extending between the first skin and the second skin and having a plurality of cavities. The panel includes at least one acoustically transparent reinforcing wall passing through a plurality of cavities of the honeycomb structure and extending from the second skin to the first skin, forming a non-orthogonal angle with the first and second skins.