公开(公告)号：US11560842B2

公开(公告)日：2023-01-24

申请号：US16633249

申请日：2018-07-25

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Georges Jean Xavier Riou ,  Norman Bruno André Jodet ,  Jéremy Paul Francisco Gonzalez

IPC: F02C7/045 ,  B32B3/12 ,  B32B3/26 ,  B64D33/02 ,  G10K11/168 ,  G10K11/172

Abstract: An acoustic panel for an aircraft propulsion unit, comprises a core and an entry layer in contact with the core, the entry layer comprising lower elements and upper elements, each comprising an inner face, an outer face and at least one through-hole, the inner faces of the lower elements and upper elements being in contact with each other and forming a channel defining a baffle and opening into a cell of the core.

公开(公告)号：US10280839B2

公开(公告)日：2019-05-07

申请号：US15513798

申请日：2015-09-23

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Georges Jean Xavier Riou ,  Jacky Novi Mardjono

IPC: B32B3/12 ,  B32B3/26 ,  F02C7/045 ,  G10K11/172 ,  B32B7/12

Abstract: An acoustic treatment panel including a cellular structure core sandwiched between a solid skin and a perforated skin, and a plurality of domes made of porous fabric and extending from at least one of the skins into the insides of the cells of the cellular structure towards the other skin so as to define at least two resonant cavities inside each cell of the cellular structure.

公开(公告)号：US20210003074A1

公开(公告)日：2021-01-07

申请号：US16969738

申请日：2019-02-15

Applicant: Safran Aircraft Engines

Inventor： Fernando Gea Aguilera ,  Mathieu Simon Paul Gruber ,  Georges Jean Xavier Riou

IPC: F02C7/045 ,  F02K1/38 ,  F15D1/00 ,  B64C21/10 ,  B64C21/02 ,  B64C3/14 ,  B64C3/16 ,  B64C7/02 ,  B64C11/18 ,  B64C5/00 ,  B64C5/06

Abstract: An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.

公开(公告)号：US11434826B2

公开(公告)日：2022-09-06

申请号：US17274558

申请日：2019-09-09

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Georges Jean Xavier Riou ,  Jeremy Paul Francisco Gonzalez ,  Jacky Novi Mardjono

IPC: F02C7/24 ,  G10K11/172

Abstract: An acoustic absorption cell including a bottom wall extending in a plane orthogonal to an axial direction, an enclosure including a first axial end secured to the bottom wall, and an acoustic horn extending inside the enclosure between a first opening of the horn and a second opening of the horn smaller than the first opening, the horn being secured to a second axial end of the enclosure opposite the first axial end, and the first and second openings of the horn each extending in a plane orthogonal to the axial direction. The horn includes at least one retaining arm protruding from the horn inside the enclosure and fixed to the bottom wall or to the enclosure.

公开(公告)号：US11248530B2

公开(公告)日：2022-02-15

申请号：US17046566

申请日：2019-04-09

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Jéremy Paul Francisco Gonzalez ,  Norman Bruno André Jodet ,  Georges Jean Xavier Riou

IPC: F02C7/24 ,  G10K11/16

Abstract: An acoustic treatment panel intended to be disposed on at least one wall of a turbojet engine in contact with a fluid flow, the panel including a first acoustically reflective plate, a second plate and a plurality of cavities mounted between the first plate and the second plate and including a plurality of cells. The second plate is a one-piece plate through which a plurality of channels pass, each opening out on the one hand onto a first orifice formed on a first face of the second plate and on the other hand onto a second orifice formed on a second face of the second plate, the length of each channel extending between its first orifice and its second orifice being greater than the thickness of the second plate.

公开(公告)号：US10557417B2

公开(公告)日：2020-02-11

申请号：US15963416

申请日：2018-04-26

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Norman Bruno Andre Jodet ,  Jeremy Paul Francisco Gonzalez ,  Jacky Novi Mardjono ,  Georges Jean Xavier Riou

IPC: F02C7/24 ,  B64D27/16

Abstract: An acoustic absorber cell (1) for mounting on a turbojet wall in contact with a fluid flow, the cell (1) having a resonant cavity (2) presenting a wall (30) having at least one orifice (4) associated with a neck (5) having a tube (51) extending inside the resonant cavity (2) and projecting from the wall (30). The neck (5) also having a tubular ring (52) coaxial with the tube (51) and movable relative to the tube (51), and the cell (1) includes electromagnetic actuator (6) for moving the ring (52) along the tube (51), and controller (7) for controlling the electromagnetic actuator (6) and configured to control movement of the ring (52) along the tube (51) as a function of the operating speed of the turbojet between at least first and second positions defining respective first and second resonant frequencies of the resonant cavity (2).

公开(公告)号：US12092033B2

公开(公告)日：2024-09-17

申请号：US17605042

申请日：2020-04-23

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Georges Jean Xavier Riou ,  Jacky Novi Mardjono ,  Renaud Yannick Fabien Daon ,  Nicolas Pierre Alain Edme De Cacqueray-Valmenier

IPC: F02C7/24

CPC classification number: F02C7/24 ,  F05D2250/191 ,  F05D2250/283 ,  F05D2260/963

Abstract: An acoustic treatment panel intended to be disposed on at least one wall of a turbojet in contact with a fluid flow, the panel comprising a first sheet, a second sheet parallel to the first sheet and having a first face intended to be in contact with a fluid flow and a second face facing the first sheet, and acoustic treatment cells extending between the first and second sheets and each including an enclosure and a cavity delimited by the enclosure. The enclosure of each cell comprises two openings facing one another, at least one of the openings being coincident with an opening of the enclosure of an adjacent cell.

公开(公告)号：US11859534B2

公开(公告)日：2024-01-02

申请号：US16969738

申请日：2019-02-15

Applicant: Safran Aircraft Engines

Inventor： Fernando Gea Aguilera ,  Mathieu Simon Paul Gruber ,  Georges Jean Xavier Riou

IPC: F02C7/045 ,  B64C3/10 ,  B64C11/18 ,  B64C21/10 ,  F02K1/34 ,  B64D33/02 ,  F01D9/04

CPC classification number: F02C7/045 ,  B64C3/10 ,  B64C11/18 ,  B64C21/10 ,  B64D33/02 ,  B64D33/06 ,  F01D9/041 ,  B64D2033/0206 ,  F05D2260/96

Abstract: An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.

公开(公告)号：US11143462B2

公开(公告)日：2021-10-12

申请号：US15517085

申请日：2015-10-23

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Bellal Waissi ,  Sébastien Chalaud ,  Lancelot Guillou ,  Jacky Novi Mardjono ,  Guillaume Mathon-Margueritte ,  Georges Jean Xavier Riou ,  Claude Sensiau

IPC: F01N1/00 ,  F28F3/04 ,  F02C7/12 ,  F02C7/24 ,  F28F3/02 ,  F28D1/03 ,  F28D9/00 ,  F01N1/02 ,  F02C7/045 ,  F02C7/14 ,  F28D21/00

Abstract: A heat exchange and noise reduction panel the panel for an aircraft comprising: an external surface intended to be swept by an airflow and from which fins extend along a first and a second main predetermined direction; cavities forming Helmholtz resonators, linked to the first ends of channels for the passage of air, the second ends of which communicate with said airflow, such that said channels form necks, referred to as Helmholtz resonators, extending substantially along the first direction; and at least one oil flow chamber extending between said external surface and said at least one cavity, and intended to discharge the thermal energy carried by the oil, wherein said channels are formed, at least in part, inside said fins.

公开(公告)号：US10662876B2

公开(公告)日：2020-05-26

申请号：US16025582

申请日：2018-07-02

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Georges Jean Xavier Riou ,  Jacky Novi Mardjono ,  Norman Bruno Andre Jodet ,  Jeremy Paul Francisco Gonzalez

IPC: F04D29/66 ,  F02C7/045 ,  F04D29/54 ,  B64D33/02 ,  F01D9/04

Abstract: A turbomachine vane includes an electroacoustic source including two membranes fixed on a support arranged such that the membranes and the support delimit a first cavity. The membranes are arranged on two opposite sides of the first cavity between the two aerodynamic surfaces of the vane. A first of the aerodynamic surfaces includes a first region arranged facing a first of the membranes for the passage of acoustic waves. The membranes and membrane vibration device are configured such that the membranes vibrate in phase opposition and along a same emission direction by applying forces to the support such that the resultant force is approximately zero. The mechanical energy lost in the form of vane deformations due to membrane vibrations can thus be minimized.