公开(公告)号：US11554534B2

公开(公告)日：2023-01-17

申请号：US16770364

申请日：2018-12-06

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Norman Bruno Andre Jodet ,  Jeremy Paul Francisco Gonzalez ,  Jacky Novi Mardjono ,  Arnaud Dubourg ,  Edith-Roland Fotsing ,  Annie Ross ,  Daniel Therriault

IPC: B29C64/118 ,  B33Y10/00 ,  B33Y30/00 ,  B29C70/32 ,  B29K63/00 ,  B29K105/24 ,  B29L31/00

Abstract: A method of a coating by additive manufacturing on a turbomachine casing includes depositing on an internal surface of the turbomachine casing a filament of an abradable material to create a three-dimensional scaffold of filaments. A filamentary material deposition system is positioned from the internal surface of the casing; a first layer of the coating is deposited over 360′; a rotation of the filamentary material deposition system is carried out by a first predetermined angle and the filamentary material deposition system is positioned from the deposited layer; a second layer of coating is deposited on the first coating layer, on a sector of the casing; a displacement is carried out corresponding to the first sector already covered, then for the following sectors until 360° is covered; and after having carried out a rotation of the filamentary material deposition system.

公开(公告)号：US10967980B2

公开(公告)日：2021-04-06

申请号：US15778415

申请日：2016-11-21

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Norman Bruno Andre Jodet ,  Jeremy Paul Francisco Gonzalez ,  Herve Rolland

IPC: B64D27/14 ,  B64D27/20 ,  B64D27/02 ,  B64D29/04

Abstract: An airplane propelled by a turbine engine having at least one fan, the turbine engine being integrated in the rear of a fuselage of the airplane, extending it rearwards, the airplane further including at least one acoustic baffle forming panel connected to the fuselage of the airplane and arranged below the turbine engine.

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.

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：US10995702B2

公开(公告)日：2021-05-04

申请号：US16105159

申请日：2018-08-20

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Guillaume Bodard ,  Jeremy Paul Francisco Gonzalez ,  Norman Bruno Andre Jodet

IPC: F02K3/115 ,  F02K3/08 ,  F02K1/38 ,  F02K1/46 ,  F02K1/48 ,  F02K1/34

Abstract: An assembly for a rear of a dual-flow turbomachine having a longitudinal axis includes a secondary nozzle and a heating system. The secondary nozzle is defined about the longitudinal axis and ejects a mixture of the flows coming from a secondary vein and a primary vein of the turbomachine. The secondary nozzle is of a convergent-divergent form with a neck corresponding to a minimal cross-cross-section of the secondary nozzle. The heating system is located on a portion of the internal circumference of the secondary nozzle longitudinally in the region of the neck or upstream from the neck.

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).