公开(公告)号：US20190078534A1

公开(公告)日：2019-03-14

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: F02K1/34 ,  F02K1/38 ,  F02K1/48

Abstract: The invention proposes an assembly for a rear of a dual-flow turbomachine (10) having a longitudinal axis (X), comprising: a secondary nozzle (110) defined about the longitudinal axis (X), said secondary nozzle being configured to eject a mixture of the flows coming from a secondary vein (Vs) and a primary vein (Vp) of the turbomachine (10), the secondary nozzle being of convergent-divergent form with a neck (112) corresponding to a minimal cross-cross-section of the secondary nozzle (110), a heating system located on at least one portion of the internal circumference of the secondary nozzle longitudinally in the region of the neck and/or upstream from the neck (112).

公开(公告)号：US20200378339A9

公开(公告)日：2020-12-03

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: F02K1/34 ,  F02K1/38 ,  F02K1/48

Abstract: The invention proposes an assembly for a rear of a dual-flow turbomachine (10) having a longitudinal axis (X), comprising: a secondary nozzle (110) defined about the longitudinal axis (X), said secondary nozzle being configured to eject a mixture of the flows coming from a secondary vein (Vs) and a primary vein (Vp) of the turbomachine (10), the secondary nozzle being of convergent-divergent form with a neck (112) corresponding to a minimal cross-cross-section of the secondary nozzle (110), a heating system located on at least one portion of the internal circumference of the secondary nozzle longitudinally in the region of the neck and/or upstream from the neck (112).

公开(公告)号：US20200376743A1

公开(公告)日：2020-12-03

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 ,  B29C70/32 ,  B33Y30/00

Abstract: A method of a coating by additive manufacturing on a turbomachine casing, including depositing on an internal surface of the turbomachine casing a filament of an abradable material to create a three-dimensional scaffold of filaments forming an ordered array of channels. A filamentary material deposition system is positioned at a predetermined position and distance 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 at a predetermined position and distance 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 by a predetermined angular deviation 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 by a second predetermined angle.

公开(公告)号：US20180354634A1

公开(公告)日：2018-12-13

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: B64D29/04 ,  B64D27/14 ,  B64C5/02 ,  B64C1/40 ,  F02C7/24 ,  G10K11/162

CPC classification number: B64D29/04 ,  B64C1/40 ,  B64C5/02 ,  B64D27/14 ,  B64D27/20 ,  F02C7/24 ,  F05D2220/323 ,  F05D2240/126 ,  G10K11/162

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：US20180313273A1

公开(公告)日：2018-11-01

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) comprising a resonant cavity (2) presenting a wall (30) having at least one orifice (4) associated with a neck (5) comprising a tube (51) extending inside the resonant cavity (2) and projecting from said wall (30).The neck (5) also comprises a tubular ring (52) coaxial with the tube (51) and movable relative to said tube (51), and the cell (1) includes translation means (6) for moving the ring (52) along the tube (51), and control means (7) for controlling the translation means (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).