Safran Aircraft Engines

Snecma

Centre National De La Recherche Scientifique

Safran Nacelles

Université De Technologie De Compiègne

Institutul National De Cercetare-dez-voltare Turbomotoare - Comoti

Université Technologie De Compiègne-utc

Jacky Novi Mardjono

Georges Jean Xavier Riou

Norman Bruno Andre Jodet

Edith-Roland Fotsing

Norman Bruno André Jodet

Marc Versaevel

Francois Marie Paul Marlin

Thierry Georges Paul Papin

Christophe Marcel Lucien Perdrigeon

Cédric Zaccardi

Bellal Waissi

Jéremy Paul Francisco Gonzalez

Arnaud Dubourg

Annie Ross

Jacques Michel Albert Julliard

Cedric Zaccardi

Philippe Gerard Chanez

Lancelot Guillou

Romain Plante

Sébastien Christophe Chalaud

Nicolas Pierre Alain Edme De Cacqueray-Valmenier

Jérémy Paul Francisco Gonzalez

Jean-Michel Boiteux

Henri Yesilcimen

Noel Robin

Claude Sensiau

Denis Ramage

Florian Gaudry

Maxime Koenig

François Marie Paul Marlin

Franck Zaganelli

Jeremy Paul Gonzalez

Guillaume Bodard

Guillaume Mathon-Margueritte

Radu Mihalache

Romulus Petcu

Valentin Silivestru

Lucia Raluca Voicu

Cristian Mihail Stanica

Renaud Yannick Fabien Daon

Daniel Therriault

Jean-Michel Jean-Francois Ville

Benjamin Andre Francois Poirier

Baptiste Cordier

Georges Riou

Sebastien Chalaud

Jérémy Gonzalez

Jean-Michel Jean-François Ville

Benjamin André François Poirier

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.

Integration of a fan flutter damper in an engine casing

A manufacturing method of a turbomachine airfoil, such as an outlet guide vane airfoil, comprising positioning a first fibrous wall preform on a first mold portion, placing at least one core on the first wall preform, positioning a second fibrous wall preform on the core, assembling a second mold portion to the first mold portion so as to form a mold around the first and second wall preforms, applying a hardening treatment to the first and second wall preforms, removing the core, and positioning a reinforcing structure between the first wall preform and the second wall preform.

Blade for a turbomachine and method for the manufacture thereof

A manufacturing method of an acoustic coating in an ordered array of interconnected micro-channels intended to receive, on a reception surface, an incident acoustic wave with direction Ac normal to this surface, the method including depositing a sacrificial material on a substrate surface to form a three-dimensional scaffold of filaments, infiltrating at least one part of the three-dimensional scaffold with a thermosetting material, solidifying the thermosetting material to form a solidified material, and removing the sacrificial material from the solidified material to form the ordered array of interconnected micro-channels, the filaments forming by superimposed layers the three-dimensional scaffold being, for a given layer of filaments, oriented in a direction forming, in a plane formed by the layer, a first angle &#x3b8; relative to the direction Ac of the incident acoustic wave, to confer acoustic properties to the ordered array of interconnected micro-channels and thus form the acoustic coating.

Method for producing an ordered array of interconnected acoustic microchannels

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&#xb0; is covered; and after having carried out a rotation of the filamentary material deposition system.

Method for in situ additive manufacturing of a coating on a turbomachine casing

A manufacturing method of an abradable coating consisting of depositing, on a substrate surface a filament of a thermosetting material while providing both a relative displacement between the substrate and the filament along a predetermined deposition path and solidification of the filament in order to create a three-dimensional scaffold of filaments, consisting of superimposed layers of which the filaments of a given layer are not contiguous and can be oriented differently from those of an adjacent layer, so as to confer upon it acoustic wave absorption properties, the thermosetting material being a thixotropic mixture free of solvent and consisting of a polymer base and a cross-linking agent in a weight ratio of a polymer base to a cross-linking agent comprised between 1:1 and 2:1, and of a flowing component, typically a petroleum jelly present between 5 and 15% by weight of the total weight of the thixotropic mixture.

Method for manufacturing an ordered network of acoustic channels made of abradable material

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.

Acoustic treatment panel for a turbojet engine

An acoustic attenuation panel for a propulsion unit including a nacelle and a turbojet engine includes a cellular core disposed between an inner skin and an outer skin, called acoustic skin, the acoustic skin including a plurality of acoustic apertures, the acoustic apertures being inclined, at a non-zero inclination angle (&#x3b2;) relative to the direction normal to the acoustic skin, upstream with respect to the flow direction of the air or gas flow to which the panel is intended to be subjected under normal operating conditions, that is to say upstream of the propulsion unit when the panel is mounted in such a unit.

Acoustic attenuation panel for an aircraft propulsion unit and propulsion unit including such a panel

An assembly for the rear of a bypass turbomachine () comprises a primary nozzle () comprising a trailing edge defining a primary flow path portion and a secondary nozzle () defining a secondary flow path portion, defined about a longitudinal axis (X), said secondary nozzle being configured to eject a mixture of the flows coming from a secondary flow path (Vs) and from a primary flow path (Vp) of the turbomachine (), the secondary nozzle being of convergent-divergent shape with a throat () corresponding to a minimum cross section of the nozzle (), the secondary nozzle () comprising, at the throat (), a periodic succession of lobes () which are situated along the internal circumference of the secondary nozzle (). The assembly also comprises a lobed mixer () at the downstream end of the primary nozzle (), this having an alternation of hot lobes () extending inside the secondary flow path and of cold lobes () extending inside the primary flow path. The lobes of the nozzle () which are concave (), which is to say radially towards the outside, and respectively which are convex (), which is to say radically towards the inside, if the longitudinal offset is disregarded, radically face the respectively hot lobes () and cold lobes () of the mixer ().

Modified acoustic secondary nozzle

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.

Panel for heat exchange and improved noise reduction for a turbomachine

A property gradient coating to be applied by additive manufacture to an inner wall of a casing mounted on the periphery of moving blades of a turbomachine rotor, the coating including in superimposed layers from an outer surface of the coating to this inner wall of the casing, on the one hand, a first layer consisting of a three-dimensional scaffolding of filaments of an abradable material forming an ordered network of channels or microchannels whose pore sizes are between 50 and 250 microns and whose porosity is greater than 85%, and, on the other hand, a second layer having a function of dissipating energy from acoustic waves striking the outer surface of the coating and consisting of a three-dimensional scaffolding of filaments of a first thermosetting material forming an ordered network of channels or microchannels whose pore sizes are between 50 and 400 microns and whose porosity is greater than 60%.

Coating with property gradient for inner wall of turbomachine

A supply duct of a compressor of a turbine engine, formed from internal and external walls of revolution around an axis and opposite one another to define a circulation stream of a fluid, is provided. The stream allows the fluid to be routed from the inlet of the duct to the inlet of the compressor. The radius of the external wall at the inlet of the duct is greater than the radius of the duct at the inlet of the compressor. The duct includes a portion for which the radius of the external wall along the portion is less than the radius of the external wall at the inlet of the compressor, and the radius of the internal wall along the portion of the duct is less than the radius of the internal wall at the inlet of the compressor.

Supply duct of a compressor of a turbine engine

An aircraft including a wing and an aeroengine having a longitudinal main axis and including a ducted nacelle with at least one fan is disclosed. The wing includes an acoustic treatment surface on a bottom portion of its outer shell on either side of the longitudinal main axis and over a width perpendicular to the longitudinal main axis that is not greater than three times the diameter of the fan. The acoustic treatment surface includes a layer of porous material for attenuating acoustic waves coming from the fan.

Aircraft including a wing with improved acoustic treatment

A ring of vanes for an aircraft turbine engine, the ring presenting an axial direction and a radial direction and including a first annular sheath presenting an inside surface and a second annular sheath presenting an inside surface facing the first inside surface of the first annular sheath, the first and second sheaths being coaxial and defining between them a flow passage for a gas stream. The ring further includes both partially annular acoustic treatment panels including resonant cavities and also vanes extending in the radial direction between the first and second sheaths. Each vane includes a radial airfoil with at least two attachment tabs at each radial end of the airfoil fastened to the first or second sheath, and the inside surface of at least one of the first and second annular sheaths and the corresponding attachment tabs are covered by acoustic treatment panels arranged between the airfoils.

Ring of turbojet vanes including an acoustic treatment structure

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.

Turbomachine vane comprising an electroacoustic source with improved assembly mode, row of outlet guide vanes and turbomachine comprising such a vane

An acoustic absorber cell () for mounting on a turbojet wall in contact with a fluid flow, the cell () having a resonant cavity () presenting a wall () having at least one orifice () associated with a neck () having a tube () extending inside the resonant cavity () and projecting from the wall (). The neck () also having a tubular ring () coaxial with the tube () and movable relative to the tube (), and the cell () includes electromagnetic actuator () for moving the ring () along the tube (), and controller () for controlling the electromagnetic actuator () and configured to control movement of the ring () along the tube () 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 ().

Acoustic absorber cell for a turbojet, and an associated acoustic treatment panel

Growing community of inventors

Nogent-Sur-Marne, France

Jacky Novi Mardjono