Patents by Inventor Jacky Novi MARDJONO
Jacky Novi MARDJONO has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20230419937Abstract: An acoustic treatment coating includes a metamaterial, wherein the metamaterial includes a solid structure including at least one free space forming a folded cavity and at least one porous material placed in the free space of the solid structure.Type: ApplicationFiled: November 9, 2021Publication date: December 28, 2023Inventors: Jean BOULVERT, Théo CAVALIERI, Jean-Philippe GROBY, Annie ROSS, Edith FOTSING ROLAND, Jacky Novi MARDJONO, Vicente ROMERO GARCIA, Gwénaël GABARD, Josué COSTA BAPTISTA
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Patent number: 11667084Abstract: 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 ? 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.Type: GrantFiled: December 6, 2018Date of Patent: June 6, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jacky Novi Mardjono, Arnaud Dubourg, Edith-Roland Fotsing, Annie Ross
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Patent number: 11554534Abstract: 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.Type: GrantFiled: December 6, 2018Date of Patent: January 17, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Norman Bruno Andre Jodet, Jeremy Paul Francisco Gonzalez, Jacky Novi Mardjono, Arnaud Dubourg, Edith-Roland Fotsing, Annie Ross, Daniel Therriault
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Patent number: 11478981Abstract: 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.Type: GrantFiled: December 6, 2018Date of Patent: October 25, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jacky Novi Mardjono, Arnaud Dubourg, Edith-Roland Fotsing, Annie Ross
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Patent number: 11434826Abstract: 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.Type: GrantFiled: September 9, 2019Date of Patent: September 6, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Georges Jean Xavier Riou, Jeremy Paul Francisco Gonzalez, Jacky Novi Mardjono
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Publication number: 20220186667Abstract: 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.Type: ApplicationFiled: April 23, 2020Publication date: June 16, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Georges Jean Xavier RIOU, Jacky Novi MARDJONO, Renaud Yannick Fabien DAON, Nicolas Pierre Alain Edme DE CACQUERAY-VALMENIER
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Publication number: 20220049657Abstract: 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.Type: ApplicationFiled: September 9, 2019Publication date: February 17, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Georges Jean Xavier RIOU, Jeremy Paul Francisco GONZALEZ, Jacky Novi MARDJONO
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Patent number: 11149685Abstract: An assembly for the rear of a bypass turbomachine (10) comprises a primary nozzle (11) comprising a trailing edge defining a primary flow path portion and a secondary nozzle (110) 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 (10), the secondary nozzle being of convergent-divergent shape with a throat (112) corresponding to a minimum cross section of the nozzle (110), the secondary nozzle (110) comprising, at the throat (112), a periodic succession of lobes (116, 118) which are situated along the internal circumference of the secondary nozzle (110). The assembly also comprises a lobed mixer (130) at the downstream end of the primary nozzle (11), this having an alternation of hot lobes (134) extending inside the secondary flow path and of cold lobes (132) extending inside the primary flow path.Type: GrantFiled: August 21, 2018Date of Patent: October 19, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jérémy Paul Francisco Gonzalez, Guillaume Bodard, Norman Bruno André Jodet, Jacky Novi Mardjono
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Patent number: 11143462Abstract: 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.Type: GrantFiled: October 23, 2015Date of Patent: October 12, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Bellal Waissi, Sébastien Chalaud, Lancelot Guillou, Jacky Novi Mardjono, Guillaume Mathon-Margueritte, Georges Jean Xavier Riou, Claude Sensiau
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Patent number: 11111808Abstract: 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%.Type: GrantFiled: December 6, 2018Date of Patent: September 7, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jacky Novi Mardjono, Arnaud Dubourg, Edith-Roland Fotsing, Annie Ross
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Patent number: 11047303Abstract: 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.Type: GrantFiled: July 23, 2018Date of Patent: June 29, 2021Assignee: Safran Aircraft EnginesInventors: Jacky Novi Mardjono, Norman Bruno André Jodet
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Publication number: 20210140319Abstract: 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.Type: ApplicationFiled: August 21, 2018Publication date: May 13, 2021Applicants: SAFRAN AIRCRAFT ENGINES, INSTITUTUL NATIONAL DE CERCETARE-DEZ-VOLTARE TURBOMOTOARE - COMOTIInventors: Jacky Novi MARDJONO, Norman Bruno André JODET, Radu MIHALACHE, Romulus PETCU, Valentin SILIVESTRU, Cristian Mihail STANICA, Lucia Raluca VOICU
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Patent number: 10894594Abstract: 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.Type: GrantFiled: March 28, 2017Date of Patent: January 19, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Norman Bruno Andre Jodet, Jean-Michel Boiteux, Jacky Novi Mardjono
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Publication number: 20200386113Abstract: 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%.Type: ApplicationFiled: December 6, 2018Publication date: December 10, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jacky Novi MARDJONO, Arnaud DUBOURG, Edith-Roland FOTSING, Annie ROSS
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Publication number: 20200384695Abstract: 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 ? 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.Type: ApplicationFiled: December 6, 2018Publication date: December 10, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jacky Novi MARDJONO, Amaud DUBOURG, Edith-Roland FOTSING, Annie ROSS
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Publication number: 20200376743Abstract: 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.Type: ApplicationFiled: December 6, 2018Publication date: December 3, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Norman Bruno Andre JODET, Jeremy Paul Francisco GONZALEZ, Jacky Novi MARDJONO, Arnaud DUBOURG, Edith-Roland FOTSING, Annie ROSS, Daniel THERRIAULT
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Publication number: 20200353673Abstract: 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.Type: ApplicationFiled: December 6, 2018Publication date: November 12, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jacky Novi MARDJONO, Arnaud DUBOURG, Edith-Roland FOTSING, Annie ROSS
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Patent number: 10723476Abstract: 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.Type: GrantFiled: November 9, 2018Date of Patent: July 28, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Cedric Zaccardi, Christophe Marcel Lucien Perdrigeon, Francois Marie Paul Marlin, Thierry Georges Paul Papin, Jacky Novi Mardjono
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Publication number: 20200173396Abstract: An assembly for the rear of a bypass turbomachine (10) comprises a primary nozzle (11) comprising a trailing edge defining a primary flow path portion and a secondary nozzle (110) 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 (10), the secondary nozzle being of convergent-divergent shape with a throat (112) corresponding to a minimum cross section of the nozzle (110), the secondary nozzle (110) comprising, at the throat (112), a periodic succession of lobes (116, 118) which are situated along the internal circumference of the secondary nozzle (110). The assembly also comprises a lobed mixer (130) at the downstream end of the primary nozzle (11), this having an alternation of hot lobes (134) extending inside the secondary flow path and of cold lobes (132) extending inside the primary flow path.Type: ApplicationFiled: August 21, 2018Publication date: June 4, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jérémy Paul Francisco GONZALEZ, Guillaume BODARD, Norman Bruno Andre JODET, Jacky Novi MARDJONO
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Patent number: 10662876Abstract: 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.Type: GrantFiled: July 2, 2018Date of Patent: May 26, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Georges Jean Xavier Riou, Jacky Novi Mardjono, Norman Bruno Andre Jodet, Jeremy Paul Francisco Gonzalez