Patents by Inventor Kamel Benderradji
Kamel Benderradji 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: 20230407749Abstract: A turbine engine assembly including a first rotor element and a second rotor element extending around a longitudinal axis X and coupled to one another by a gear coupling, the first rotor element including teeth and the second rotor element including complementary teeth which extend along the longitudinal axis and form the gear coupling. The first and second rotor elements each include a first and a second radial flange which are annular and arranged facing one another, and the assembly includes a sealing device configured to ensure that the gear coupling is sealed at the first and second flanges.Type: ApplicationFiled: November 17, 2021Publication date: December 21, 2023Inventors: Kamel BENDERRADJI, Delphine Hermance Maxime PARENT, Pauline Anne FRECHE, Joel Robert MATHIEU, Laurent JABLONSKI
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Patent number: 11686205Abstract: An angular sector of a fixed blade ring of a turbomachine, in particular a stator or a guide vane assembly, includes, relative to the axis of said fixed blade ring, a radially outer platform, a radially inner platform, at least two blades extending between said platforms, and at least one block of abradable honeycomb material extending on the inside of the inner platform between transverse ends of the sector. The block of abradable material includes at least one transverse end wall shaped according to a toothed profile having at least one radially oriented tooth extending across an entire radial thickness of said block.Type: GrantFiled: May 22, 2019Date of Patent: June 27, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thomas Nolwenn Emmanuel Delahaye, Kamel Benderradji, Alain Marc Lucien Bromann, Liliana Gomes Pereira, Delphine Hermance Maxime Parent
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Patent number: 11371352Abstract: A holding device is used with a centripetal air sampling member of a rotor assembly that includes and downstream rotor discs and a centripetal air sampling member. The holding device has an annular support element with a housing configured to receive the air sampling member in a radial orientation, a first lateral extension, and a second lateral extension rigidly attached to the downstream rotor disc, extending substantially following the longitudinal axis and radially arranged externally with respect to the first extension. The holding device also includes a wedging ring axially arranged between a portion of the downstream rotor disc and the support element, the wedging ring being configured to simultaneously urge, under the action of a centrifugal force, the first extension in radial abutment against the second extension and the support element in radial abutment against a portion of the upstream rotor disc.Type: GrantFiled: November 13, 2018Date of Patent: June 28, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thomas Nolwenn Emmanuel Delahaye, Alain Marc Lucien Bromann, Liliana Gomes Pereira, Delphine Hermance Maxime Parent, Kamel Benderradji
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Patent number: 11149571Abstract: A ring for guiding variable-pitch blades and supporting an abradable coating for an aircraft turbomachine ring extends about an axis (X) and includes substantially radial orifices for mounting guiding sleeves intended each to receive a pivot of one of the blades. The ring may include a radially inner crown divided into sectors and supports the abradable coating. A radially outer annular ferrule may be divided into sectors and include the orifices for mounting the sleeves. In some embodiments, each ferrule sector is mounted about a crown sector by a circumferential sliding connection. The crown sector may include an immobilizer for rotationally immobilizing the sleeves of this ferrule sector about the axis.Type: GrantFiled: August 15, 2019Date of Patent: October 19, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thomas Nolwenn Emmanuel Delahaye, Kamel Benderradji, Delphine Hermanee Maxime Parent, Sandrine Hélène Quevreux
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Publication number: 20210207488Abstract: An angular sector of a fixed blade ring of a turbomachine, in particular a stator or a guide vane assembly, includes, relative to the axis of said fixed blade ring, a radially outer platform, a radially inner platform, at least two blades extending between said platforms, and at least one block of abradable honeycomb material extending on the inside of the inner platform between transverse ends of the sector. The block of abradable material includes at least one transverse end wall shaped according to a toothed profile having at least one radially oriented tooth extending across an entire radial thickness of said block.Type: ApplicationFiled: May 22, 2019Publication date: July 8, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Thomas Nolwenn Emmanuel Delahaye, Kamel Benderradji, Alain Marc Lucien Bromann, Liliana Gomes Pereira, Delphine Hermance Maxime Parent
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Patent number: 10927699Abstract: Variable-pitch blade control ring (44) for a turbine engine, including an annular body (42) configured to be mounted so as to be rotatable about an annular casing (16) of the turbine engine. The body links to levers (34) for connecting to the vanes. The ring has a mechanism for guiding in an axial and/or helical direction, supported by the body. The mechanism includes at least one substantially radial finger (60, 62) for axial abutment on at least one first surface (72, 74) of the casing and for sliding on the surface.Type: GrantFiled: June 27, 2016Date of Patent: February 23, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alain Marc Lucien Bromann, Kamel Benderradji, Lilian Yann Dumas, Blaise Bergon, Suzanne Madeleine Coustillas
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Publication number: 20200263549Abstract: A holding device is disclosed for a centripetal air sampling member of a rotor assembly that includes and downstream rotor discs and a centripetal air sampling member. The holding device has an annular support element with a housing configured to receive the air sampling member in a radial orientation, a first lateral extension, and a second lateral extension rigidly attached to the downstream rotor disc, extending substantially following the longitudinal axis and radially arranged externally with respect to the first extension. The holding device also includes a wedging ring axially arranged between a portion of the downstream rotor disc and the support element, the wedging ring being configured to simultaneously urge, under the action of a centrifugal force, the first extension in radial abutment against the second extension and the support element in radial abutment against a portion of the upstream rotor disc.Type: ApplicationFiled: November 13, 2018Publication date: August 20, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Thomas Nolwenn Emmanuel Delahaye, Alain Marc Lucien Bromann, Liliana Gomes Pereira, Delphine Hermance Maxime Parent, Kamel Benderradji
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Patent number: 10648359Abstract: The invention relates to a system for controlling variable-setting blades (14) for a turbine engine, which includes at least one control ring (36) mounted rotatably mobile about an annular casing (16) with axis of revolution A, at least one annular row of variable-setting blades (14) extending substantially radially relative to said axis A and connected to said at least one control ring so that a rotation of the ring about the casing rotates the blades about substantially radial axes B, and means (40) for actuating said at least one ring in order to rotate same about the casing, characterised in that said actuation means are connected to said at least one ring by linking means comprising a shaft (52) extending along an axis C which is substantially radial relative to said axis A and mounted rotatably mobile about said axis C on the housing.Type: GrantFiled: June 14, 2016Date of Patent: May 12, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alain Marc Lucien Bromann, Kamel Benderradji, Lilian Yann Dumas, Pamela Dominique Daniele Reichert
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Publication number: 20200056494Abstract: A ring for guiding variable-pitch blades and supporting an abradable coating for an aircraft turbomachine ring extends about an axis (X) and includes substantially radial orifices for mounting guiding sleeves intended each to receive a pivot of one of the blades. The ring may include a radially inner crown divided into sectors and supports the abradable coating. A radially outer annular ferrule may be divided into sectors and include the orifices for mounting the sleeves. In some embodiments, each ferrule sector is mounted about a crown sector by a circumferential sliding connection. The crown sector may include an immobilizer for rotationally immobilizing the sleeves of this ferrule sector about the axis.Type: ApplicationFiled: August 15, 2019Publication date: February 20, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Thomas Nolwenn Emmanuel Delahaye, Kamel Benderradji, Delphine Hermance Maxime Parent, Sandrine Hélène Quevreux
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Patent number: 10502087Abstract: An assembly for controlling variable pitch vanes in a turbine engine, the assembly comprising an actuating ring surrounding a casing of the turbine engine and connected by rods to variable pitch vanes. The actuating ring is configured to rotate around the casing. The assembly further includes a passive element including a first end sliding connected to a second end. The first end is connected by a sliding pivoting link on the actuating ring, and the second end is connected by a ball-joint link to the casing.Type: GrantFiled: July 10, 2017Date of Patent: December 10, 2019Assignee: Safran Aircraft EnginesInventors: Kamel Benderradji, Blaise Bergon, Alain Marc Lucien Bromann, Suzanne Madeleine Coustillas, Lilian Yann Dumas
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Patent number: 10385721Abstract: The invention relates to a system for controlling variable pitch blades for a turbine engine, comprising an annular row of variable pitch blades extending about an axis (A) and each comprising a blade connected at the radially outer end thereof to a pivot (20) that defines a substantially radial axis of rotation of the blade and which is connected by a lever (34) to control means (40a, 40b) extending about said axis. The invention is characterized in that said control means include first links (40a) supported by said pivots and second links (40b) extending between said first links, said first and second links extending substantially along a same circumference of said axis and being connected to one another and to actuation means (56).Type: GrantFiled: January 13, 2016Date of Patent: August 20, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Lilian Yann Dumas, Kamel Benderradji, Alain Marc Lucien Bromann, Suzanne Madeleine Coustillas
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Patent number: 10330021Abstract: A system for controlling variable-pitch vanes for a turbine engine, including a control ring having an axis of revolution and, about the axis of revolution, an annular row of connecting rods for connecting the ring to the vanes, each connecting rod including a first end designed so as to be connected to one of the vanes, and a second end which is connected to an elongate shaft which is connected to s the ring. The shaft connected to each connecting rod has an axis of elongation which is inclined relative to a plane extending substantially through the axis of revolution and the connecting rod.Type: GrantFiled: October 7, 2015Date of Patent: June 25, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Kamel Benderradji, Alain Marc Lucien Bromann, Lilian Yann Dumas, Pamela Dominique Daniele Reichert
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Publication number: 20180371939Abstract: Variable-pitch blade control ring (44) for a turbine engine, comprising an annular body (42) configured to be mounted so as to be rotatable about an annular casing (16) of the turbine engine, said body comprising means (46) for linking to levers (34) for connecting to said vanes, characterised in that said ring further comprises first means (60, 62, 64) for guiding in an axial and/or helical direction, which means are supported by said body and comprise at least one substantially radial finger (60, 62) comprising means (62) for axial abutment on at least one first surface (72, 74) of said casing and for sliding on said surface.Type: ApplicationFiled: June 27, 2016Publication date: December 27, 2018Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN AIRCRAFT ENGINESInventors: Alain Marc Lucien BROMANN, Kamel BENDERRADJI, Lilian Yann DUMAS, Blaise BERGON, Suzanne Madeleine COUSTILLAS
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Patent number: 10100842Abstract: A cover of a centrifugal compressor intended to be rigidly connected to a turbomachine housing, which includes a plurality of ports, is provided. The cover further includes a fastening device for fastening the cover to the housing. A portion of the fastening device is located upstream relative to the ports and can be accessed by a fastening tool through at least one of the ports of the cover. A turbomachine uses this cover to form a sealed space, in particular with a view to collecting air.Type: GrantFiled: July 17, 2014Date of Patent: October 16, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alain Marc Lucien Bromann, Kamel Benderradji, Pamela Dominique Daniele Reichert
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Patent number: 10066509Abstract: The invention primarily relates to a turbomachine part (10) comprising a first upstream casing (2) and a second downstream casing (3), assembled to one another using at least one flange (6) formed by an upstream flange part (4) of the first upstream casing (2) and a downstream flange part (5) of the second downstream casing (3), the first upstream casing (2) and the second downstream casing (3) together at least partially delimiting the contour of an enclosure (30) in which at least one fluid (C) to be evacuated is contained, characterized in that it comprises a drainage device (1) comprising at least one drainage orifice (7a, 7b) formed on the flange (6) connecting the first upstream casing (2) and second downstream casing (3), in particular on the upstream flange part (4) of the flange (6), allowing the discharge of said at least one fluid (C) outside the enclosure (30).Type: GrantFiled: March 31, 2015Date of Patent: September 4, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: Pamela Dominique Danièle Reichert, Alain Marc Lucien Bromann, Kamel Benderradji, Alexandre Pierre François Leon
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Publication number: 20180223685Abstract: The invention relates to a system for controlling variable-setting blades (14) for a turbine engine, which includes at least one control ring (36) mounted rotatably mobile about an annular casing (16) with axis of revolution A, at least one annular row of variable-setting blades (14) extending substantially radially relative to said axis A and connected to said at least one control ring so that a rotation of the ring about the casing rotates the blades about substantially radial axes B, and means (40) for actuating said at least one ring in order to rotate same about the casing, characterised in that said actuation means are connected to said at least one ring by linking means comprising a shaft (52) extending along an axis C which is substantially radial relative to said axis A and mounted rotatably mobile about said axis C on the housing.Type: ApplicationFiled: June 14, 2016Publication date: August 9, 2018Inventors: Alain Marc Lucien BROMANN, Kamel BENDERRADJI, Lilian Yann DUMAS, Pamela Dominique Daniele REICHERT
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Publication number: 20180016931Abstract: An assembly, in particular for controlling variable pitch vanes in a turbine engine, comprising an actuating ring surrounding a casing of the turbine engine and connected by rods to variable pitch vanes, in addition to a driving means for rotating the actuating ring around the casing. The assembly includes a slidingly connected passive element, one end of which is connected by a sliding pivoting link on the actuating ring and a second end is connected by a ball-joint link to the casing.Type: ApplicationFiled: July 10, 2017Publication date: January 18, 2018Applicant: Safran Aircraft EnginesInventors: Kamel Benderradji, Blaise Bergan, Alain Marc Lucien Bromann, Suzanne Madeleine Coustillas, Lilian Yann Dumas
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Publication number: 20180010478Abstract: The invention relates to a system for controlling variable pitch blades for a turbine engine, comprising an annular row of variable pitch blades extending about an axis (A) and each comprising a blade connected at the radially outer end thereof to a pivot (20) that defines a substantially radial axis of rotation of the blade and which is connected by a lever (34) to control means (40a, 40b) extending about said axis. The invention is characterized in that said control means include first links (40a) supported by said pivots and second links (40b) extending between said first links, said first and second links extending substantially along a same circumference of said axis and being connected to one another and to actuation means (56).Type: ApplicationFiled: January 13, 2016Publication date: January 11, 2018Inventors: Lilian Yann DUMAS, Kamel BENDERRADJI, Alain Marc, Lucien BROMANN, Suzanne Madeleine COUSTILLAS
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Publication number: 20160195099Abstract: A cover of a centrifugal compressor intended to be rigidly connected to a turbomachine housing, which includes a plurality of ports, is provided. The cover further includes a fastening device for fastening the cover to the housing. A portion of the fastening device is located upstream relative to the ports and can be accessed by a fastening tool through at least one of the ports of the cover. A turbomachine uses this cover to form a sealed space, in particular with a view to collecting air.Type: ApplicationFiled: July 17, 2014Publication date: July 7, 2016Applicant: SNECMAInventors: Alain Marc, Lucien BROMANN, Kamel BENDERRADJI, Pamela Dominique, Daniele REICHERT
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Publication number: 20160115875Abstract: A system for controlling variable-pitch vanes for a turbine engine, including a control ring having an axis of revolution and, about the axis of revolution, an annular row of connecting rods for connecting the ring to the vanes, each connecting rod including a first end designed so as to be connected to one of the vanes, and a second end which is connected to an elongate shaft which is connected to said the ring. The shaft connected to each connecting rod has an axis of elongation which is inclined relative to a plane extending substantially through the axis of revolution and the connecting rod.Type: ApplicationFiled: October 7, 2015Publication date: April 28, 2016Applicant: SNECMAInventors: Kamel BENDERRADJI, Alain Marc Lucien BROMANN, Lilian Yann DUMAS, Pamela Dominique Daniele REICHERT