Patents by Inventor Nils BORDONI
Nils BORDONI 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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Patent number: 11047252Abstract: Aircraft turbine engine comprising a low-pressure spool that comprises a low-pressure shaft (24), means (44) for taking off power from said low-pressure shaft, and a fan (28) that is driven by said low-pressure shaft by means of a reduction gear (32), said reduction gear comprising at least one first element (50) that is connected to said low-pressure shaft for conjoint rotation, at least one second element (56) that is connected to said fan for conjoint rotation, and at least one third element (52) that is connected to a stator casing of the turbine engine, characterised in that said at least one third element is connected to said stator casing by disengageable connection means (60), and comprising at least one member that can move from a first position in which said at least one third element is fixedly connected to said stator casing into a second position in which said at least one third element is separated from said stator casing and is free to rotate about said longitudinal axis.Type: GrantFiled: March 22, 2016Date of Patent: June 29, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nils Bordoni, Guillaume Patrice Kubiak, Kevin Morgane Lemarchand
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Patent number: 10760486Abstract: The invention relates to an aviation turbine engine fan module including a de-icing system (10) for de-icing an inlet cone (1) and comprising a sheath (30) placed inside an inside space defined upstream by the inlet cone, said sheath comprising a first duct (38) having at least one hot air admission orifice (42), said first duct being configured to convey hot air from a bearing enclosure (22) of the engine towards a wall of the inlet cone in order to heat it from the inside, the sheath further comprising a second duct (40) having at least one outlet situated downstream from the admission orifice of the first duct, said second duct being configured to discharge air from the first duct towards the downstream end of the engine. The invention also provides a method of de-icing a turbine engine inlet cone.Type: GrantFiled: March 31, 2016Date of Patent: September 1, 2020Assignee: Safran Aircraft EnginesInventors: Kevin Morgane Lemarchand, Nils Bordoni, Guillaume Kubiak
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Patent number: 10598039Abstract: A device for adjusting the pitch of at least one annular row of stator vanes for a turbine engine module. The device includes a first control ring mounted to rotate freely about an axis of the turbine engine. The device also includes connecting rods for connecting the first control ring to the vanes and a second control ring mounted to rotate freely about the axis. Each vane of the at least one row is simultaneously connected to the first and second control rings by a set of at least two connecting rods. The device is suitable for use as part of a module and is suitable for use in a turbine engine.Type: GrantFiled: February 9, 2016Date of Patent: March 24, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventor: Nils Bordoni
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Patent number: 10145253Abstract: A stator vane for a turbine machine includes a set of vane parts arranged relative to each other to define air flow stream paths between vane parts, and a mechanism circulating a fluid to be cooled by the air flow.Type: GrantFiled: April 4, 2013Date of Patent: December 4, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventor: Nils Bordoni
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Publication number: 20180334907Abstract: The invention relates to an assembly including a one-piece bladed disk (1), at least one low-pressure compressor rotor (2) and a low-pressure compressor shaft, characterized in that the bladed disk and the low-pressure compressor rotor (2) are both adapted to be shrunk onto the low-pressure compressor shaft and mechanically attached to it by sets of splines. At least one clamping member (16) blocks axially the different collars with respect to the shaft.Type: ApplicationFiled: May 21, 2018Publication date: November 22, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Mathieu PERRIER, Louis LAURENT, Nils BORDONI, Romain EDOUARD, Gilles Alain Marie CHARIER
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Publication number: 20180128173Abstract: The invention relates to an aviation turbine engine fan module including a de-icing system (10) for de-icing an inlet cone (1) and comprising a sheath (30) placed inside an inside space defined upstream by the inlet cone, said sheath comprising a first duct (38) having at least one hot air admission orifice (42), said first duct being configured to convey hot air from a bearing enclosure (22) of the engine towards a wall of the inlet cone in order to heat it from the inside, the sheath further comprising a second duct (40) having at least one outlet situated downstream from the admission orifice of the first duct, said second duct being configured to discharge air from the first duct towards the downstream end of the engine. The invention also provides a method of de-icing a turbine engine inlet cone.Type: ApplicationFiled: March 31, 2016Publication date: May 10, 2018Applicant: Safran Aircraft EnginesInventors: Kevin Morgane LEMARCHAND, Nils BORDONI, Guillaume KUBIAK
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Publication number: 20180073384Abstract: Aircraft turbine engine comprising a low-pressure spool that comprises a low-pressure shaft (24), means (44) for taking off power from said low-pressure shaft, and a fan (28) that is driven by said low-pressure shaft by means of a reduction gear (32), said reduction gear comprising at least one first element (50) that is connected to said low-pressure shaft for conjoint rotation, at least one second element (56) that is connected to said fan for conjoint rotation, and at least one third element (52) that is connected to a stator casing of the turbine engine, characterised in that said at least one third element is connected to said stator casing by disengageable connection means (60), and comprising at least one member that can move from a first position in which said at least one third element is fixedly connected to said stator casing into a second position in which said at least one third element is separated from said stator casing and is free to rotate about said longitudinal axis.Type: ApplicationFiled: March 22, 2016Publication date: March 15, 2018Inventors: Nils BORDONI, Guillaume Patrice KUBIAK, Kevin Morgane LEMARCHAND
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Patent number: 9885291Abstract: A bypass turbine engine including: an inner casing, an inter-duct casing, and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing; a rotary shaft including a movable fan including radial blades of which free ends face the outer casing of the turbine engine to compress an air flow in the secondary duct; a plurality of variable-pitch radial stator vanes mounted upstream of the movable fan so as to deflect the incident axial air prior to it being axially rectified by the movable fan in the secondary duct; and a system for individually regulating the pitch of the variable-pitch radial vanes if heterogeneity of the air flow in the secondary duct is detected, is provided.Type: GrantFiled: February 19, 2015Date of Patent: February 6, 2018Assignee: SNECMAInventors: Jean-Loic Herve Lecordix, Nils Bordoni
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Publication number: 20180030849Abstract: A device for adjusting the pitch of at least one annular row of stator vanes for a turbine engine module. The device includes a first control ring mounted to rotate freely about an axis of the turbine engine. The device also includes connecting rods for connecting the first control ring to the vanes and a second control ring mounted to rotate freely about the axis. Each vane of the at least one row is simultaneously connected to the first and second control rings by a set of at least two connecting rods. The device is suitable for use as part of a module and is suitable for use in a turbine engine.Type: ApplicationFiled: February 9, 2016Publication date: February 1, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventor: Nils Bordoni
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Patent number: 9879561Abstract: A bypass turbine engine including: an inner casing, an inter-duct casing and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing; a rotary shaft including, at an upstream end, a movable fan with radial blades of which the free ends face the outer casing to compress an air flow at least in the secondary duct; a plurality of variable-pitch radial stator vanes mounted upstream of the movable fan so as to deflect the incident axial air prior to it being axially rectified by the movable fan in the secondary duct; and a system for individually adjusting the pitch of the radial vanes including a single control ring and rods for connecting the control ring to each of said radial vanes, is provided.Type: GrantFiled: February 19, 2015Date of Patent: January 30, 2018Assignee: SNECMAInventors: Jean-Loic Herve Lecordix, Nils Bordoni, Guillaume Patrice Kubiak
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Publication number: 20160069275Abstract: Bypass turbine engine, in particular for an aircraft, in which air flows circulate from upstream to downstream, the turbine engine extending axially and comprising: an inner casing, an inter-duct casing and an outer casing (13) so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing (13), a rotary shaft comprising, at the upstream end, a movable fan comprising radial blades of which the free ends face the outer casing (13) of the turbine engine so as to compress an air flow at least in the secondary duct, a plurality of variable-pitch radial stator vanes (5) mounted upstream of the movable fan so as to deflect the incident axial air prior to it being axially rectified by the movable fan in the secondary duct, means for individually regulating the pitch of the variable-pitch radial vanes (5) if heterogeneity of the air flow in the secondary duct is detected.Type: ApplicationFiled: February 19, 2015Publication date: March 10, 2016Applicant: SNECMAInventors: Jean-Loic Herve LECORDIX, Nils Bordoni
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Publication number: 20160069205Abstract: Bypass turbine engine, in particular for an aircraft, in which air flows circulate from upstream to downstream, the turbine engine extending axially and comprising: an inner casing, an inter-duct casing and an outer casing (13) so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing (13), a rotary shaft comprising, at the upstream end, a movable fan comprising radial blades of which the free ends face the outer casing (13) of the turbine engine so as to compress an air flow at least in the secondary duct, and a plurality of variable-pitch radial stator vanes (5) mounted upstream of the movable fan so as to deflect the incident axial air prior to it being axially rectified by the movable fan in the secondary duct, and means for individually adjusting the pitch of the radial vanes (5), which comprise a single control ring and rods (25, 30) for connecting said control ring (24) to each of said radial vanes (5).Type: ApplicationFiled: February 19, 2015Publication date: March 10, 2016Applicant: SNECMAInventors: Jean-Loic Herve LECORDIX, Nils BORDONI, Guillaume Patrice KUBIAK
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Publication number: 20150315923Abstract: A stator vane for a turbine machine includes a set of vane parts arranged relative to each other to define air flow stream paths between vane parts, and a mechanism circulating a fluid to be cooled by the air flow.Type: ApplicationFiled: April 4, 2013Publication date: November 5, 2015Applicant: SNECMAInventor: Nils BORDONI