Patents by Inventor Dominik Igel
Dominik Igel 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: 11274676Abstract: A ducted fan module with variable-pitch blades for a turbo engine includes a rotor carrying a plurality of blades, a stationary casing, and a blade pitch changing and control system. The rotor includes a central shaft and a surrounding blade support ring. A front end of the blade support ring is connected to a front end of the central shaft, creating a rearward-opening annular space between the blade support ring and the central shaft. A tubular part is connected to the stationary casing and extends into the annular space.Type: GrantFiled: December 22, 2016Date of Patent: March 15, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Serge René Morreale, Yanis Benslama, Jérémy Dievart, Dominik Igel
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Patent number: 11162506Abstract: The invention relates to a fan module having variable-pitch blades for a turbine engine, including a rotor (2) having blades (3), a stationary casing (7), and a system for adjusting and controlling the pitch of the blades (3), the rotor (2) including a central shaft (6) and a ring (9) for supporting the blades surrounding the shaft, a front end of the ring being connected to a front end of the shaft so as to define an annular space between the ring and the shaft which is open towards the rear, said annular space of the rotor (2) housing said system, and the shaft (6) being guided by a first bearing (8) mounted in the stationary casing (7), to the rear of the ring (9), characterised in that the ring (9) is guided by at least one complementary bearing (31) located upstream of the first bearing (8).Type: GrantFiled: December 22, 2016Date of Patent: November 2, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Serge Rene Morreale, Yanis Benslama, Jeremy Dievart, Dominik Igel
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Patent number: 11124287Abstract: The invention relates to a fan module with variable-pitch blades for a turbomachine, comprising a rotor (2) carrying blades (3), a stationary housing (7), a mechanism (11, 12, 13, 14, 20) for regulating the pitch of the blades (3), which is connected to the rotor, and a control means (16, 17) mounted on the stationary housing (7) and comprising a control part (18) that can be moved in translation according to an axis (X) of rotation of the rotor (2), and a bearing (19) for load transfer between the control part (18) and said mechanism, characterised in that it also comprises a stationary track (23) supporting the elastic restoring means (26, 27) which are arranged so as to exert an axial restoring force on the control part (18) towards a determined position, preferably corresponding to the blade (3) feathering.Type: GrantFiled: December 22, 2016Date of Patent: September 21, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Serge Rene Morreale, Yanis Benslama, Jeremy Dievart, Dominik Igel
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Patent number: 10883422Abstract: The invention relates to a turbine engine, comprising: a device for bleeding a compressor, particularly a high-pressure compressor, comprising at least one valve for bleeding said compressor, an outlet of said valve being connected to a bleed system designed to discharge a bleed airflow; and at least one device for cooling at least one unit, comprising a heat exchanger, an air outlet of which is connected to an ejector of the jet pump type, which comprises a feed-through duct for a secondary airflow coming from said air outlet, as well as a nozzle for spraying a primary airflow inside said feed-through duct, wherein the nozzle is connected to said bleed system.Type: GrantFiled: November 24, 2015Date of Patent: January 5, 2021Assignee: SNECMAInventors: Benissa Boujida, Daniel Bernava, Dominik Igel, Maxime Aurélien Rotenberg
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Publication number: 20200369369Abstract: The invention relates to a fan module with variable-pitch blades for a turbomachine, comprising a rotor (2) carrying blades (3), a stationary housing (7), a mechanism (11, 12, 13, 14, 20) for regulating the pitch of the blades (3), which is connected to the rotor, and a control means (16, 17) mounted on the stationary housing (7) and comprising a control part (18) that can be moved in translation according to an axis (X) of rotation of the rotor (2), and a bearing (19) for load transfer between the control part (18) and said mechanism, characterised in that it also comprises a stationary track (23) supporting the elastic restoring means (26, 27) which are arranged so as to exert an axial restoring force on the control part (18) towards a determined position, preferably corresponding to the blade (3) feathering.Type: ApplicationFiled: December 22, 2016Publication date: November 26, 2020Inventors: Serge Rene MORREALE, Yanis BENSLAMA, Jeremy DIEVART, Dominik IGEL
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Publication number: 20190024672Abstract: A ducted fan module with variable-pitch blades for a turbo engine includes a rotor carrying a plurality of blades, a stationary casing and a pitch changing and control system for adjusting and controlling the setting of the blades. The rotor includes a central shaft and a blade support ring surrounding the central shaft, a front end of the ring that is connected to a front end of the central shaft, so as to create a rearward-opening annular space between the ring and the shaft. The annular space of the rotor housing the blade changing and control system and the central shaft are guided by a first bearing mounted in a stationary casing behind the ring. The fan has a tubular part connected to the stationary casing and extending into the annular space in front of the first bearing and carrying at least a first complementary bearing for guiding the shaft.Type: ApplicationFiled: December 22, 2016Publication date: January 24, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Serge René Morreale, Yanis Benslama, Jérémy Dievart, Dominik Igel
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Publication number: 20190003484Abstract: The invention relates to a fan module having variable-pitch blades for a turbine engine, including a rotor (2) having blades (3), a stationary casing (7), and a system for adjusting and controlling the pitch of the blades (3), the rotor (2) including a central shaft (6) and a ring (9) for supporting the blades surrounding the shaft, a front end of the ring being connected to a front end of the shaft so as to define an annular space between the ring and the shaft which is open towards the rear, said annular space of the rotor (2) housing said system, and the shaft (6) being guided by a first bearing (8) mounted in the stationary casing (7), to the rear of the ring (9), characterised in that the ring (9) is guided by at least one complementary bearing (31) located upstream of the first bearing (8).Type: ApplicationFiled: December 22, 2016Publication date: January 3, 2019Inventors: Serge Rene MORREALE, Yanis BENSLAMA, Jeremy DIEVART, Dominik IGEL
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Patent number: 10012110Abstract: A turbomachine assembly including first and second bodies, in which one of the bodies is rotating relative to the other body around the axis of rotation of the turbomachine, is provided. A tight zone is formed between the bodies and includes a sealing gasket. A flowing fluid, in particular lubricant oil, is able to circulate inside the first and second bodies and to be driven toward the one rotating body from the other body. The one rotating body includes a device for guiding the rotation, in the direction of rotation of the one rotating body, of the flow of fluid inside the one rotating body so as to drive the flowing fluid away from the tight zone.Type: GrantFiled: December 29, 2014Date of Patent: July 3, 2018Assignee: SNECMAInventors: Catherine Pikovsky, Dominik Igel, Boris Lemattre
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Patent number: 9982551Abstract: A system for sealing an oil chamber from an adjoining exterior volume, and a turbo-machine including a sealing system. The system for sealing the oil chamber from the adjoining exterior volume, both of which are delimited by a mobile rotor in rotation about an axis and a part, fixed or mobile, includes: a first seal arranged between the rotor and the part; a second seal that is mounted between the rotor and the part and which is offset longitudinally relative to the first seal, to form with the first seal a sealing chamber delimited by the rotor, the part, and the two seals; and a mechanism for supplying gas to the sealing chamber, such that the gas can be compressed when the rotor begins to rotate, the chamber communicating with the oil chamber and/or the adjoining exterior volume via the first and second seals alone, respectively.Type: GrantFiled: December 5, 2012Date of Patent: May 29, 2018Assignee: SNECMAInventors: Dominik Igel, Delphine Leroux
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Patent number: 9951651Abstract: A bearing, such as a rolling bearing, is mounted on a support mobile in translation and includes a lubrication mechanism. The lubrication mechanism includes at least one pipe delivering a lubricant, linked to a lubricant supply source, and at least partially engaging in the support mobile in translation to deliver the lubricant from the mobile support along an internal channel to the bearing, passing through an inner ring of the bearing.Type: GrantFiled: June 27, 2013Date of Patent: April 24, 2018Assignee: SNECMAInventors: Caroline Frantz, Dominik Igel, Nadege Hugon, Augustin Curlier
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Publication number: 20170335769Abstract: The invention relates to a turbine engine, comprising: a device for bleeding a compressor, particularly a high-pressure compressor, comprising at least one valve for bleeding said compressor, an outlet of said valve being connected to a bleed system designed to discharge a bleed airflow; and at least one device for cooling at least one unit, comprising a heat exchanger, an air outlet of which is connected to an ejector of the jet pump type, which comprises a feed-through duct for a secondary airflow coming from said air outlet, as well as a nozzle for spraying a primary airflow inside said feed-through duct, wherein the nozzle is connected to said bleed system.Type: ApplicationFiled: November 24, 2015Publication date: November 23, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Benissa Boujida, Daniel Bernava, Dominik Igel, Maxime Rotenberg
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Patent number: 9810095Abstract: A sealing device for a turbine engine bearing oil enclosure including a rotor shaft; an annular cover secured to an engine casing and arranged around the rotor shaft to co-operate therewith to define an oil enclosure that is to receive a bearing rotatably supporting the rotor shaft relative to the engine casing; a labyrinth seal mounted on the rotor shaft facing one end of the cover; an annular rim mounted inside the cover; a dynamic annular gasket interposed radially between the rim and the rotor shaft; and a clip for axially blocking the rim inside the cover and including at least one latch passing radially through the rim and being received radially inside a groove formed in the cover, is provided.Type: GrantFiled: April 15, 2016Date of Patent: November 7, 2017Assignee: SNECMAInventors: Serge Rene Morreale, Dominik Igel
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Patent number: 9790794Abstract: The main purpose of the invention is a propeller (32) for a turbomachine (1) comprising a plurality of blades (48) and a blade support ring (47) fitted with housings (50) each of which holding a pivot (52) supporting the root (58) of one of said blades (48), characterized in that at least one of the pivots (52) is associated with at least one dynamic scoop (100), capable of moving between distinct positions, an open position in which a cooling airflow (F) can be captured, and a closed position as a function of the orientation of the corresponding blade.Type: GrantFiled: October 8, 2013Date of Patent: October 17, 2017Assignee: SNECMAInventors: Sarah Chartier, Adrien Jacques Philippe Fabre, Dominik Igel, Christophe Jacquemard, Sébastien Tajan
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Patent number: 9540951Abstract: A system for pressurizing at least one chamber for lubricating bearings of a turbine engine, including a circuit for supplying the chamber with pressurized air, and a circuit for recovering oil mist formed in the chamber and for returning the mist to an oil tank of the turbine engine. The supply circuit supplies the chamber with air taken upstream from the low-pressure compressor.Type: GrantFiled: September 22, 2011Date of Patent: January 10, 2017Assignee: SNECMAInventors: Nelson Dos Santos, Dominik Igel, Serge Rene Morreale
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Publication number: 20160305283Abstract: A sealing device for a turbine engine bearing oil enclosure including a rotor shaft; an annular cover secured to an engine casing and arranged around the rotor shaft to co-operate therewith to define an oil enclosure that is to receive a bearing (8) rotatably supporting the rotor shaft relative to the engine casing; a labyrinth seal mounted on the rotor shaft facing one end of the cover; an annular rim mounted inside the cover; a dynamic annular gasket interposed radially between the rim and the rotor shaft; and a clip for axially blocking the rim inside the cover and including at least one latch passing radially through the rim and being received radially inside a groove formed in the cover, is provided.Type: ApplicationFiled: April 15, 2016Publication date: October 20, 2016Applicant: SNECMAInventors: Serge Rene MORREALE, Dominik IGEL
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Publication number: 20150260045Abstract: The main purpose of the invention is a propeller (32) for a turbomachine (1) comprising a plurality of blades (48) and a blade support ring (47) fitted with housings (50) each of which holding a pivot (52) supporting the root (58) of one of said blades (48), characterised in that at least one of the pivots (52) is associated with at least one dynamic scoop (100), capable of moving between distinct positions, an open position in which a cooling airflow (F) can be captured, and a closed position as a function of the orientation of the corresponding blade.Type: ApplicationFiled: October 8, 2013Publication date: September 17, 2015Applicant: SNECMAInventors: Sarah Chartier, Adrien Jacques, Philippe Fabre, Dominik Igel, Christophe Jacquemard, Sébastien Tajan
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Publication number: 20150198065Abstract: The primary subject-matter of the invention is a turbomachine assembly (1), comprising first (2) and second (3) bodies, at least one (2) of which is rotating relative to the other (3) around the axis of rotation (T) of the turbomachine (10), between which a tight zone (EH) is formed comprising a sealing gasket (16), a flowing fluid (H), in particular lubricant oil (H), able to circulate inside the first (2) and second (3) bodies and to be driven toward said at least one rotating body (2) from the other body (3), characterized in that said at least one rotating body (2) comprises means (4a, 4b, 4c; 5a, 5b) for guiding the rotation, in the direction of rotation (F3) of said at least one rotating body (2), of the flow of fluid (H) inside said at least one rotating body (2) so as to drive the flowing fluid (H) away from the tight zone (EH).Type: ApplicationFiled: December 29, 2014Publication date: July 16, 2015Applicant: SNECMAInventors: Catherine PIKOVSKY, Dominik IGEL, Boris LEMATTRE
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Publication number: 20150147178Abstract: A bearing, such as a rolling bearing, is mounted on a support mobile in translation and includes a lubrication mechanism. The lubrication mechanism includes at least one pipe delivering a lubricant, linked to a lubricant supply source, and at least partially engaging in the support mobile in translation to deliver the lubricant from the mobile support along an internal channel to the bearing, passing through an inner ring of the bearing.Type: ApplicationFiled: June 27, 2013Publication date: May 28, 2015Applicant: SNECMAInventors: Caroline Frantz, Dominik Igel, Nadege Hugon, Augustin Curlier
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Publication number: 20140334913Abstract: A system for sealing an oil chamber from an adjoining exterior volume, and a turbo-machine including a sealing system. The system for sealing the oil chamber from the adjoining exterior volume, both of which are delimited by a mobile rotor in rotation about an axis and a part, fixed or mobile, includes: a first seal arranged between the rotor and the part; a second seal that is mounted between the rotor and the part and which is offset longitudinally relative to the first seal, to form with the first seal a sealing chamber delimited by the rotor, the part, and the two seals; and a mechanism for supplying gas to the sealing chamber, such that the gas can be compressed when the rotor begins to rotate, the chamber communicating with the oil chamber and/or the adjoining exterior volume via the first and second seals alone, respectively.Type: ApplicationFiled: December 5, 2012Publication date: November 13, 2014Applicant: SNECMAInventors: Dominik Igel, Delphine Leroux
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Patent number: 8864138Abstract: The invention concerns a system for providing a seal between two volumes (V1, V2) delimited by a part (2A) mounted to rotate about an axis (A) and a stator (6), said system (S) including an annular brush seal (7) that comprises: a brush body (8) pivotally mounted in the stator; and fibers (10) fixed to the brush body and inclined at an angle ? relative to a plane (P) orthogonal to the rotation axis (A), wherein it includes means (11, 12) for adjusting the angle ? of the fibers (10) so as to be able to adjust precisely the clearance between the free end (10A) of the fibers and the rotary part (2A).Type: GrantFiled: November 18, 2011Date of Patent: October 21, 2014Assignee: SNECMAInventors: Nelson Dos Santos, Dominik Igel, Gerard Philippe Gauthier