Patents by Inventor Jonathan Evert VLASTUIN
Jonathan Evert VLASTUIN 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: 11891967Abstract: A turbofan includes a fan, a casing positioned downstream of the fan and separating a primary flowpath from a secondary flowpath, a compressor, a combustion chamber and a turbine being arranged in the primary flowpath, the turbofan having a differential transmission coupled to the turbine, and a power supply device configured to provide additional power to the one provided by the turbine to drive the compressor.Type: GrantFiled: September 20, 2019Date of Patent: February 6, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Henri Yesilcimen, Caroline Marie Frantz, Nicolas Jérôme Jean Tantot, Nathalie Nowakowski, Gilles Alain Marie Charier, Kévin Morgane Lemarchand, Jonathan Evert Vlastuin
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Patent number: 11772777Abstract: A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.Type: GrantFiled: June 7, 2021Date of Patent: October 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clement Marcel Maurice Dejeu, Jonathan Evert Vlastuin, Mathieu Simon Paul Gruber
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Patent number: 11591913Abstract: A variable-pitch bladed disc including a plurality of blades, each at a variable pitch in relation to a rotation axis of the blade and each having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each having a root and a tip, each root being mounted at the tip of a corresponding rotor connecting shaft by way of a pivot so as to allow each blade to rotate about the blade rotation axis, the first blade having a first blade inclination, such that the first blade is inclined in a fixed manner with respect to the blade rotation axis of the first blade, and the second blade having a second blade inclination different from the first blade inclination.Type: GrantFiled: August 28, 2015Date of Patent: February 28, 2023Assignee: Safran Aircraft EnginesInventors: Clement Marcel Maurice Dejeu, Jonathan Evert Vlastuin, Mathieu Simon Paul Gruber
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Patent number: 11499432Abstract: A method of altering the twisting relationship for the aerodynamic surface of a fan blade of a gas turbine engine, wherein the following steps are performed: establishing, for a portion of the aerodynamic surface of the fan blade, an alteration relationship defined by variation of a pitch angle of the blade as a function of radial height along the blade, the alteration relationship including alterations that are each defined by a height along with the radial height of the fan blade and by an amplitude; and applying the alteration relationship as established in this way to an initial twisting relationship of the fan blade so as to obtain an altered twisting relationship for the fan blade, the initial twisting relationship being defined by a polynomial for the radial height of the fan blade as a function of its pitch angle.Type: GrantFiled: July 1, 2016Date of Patent: November 15, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Vivien Mickaël Courtier, Adrien Louis Nicolas Laurenceau, Dominique Gerhadt Mayhew, Jonathan Evert Vlastuin
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Patent number: 11421603Abstract: Turbojet engine includes a fan, a compressor, a combustion chamber, and a turbine configured to rotatably drive the fan via a first reduction gear and the compressor via a second reduction gear, in which an outlet of the first reduction gear is rotatably coupled to an inlet of the second reduction gear by a reduction shaft, the reduction shaft being supported by a bearing arranged between the first reduction gear and the second reduction gear.Type: GrantFiled: September 20, 2019Date of Patent: August 23, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nathalie Nowakowski, Gilles Alain Marie Charier, Kévin Morgane Lemarchand, Nicolas Jérôme Jean Tantot, Jonathan Evert Vlastuin, Henri Yesilcimen
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Publication number: 20210348566Abstract: Turbojet engine includes a fan, a compressor, a combustion chamber, and a turbine configured to rotatably drive the fan via a first reduction gear and the compressor via a second reduction gear, in which an outlet of the first reduction gear is rotatably coupled to an inlet of the second reduction gear by a reduction shaft, the reduction shaft being supported by a bearing arranged between the first reduction gear and the second reduction gear.Type: ApplicationFiled: September 20, 2019Publication date: November 11, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Nathalie NOWAKOWSKI, Gilles Alain Marie CHARIER, Kévin Morgane LEMARCHAND, Nicolas Jérôme Jean TANTOT, Jonathan Evert VLASTUIN, Henri YESILCIMEN
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Publication number: 20210317800Abstract: A turbofan includes a fan, a casing positioned downstream of the fan and separating a primary flowpath from a secondary flowpath, a compressor, a combustion chamber and a turbine being arranged in the primary flowpath, the turbofan having a differential transmission coupled to the turbine, and a power supply device configured to provide additional power to the one provided by the turbine to drive the compressor.Type: ApplicationFiled: September 20, 2019Publication date: October 14, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Henri YESILCIMEN, Caroline Marie FRANTZ, Nicolas Jérôme Jean TANTOT, Nathalie NOWAKOWSKI, Gilles Alain Marie CHARIER, Kévin Morgane LEMARCHAND, Jonathan Evert VLASTUIN
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Publication number: 20210291962Abstract: A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.Type: ApplicationFiled: June 7, 2021Publication date: September 23, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Clement Marcel Maurice DEJEU, Jonathan Evert VLASTUIN, Mathieu Simon Paul GRUBER
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Patent number: 11047238Abstract: A vane configured to be placed with a plurality of identical vanes so as to form a vane wheel for an aeroengine, the vane wheel defining an axis, the vane having an airfoil presenting a leading edge and a trailing edge, the leading-edge curve describing the shape of the leading edge of the airfoil in a view perpendicular to the airfoil presenting at least one leading-edge undulation, said at least one leading-edge undulation extending over less than 30% of a length of the airfoil from the first end of the airfoil.Type: GrantFiled: January 25, 2018Date of Patent: June 29, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Damien Bernard Emeric Guegan, Prasaad Cojande, Pierre-Hugues Ambroise Maxime Victor Retiveau, Jonathan Evert Vlastuin
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Patent number: 11046424Abstract: A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.Type: GrantFiled: August 28, 2015Date of Patent: June 29, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clement Marcel Maurice Dejeu, Jonathan Evert Vlastuin, Mathieu Simon Paul Gruber
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Patent number: 10669010Abstract: The invention relates to an unducted-fan aircraft engine comprising a generally cylindrical nacelle through which a primary jet flows, the nacelle bearing a fan rotor comprising variable-pitch vanes (33) located radially outside the nacelle in order to be traversed by a secondary jet (31) flowing longitudinally around the nacelle. The rotor comprises a hub bearing variable-pitch vane supports each carrying one vane (33), each vane (33) comprising a blade extending from a root that is used to removably attach same to a base of the associated support (34). Each base (36) is located radially outside the nacelle so that it is in the secondary jet, and each assembly formed by a base (36) and the vane root supported by the base (36) is surrounded and covered by a detachable aerodynamic cover (37).Type: GrantFiled: April 25, 2016Date of Patent: June 2, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Emile Philippe Tajan, Adrien Jacques Philippe Fabre, Adrien Louis Nicolas Laurenceau, Jonathan Evert Vlastuin, Laurence Francine Vion
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Publication number: 20190368356Abstract: A vane configured to be placed with a plurality of identical vanes so as to form a vane wheel for an aeroengine, the vane wheel defining an axis, the vane having an airfoil presenting a leading edge and a trailing edge, the leading-edge curve describing the shape of the leading edge of the airfoil in a view perpendicular to the airfoil presenting at least one leading-edge undulation , said at least one leading-edge undulation extending over less than 30% of a length of the airfoil from the first end of the airfoil.Type: ApplicationFiled: January 25, 2018Publication date: December 5, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Damien Bernard Emeric GUEGAN, Prasaad COJANDE, Pierre-Hugues Ambroise Maxime Victor RETIVEAU, Jonathan Evert VLASTUIN
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Patent number: 10387611Abstract: A method for modeling an offset portion of a blade of a non-ducted propeller is provided. The method includes: parametrizing a C1-class curve representing a deformation of the blade characterizing the offset, according to a position along a section at a given height in the blade, the curve intersecting consecutively through a first bend control point, a central control point, and a second bend control point, the first and second bend control points defining the extent of the blade section, the parametrization being implemented according to a first deformation parameter defining the abscissa of the central control point, a second parameter of deformation defining the ordinate of the second bend point, and a third deformation parameter defining the angle of the tangent to the curve at the second bend control point; optimizing one of the deformation parameters; and plotting the values of the optimized parameters on an interface.Type: GrantFiled: October 8, 2015Date of Patent: August 20, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Cyril Verbrugge, Clement Marcel Maurice Dejeu, Anthony Pascal Eloi Louet, Jonathan Evert Vlastuin
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Patent number: 10035582Abstract: A propeller blade extending radially between a blade root and a blade tip and having a leading edge and a trailing edge, together with a pressure side face and a suction side face. Along the leading edge, the angle (?) between the radial direction and a tangent to the leading edge passes through a local maximum zmax situated in the range 60% to 80% of the height of the blade. Furthermore, the suction side face of the blade includes an indentation extending axially from the leading edge to the trailing edge and located at a height of the blade between the local maximum zmax and the blade tip.Type: GrantFiled: December 5, 2013Date of Patent: July 31, 2018Assignee: SNECMAInventors: Jonathan Evert Vlastuin, Clement Marcel Maurice Dejeu
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Publication number: 20180127084Abstract: The invention relates to an unducted-fan aircraft engine comprising a generally cylindrical nacelle through which a primary jet flows, the nacelle bearing a fan rotor comprising variable-pitch vanes (33) located radially outside the nacelle in order to be traversed by a secondary jet (31) flowing longitudinally around the nacelle. The rotor comprises a hub bearing variable-pitch vane supports each carrying one vane (33), each vane (33) comprising a blade extending from a root that is used to removably attach same to a base of the associated support (34). Each base (36) is located radially outside the nacelle so that it is in the secondary jet, and each assembly formed by a base (36) and the vane root supported by the base (36) is surrounded and covered by a detachable aerodynamic cover (37).Type: ApplicationFiled: April 25, 2016Publication date: May 10, 2018Inventors: Sébastien Emile Philippe TAJAN, Adrien Jacques Philippe FABRE, Adrien Louis Nicolas LAURENCEAU, Jonathan Evert VLASTUIN, Laurence Francine VION
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Publication number: 20170300612Abstract: (EN) The present invention relates to a method for modeling at least one portion of a blade (2) of a non-ducted propeller (1), wherein the blade portion (2) is offset (3).Type: ApplicationFiled: October 8, 2015Publication date: October 19, 2017Applicant: Safran Aircraft EnginesInventors: Cyril VERBRUGGE, Clement Marcel Maurice DEJEU, Anthony Pascal Eloi LOUET, Jonathan Evert VLASTUIN
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Publication number: 20170284205Abstract: A variable-pitch bladed disc including a plurality of blades, each at a variable pitch in relation to a rotation axis of the blade and each having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each having a root and a tip, each root being mounted at the tip of a corresponding rotor connecting shaft by way of a pivot so as to allow each blade to rotate about the blade rotation axis, the first blade having a first blade inclination, such that the first blade is inclined in a fixed manner with respect to the blade rotation axis of the first blade, and the second blade having a second blade inclination different from the first blade inclination.Type: ApplicationFiled: August 28, 2015Publication date: October 5, 2017Applicant: Safran Aircraft EnginesInventors: Clément Marcel Maurice DEJEU, Jonathan Evert VLASTUIN, Mathieu Simon Paul GRUBER
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Patent number: 9776707Abstract: The invention relates to an aircraft turboprop engine having two unducted propellers, coaxial about a rotation axis (LL), respectively upstream (12) and downstream (14?), each propeller comprising an annular row of blades, the blades of the downstream propeller (14?) each having a truncated head and each comprising a leading edge (20?) and a trailing edge (22?), the radially external ends (A2, B1) of which are distant from each other and are connected by a terminal edge (21?), characterised in that the terminal edge (21?) of each blade of the downstream propeller (14?) has, at at least two points, tangents in a meridian plane having different slopes, the upstream end (A) of the terminal edge defining a maximum radial dimension (R2) of the blade and its downstream end (B1) defining a minimum radial dimension (R3) of the terminal edge.Type: GrantFiled: May 28, 2015Date of Patent: October 3, 2017Assignee: SNECMAInventors: Anthony Pascal Eloi Louet, Clement Marcel Maurice Dejeu, Jonathan Evert Vlastuin
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Publication number: 20170274980Abstract: A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.Type: ApplicationFiled: August 28, 2015Publication date: September 28, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Clement Marcel Maurice DEJEU, Jonathan Evert VLASTUIN, Mathieu Simon Paul GRUBER
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Publication number: 20160159459Abstract: The invention relates to an aircraft turboprop engine comprising two unducted propellers, coaxial about a rotation axis (LL), respectively upstream (12) and downstream (14?), each propeller comprising an annular row of blades, the blades of the downstream propeller (14?) each having a truncated head and each comprising a leading edge (20?) and a trailing edge (22?), the radially external ends (A2, B1) of which are distant from each other and are connected by a terminal edge (21?), characterised in that the terminal edge (21?) of each blade of the downstream propeller (14?) has, at at least two points, tangents in a meridian plane having different slopes, the upstream end (A) of the terminal edge defining a maximum radial dimension (R2) of the blade and its downstream end (B1) defining a minimum radial dimension (R3) of said terminal edge.Type: ApplicationFiled: May 28, 2015Publication date: June 9, 2016Applicant: SNECMAInventors: Anthony Pascal Eloi LOUET, Clement Marcel Maurice DEJEU, Jonathan Evert VLASTUIN