Patents by Inventor Mathieu Simon Paul GRUBER
Mathieu Simon Paul GRUBER 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).
-
Patent number: 11913405Abstract: An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile having a succession of teeth and depressions. Along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.Type: GrantFiled: March 14, 2023Date of Patent: February 27, 2024Assignee: Safran Aircraft EnginesInventors: Fernando Gea Aguilera, Matthieu Fiack, Mathieu Simon Paul Gruber
-
Patent number: 11859534Abstract: An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.Type: GrantFiled: February 15, 2019Date of Patent: January 2, 2024Assignee: Safran Aircraft EnginesInventors: Fernando Gea Aguilera, Mathieu Simon Paul Gruber, Georges Jean Xavier Riou
-
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
-
Patent number: 11732588Abstract: A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.Type: GrantFiled: December 7, 2022Date of Patent: August 22, 2023Assignees: SAFRAN AIRCRAFT ENGINES, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALESInventors: Fernando Gea Aguilera, Raphaël Barrier, Mathieu Simon Paul Gruber, Cyril Polacsek, Hélène Dominique Jeanne Posson
-
Publication number: 20230213000Abstract: An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile having a succession of teeth and depressions. Along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.Type: ApplicationFiled: March 14, 2023Publication date: July 6, 2023Inventors: Fernando Gea Aguilera, Matthieu Fiack, Mathieu Simon Paul Gruber
-
Patent number: 11668196Abstract: A profiled structure for an aircraft or turbomachine is elongated in a direction in which the structure has a length exposed to an airflow and includes serrations defined by successive teeth and depressions. The serrations may be transverse to a leading edge and/or a trailing edge of the profiled structure and in the direction of elongation. Along the profiled leading edge and/or profiled trailing edge, the successive teeth and depressions may extend only over a part of the length exposed to the flow. The amplitude and/or spacing of the teeth may vary monotonically except for the few teeth nearest each end of the part, with a remaining part of the length being smooth.Type: GrantFiled: September 24, 2019Date of Patent: June 6, 2023Assignees: SAFRAN AIRCRAFT ENGINES, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALESInventors: Fernando Gea Aguilera, Raphaël Barrier, Mathieu Simon Paul Gruber, Cyril Polacsek, Hélène Dominique Jeanne Posson
-
Publication number: 20230123376Abstract: A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.Type: ApplicationFiled: December 7, 2022Publication date: April 20, 2023Inventors: Fernando GEA AGUILERA, Raphaël BARRIER, Mathieu Simon Paul GRUBER, Cyril POLACSEK, Hélène Dominique Jeanne POSSON
-
Patent number: 11629664Abstract: An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile. The serrated profile has a succession of teeth and depressions, characterized in that, along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.Type: GrantFiled: February 15, 2019Date of Patent: April 18, 2023Assignee: Safran Aircraft EnginesInventors: Fernando Gea Aguilera, Matthieu Fiack, Mathieu Simon Paul Gruber
-
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
-
Patent number: 11560796Abstract: The invention relates to a profiled structure elongated in a direction in which the structure has a length exposed to an airflow and transversely to which the structure has a leading edge and/or a trailing edge, at least one of which is profiled and has, along said direction of elongation, geometric serration patterns defined by a succession of peaks and troughs. Along the profiled leading edge and/or trailing edge, the serration patterns have a geometric pattern that is repeated in the direction of elongation, the shape of which is stretched and/or contracted transversely to the direction of elongation and/or in the direction of elongation.Type: GrantFiled: October 18, 2019Date of Patent: January 24, 2023Assignees: SAFRAN AIRCRAFT ENGINES, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALESInventors: Fernando Gea Aguilera, Raphaël Barrier, Mathieu Simon Paul Gruber, Cyril Polacsek, Hélène Dominique Jeanne Posson
-
Patent number: 11525365Abstract: A front fan turbomachine includes an annular separating wall having a slat for separating an air flow between a primary flow and a secondary flow, the slat having a leading edge; inlet guide vanes (IGV) for guiding the primary flow and outlet guide vanes (OGV) blades for guiding the secondary flow. The leading edge of the slat has a serrated profile having a succession of teeth and depressions.Type: GrantFiled: February 15, 2019Date of Patent: December 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Fernando Gea Aguilera, Matthieu Fiack, Mathieu Simon Paul Gruber
-
Publication number: 20210388725Abstract: The invention relates to a profiled structure, elongated in a direction in which the structure has a length exposed to an airflow, and transversely to which the structure has a leading edge (164) and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations (28a) defined by successive teeth (30) and depressions (32). Along the profiled leading edge and/or profiled trailing edge, the successive teeth (30) and depressions (32) extend only over a part of said length exposed to the flow over which the amplitude and/or spacing of the teeth varies monotonically except for the few teeth nearest each end of said part, a remaining part (280) of said length being smooth.Type: ApplicationFiled: September 24, 2019Publication date: December 16, 2021Inventors: Fernando GEA AGUILERA, Raphaël BARRIER, Mathieu Simon Paul GRUBER, Cyril POLACSEK, Hélène Dominique Jeanne POSSON
-
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
-
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
-
Aircraft comprising a rear fairing propulsion system with inlet stator comprising a blowing function
Patent number: 10975803Abstract: An aircraft comprising a fuselage and a propulsion assembly, the propulsion assembly comprising at least one fan rotor located at the rear of the fuselage in the extension thereof along a longitudinal axis, and a nacelle forming a fairing of the at least one fan rotor into which a flow of air passes. The aircraft also comprises a plurality of radial stator arms mounted upstream of the at least one fan rotor and extending between the fuselage and the nacelle, the radial arms comprising blowing means configured for blowing, into the environment of a trailing edge of the radial arms, an additional air flow adding to the airflow in the extension of the trailing edge.Type: GrantFiled: July 21, 2016Date of Patent: April 13, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Pascal Romano, Mathieu Simon Paul Gruber -
Patent number: 10941667Abstract: A stator vane including a vane root, a vane tip, a leading edge extending between the root and the tip, the leading edge having a serrated profile having a succession of teeth and of troughs each having an amplitude and a thickness, wherein a series of at least three teeth and three consecutive troughs starting from the vane root and/or from the vane tip have a growing amplitude and/or thickness.Type: GrantFiled: October 30, 2018Date of Patent: March 9, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Claire Marie Figeureu, Eric Pierre Georges Lemarechal, Benjamin Bulot, Mathieu Simon Paul Gruber, Raphael Barrier, Cyril Polacsek
-
Publication number: 20210003074Abstract: An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.Type: ApplicationFiled: February 15, 2019Publication date: January 7, 2021Applicant: Safran Aircraft EnginesInventors: Fernando Gea Aguilera, Mathieu Simon Paul Gruber, Georges Jean Xavier Riou
-
Publication number: 20200408101Abstract: A front fan turbomachine comprising an annular separating wall (160) having a slat (16) for separating an air flow between a primary flow and a secondary flow, the slat having a leading edge; IGV blades for guiding the primary flow and OGV blades for guiding the secondary flow. The leading edge of the slat (16) has a serrated profile (28) having a succession of teeth and depressions.Type: ApplicationFiled: February 15, 2019Publication date: December 31, 2020Inventors: Fernando GEA AGUILERA, Matthieu FIACK, Mathieu Simon Paul GRUBER
-
Publication number: 20200400069Abstract: An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile. The serrated profile has a succession of teeth and depressions, characterized in that, along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.Type: ApplicationFiled: February 15, 2019Publication date: December 24, 2020Applicant: Safran Aircraft EnginesInventors: Fernando Gea Aguilera, Matthieu Fiack, Mathieu Simon Paul Gruber
-
Patent number: 10737796Abstract: A propulsion assembly for an aircraft, the assembly including a turbojet having at least one unducted propulsive propeller, and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having a streamlined profile defined by two opposite side faces extending transversely between a leading edge and a trailing edge. The pylon includes a plurality of blow nozzles situated in the vicinity of its trailing edge and configured to blow air taken from a pressurized portion of the turbojet, the blow nozzles being positioned over at least a fraction of the trailing edge of the pylon that extends longitudinally facing at least a portion of the propeller. A method of reducing the noise generated by a pylon attaching a turbojet to an aircraft is presented.Type: GrantFiled: June 15, 2016Date of Patent: August 11, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Mathieu Simon Paul Gruber, Timothy Delteil McWilliams