Patents by Inventor Guillaume Pascal Jean-Charles GONDRE
Guillaume Pascal Jean-Charles GONDRE 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: 20240093611Abstract: The invention relates to a fan blade (3) made of composite material the fibrous reinforcement of which comprises first strands (12) having a first stiffness, second strands (13) having a second stiffness and third strands (14) having a third stiffness lower than the first stiffness and greater than the second stiffness, the blade comprising a first portion (15) comprising only first strands (12), a second portion (16) comprising only second strands (13) and a third portion (17) which is located between the first and second portions (15, 16) and which comprises both first, second and third strands (12, 13, 14); there is a gradual transition of properties at the interface between the different portions (15, 16, 17).Type: ApplicationFiled: November 29, 2021Publication date: March 21, 2024Applicant: Safran Aircraft EnginesInventors: Carole Onja RAKOTOARISOA, Teddy FIXY, Guillaume Pascal Jean-Charles GONDRE, Julien Paul SCHNEIDER-DIE-GROSS
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Patent number: 11920494Abstract: The present invention relates to a turbomachine rotary-fan blade (2), comprising a body (20) made of a composite material, a metal reinforcement part (3) comprising a metal upstream nose (31), characterised in that the metal upstream nose (31) comprises, at least on the metal part (27b) of the blade tip, a recess (4) of longitudinally tapering thickness (AX), delimiting on the metal part (27b) over a height (H) at least one metal projection (5) with prescribed wear, which has a longitudinally tapering thickness and which is configured to detach at least partially in the presence of tangential friction in the second thickness direction (EP) against the metal part (27b), the recess (4) and the metal projection (5) with prescribed wear extending the first metal fin (32) and/or the second metal fin (33) and/or the upstream edge (22) of the body (20) made of composite material.Type: GrantFiled: March 24, 2021Date of Patent: March 5, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Pascal Jean-Charles Gondre, Thomas Alain De Gaillard, Pierre Jean Faivre D'arcier
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Patent number: 11885239Abstract: The invention relates to a turbomachine rotary-fan blade having a predetermined breaking zone, which extends from the upstream edge along a given length and from the blade-tip edge over a given height. According to the invention, the body is made of a composite material comprising a fibre reinforcement obtained by three-dimensional weaving of warp and weft strands, and a resin matrix in which the fibre reinforcement is embedded, and has, in or in the vicinity of the zone, a discontinuity of at least some of the strands, configured such that the zone partially detaches when there is tangential friction in the thickness direction against the blade-tip edge, the height being less than 3% of the aerodynamic stream height of the blade.Type: GrantFiled: November 18, 2020Date of Patent: January 30, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Pascal Jean-Charles Gondre, Thomas Alain De Gaillard, Pierre Jean Faivre D'Arcier
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Publication number: 20240003265Abstract: The invention relates to a blade comprising a shield (14) attached to the upstream end of the body of the blade, the shield (14) comprising an upstream end forming a leading edge of the blade, the shield (14) further comprising a nose (141) upstream from which the leading edge is located, an pressure-face fin and an suction-face fin laterally attached on the blade, the fins extending from the nose, the blade comprising a defrosting air passage duct (15) arranged inside the nose and extending radially inside the nose, the duct (15) having an inner end (151) emerging opposite the root (125) and a radially external end emerging from the nose between the leading edge and its junction at the pressure-face fin.Type: ApplicationFiled: November 10, 2021Publication date: January 4, 2024Applicant: Safran Aircraft EnginesInventors: Guillaume Pascal Jean-Charles GONDRE, Morgane Astrid LEGER, Stéphane Roger MAHIAS, Romuald Bernard MAUVAIS
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Publication number: 20230392502Abstract: The present invention relates to a blade (3) of a fan (1), made of composite material, of a turbomachine. On a portion (15) of the blade (7) which extends from a lower limit (16) located at a predetermined distance (d) from the shank (6) of the blade equal to at least 80% of the predetermined height (h) to the top (11) of the blade (7), a dihedral angle (D) measured at at least one predefined point on the chord of the blade (3), located on the chord of the blade (3) at the upstream end (13a) of the nose (13) of the shield (12), is greater than or equal to ?3° and less than or equal to 0°.Type: ApplicationFiled: October 19, 2021Publication date: December 7, 2023Applicant: Safran Aircraft EnginesInventors: Guillaume, Pascal, Jean-Charles GONDRE, Stéphane, Roger MAHIAS, Olivier BAZOT, Guillaume, Claude, Robert BELMON, Charles-Henri, Claude, Jacky SULLET
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Publication number: 20230392507Abstract: A blade comprising a blade body made of fiber-reinforced organic-matrix composite material and a leading edge shield made of a material having a better resistance to point impacts than the composite material of the blade body, the leading edge shield being assembled on the blade body and including a pressure side fin and an suction side fin connected by a thicker central part, the blade including an aerodynamic airfoil height and a chord length, the suction side fin having a first length projected onto the chord between 10 and 18% of the chord length, the first length being disposed between 70 and 80% of the aerodynamic airfoil height, a second length projected onto the chord between 18 and 26% of the chord length, the second length being disposed between 85 and 95% of the aerodynamic airfoil height.Type: ApplicationFiled: October 5, 2021Publication date: December 7, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Charles-Henri Claude Jacky SULLET, Guillaume Pascal Jean-Charles GONDRE
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Publication number: 20230358143Abstract: The present invention relates to a fan blade of a turbomachine comprising a structure made of composite material comprising a fibrous reinforcement obtained by three-dimensional weaving of strands and a matrix in which the fibrous reinforcement is embedded, which comprises a first portion forming the suction-side wall and a second portion forming the pressure-side wall, the strands of the fibrous reinforcement comprising first strands comprising carbon or aramid fibres, the Young's modulus of which is greater than 250 GPa, and second strands produced from a viscoelastic material and having a Young's modulus less than 10 GPa, the first portion comprises uniquely first strands whereas the second portion comprises second strands.Type: ApplicationFiled: August 31, 2021Publication date: November 9, 2023Applicant: Safran Aircraft EnginesInventors: Clément Pierre POSTEC, Thomas Alain DE GAILLARD, Guillaume Pascal Jean-Charles GONDRE, Pierre-Antoine Gérard Joseph BARBIER
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Patent number: 11788420Abstract: The present invention relates to a fan blade (3) having a structure made from a composite material, comprising a fibrous reinforcement (5), which is obtained by three-dimensional weaving of warp strands and weft strands, and a matrix in which the fibrous reinforcement (5) is embedded, wherein—the fibrous reinforcement (5) comprises a first portion (14) forming the trailing edge (9) of the structure made from a composite material and a second portion (15) forming its leading edge (8), and wherein—the warp strands of the fibrous reinforcement (5) comprise first strands (12) having a predetermined stiffness and second strands (13) having a greater stiffness than that of the first strands (12), the first portion (14) comprising all or part of the first strands (12) and being devoid of second strands (13) while the second portion (15) comprises all or part of the second strands (13).Type: GrantFiled: March 3, 2021Date of Patent: October 17, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Pascal Jean-Charles Gondre, Thomas Alain De Gaillard
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Patent number: 11753949Abstract: A fibrous texture intended to form the fibrous reinforcement of a turbomachine blade made of composite material including a fibrous reinforcement densified by a matrix, wherein the fibrous texture includes an area of reduced stiffness including warp yarns or strands made of second fibers having a second elongation at break greater than the first elongation at break, the area of reduced stiffness extending in the longitudinal direction from the stilt area and up to a height less than or equal to 30% of the height of the blade, extending in the transverse direction between a first area and a second area, the first area extending over a first length from a first edge of the texture intended to form a leading edge, and the second area extending over a second length from a second edge of the texture intended to form a trailing edge.Type: GrantFiled: February 1, 2021Date of Patent: September 12, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Pascal Jean-Charles Gondre, Clément Pierre Postec
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Patent number: 11753943Abstract: A turbomachine rotor blade includes plural blade sections stacked along an axis between a blade root and a blade head defining between the blade root and the blade head the height of the blade, each blade section including a chord and a maximum sweep defined by the maximum length of a segment perpendicular to the chord line and connecting a point of the chord line and a point of a camber line formed of all points located equidistant from the extrados and the intrados in the section, and verifying that the ratio between the maximum sweep and the chord at mid-height of the blade and the same blade head ratio is between 25% and 40% of the ratio between a maximum sweep and a blade root chord.Type: GrantFiled: December 10, 2019Date of Patent: September 12, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Pascal Jean-Charles Gondre, Nicolas Pierre Alain Edme De Cacqueray-Valmenier, Mickaël Cavarec, Sadim Dieudonne
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Publication number: 20230129130Abstract: The present invention relates to a turbomachine rotary-fan blade (2), comprising a body (20) made of a composite material, a metal reinforcement part (3) comprising a metal upstream nose (31), characterised in that the metal upstream nose (31) comprises, at least on the metal part (27b) of the blade tip, a recess (4) of longitudinally tapering thickness (AX), delimiting on the metal part (27b) over a height (H) at least one metal projection (5) with prescribed wear, which has a longitudinally tapering thickness and which is configured to detach at least partially in the presence of tangential friction in the second thickness direction (EP) against the metal part (27b), the recess (4) and the metal projection (5) with prescribed wear extending the first metal fin (32) and/or the second metal fin (33) and/or the upstream edge (22) of the body (20) made of composite material.Type: ApplicationFiled: March 24, 2021Publication date: April 27, 2023Applicant: Safran Aircraft EnginesInventors: Guillaume Pascal Jean-Charles GONDRE, Thomas Alain DE GAILLARD, Pierre Jean FAIVRE D'ARCIER
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Patent number: 11634988Abstract: A turbomachine rotor blade is formed of plural blade sections stacked along an axis extending from a blade root to a blade tip. Each blade section located at various heights along the blade is designed to have a given ratio between a maximum thickness, which is measured between a suction side and pressure side of the blade, and a chord, which is defined by a line connecting a leading edge and a trailing edge of the blade. Each blade section is further designed to have a ratio of the maximum thickness to the chord at a given height of the blade relative to a ratio of the maximum thickness to the chord of another blade section located at a different height of the blade.Type: GrantFiled: December 10, 2019Date of Patent: April 25, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Sadim Dieudonne, Mickaël Cavarec, Guillaume Pascal Jean-Charles Gondre, Nicolas Pierre Alain Edme De Cacqueray-Valmenier
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Publication number: 20230088650Abstract: The present invention relates to a fan blade (3) having a structure made from a composite material, comprising a fibrous reinforcement (5), which is obtained by three-dimensional weaving of warp strands and weft strands, and a matrix in which the fibrous reinforcement (5) is embedded, wherein—the fibrous reinforcement (5) comprises a first portion (14) forming the trailing edge (9) of the structure made from a composite material and a second portion (15) forming its leading edge (8), and wherein—the warp strands of the fibrous reinforcement (5) comprise first strands (12) having a predetermined stiffness and second strands (13) having a greater stiffness than that of the first strands (12), the first portion (14) comprising all or part of the first strands (12) and being devoid of second strands (13) while the second portion (15) comprises all or part of the second strands (13).Type: ApplicationFiled: March 3, 2021Publication date: March 23, 2023Applicant: Safran Aircraft EnginesInventors: Guillaume Pascal Jean-Charles GONDRE, Thomas Alain DE GAILLARD
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Publication number: 20230076445Abstract: A fibrous texture intended to form the fibrous reinforcement of a turbomachine blade made of composite material including a fibrous reinforcement densified by a matrix, wherein the fibrous texture includes an area of reduced stiffness including warp yarns or strands made of second fibers having a second elongation at break greater than the first elongation at break, the area of reduced stiffness extending in the longitudinal direction from the stilt area and up to a height less than or equal to 30% of the height of the blade, extending in the transverse direction between a first area and a second area, the first area extending over a first length from a first edge of the texture intended to form a leading edge, and the second area extending over a second length from a second edge of the texture intended to form a trailing edge.Type: ApplicationFiled: February 1, 2021Publication date: March 9, 2023Inventors: Guillaume Pascal Jean-Charles GONDRE, Clément Pierre POSTEC
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Publication number: 20230003133Abstract: A method for manufacturing a blade in composite material having an added metal leading edge for gas turbine aeroengine, includes producing a blade body in composite material including in longitudinal direction, a blade root part, a shank part and an airfoil body part; manufacturing, via additive manufacturing, a leading edge extending in longitudinal direction between a lower end present at the shank part in composite material and an upper end present at the tip; bonding the manufactured leading edge onto the foremost edge portion of the airfoil body of the blade body in composite material.Type: ApplicationFiled: December 14, 2020Publication date: January 5, 2023Inventors: Guillaume Pascal Jean-Charles GONDRE, Olivier BAZOT, Matthieu Pierre Michel DUBOSC
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Publication number: 20220381148Abstract: The invention relates to a turbomachine rotary-fan blade having a predetermined breaking zone, which extends from the upstream edge along a given length and from the blade-tip edge over a given height. According to the invention, the body is made of a composite material comprising a fibre reinforcement obtained by three-dimensional weaving of warp and weft strands, and a resin matrix in which the fibre reinforcement is embedded, and has, in or in the vicinity of the zone, a discontinuity of at least some of the strands, configured such that the zone partially detaches when there is tangential friction in the thickness direction against the blade-tip edge, the height being less than 3% of the aerodynamic stream height of the blade.Type: ApplicationFiled: November 18, 2020Publication date: December 1, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Pascal Jean-Charles GONDRE, Thomas Alain DE GAILLARD, Pierre Jean FAIVRE D'ARCIER
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Publication number: 20220018259Abstract: A turbomachine rotor blade includes plural blade sections stacked along an axis between a blade root and a blade head defining between the blade root and the blade head the height of the blade, each blade section including a chord and a maximum sweep defined by the maximum length of a segment perpendicular to the chord line and connecting a point of the chord line and a point of a camber line formed of all points located equidistant from the extrados and the intrados in the section, and verifying that the ratio between the maximum sweep and the chord at mid-height of the blade and the same blade head ratio is between 25% and 40% of the ratio between a maximum sweep and a blade root chord.Type: ApplicationFiled: December 10, 2019Publication date: January 20, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Pascal Jean-Charles GONDRE, Nicolas Pierre Alain Edme DE CACQUERAY-VALMENIER, Mickaél CAVAREC, Sadim DIEUDONNE
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Publication number: 20220018257Abstract: The invention relates to a turbomachine rotor blade which is characterized in that:—the ratio between the maximum thickness and the chord at 30% of the height of the blade is between 20% and 42% of the ratio between the maximum thickness and the chord at the blade root,—the ratio between the maximum thickness and the chord at 70% of the height of the blade is between 10% and 30% of the ratio between the maximum thickness and the chord at the blade root,—the ratio between the maximum thickness and the chord at 90% of the height of the blade is between 10% and 30% of the ratio between the maximum thickness and the chord at the blade root,—the ratio between the maximum thickness and the chord at the blade head is between 3% and 21% of the ratio between the maximum thickness and the chord at the blade root.Type: ApplicationFiled: December 10, 2019Publication date: January 20, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Sadim DIEUDONNE, Mickaël CAVAREC, Guillaume Pascal Jean-Charle GONDRE, Nicolas Pierre Alain Edme DE CACQUERAY-VALMENIER
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Patent number: 11168567Abstract: A fibrous texture to form the fibrous reinforcement of a turbomachine blade made of composite material, the texture being made in one piece and having a three-dimensional weaving, and includes blade root, blade airfoil and blade support portions. The blade support portion includes a first area extending transversely from a first edge of the texture to form a leading edge and a second area extending transversely from the first area up to a second edge of the texture to form a trailing edge, the first area including warp yarns or strands made of second fibers different from the first fibers, the second fibers having an elongation at break greater than that of the first fibers, the first area having a first volume ratio in yarns or strands made of second fibers strictly greater than a second volume ratio in yarns or strands made of second fibers in the second area.Type: GrantFiled: October 8, 2019Date of Patent: November 9, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Pascal Jean-Charles Gondre, Thomas Alain De Gaillard
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Patent number: 11098590Abstract: A turbine engine rotor blade including a plurality of blade cross sections stacked along an axis Z between a blade root and a blade tip defining therebetween the height of the blade, each blade cross section including a leading edge (16) and a trailing edge (17) and a chord defined by the length of the segment which extends from the leading edge to the trailing edge and ensuring that: the ratio of the chord at mid-height and of the chord at the blade root is comprised between 140% and 160%; the ratio of the chord at the blade tip and of the chord at the blade root is comprised between 115% and 135%; the chord is locally constant in a blade root zone and in a blade mid-height zone.Type: GrantFiled: December 11, 2019Date of Patent: August 24, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Mickael Cavarec, Sadim Dieudonne, Nicolas Pierre Alain Edme De Cacqueray-Valmenier, Guillaume Pascal Jean-Charles Gondre