Patents by Inventor Caroline Jacqueline Denise BERDOU
Caroline Jacqueline Denise BERDOU 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: 11719253Abstract: A preform for a turbine engine blade, comprising a main fiber preform obtained by three-dimensional weaving and comprising: a first longitudinal segment, suitable for forming a blade root; a second longitudinal segment, extending upwards from the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment, extending transversely from the junction between the first and second longitudinal segments to a substantially linear distal edge and suitable for forming a first platform; the preform further including at least one attachment tab provided under the first transverse segment at its distal edge, suitable for forming an attachment portion of the platform.Type: GrantFiled: April 28, 2016Date of Patent: August 8, 2023Assignee: Safran Aircraft EnginesInventors: Thomas Alain De Gaillard, Caroline Jacqueline Denise Berdou, Alexandre Bernard Marie Boisson
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Patent number: 10619493Abstract: A preform for a turbine engine blade, the preform being obtained by three-dimensional weaving and comprising a first longitudinal segment (31) suitable for forming at least a portion of a blade root, a second longitudinal segment (32) extending the first longitudinal segment (31) upwards, and suitable for forming at least a portion of a stilt portion, a third longitudinal segment (33) extending the second longitudinal segment (32) upwards, and suitable for forming an airfoil portion, a first transverse segment (34) extending transversely from the junction between the second and third longitudinal segments (32, 33), and suitable for forming a first platform, and a first oblique segment (36) extending from the junction between the first and second longitudinal segments (31, 32) to the first transverse segment (34), and suitable for forming a retaining leg (26) for the first platform.Type: GrantFiled: April 26, 2016Date of Patent: April 14, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thomas Alain De Gaillard, Caroline Jacqueline Denise Berdou, Alexandre Bernard Marie Boisson, Matthieu Arnaud Gimat
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Patent number: 10519776Abstract: A preform for a turbine engine blade, the preform comprising a main fiber preform obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards, and suitable for forming an airfoil portion (22), and a first transverse segment extending transversely from the junction between the first and second longitudinal segments, and suitable for forming a first platform (23), wherein the preform also includes at least one stiffener (40) fitted on the main fiber preform along at least a portion of the distal edge of the first transverse segment.Type: GrantFiled: April 26, 2016Date of Patent: December 31, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Caroline Jacqueline Denise Berdou, Thomas Alain De Gaillard
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Patent number: 10267164Abstract: A fiber preform for a turbine engine blade and a single-piece blade suitable for being made by means of such a preform, a bladed wheel, and a turbine engine including such a blade; the fiber preform obtained by three-dimensional weaving comprises a first longitudinal segment (41) suitable for forming a blade root, a second longitudinal segment (42) extending the first longitudinal segment (41) upwards and suitable for forming an airfoil portion, a first transverse segment (51) extending transversely from the junction between the first and second longitudinal segments (41, 42), and suitable for forming a first platform; the first transverse segment (51) includes at least one non-interlinked portion comprising a top strip (51b) and a bottom strip (51a), and at least one insert (61) is arranged between the top and bottom strips (51b, 51a) of the non-interlinked portion of the first transverse segment (51).Type: GrantFiled: April 26, 2016Date of Patent: April 23, 2019Assignee: SNECMAInventors: Caroline Jacqueline Denise Berdou, Alexandre Bernard Marie Boisson, Matthieu Arnaud Gimat, Audrey Laguerre
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Patent number: 10094390Abstract: A rotary assembly includes a fan disk including a tooth with an upstream face; a platform mounted on the tooth; and a shroud mounted at the upstream end of the disk. The platform, at its upstream end, includes a step with a radial portion that is extended by an axial portion to form a substantially L-shaped longitudinal section. The axial portion radially retains the platform against the tooth. The radial portion extends along the upstream face of the tooth and includes an opening for having a fastener element passing axially therethrough to mount the shroud on the disk. A face of the shroud includes an element that projects and passes through the opening and comes into contact with the upstream face. The element extends from the face of the shroud over a length that is longer than a thickness of the radial portion of the step of the platform.Type: GrantFiled: February 23, 2016Date of Patent: October 9, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alexandre Bernard Marie Boisson, Caroline Jacqueline Denise Berdou, Thomas Alain De Gaillard, Matthieu Arnaud Gimat
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Publication number: 20180135436Abstract: A fiber preform for a turbine engine blade and a single-piece blade suitable for being made by means of such a preform, a bladed wheel, and a turbine engine including such a blade; the fiber preform obtained by three-dimensional weaving comprises a first longitudinal segment (41) suitable for forming a blade root, a second longitudinal segment (42) extending the first longitudinal segment (41) upwards and suitable for forming an airfoil portion, a first transverse segment (51) extending transversely from the junction between the first and second longitudinal segments (41, 42), and suitable for forming a first platform; the first transverse segment (51) includes at least one non-interlinked portion comprising a top strip (51b) and a bottom strip (51a), and at least one insert (61) is arranged between the top and bottom strips (51b, 51a) of the non-interlinked portion of the first transverse segment (51).Type: ApplicationFiled: April 26, 2016Publication date: May 17, 2018Inventors: Caroline Jacqueline Denise BERDOU, Alexandre Bernard Marie BOISSON, Matthieu Arnaud GIMAT, Audrey LAGUERRE
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Publication number: 20180119550Abstract: A preform for a turbine engine blade, the preform comprising a main fiber preform obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards, and suitable for forming an airfoil portion (22), and a first transverse segment extending transversely from the junction between the first and second longitudinal segments, and suitable for forming a first platform (23), wherein the preform also includes at least one stiffener (40) fitted on the main fiber preform along at least a portion of the distal edge of the first transverse segment.Type: ApplicationFiled: April 26, 2016Publication date: May 3, 2018Inventors: Caroline Jacqueline Denise BERDOU, Thomas Alain DE GAILLARD
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Publication number: 20180100400Abstract: A preform for a turbine engine blade, the preform being obtained by three-dimensional weaving and comprising a first longitudinal segment (31) suitable for forming at least a portion of a blade root, a second longitudinal segment (32) extending the first longitudinal segment (31) upwards, and suitable for forming at least a portion of a stilt portion, a third longitudinal segment (33) extending the second longitudinal segment (32) upwards, and suitable for forming an airfoil portion, a first transverse segment (34) extending transversely from the junction between the second and third longitudinal segments (32, 33), and suitable for forming a first platform, and a first oblique segment (36) extending from the junction between the first and second longitudinal segments (31, 32) to the first transverse segment (34), and suitable for forming a retaining leg (26) for the first platform.Type: ApplicationFiled: April 26, 2016Publication date: April 12, 2018Applicant: Safran Aircraft EnginesInventors: Thomas Alain DE GAILLARD, Caroline Jacqueline Denise BERDOU, Alexandre Bernard Marie BOISSON, Matthieu Arnaud GIMAT
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Patent number: 9897316Abstract: A combustion chamber for a turbine engine such as an airplane turboprop or turbojet has inner and outer annular walls forming bodies of revolution that are connected together by an annular chamber end wall. The inner wall is constituted by a single thickness of material that presents thickness and/or nature varying along the longitudinal axis and/or the circumferential direction of said wall.Type: GrantFiled: December 2, 2010Date of Patent: February 20, 2018Assignee: SNECMAInventors: Caroline Jacqueline Denise Berdou, Laurent Bernard Cameriano
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Publication number: 20170058912Abstract: A preform for a turbine engine blade, comprising a main fiber preform obtained by three-dimensional weaving and comprising: a first longitudinal segment, suitable for forming a blade root; a second longitudinal segment, extending upwards from the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment, extending transversely from the junction between the first and second longitudinal segments to a substantially linear distal edge and suitable for forming a first platform; the preform further including at least one attachment tab provided under the first transverse segment at its distal edge, suitable for forming an attachment portion of the platform.Type: ApplicationFiled: April 28, 2016Publication date: March 2, 2017Applicant: SNECMAInventors: Thomas Alain DE GAILLARD, Caroline Jacqueline Denise BERDOU, Alexandre Bernard Marie BOISSON
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Publication number: 20160252102Abstract: A rotary assembly includes a fan disk including a tooth with an upstream face; a platform mounted on the tooth; and a shroud mounted at the upstream end of the disk. The platform, at its upstream end, includes a step with a radial portion that is extended by an axial portion to form a substantially L-shaped longitudinal section. The axial portion radially retains the platform against the tooth. The radial portion extends along the upstream face of the tooth and includes an opening for having a fastener element passing axially therethrough to mount the shroud on the disk. A face of the shroud includes an element that projects and passes through the opening and comes into contact with the upstream face. The element extends from the face of the shroud over a length that is longer than a thickness of the radial portion of the step of the platform.Type: ApplicationFiled: February 23, 2016Publication date: September 1, 2016Inventors: Alexandre Bernard Marie BOISSON, Caroline Jacqueline Denise BERDOU, Thomas Alain DE GAILLARD, Matthieu Arnaud GIMAT
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Patent number: 8769958Abstract: A flame-holder device for an afterburner of a turbofan, the turbofan including a first inner annular casing and a second inner annular casing, these defining a passage for a primary flow, and an outer annular casing defining with the first inner annular casing a passage for a secondary flow, including at least one arm-support made of metallic material configured to be fixed to the outer casing by an upper plate and at least one flame-holder arm of a one-piece structure of composite material including two mutually attached walls arranged to define a groove whose profile is approximately a V. The walls support, on their upper part situated in the secondary flow, a fixing mechanism for fixing to the arm-support. The upper parts are approximately planar and are positioned facing each other.Type: GrantFiled: August 31, 2009Date of Patent: July 8, 2014Assignee: SNECMAInventors: Didier Hyppolyte Hernandez, Caroline Jacqueline Denise Berdou, Jacques Marcel Arthur Bunel, Yann Francois Jean-Claude Vuillemont
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Publication number: 20120240584Abstract: A combustion chamber for a turbine engine such as an airplane turboprop or turbojet has inner and outer annular walls forming bodies of revolution that are connected together by an annular chamber end wall. The inner wall is constituted by a single thickness of material that presents thickness and/or nature varying along the longitudinal axis and/or the circumferential direction of said wall.Type: ApplicationFiled: December 2, 2010Publication date: September 27, 2012Applicant: SNECMAInventors: Caroline Jacqueline Denise Berdou, Laurent Bernard Cameriano
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Publication number: 20110138773Abstract: A flame-holder device for an afterburner of a turbofan, the turbofan including a first inner annular casing and a second inner annular casing, these defining a passage for a primary flow, and an outer annular casing defining with the first inner annular casing a passage for a secondary flow, including at least one arm-support made of metallic material configured to be fixed to the outer casing by an upper plate and at least one flame-holder arm of a one-piece structure of composite material including two mutually attached walls arranged to define a groove whose profile is approximately a V. The walls support, on their upper part situated in the secondary flow, a fixing mechanism for fixing to the arm-support. The upper parts are approximately planar and are positioned facing each other.Type: ApplicationFiled: August 31, 2009Publication date: June 16, 2011Applicant: SNECMAInventors: Didier Hippolyte Hernandez, Caroline Jacqueline Denise Berdou, Jacques Marces Arthur Bunel, Yann Francois Jean-Claude Vuillemont
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Publication number: 20110120144Abstract: An annular combustion chamber for a turbomachine, such as a jet engine or a turboprop engine for an aircraft, including at the downstream end of one of its external or internal walls of revolution an annular flange for fastening to a casing of the turbomachine, the downstream end of the other wall of revolution of the chamber including a bearing mechanism which are spaced apart from another casing of the turbomachine when cold and bear radially on this casing when hot.Type: ApplicationFiled: April 21, 2009Publication date: May 26, 2011Applicant: SNECMAInventors: Caroline Jacqueline Denise Berdou, Sylvain Duval, Romain Nicolas Lunel
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Publication number: 20110067407Abstract: A flame-holder device for the afterburning of a bypass turbojet, said turbojet comprising first and second internal annular casings, defining a passageway for a main flow, and an external annular casing defining with said first internal annular casing a passageway for a bypass flow, comprising: at least one metal arm support designed to be attached to said external casing by means of a top plate, at least one flame-holder arm, having a trough shape making a cavity, designed to be attached to the arm support, and at least one screen for the heat protection of the arm cavity, the arm support and the heat-protection screen being in one piece.Type: ApplicationFiled: September 22, 2010Publication date: March 24, 2011Applicant: SNECMAInventors: Caroline Jacqueline Denise BERDOU, Sylvain Yves Jean Duval