Patents by Inventor Olivier BAZOT
Olivier BAZOT 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: 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: 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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Patent number: 11199199Abstract: An interface member equips a control ring of a high-pressure compressor of an engine. This control ring has at least one housing intended to partially house a guide shoe. This interface member includes a central wall to which two holding tabs are secured, delimiting a through-housing having dimensions substantially identical to the initial dimensions of the housing, and suitable for being inserted into the housing, after it has been machined to receive same following a deformation, until the holding tabs keep it stationary relative to the control ring.Type: GrantFiled: August 22, 2017Date of Patent: December 14, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Olivier Bazot, Jérémy Philippe Pierre Edynak
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Patent number: 11111810Abstract: A control assembly for a stage of variable-pitch vanes for a turbine engine generally includes an actuating ring having an annular body, a vane guidance means for connecting to the cylindrical pivots of the variable pitch vanes, a rotating means for rotating the actuating ring about a casing of the turbine engine, and a centering means for cooperating with the casing to center the actuating ring. The centering means may have at least one skid bearing against the casing. At least one of the skid or the rod may be configured to cooperate by radial sliding with an inner wall of a housing. The skid may be configured to be mobile during operation by sliding between a radially internal position and a radially external position.Type: GrantFiled: February 8, 2019Date of Patent: September 7, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventor: Olivier Bazot
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Patent number: 10858954Abstract: A turbo-engine module comprises a turbo-engine housing, and a thermal protection shell of the housing. The thermal protection shell is configured to cover at least partially the housing in order to protect same thermally. The module comprises a wear protection strip which is situated between the housing and the thermal protection shell, in a junction region of the housing and the thermal protection shell.Type: GrantFiled: October 18, 2018Date of Patent: December 8, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Olivier Bazot, Jérémy Philippe Pierre Edynak, Farhana Hussain, Fanny Marie Libes
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Patent number: 10837308Abstract: A device for controlling variable-pitch turbomachine members such as stator vanes, wherein the movement of a control mechanism is imparted to a ring that rotates the levers for pivoting the vanes about a stator, and takes place with a possible change in the length of the bottle screw connecting the ring to the control mechanism, thereby allowing the blade pitch angle law to be changed according to the extension of the control device. A greater freedom of adjustment is thus obtained. The device can be useful when a single control mechanism is used for multiple rings arranged side by side, making it possible to have different control laws for the rings.Type: GrantFiled: May 23, 2017Date of Patent: November 17, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Olivier Bazot, Jeremy Philippe Pierre Edynak
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Patent number: 10662805Abstract: A control ring for a stage of variable-pitch vanes for a turbine engine includes at least one member for bearing on a casing and means for fixing the member. The member includes a bushing with an axial bore for the passage of the member or an element for supporting the member. A through-slot opens into the bore and allows for substantial radial deformation of the bushing. The member further includes an outer thread for screwing the bushing into a complementary thread of a hole in the body, thereby deforming the bushing. The member or support can be mounted and moved inside the bore, to a second position, in which the bushing is radially constrained and is tightly mounted on the member or support, which is thus immobilized in relation to the bushing.Type: GrantFiled: June 18, 2019Date of Patent: May 26, 2020Assignee: SNECMAInventors: Jérémy Edynak, Olivier Bazot
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Publication number: 20190330996Abstract: A control ring for a stage of variable-pitch vanes for a turbine engine includes at least one member for bearing on a casing and means for fixing the member. The member includes a bushing with an axial bore for the passage of the member or an element for supporting the member. A through-slot opens into the bore and allows for substantial radial deformation of the bushing. The member further includes an outer thread for screwing the bushing into a complementary thread of a hole in the body, thereby deforming the bushing. The member or support can be mounted and moved inside the bore, to a second position, in which the bushing is radially constrained and is tightly mounted on the member or support, which is thus immobilized in relation to the bushing.Type: ApplicationFiled: June 18, 2019Publication date: October 31, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jérémy Edynak, Olivier Bazot
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Patent number: 10393146Abstract: A flexible metal foil can be fixed on the inside part of a variable pitch vane control ring of a turbojet compressor, so as to close all through holes in which lever pins and their surrounding bushes are housed. As a result, the foil can retain the shank of the bush if the bush breaks. The use of such foil does not impose the development of a new model of control ring and its impact on the mass is small enough so that it does not affect engine performances. Therefore it avoids problems related to the breakage of bushes without having to make major changes to the existing system.Type: GrantFiled: July 3, 2017Date of Patent: August 27, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Olivier Bazot, Jérémy Philippe Pierre Edynak
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Publication number: 20190249561Abstract: A control assembly for a stage of variable-pitch vanes for a turbine engine generally includes an actuating ring having an annular body, a vane guidance means for connecting to the cylindrical pivots of the variable pitch vanes, a rotating means for rotating the actuating ring about a casing of the turbine engine, and a centering means for cooperating with the casing to center the actuating ring. The centering means may have at least one skid bearing against the casing. At least one of the skid or the rod may be configured to cooperate by radial sliding with an inner wall of a housing. The skid may be configured to be mobile during operation by sliding between a radially internal position and a radially external position.Type: ApplicationFiled: February 8, 2019Publication date: August 15, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventor: Olivier Bazot
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Publication number: 20190218929Abstract: A device for controlling variable-pitch turbomachine members such as stator vanes, wherein the movement of a control mechanism is imparted to a ring that rotates the levers for pivoting the vanes about a stator, and takes place with a possible change in the length of the bottle screw connecting the ring to the control mechanism, thereby allowing the blade pitch angle law to be changed according to the extension of the control device. A greater freedom of adjustment is thus obtained. The device can be useful when a single control mechanism is used for multiple rings arranged side by side, making it possible to have different control laws for the rings.Type: ApplicationFiled: May 23, 2017Publication date: July 18, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Olivier BAZOT, Jeremy Philippe Pierre EDYNAK
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Publication number: 20190195239Abstract: An interface member equips a control ring of a high-pressure compressor of an engine. This control ring has at least one housing intended to partially house a guide shoe. This interface member includes a central wall to which two holding tabs are secured, delimiting a through-housing having dimensions substantially identical to the initial dimensions of the housing, and suitable for being inserted into the housing, after it has been machined to receive same following a deformation, until the holding tabs keep it stationary relative to the control ring.Type: ApplicationFiled: August 22, 2017Publication date: June 27, 2019Inventors: Olivier BAZOT, Jérémy Philippe Pierre EDYNAK
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Publication number: 20190120083Abstract: A turbo-engine module comprises a turbo-engine housing, and a thermal protection shell of the housing. The thermal protection shell is configured to cover at least partially the housing in order to protect same thermally. The module comprises a wear protection strip which is situated between the housing and the thermal protection shell, in a junction region of the housing and the thermal protection shell.Type: ApplicationFiled: October 18, 2018Publication date: April 25, 2019Inventors: Olivier BAZOT, Jérémy Philippe Pierre EDYNAK, Farhana HUSSAIN, Fanny Marie LIBES
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Publication number: 20180266267Abstract: A control ring for a stage of variable-pitch vanes for a turbine engine includes at least one member for bearing on a casing and means for fixing the member. The member includes a bushing with an axial bore for the passage of the member or an element for supporting the member. A through-slot opens into the bore and allows for substantial radial deformation of the bushing. The member further include an outer thread for screwing the bushing into a complementary thread of a hole in the body, thereby deforming the bushing. The member or support can be mounted and moved inside the bore, to a second position, in which the bushing is radially constrained and is tightly mounted on the member or support, which is thus immobilized in relation to the bushing.Type: ApplicationFiled: November 24, 2015Publication date: September 20, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jérémy EDYNAK, Olivier BAZOT
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Publication number: 20180003193Abstract: A flexible metal foil can be fixed on the inside part of a variable pitch vane control ring of a turbojet compressor, so as to close all through holes in which lever pins and their surrounding bushes are housed. As a result, the foil can retain the shank of the bush if the bush breaks. The use of such foil does not impose the development of a new model of control ring and its impact on the mass is small enough so that it does not affect engine performances. Therefore it avoids problems related to the breakage of bushes without having to make major changes to the existing system.Type: ApplicationFiled: July 3, 2017Publication date: January 4, 2018Inventors: Olivier BAZOT, Jérémy Philippe Pierre EDYNAK