Patents Assigned to SNECMA
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Patent number: 11460040Abstract: A blade including at least one web and a vane having a leading edge and a trailing edge, wherein, for at least one aerofoil of the vane in the vicinity of the web, a maximum sweep angle associated with a position along a chord of the aerofoil extending from the leading edge to the trailing edge of the vane corresponding to a relative chord length of at least 50%.Type: GrantFiled: February 4, 2016Date of Patent: October 4, 2022Assignee: SNECMAInventors: Guillaume Olivier Vartan Martin, Alexandre Bernard Marie Boisson, Claire Marie Figeureu, Frederic Alain Edouard Allair, Thea Claire Lancien
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Patent number: 10883422Abstract: The invention relates to a turbine engine, comprising: a device for bleeding a compressor, particularly a high-pressure compressor, comprising at least one valve for bleeding said compressor, an outlet of said valve being connected to a bleed system designed to discharge a bleed airflow; and at least one device for cooling at least one unit, comprising a heat exchanger, an air outlet of which is connected to an ejector of the jet pump type, which comprises a feed-through duct for a secondary airflow coming from said air outlet, as well as a nozzle for spraying a primary airflow inside said feed-through duct, wherein the nozzle is connected to said bleed system.Type: GrantFiled: November 24, 2015Date of Patent: January 5, 2021Assignee: SNECMAInventors: Benissa Boujida, Daniel Bernava, Dominik Igel, Maxime Aurélien Rotenberg
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Patent number: 10870147Abstract: A method for knocking out a foundry core confined in an internal cavity in a part at the end of a casting operation, in particular a lost-wax casting operation, includes at least a primary chemical knocking-out step. During the primary chemical knowing-out step, the part is subjected to a chemical solution to dissolve the core, in a sealed enclosure. The method further includes a secondary step of knocking out by ultrasounds in water or an aqueous solution contained in an ultrasound tank, during which the part is subjected to ultrasounds to loosen core residues from walls of the cavity.Type: GrantFiled: May 19, 2016Date of Patent: December 22, 2020Assignee: SNECMAInventors: Didier Ballant, Patrick Fauvelliere, Vincent Kaleta, Yann Margutti, Jean-Paul Parlange
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Patent number: 10738654Abstract: An annular cap for collecting lubricating oil for turbomachine equipment is configured to extend around the equipment and to rotate about an axis. The cap includes through-orifices through which the oil can pass radially under the effect of spinning. The cap further includes means of deflecting the oil leaving the orifices in a direction substantially transverse to the axis and substantially tangential to the cap.Type: GrantFiled: October 13, 2015Date of Patent: August 11, 2020Assignee: SNECMAInventors: Catherine Pikovsky, Benoit Guillaume Farvacque, Serge René Morreale, Mathieu Jean Pierre Trohel
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Patent number: 10662795Abstract: The invention concerns a rotary assembly for a turbomachine, comprising a disk of which the outer periphery is formed from an alternation of cavities and teeth (12), and blades extending radially from the disk and of which the roots (16) are engaged axially and held radially in the cavities of the disk. According to the invention, the teeth of the disk and the blade roots comprise, at the upstream and/or downstream axial ends of same, axial shoulders (74, 76) disposed circumferentially end-to-end in alternation and together forming a cylindrical surface (78) facing radially towards the inside of the disk.Type: GrantFiled: September 23, 2014Date of Patent: May 26, 2020Assignee: SnecmaInventors: Mathieu Louis Jean Leduc, Pierre-Louis Alexandre Carlos, Clement Roussille
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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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Patent number: 10539028Abstract: A method optimizing a composite material blade profile for a rotor wheel of a turbine engine, and a blade including a tang compensated by the method. The method includes: compensating a blade airfoil by subdividing the airfoil into slices, and for each airfoil slice and a predetermined rotation speed of a disk of the wheel, calculating centrifugal force applied to the slice, calculating an aerodynamic force moment acting on a bottom section of the slice, and calculating shift values to be applied to a center of gravity of the slice to cancel the aerodynamic force moment; and compensating the blade tang by calculating centrifugal force applied to a blade portion situated beyond the airfoil neck, calculating an aerodynamic force moment acting on a bottom section of the blade tang, and calculating shift values to be applied to a center of gravity of the blade tang to cancel the aerodynamic force moment.Type: GrantFiled: November 8, 2011Date of Patent: January 21, 2020Assignees: SNECMA, HERAKLESInventors: Sylvain Yves Jean Duval, Clement Roussille, Alain Schweitzer, Patrick Joseph Marie Girard
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Patent number: 10532833Abstract: A space propulsion module for fitting to spacecraft is provided. The space propulsion module includes a solid propellant chemical thruster including a main body, and at least one electric thruster. The at least one electric thruster is mounted on main body of the solid propellant chemical thruster.Type: GrantFiled: February 26, 2014Date of Patent: January 14, 2020Assignees: SNECMA, HERAKLESInventors: Olivier Bernard Duchemin, Dominique Indersie, Pascal Benoit Caubet, Pierre Yvart
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Patent number: 10526906Abstract: A turbine blade for an aircraft turbomachine including a root, an airfoil and a platform inserted between the airfoil and the root and delimiting a gas circulation flowpath, the platform having two axial ends each forming an angel wing of which at least one has an internal cavity that will be supplied with air from the root of the blade. At least one of the two angel wings is drilled with at least one bleed hole for passage of a bleed flow from the internal cavity that will limit/prevent gas recirculation outside the flowpath.Type: GrantFiled: March 25, 2016Date of Patent: January 7, 2020Assignee: SNECMAInventors: David Thien-Roger Nguyen, Franck Boisnault, Maurice Guy Judet, Laetitia Person
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Patent number: 10428733Abstract: A turboprop includes a rotary propeller upstream from an engine and an air intake that is not coaxial to the propeller, said air intake defining a conduit for supplying air to the engine and further defining a bypass to said conduit, the bypass having an outlet oriented substantially axially towards the downstream of the engine. The turboprop further includes a nacelle surrounding the engine and the air intake, wherein the air intake is secured to a housing of the engine and is not rigidly connected to the nacelle, so as to allow, during operation, relative movements between the air intake and the nacelle. The outlet is connected by a flexible link to an intake of an air circuit carried by the nacelle.Type: GrantFiled: October 14, 2014Date of Patent: October 1, 2019Assignees: SNECMA, SOCIETE LORRAINE DE CONSTRUCTION AERONAUTIQUEInventors: Mathieu Ange Poisson, Stéphane Orcel, Guillaume Glemarec, Jean-Luc Pacary
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Patent number: 10385708Abstract: The invention relates to a turbine engine air flow guide assembly including: a structural arm (30); and a guide vane (21) on the lower surface of the structural arm, comprising a leading edge (22), a trailing edge (23), and a camber line (24), said vane and arm extending radially about an axis (X-X) of the turbine engine and defining therebetween an air flow channel. The structural arm (30) comprises: an upstream end (31) having a guide vane profile (21) and comprising a leading edge (32) aligned with that of the vane; and a shoulder (35) located on the lower surface of the arm, defining a neck in the channel. The assembly is characterized in that the area (Aneck) of the section of the channel at the neck is between 0.7 and 0.9 times the area (Ainlet) of the section of the channel at the leading edges.Type: GrantFiled: February 9, 2016Date of Patent: August 20, 2019Assignee: SNECMAInventors: Henri-Marie Damevin, Philippe Jacques Pierre Fessou, Vianney Christophe Marie Maniere, Michael Franck Antoine Schvallinger
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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: 10267172Abstract: The invention concerns a rotary assembly for a turbomachine, comprising: a disc (16) having an external periphery having an alternation of slots (22) and teeth (20), blades (14) extending radially from the disc (16), and the roots (24) of which are engaged axially and held radially in the slots (22) of the disc, platforms (30) extending circumferentially from the blades (14) and which are arranged circumferentially end to end, opposite each other, axial sealing means upstream and/or downstream of an annular zone extending radially from the platforms (30) as far as the disc (16). According to the invention, the sealing means comprise radially an internal annular part (64) and an external annular part (66) structurally separate from each other, and the facing radial ends of which are adapted for a relative radial movements by sliding sealingly, only an absorption of the centrifugal forces of the external part (66) being provided rotationally by the platforms (30).Type: GrantFiled: September 23, 2014Date of Patent: April 23, 2019Assignee: SnecmaInventors: Mathieu Louis Jean Leduc, Pierre-Louis Alexandre Carlos, Clement Roussille
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Patent number: 10233572Abstract: A warp yarn take-up system includes a clamping device for holding a plurality of layers of warp yarns, the clamping device being movable at least in a direction corresponding to the advance direction of the warp yarns. The clamping device includes a bottom clamp, a top clamp, and at least one intermediate clamping element present between the bottom clamp and the top clamp. The bottom clamp, the top clamp, and the at least one intermediate clamping element are held together by clamping.Type: GrantFiled: June 29, 2016Date of Patent: March 19, 2019Assignee: SNECMAInventors: Claire Rousseau, Dominique Michel Serge Magnaudeix, Jérémy Hellot
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Patent number: 10233837Abstract: The present invention relates to an assembly (20) for an aircraft turbine engine comprising a fan casing (14) having an inner surface (14b), at least one acoustic panel (26) fastened using fastening elements (48, 54) to the inner surface of the fan casing, and at least one circumferential stiffener (40) of the fan casing (14). According to the invention, the fastening elements (48, 54) connect the fan casing (14) to the stiffener (40) incorporated with the acoustic panel (26).Type: GrantFiled: March 14, 2016Date of Patent: March 19, 2019Assignee: SNECMAInventors: Cédric Zaccardi, Gwenael Sébastien François Marion
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Patent number: 10190655Abstract: Tooling for balancing a turbine engine module (10) in a balancing machine, the turbine engine module having at least one stator housing (14) and a rotor (16) having a shaft (18) with a longitudinal axis A and at least one blade stage (20) surrounded by the stator housing (14). The tooling has at least a balancing frame (14), having rotor (16) guide bearings, first and second annular plates (30, 32) designed to be attached to the stator housing (14), third and fourth attachment lugs (34, 36) provided on the balancing frame (24), to attach the first and second annular plates (30, 32) to the frame. A trolley is for transporting the frame (24), and a support (84, 94) for supporting the frame, provided on the balancing frame (24) and cooperating equally well with the balancing machine and with the trolley.Type: GrantFiled: June 21, 2016Date of Patent: January 29, 2019Assignee: SNECMAInventors: Alain Roland Luinaud, Alain Decocq, Francois Viviande
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Publication number: 20190024274Abstract: A fiber blank woven as a single piece by three-dimensional weaving to make a closed box-structure platform out of composite material for a turbine engine fan. In each plane of the fiber blank, a set of warp yarns interlinks layers of weft yarns in first, second, and third portions of the fiber blank, while leaving a closed non-interlinked zone separating the first and second portions over a fraction of the dimension of the fiber blank in the warp direction between an upstream non-interlinking limit and a downstream non-interlinking limit, and while leaving at least one open non-interlinked zone separating the second and third portions over a fraction of the dimension of the fiber blank in the warp direction from a non-interlinking limit to a downstream edge of the fiber blank. A method of fabricating a preform for the closed box-structure platform can use such a fiber blank.Type: ApplicationFiled: September 21, 2018Publication date: January 24, 2019Applicant: SNECMAInventors: Yann Marchal, Matthieu Gimat, Dominique Coupe, Bruno Dambrine
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Publication number: 20190009387Abstract: A guard for a part to be shot-blasted and having an axis of revolution, the guard including: a cover and a chamber shaped for receiving the part to be shot-blasted; the chamber having at least one planar section with a shape matching at least one planar section of the cover; two side guards mounted on the part to be shot-blasted and having one degree of freedom relative to the chamber and the cover, wherein the cover, the chamber and the two side guards form a box for sealing the shot, the box including a window for projecting the shot, the surface of which matches a portion of a surface of the chamber.Type: ApplicationFiled: December 27, 2016Publication date: January 10, 2019Applicant: Snecma Mexico, S.A. de C.V.Inventors: Gumaro RODRIGUEZ, Jesus CAMARENA, Yohannes MARCELET, Jesus MURILLO, Allan PUENTE
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Patent number: 10144099Abstract: A method for assembling two blades of a turbomachine nozzle, includes positioning a first surface of a first blade and a second surface of a second blade facing one another, the first and second surfaces being spaced apart from one another by an assembly clearance, and vapor phase aluminizing the first and second surfaces so as to fill the assembly clearance.Type: GrantFiled: August 18, 2014Date of Patent: December 4, 2018Assignee: SNECMAInventors: Pascal Fabrice Bilhe, Annie Pasquet
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Patent number: 10125615Abstract: A turbine wheel for a turbine engine comprising a disc carrying blades. Each blade comprises an upstream radial wall and a downstream radial wall which extend inwards from the platform of the blade. Inter-blade cavities each accommodate one inter-blade sealing and vibration damping member. According to the invention, each inter-blade sealing and vibration damping member comprises at least a first transverse partition wall axially arranged at a distance from a downstream (or upstream, respectively) portion of the member and axially opposite two upstream (or downstream, respectively) so as to obstruct a flow of incoming air into the cavity between two adjacent upstream radial walls or two adjacent downstream radial walls.Type: GrantFiled: November 3, 2015Date of Patent: November 13, 2018Assignee: SNECMAInventors: Sébastien Serge Francis Congratel, Franck Boisnault, Patrice Jean-Marc Rosset