Patents Assigned to SNECMA
  • Patent number: 10662805
    Abstract: 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: Grant
    Filed: June 18, 2019
    Date of Patent: May 26, 2020
    Assignee: SNECMA
    Inventors: Jérémy Edynak, Olivier Bazot
  • Patent number: 10662795
    Abstract: 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: Grant
    Filed: September 23, 2014
    Date of Patent: May 26, 2020
    Assignee: Snecma
    Inventors: Mathieu Louis Jean Leduc, Pierre-Louis Alexandre Carlos, Clement Roussille
  • Patent number: 10539028
    Abstract: 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: Grant
    Filed: November 8, 2011
    Date of Patent: January 21, 2020
    Assignees: SNECMA, HERAKLES
    Inventors: Sylvain Yves Jean Duval, Clement Roussille, Alain Schweitzer, Patrick Joseph Marie Girard
  • Patent number: 10532833
    Abstract: 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: Grant
    Filed: February 26, 2014
    Date of Patent: January 14, 2020
    Assignees: SNECMA, HERAKLES
    Inventors: Olivier Bernard Duchemin, Dominique Indersie, Pascal Benoit Caubet, Pierre Yvart
  • Patent number: 10526906
    Abstract: 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: Grant
    Filed: March 25, 2016
    Date of Patent: January 7, 2020
    Assignee: SNECMA
    Inventors: David Thien-Roger Nguyen, Franck Boisnault, Maurice Guy Judet, Laetitia Person
  • Patent number: 10428733
    Abstract: 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: Grant
    Filed: October 14, 2014
    Date of Patent: October 1, 2019
    Assignees: SNECMA, SOCIETE LORRAINE DE CONSTRUCTION AERONAUTIQUE
    Inventors: Mathieu Ange Poisson, Stéphane Orcel, Guillaume Glemarec, Jean-Luc Pacary
  • Patent number: 10385708
    Abstract: 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: Grant
    Filed: February 9, 2016
    Date of Patent: August 20, 2019
    Assignee: SNECMA
    Inventors: Henri-Marie Damevin, Philippe Jacques Pierre Fessou, Vianney Christophe Marie Maniere, Michael Franck Antoine Schvallinger
  • Patent number: 10267172
    Abstract: 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: Grant
    Filed: September 23, 2014
    Date of Patent: April 23, 2019
    Assignee: Snecma
    Inventors: Mathieu Louis Jean Leduc, Pierre-Louis Alexandre Carlos, Clement Roussille
  • Patent number: 10267164
    Abstract: 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: Grant
    Filed: April 26, 2016
    Date of Patent: April 23, 2019
    Assignee: SNECMA
    Inventors: Caroline Jacqueline Denise Berdou, Alexandre Bernard Marie Boisson, Matthieu Arnaud Gimat, Audrey Laguerre
  • Patent number: 10233837
    Abstract: 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: Grant
    Filed: March 14, 2016
    Date of Patent: March 19, 2019
    Assignee: SNECMA
    Inventors: Cédric Zaccardi, Gwenael Sébastien François Marion
  • Patent number: 10233572
    Abstract: 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: Grant
    Filed: June 29, 2016
    Date of Patent: March 19, 2019
    Assignee: SNECMA
    Inventors: Claire Rousseau, Dominique Michel Serge Magnaudeix, Jérémy Hellot
  • Patent number: 10190655
    Abstract: 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: Grant
    Filed: June 21, 2016
    Date of Patent: January 29, 2019
    Assignee: SNECMA
    Inventors: Alain Roland Luinaud, Alain Decocq, Francois Viviande
  • Publication number: 20190024274
    Abstract: 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: Application
    Filed: September 21, 2018
    Publication date: January 24, 2019
    Applicant: SNECMA
    Inventors: Yann Marchal, Matthieu Gimat, Dominique Coupe, Bruno Dambrine
  • Publication number: 20190009387
    Abstract: 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: Application
    Filed: December 27, 2016
    Publication date: January 10, 2019
    Applicant: Snecma Mexico, S.A. de C.V.
    Inventors: Gumaro RODRIGUEZ, Jesus CAMARENA, Yohannes MARCELET, Jesus MURILLO, Allan PUENTE
  • Patent number: 10144099
    Abstract: 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: Grant
    Filed: August 18, 2014
    Date of Patent: December 4, 2018
    Assignee: SNECMA
    Inventors: Pascal Fabrice Bilhe, Annie Pasquet
  • Patent number: 10125615
    Abstract: 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: Grant
    Filed: November 3, 2015
    Date of Patent: November 13, 2018
    Assignee: SNECMA
    Inventors: Sébastien Serge Francis Congratel, Franck Boisnault, Patrice Jean-Marc Rosset
  • Publication number: 20180304421
    Abstract: A method for cutting a preform usable for production of a turbomachine part and including a weaving of a plurality of threads, the threads including single threads that are visually identifiable, along a cutting contour calculated based on a preform model in which the threads have a reference arrangement, the method including: taking an image of the preform; processing the image to determine a deviation in an arrangement of the threads which are visually identifiable relative to the reference layout; correcting the cutting contour according to the deviation; and cutting the preform along the corrected cutting contour.
    Type: Application
    Filed: June 26, 2018
    Publication date: October 25, 2018
    Applicant: SNECMA
    Inventors: Yann Marchal, Philippe Marolle, Claire Rousseau
  • Patent number: 10066875
    Abstract: A heat exchanger for an air circulation channel of a turbomachine, with the heat exchanger being configured to be passed through by a fluid to be cooled, is provided. The heat exchanger includes a plurality of fins protruding with respect to a support surface, each fin extends axially over a length in the direction of the circulation of air and includes a leading edge and a trailing edge. Each fin further includes a central body, between the leading edge and the trailing edge, with the central body having, in a plane parallel to the support surface, a curved central profile.
    Type: Grant
    Filed: January 26, 2015
    Date of Patent: September 4, 2018
    Assignee: SNECMA
    Inventors: Gabriela Philippart, Imane Ghazlane, Julien Szydlowski
  • Patent number: 10054001
    Abstract: A gearbox for driving equipment of a turbomachine, including a substantially V-shaped box having two arms joined together by a joining part, the arms containing gear trains joined together at the joining part, and an attachment to the turbomachine. The attachment include a mechanism for insetting and/or for attaching the joining part and a suspension device of the arms.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: August 21, 2018
    Assignee: SNECMA
    Inventors: Bruno Albert Beutin, Carmen Ancuta, Lambert Olivier Marie Demoulin
  • Patent number: 10054000
    Abstract: The invention proposes a casing (30) of an aircraft turbine (16), intended to support a set of ring sectors (28) which partly delimits a channel for the passage of a gas stream through the turbine (16), where the casing (30) includes means for dynamic adjustment of the radial position of the ring sectors (28) by controlled injection of an air stream on to portions (36) of an annular wall (34) of the casing (30), where the casing (30) includes an upstream radial tab (38) which connects an upstream end of each ring sector (28), in the flow direction of the gas stream, to the casing (30), and a downstream radial tab (40) which connects a downstream end of each ring sector (28) to the casing (30), where both upstream and downstream radial tabs (38, 40) are made from a single piece with the casing (30), characterized in that each radial tab (38, 40) is made as two portions (42, 44) from different materials.
    Type: Grant
    Filed: August 1, 2014
    Date of Patent: August 21, 2018
    Assignee: SNECMA
    Inventors: Fabrice Marcel Noel Garin, Florence Valerie Bon, Jerome Etienne Robert Cameau, Jean-Marc Michel Lesaine, Alain Paul Madec