Patents by Inventor Stéphane Pierre Guillaume Blanchard

Stéphane Pierre Guillaume Blanchard 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).

  • Publication number: 20210054743
    Abstract: The invention relates to an assembly (1) for a turbine of a turbomachine, comprising: a first rotor disk (20a), a second rotor disk (20b), a part forming a mobile ring (28), comprising a system for preventing rotation of the mobile ring (28) relative to the rotor disks (20a, 20b), said system comprising: a rotor disk securing flange (222) having a plurality of teeth (224) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), and a mobile ring securing flange (282) having a plurality of lugs (284) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), the engagement of the rotor disk securing flange (222) with the mobile ring securing flange (282) ensuring, by means of the teeth (224) and the lugs (284), that the mobile ring (28) does not rotate relative to the rotor disks (20a, 20b).
    Type: Application
    Filed: January 29, 2019
    Publication date: February 25, 2021
    Applicant: Safran Aircraft Engines
    Inventors: Stéphane Pierre Guillaume BLANCHARD, Nicolas Xavier TRAPPIER, Quentin DE RICHAUD
  • Patent number: 10920609
    Abstract: A turbine assembly for a turbine engine, includes a rotor disk having a plurality of CMC material blades, a stationary nozzle made of CMC material having a plurality of vanes with outer platforms forming a nozzle ring, a turbine ring made as a single piece of CMC material, and a casing of material presenting a coefficient of thermal expansion that is strictly greater than the coefficient of thermal expansion of the ceramic matrix composite material forming the blades of the rotor disk, the nozzle, and the turbine ring, the casing extending around the nozzle ring and the turbine ring, at least the nozzle ring or the turbine ring being connected to the casing via at least one sliding connection having a degree of freedom to move radially.
    Type: Grant
    Filed: April 24, 2018
    Date of Patent: February 16, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Hélène Myriam Condat, Stéphane Pierre Guillaume Blanchard, Sylvain Yves Jean Duval
  • Patent number: 10767505
    Abstract: A tubular shaft (8) of a turbomachine, including at the inner periphery of same, a bath (11), substantially perpendicular to splines (9), the bath (11) includes cavities (17) distributed over a circumference centred on an axis of rotation (LL) of the shaft (8).
    Type: Grant
    Filed: August 28, 2015
    Date of Patent: September 8, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Youki Olivier Ito-Lardeau, Pierrick Raphael Americo Bauduin, Stephane Pierre Guillaume Blanchard, Bertrand Guillaume Robin Pellaton
  • Publication number: 20200182058
    Abstract: A device for holding (101) at least one cooling tube (120) of a turbomachine casing (10) cooling system (100), the holding device including a fixing frame (104), a holding member (160) being configured to hold two cooling tubes (120), and a connection assembly (140) between the holding member (160) and a fixing frame (104), extending on either side of the frame, the connection assembly (160) comprising a connection part (150) extending through an opening (108) of the fixing frame from an outer portion (141) to the inner portion (142) of the connection assembly, the inner portion (142) being disposed between two cooling tubes (120) and secured to the holding member (160) while the outer portion (141) comprises a resilient return member (170) urged in compression towards the fixing frame by the connection part (150).
    Type: Application
    Filed: December 5, 2019
    Publication date: June 11, 2020
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Simon Nicolas MORLIERE, Nicolas Jean-Marc Marcel BEAUQUIN, Stéphane Pierre Guillaume BLANCHARD, Gaëlle Inès Méganne MOREAUX
  • Patent number: 10598031
    Abstract: A turbine rotor is fitted to a turbomachine and includes disks each containing a coupling portion with recesses each holding a root of a blade, and coupled to one another by a first annular ferrule attached to one of them close to the recesses, and second rotationally coupled ferrules, which are respectively coupled radially to the disks, which each consists of at least two semi-annular sectors, and which form with the associated disk a space which communicates with the recesses of the coupling portion of this latter disk. In addition, each first ferrule includes through-holes enabling air to enter this space, and then the recesses, intended to cool the coupling portion which couples its disk and the blade roots.
    Type: Grant
    Filed: September 8, 2017
    Date of Patent: March 24, 2020
    Assignee: SAFRAN AIRCTAFT ENGINES
    Inventors: Stéphane Pierre Guillaume Blanchard, Joao Antonio Amorim, Maxime Aurélien Rotenberg, Nicolas Xavier Trappier
  • Patent number: 10385706
    Abstract: The invention relates to a rotary assembly for a turbomachine, comprising: a disk (16) having an external periphery exhibiting an alternation of slots (22) and of teeth (20), vanes (14) extending radially from the disk (16), the roots (24) of which are engaged axially and retained radially in the slots (22) of the disk, upstream and/or downstream of the disk, an annular sealing flange (52) of cavities (36) formed radially between, respectively, the roots of the vanes and the bottoms of the slots of the disk, said flange comprising an external part (56) arranged axially facing the upstream and/or downstream ends, respectively, of the teeth of the disk and of the roots of the vanes.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: August 20, 2019
    Assignee: Safran Aircraft Engines
    Inventors: Stéphane Pierre Guillaume Blanchard, Youki Olivier Ito-Lardeau
  • Patent number: 10301972
    Abstract: A turbine comprising an intermediate casing axially inserted between an upstream high pressure turbine casing and a downstream low pressure turbine casing and comprising an outer annular shroud from which an annular flange radially extends, characterized in that the downstream end of the high pressure turbine casing and the upstream end of the low pressure turbine casing are attached on the radial annular flange of the intermediate casing.
    Type: Grant
    Filed: September 5, 2017
    Date of Patent: May 28, 2019
    Assignee: Safran Aircraft Engines
    Inventors: Stéphane Pierre Guillaume Blanchard, Hélène Myriam Condat
  • Publication number: 20180306057
    Abstract: A turbine assembly for a turbine engine, includes a rotor disk having a plurality of CMC material blades, a stationary nozzle made of CMC material having a plurality of vanes with outer platforms forming a nozzle ring, a turbine ring made as a single piece of CMC material, and a casing of material presenting a coefficient of thermal expansion that is strictly greater than the coefficient of thermal expansion of the ceramic matrix composite material forming the blades of the rotor disk, the nozzle, and the turbine ring, the casing extending around the nozzle ring and the turbine ring, at least the nozzle ring or the turbine ring being connected to the casing via at least one sliding connection having a degree of freedom to move radially.
    Type: Application
    Filed: April 24, 2018
    Publication date: October 25, 2018
    Inventors: Hélène Myriam CONDAT, Stéphane Pierre Guillaume BLANCHARD, Sylvain Yves Jean DUVAL
  • Publication number: 20180066540
    Abstract: A turbine comprising an intermediate casing axially inserted between an upstream high pressure turbine casing and a downstream low pressure turbine casing and comprising an outer annular shroud from which an annular flange radially extends, characterized in that the downstream end of the high pressure turbine casing and the upstream end of the low pressure turbine casing are attached on the radial annular flange of the intermediate casing.
    Type: Application
    Filed: September 5, 2017
    Publication date: March 8, 2018
    Applicant: Safran Aircraft Engines
    Inventors: Stéphane Pierre Guillaume Blanchard, Hélène Myriam Condat
  • Publication number: 20180066528
    Abstract: A turbine rotor is fitted to a turbomachine and includes disks each containing a coupling portion with recesses each holding a root of a blade, and coupled to one another by a first annular ferrule attached to one of them close to the recesses, and second rotationally coupled ferrules, which are respectively coupled radially to the disks, which each consists of at least two semi-annular sectors, and which form with the associated disk a space which communicates with the recesses of the coupling portion of this latter disk. In addition, each first ferrule includes through-holes enabling air to enter this space, and then the recesses, intended to cool the coupling portion which couples its disk and the blade roots.
    Type: Application
    Filed: September 8, 2017
    Publication date: March 8, 2018
    Inventors: Stéphane Pierre Guillaume BLANCHARD, Joao Antonio AMORIM, Maxime Aurélien ROTENBERG, Nicolas Xavier TRAPPIER
  • Patent number: 9784114
    Abstract: A rotating assembly for a turbomachine, including a disc having an external periphery with alternating recesses and teeth, blades extending radially from the disc and the feet of which are axially engaged and radially retained in the recesses of the disc, platforms extending on the circumference from the blades and being arranged end to end on the circumference, with respect to each other, axial sealing device upstream and/or downstream of an annular zone extending radially from the platforms up to the disc. The sealing device radially includes an internal annular portion and an external annular portion structurally distinct from each other, and the external annular portion of which is elastically constrained radially inwards by the internal annular portion.
    Type: Grant
    Filed: April 23, 2015
    Date of Patent: October 10, 2017
    Assignee: SNECMA
    Inventors: Stephane Pierre Guillaume Blanchard, Youki Olivier Ito-Lardeau
  • Publication number: 20170254213
    Abstract: The invention concerns a tubular shaft (8) of a turbomachine, comprising, at the inner periphery of same, a bath (11), substantially perpendicular to said splines (9), characterised in that said bath (11) comprises cavities (17) distributed over a circumference centred on the axis of rotation (LL) of the shaft (8). The invention also concerns an assembly comprising said turbomachine shaft, a turbomachine and a method for detecting an oil imbalance.
    Type: Application
    Filed: August 28, 2015
    Publication date: September 7, 2017
    Inventors: Youki Olivier ITO-LARDEAU, Pierrick Raphael Americo BAUDUIN, Stephane Pierre Guillaume BLANCHARD, Bertrand Guillaume Robin PELLATON
  • Publication number: 20170218781
    Abstract: The invention relates to a rotary assembly for a turbomachine, comprising: a disk (16) having an external periphery exhibiting an alternation of slots (22) and of teeth (20), vanes (14) extending radially from the disk (16), the roots (24) of which are engaged axially and retained radially in the slots (22) of the disk, upstream and/or downstream of the disk, an annular sealing flange (52) of cavities (36) formed radially between, respectively, the roots of the vanes and the bottoms of the slots of the disk, said flange comprising an external part (56) arranged axially facing the upstream and/or downstream ends, respectively, of the teeth of the disk and of the roots of the vanes.
    Type: Application
    Filed: June 24, 2015
    Publication date: August 3, 2017
    Applicant: Safran Aircraft Engines
    Inventors: Stéphane Pierre Guillaume Blanchard, Youki Olivier Ito-Lardeau
  • Patent number: 9650895
    Abstract: A turbine wheel including a plurality of blades having roots engaged axially and held radially in slots in a disk alternating between teeth of the disk, in which the blades have platforms arranged circumferentially end to end and each connected to a blade root by a tang, is provided. Separator walls extend from the tangs in a circumferential direction and from upstream to downstream so as to define radially between the platforms and the teeth of the disk at least a radially inner cavity and a radially outer cavity between two adjacent tangs.
    Type: Grant
    Filed: May 28, 2014
    Date of Patent: May 16, 2017
    Assignee: SNECMA
    Inventors: Josselin Sicard, Helene Barret, Stephane Pierre Guillaume Blanchard, Youki Olivier Ito-Lardeau, Bertrand Pellaton
  • Patent number: 9422818
    Abstract: A rotor wheel for a gas turbine engine, the wheel including: a metal holder disk including a plurality of teeth at its periphery, the teeth extending radially outwards from the disk; a plurality of composite material blades, each blade including a root engaged between two adjacent teeth of the holder disk and that is held against the teeth by a pivot connection; a clamp disk including a plurality of teeth at its periphery extending in an axial direction, the clamp disk being fastened against the holder disk and on the same axis, with each of its teeth taking up a circumferential position between a blade root and a tooth of the holder disk; and a mechanism exerting a clamping force in a circumferential direction urging the teeth of the clamp disk against the blade roots.
    Type: Grant
    Filed: June 21, 2011
    Date of Patent: August 23, 2016
    Assignee: SNECMA
    Inventors: Stephane Pierre Guillaume Blanchard, Laurent Pierre Joseph Ricou
  • Patent number: 9194240
    Abstract: A vibration damper between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel, the damper including a peg having a substantially spherical portion at each of its two ends, and two hollow inserts for being received in tangential cavities that are provided facing each other in outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel, each spherical portion of the peg coming to bear with point contact against the inside of one of the inserts.
    Type: Grant
    Filed: January 11, 2011
    Date of Patent: November 24, 2015
    Assignees: SNECMA, HERAKLES
    Inventors: Stephane Pierre Guillaume Blanchard, Thierry Fachat, Patrick Joseph Marie Girard, Clement Roussille
  • Publication number: 20150308279
    Abstract: A rotating assembly for a turbomachine, including a disc having an external periphery with alternating recesses and teeth, blades extending radially from the disc and the feet of which are axially engaged and radially retained in the recesses of the disc, platforms extending on the circumference from the blades and being arranged end to end on the circumference, with respect to each other, axial sealing device upstream and/or downstream of an annular zone extending radially from the platforms up to the disc. The sealing device radially includes an internal annular portion and an external annular portion structurally distinct from each other, and the external annular portion of which is elastically constrained radially inwards by the internal annular portion.
    Type: Application
    Filed: April 23, 2015
    Publication date: October 29, 2015
    Applicant: SNECMA
    Inventors: Stephane Pierre Guillaume BLANCHARD, Youki Olivier ITO-LARDEAU
  • Publication number: 20140356172
    Abstract: The invention relates to a turbine wheel (104) comprising a plurality of blades having roots engaged axially and held radially in slots (34) in a disk (22) alternating between teeth (36) of the disk (22), the blades having platforms (100) arranged circumferentially end to end and each connected to a blade root (26) by a tang (102). According to the invention, separator walls (90) extend from the tangs (102) in a circumferential direction and from upstream to downstream so as to define radially between the platforms (100) and the teeth (36) of the disk at least a radially inner cavity (92) and a radially outer cavity (94) between two adjacent tangs.
    Type: Application
    Filed: May 28, 2014
    Publication date: December 4, 2014
    Applicant: SNECMA
    Inventors: Josselin Sicard, Helene Barret, Stephane Pierre Guillaume Blanchard, Youki Olivier Ito-Lardeau, Bertrand Pellaton
  • Patent number: 8870531
    Abstract: The invention provides a turbine machine rotor having blades of composite material, the rotor comprising an assembly disk, a plurality of composite material blades mounted on the assembly disk via their roots and each provided at its free end with a platform, and a metal shroud positioned on the blade platforms concentrically around the assembly disk and including labyrinth teeth that project radially outwards in order to abrade an abradable material carried by a casing surrounding the rotor, the casing being held stationary both axially and circumferentially relative to the blade platforms and being suitable for moving radially outwards in operation relative to the blade platforms.
    Type: Grant
    Filed: December 11, 2009
    Date of Patent: October 28, 2014
    Assignee: SNECMA
    Inventors: Stephane Pierre Guillaume Blanchard, Julien Mateo, Stephane Otin
  • Patent number: 8864458
    Abstract: A stationary vane assembly for a turbine engine including an inner casing and at least two angular sectors forming a high-pressure guide vane assembly, each angular sector including a fastening tab for fastening the angular sector on the casing. The stationary vane assembly including a ring of abradable material fixed on the casing, on the side of a mobile vane assembly using a plurality of screw-nut assemblies, the stationary vane assembly also including radial retaining pins for the angular sectors introduced into first bores formed in the fastening tabs and in the mounting clip, the bores having axes substantially parallel to the longitudinal axis, the mounting clip being fixed on the casing by the same screw-nut assemblies as those fixing the ring of abradable material support on the casing.
    Type: Grant
    Filed: August 25, 2009
    Date of Patent: October 21, 2014
    Assignee: SNECMA
    Inventors: Stephane Pierre Guillaume Blanchard, Mathieu Dakowski, Fabrice Marcel Noel Garin, Maurice Guy Judet