Patents by Inventor Pierre Guillaume
Pierre Guillaume 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: 9422818Abstract: 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: GrantFiled: June 21, 2011Date of Patent: August 23, 2016Assignee: SNECMAInventors: Stephane Pierre Guillaume Blanchard, Laurent Pierre Joseph Ricou
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Publication number: 20160214708Abstract: Drive equipment for rotating by friction an aircraft wheel equipped with a drive track and mounted to turn about an axis (X) on an axle of an aircraft undercarriage. The equipment comprise a base (22), a slide (24) mounted on the base on a sliding axis extending in a radial direction (R1, R1), a support (26) pivotable on the slide on an axis parallel to the rotation axis of the wheel; two rollers (21) rotatable on rotation axes parallel to the pivot axis; a central shaft (28) mounted for rotation on the support and being in engagement with the two rollers to provide their rotation; and an actuator (23A, 23B, 30) for moving the slide and the support between a disengagement position with the rollers distant from the wheel drive track and an engagement position with the rollers are held in contact with the drive track of the wheel.Type: ApplicationFiled: January 21, 2016Publication date: July 28, 2016Applicant: MESSIER-BUGATTI-DOWTYInventors: Frederic MARTIN, Yves COURTOIS de LOURMEL, Maxence WANGERMEZ, Mathieu DAFFOS, Pierre-Guillaume PHELUT
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Publication number: 20160090855Abstract: A rotating assembly for a turbine engine, comprising a disc having an outer periphery having alternating slots and teeth, blades radially extending from the disc and roots of which are axially engaged in the slots, with spaces called slot cavities being provided between the roots of the blades and the slots, platforms laterally extending from the blades and circumferentially arranged end-to-end, so as to form spaces called inter-blade cavities, and a downstream annular shroud, comprising an outer annular sealing lip opposite the downstream ends of the platforms. The downstream shroud further comprises an intermediate annular sealing lip opposite the downstream faces of the teeth of the disc, radially between the slot cavities and the inter-blade cavities.Type: ApplicationFiled: September 29, 2015Publication date: March 31, 2016Applicant: SnecmaInventors: Maurice Guy Judet, Pierre Guillaume Auzillon, Matthieu Simon
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Patent number: 9194240Abstract: 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: GrantFiled: January 11, 2011Date of Patent: November 24, 2015Assignees: SNECMA, HERAKLESInventors: Stephane Pierre Guillaume Blanchard, Thierry Fachat, Patrick Joseph Marie Girard, Clement Roussille
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Publication number: 20150308279Abstract: 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: ApplicationFiled: April 23, 2015Publication date: October 29, 2015Applicant: SNECMAInventors: Stephane Pierre Guillaume BLANCHARD, Youki Olivier ITO-LARDEAU
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Publication number: 20150263440Abstract: The invention relates to a system (5) for attaching electrical equipment (1) to a metallic support (20) and comprising: a pin (3) designed to be inserted through a through-housing (21) of the metallic support (20) and a metallic insert (10) of the electrical equipment (1), and means (30, 32, 34) of insulating the metallic support (20), extending between the metallic support (20) and the metallic insert (10), and characterized in that it further comprises mechanical retention means (40, 42) designed to apply load to the insulating means (30, 32) so as to keep them in contact with the metallic support (20) and with the metallic insert (10).Type: ApplicationFiled: October 23, 2013Publication date: September 17, 2015Applicant: SNECMAInventors: Sylvain Van Ceulen, Francois Jean Comin, Pierre-Guillaume Bardin
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Patent number: 9016351Abstract: An aircraft includes a heat exchanger between a first fluid that flows into the narrow pipes of the exchanger and that is able to contain solid elements that can melt, and, a second fluid to be cooled. The heat exchanger includes a device for preheating the first fluid upstream from the pipes of the exchanger, a number of pipes arranged in at least one plane that intersects the direction of flow of the first fluid, whereby the spacing between two adjacent pipes is suitable for retaining the solid elements of large dimensions and for allowing them to pass only when they have melted at least partially.Type: GrantFiled: June 1, 2011Date of Patent: April 28, 2015Assignees: Airbus Operations, AirbusInventors: Pierre Guillaume, Patrick Lair
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Publication number: 20140356172Abstract: 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: ApplicationFiled: May 28, 2014Publication date: December 4, 2014Applicant: SNECMAInventors: Josselin Sicard, Helene Barret, Stephane Pierre Guillaume Blanchard, Youki Olivier Ito-Lardeau, Bertrand Pellaton
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Patent number: 8870531Abstract: 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: GrantFiled: December 11, 2009Date of Patent: October 28, 2014Assignee: SNECMAInventors: Stephane Pierre Guillaume Blanchard, Julien Mateo, Stephane Otin
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Patent number: 8864458Abstract: 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: GrantFiled: August 25, 2009Date of Patent: October 21, 2014Assignee: SNECMAInventors: Stephane Pierre Guillaume Blanchard, Mathieu Dakowski, Fabrice Marcel Noel Garin, Maurice Guy Judet
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Patent number: 8757966Abstract: A stationary vane assembly of a turbine engine including an inner casing and a high-pressure turbine guide vane assembly including at least two angular sectors including blades, the angular sectors being fixed on the casing, each angular sector including a platform and a fastening tab. The fastening tab protrudes from the platform radially inwardly. The casing includes a first annular groove receiving the fastening tabs, radial retaining pins for the angular sectors being introduced into bores made in the casing and the fastening tabs, the axial retaining pins being axially stopped by a ring mounted in a second annular groove of the casing.Type: GrantFiled: August 25, 2009Date of Patent: June 24, 2014Assignee: SNECMAInventors: Stéphane Pierre Guillaume Blanchard, Fabrice Marcel Noël Garin, Laurent Pierre Joseph Ricou, Mathieu Dakowski
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Patent number: 8714477Abstract: An aircraft support pylon designed to attach a turbomachine housed in a nacelle to an aircraft fuselage is disclosed. The pylon includes a cooler, located substantially in the vicinity of a leading edge of the pylon, and able to be heated by a hot fluid, the hot fluid intended to be cooled by heat exchange with cold air outside the cooler. The pylon also includes at least one air evacuation duct, at the exit from the cooler and extending longitudinally in an internal volume of the pylon to a trailing edge of the pylon.Type: GrantFiled: April 26, 2011Date of Patent: May 6, 2014Assignee: Airbus Operations S.A.S.Inventors: Christelle Rinjonneau, Pierre Guillaume
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Patent number: 8657234Abstract: A door for an aircraft engine nacelle, comprising an opening leaf, locking device with which the opening leaf may be locked in the closed position, as well a device for setting the opening leaf into motion with which the latter may be displaced from the closed position to the open position. The locking device has a mechanical fuse intended to break under the effect of a force exerted by the opening leaf and resulting from an opening gas pressure being applied on the opening leaf, with a value greater than or equal to a predetermined value and causing displacement of the opening leaf from the closed position to the open position after breakage of the mechanical fuse.Type: GrantFiled: June 3, 2011Date of Patent: February 25, 2014Assignees: Airbus Operations S.A.S., AirbusInventors: Pierre Guillaume, Patrick Lair
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Patent number: 8626364Abstract: The invention relates to method characterized in that said method comprises steps of acquiring movements, calculating the mean position, calculating position predictions, and calculating minimum grid (5) movement speeds, and a step of acquiring the position of the drone (4) so that, if the drone cannot follow the movements of the grid and the movements of the grid are small, i.e. smaller than the radius of the latter, it is possible to apply a landing strategy by monitoring the mean position of the grid, and if the movements of the grid are large, i.e. larger than the radius of the grid, it is possible to apply a landing strategy by positioning at the minimum speeds of the grid, and if the drone (4) can follow the movements of the grid (5) and the movements of the grid are small, i.e. smaller than the radius of the grid, it is possible to apply a landing strategy according to the mean position of the grid, and if the movements of the grid are large, i.e.Type: GrantFiled: October 13, 2009Date of Patent: January 7, 2014Assignee: DCNSInventor: Julien Pierre Guillaume Moresve
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Patent number: 8607454Abstract: A method of fabricating a composite-material turbomachine blade having platform incorporated therein includes separately making a blade platform element that includes rigidified fiber reinforcement and that has a shape close to that of a platform of the blade to be fabricated, with at least one opening being formed through the platform element. The opening has the shape of the profile of the airfoil of the blade to be fabricated. Three-dimensional weaving is used to make a flexible fiber blank as a single piece that includes blade airfoil-and-root preform portions. The platform element is engaged, via its opening, on the flexible fiber blank while deforming it so as to assemble the platform element with the fiber blank. The fiber blank is shaped together with the platform element assembled thereon to obtain a blade preform of a shape that is close to the shape of the blade to be fabricated. After shaping, the blade preform is consolidated in its shape in a shaper.Type: GrantFiled: March 26, 2010Date of Patent: December 17, 2013Assignees: SNECMA, HeraklesInventors: Stephane Pierre Guillaume Blanchard, Eric Bouillon, Dominique Coupe, Hubert Illand, Clement Roussille
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Patent number: 8538133Abstract: This system for guiding a drone during the approach phase to a platform, particularly a naval platform, with a view to landing the same, is characterized in that the platform is equipped with a glide slope indicator installation emitting an array of optical guide beams over an angular sector predetermined from the horizontal, and in that the drone is equipped with a beam acquisition camera connected to image analysis means and to computing means of orders for commanding automatic piloting means of the drone to cause it to follow the guide beams.Type: GrantFiled: October 13, 2009Date of Patent: September 17, 2013Assignee: DCNSInventor: Julien Pierre Guillaume Moresve
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Publication number: 20130156590Abstract: 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: ApplicationFiled: June 21, 2011Publication date: June 20, 2013Applicant: SNECMAInventors: Stephane Pierre Guillaume Blanchard, Laurent Pierre Joseph Ricou
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Patent number: 8448448Abstract: An air bleed device for cooling components in a turbine engine, including an annular conduit having a substantially rectangular cross-section formed in a housing and having a radially internal wall swept by an airflow is disclosed. The device includes an air inlet orifice, and a flap valve for controlling the airflow entering through the orifice, formed by a plate borne by a maneuvering member mobile in translation parallel to the axis of the orifice between a position in which the plate closes off the orifice and a position in which the plate opens the orifice.Type: GrantFiled: June 24, 2009Date of Patent: May 28, 2013Assignee: SNECMAInventors: Stephane Pierre Guillaume Blanchard, Mathieu Dakowski, Thomas Daris, Romain Nicolas Lunel
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Patent number: 8408009Abstract: Air bleed device for cooling components in a turbine engine, including an annular conduit (18) having a radially internal portion swept by an airflow (22) and which comprises at least one air inlet orifice (20) formed in an upstream radial wall (38) of the conduit (18), a flap valve (40) for controlling the airflow entering through the orifice (20) and of which the flapper (41) includes a plate (42) applied against the wall (38) and capable of being moved by sliding on said wall (38) by a maneuvering member (50) mobile in translation parallel to the wall (38) between a position in which the plate (42) closes off the orifice (20) and a position in which the plate (42) opens said orifice.Type: GrantFiled: June 23, 2009Date of Patent: April 2, 2013Assignee: SnecmaInventors: Stephane Pierre Guillaume Blanchard, Mathieu Dakowski, Thomas Daris, Romain Nicolas Lunel
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Patent number: 8397513Abstract: Device (10) for the tapping of air for the cooling of flaps of a turbojet nozzle, comprising an annular duct (18) having a radially internal wall (22) swept by a stream of air (24) and which comprises at least one air inlet orifice (20), a flap valve (40) for controlling the flow rate of air entering through the orifice (20), formed of an elastically deformable metal plate (42) of which a downstream end is fixed on an edge of the orifice (20), and of which an upstream end can be displaced by a manoeuvring member (46) mobile in translation parallel to the axis (52) of the orifice between a position where the plate (42) seals this orifice and a position where the plate (42) opens this orifice.Type: GrantFiled: October 22, 2009Date of Patent: March 19, 2013Assignee: SNECMAInventors: Stephane Pierre Guillaume Blanchard, Mathieu Dakowski, Thomas Daris, Romain Nicolas Lunel