Patents by Inventor Philippe Gerard
Philippe Gerard 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: 10598033Abstract: Relates to a vane for a turbomachine. The vane (12?) has a blade (13?) and a root (18?) to be engaged in an axial groove in a disc of the turbomachine. The upstream end (450?) of the root is connected to a radially internal end (430?) of the leading edge (431?) of the blade by the upstream end of a connecting zone having a discontinuity towards the downstream end, so that said radially internal end of the leading edge of the blade is situated further downstream than the upstream end of the root.Type: GrantFiled: September 3, 2015Date of Patent: March 24, 2020Assignee: Safran Aircraft EnginesInventors: Laurent Jablonski, Pierre-Guillaume Bardin, Philippe Gérard Edmond Joly
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Patent number: 10539155Abstract: A propulsive assembly for an aircraft includes a nacelle and a turbojet. The nacelle includes an upstream air inlet section. The turbojet includes a fan with removable blades. The air inlet section extends longitudinally. The fan includes a rotary disk including an annular peripheral wall and a plurality of curvilinear recesses positioned circumferentially in the wall. Each blade includes a blade body extending between a blade root and a blade head in a blade axis which is roughly radial relative to a fan rotation axis. Each blade root includes a curvilinear attachment housed in a respective recess of the rotary disk. Each attachment has a support surface forming an arc. The function of the support surface is to hold the attachment in the recess. The arc extends in or parallel to an attachment plane containing the blade axis or forming with the blade axis an angle of less than 15°.Type: GrantFiled: October 27, 2016Date of Patent: January 21, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventor: Philippe Gérard Chanez
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Patent number: 10518890Abstract: The invention relates to an aircraft propulsion assembly (10), comprising a single gas generator (11) and two fans (12) drive in rotation by the gas generator (11) and offset on either side of a vertical plane passing through a longitudinal axis (X) of the gas generator, the rotational axes of the fans lying substantially in the same fan plane. According to the invention, the propulsion assembly (10) comprises an air inlet fairing formed upstream of a nacelle (25) connecting the fans, said fairing (15) having, between the fans (12), an air inlet opening (17, 17?) lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator (11) with a part of the incoming air and to take off, from the remaining part of the incoming air, a cooling airflow intended to cool elements of the propulsion assembly and/or a wing supporting the propulsion assembly.Type: GrantFiled: November 8, 2016Date of Patent: December 31, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gerard Chanez, Mathieu Patrick Jean-Louis Lallia, Christian Sylvain Vessot
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Patent number: 10502227Abstract: The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream (26) at the radially inner ends of the leading edges of the fan blades (10), divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.Type: GrantFiled: November 26, 2014Date of Patent: December 10, 2019Assignee: Safran Aircraft EnginesInventors: Laurent Jablonski, Philippe Gérard Edmond Joly, Christophe Perdrigeon, Damien Merlot, Hervé Pohier
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Patent number: 10436212Abstract: The invention relates to a fan, in particular for a small turbine engine such as a jet engine, having a hub ratio corresponding to the ratio of the diameter of the inner limit of the air intake section (26) at the radially internal ends of the leading edges of the fan blades (10), divided by the diameter of the circle through which the outer ends of the fan blades pass, which has a value of 0.25 to 0.27.Type: GrantFiled: November 24, 2014Date of Patent: October 8, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Christophe Perdrigeon, Laurent Jablonski, Philippe Gérard Edmond Joly
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Publication number: 20190249683Abstract: The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream at the radially inner ends of the leading edges of the fan blades, divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.Type: ApplicationFiled: April 24, 2019Publication date: August 15, 2019Applicant: Safran Aircraft EnginesInventors: Laurent Jablonski, Philippe Gérard Edmond Joly, Christophe Perdrigeon, Damien Merlot, Hervé Pohier
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Publication number: 20190186270Abstract: The invention relates to an assembly for a turbomachine comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade with a smaller length than the first blade (20), and a damping device (4) attached to the second rotor module (3) and comprising a radial external surface (40) supported with friction against the first module (2), so as to couple the modules (2, 3) for the purpose of damping their respective vibrational movements during operation.Type: ApplicationFiled: December 14, 2018Publication date: June 20, 2019Inventors: Philippe Gerard Edmond JOLY, Francois Jean COMIN, Laurent JABLONSKI, Romain Nicolas LAGARDE, Jean-Marc Claude PERROLLAZ
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Publication number: 20190186276Abstract: The invention relates to a turbomachine assembly (1) comprising: a first rotor module (2) comprising a disk (21), a first blade (20) being mounted on the external periphery of the disk (21), the first blade (20) comprising a platform (25) and a support (27), a second rotor module (3), connected to the first rotor module (2) by means of at least two attachments (22) and comprising a second blade of smaller length than the first blade (20), and a damping device (4) attached to the attachment (22) between the first (2) and the second (3) rotor module so as to dampen their vibrational movements during operation, and comprising: a head (40) comprising a first radial external surface (42) supported with friction against the platform (25), and two attachment feet (41) extending on either side of the support (27) of the first blade (20).Type: ApplicationFiled: December 13, 2018Publication date: June 20, 2019Inventors: Philippe Gerard Edmond JOLY, Francois Jean COMIN, Laurent JABLONSKI, Romain Nicolas LAGARDE, Jean-Marc Claude PERROLLAZ, Charles Jean-Pierre Douguet
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Patent number: 10287065Abstract: The invention relates to a tamper evident closure cap (101). A tamper evident band is provided with an extension (107) having an upper edge (113) extending above an engagement surface (110) of a projection (109). The extension (107) and the projections (109) are arranged on an annular, circumferentially running band (105). When the closure is applied to a container, the extension (107) is clamped between the inner surface (114) of the tamper evident band or the closure and a retaining structure on a container finish.Type: GrantFiled: January 9, 2008Date of Patent: May 14, 2019Assignee: OBRIST CLOSURES SWITZERLAND GMBHInventors: Sebastien Cedric Widmer, Lino Dreyer, Philippe Gerard Odet
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Publication number: 20190010896Abstract: A double flow turbojet includes a fan including a disk centered on an axis of the fan which is provided with fan blades on its periphery, the blades having a leading edge, and an air inlet sleeve extending upstream of the fan and configured to delimit a gas flow designed to enter into the fan the air inlet sleeve having a collecting surface, the turbojet having an aspect ratio S 2 S col included in the interval [ 1.0 ; 1.0 + 0.4 ? ( L D ) ] , where L/D is the form factor of the air inlet sleeve.Type: ApplicationFiled: July 6, 2018Publication date: January 10, 2019Applicant: Safran Aircraft EnginesInventors: Philippe Gerard Chanez, Claude Sensiau
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Publication number: 20180281978Abstract: The present invention relates to an aircraft comprising a fuselage, a lateral support wing (1) and propulsion assembly (100) mounted under the wing, the wing comprising at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream, and the propulsion assembly comprising a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The aircraft is characterized in that the offset fans (102, 104) are attached directly to one of the said spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. In particular, with the leading edge of the wing forming a given sweep of angle (?) with the axis of the fuselage, the two offset fans (102, 104) are axially offset from one another.Type: ApplicationFiled: September 29, 2016Publication date: October 4, 2018Inventors: Bruno Albert BEUTIN, Nicolas Maurice Herve AUSSEDAT, Nicolas Alain BADER, Philippe Gerard CHANEZ, Gilles Alain CHARIER, Mathieu LALLIA, Lionel Jean Leon LEFRANC, Kevin Morgane LEMARCHAND, Herve Jean Albert MOUTON, Nicolas Joseph SIRVIN, Ludovic Michael Laurent TOUPET, Christian Sylvain VESSOT, Nathalie NOWAKOWSKI
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Patent number: 9957096Abstract: The invention relates to a pressurized can, such as an aerosol can, having a bottom comprising a panel connected via a countersink and a foot to the can body wall, which bottom has a panel with a substantially non-concave form.Type: GrantFiled: November 29, 2007Date of Patent: May 1, 2018Assignee: Ardagh MP Group Netherlands B.V.Inventor: Philippe Gérard Stanislas Niec
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Publication number: 20180087389Abstract: A fan blisk for a turbomachine, the blisk comprising a hub delimited by an upstream face and a downstream face in addition to an outer peripheral face and a revolving inner peripheral face delimiting an inner opening, the hub carrying blades each having a leading edge and a trailing edge, the hub and the blades forming a one-piece assembly. The upstream face and/or the downstream face is offset, being located along the axis of rotation (AX) between the leading edges and the trailing edges of the blades, the blisk (bladed disk) comprising a filling member mounted on the offset face, the filling member comprising an inner centring ferrule engaging in the inner face of the hub, a radial portion resting against the offset face and an outer ferrule extending the outer peripheral face of the hub.Type: ApplicationFiled: March 1, 2016Publication date: March 29, 2018Inventors: Philippe Gérard Edmond Joly, François Jean Comin, Laurent Jablonski, Damien Merlot, Jean-Marc Claude Perrollaz
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Patent number: 9863252Abstract: The invention relates to a single-piece fan blisk (14) for a turbojet, this blisk (14) comprising a hub (16) with a general shape of revolution about a rotation axis (AX) and comprising an external peripheral face (18) of revolution extending radially towards the rotation axis at an upstream face (19) and a downstream face both of which are in the form of rings. This hub (16) supports radially oriented blades (17) at its external peripheral face (18), each comprising a base through which it is connected to this external peripheral face (18), each blade (17) having a leading edge (22) and a trailing edge (23) that are radially oriented. The spacing between the upstream face (19) and the downstream face of the hub (16) along the rotation axis (AX) is less than the distance separating the leading edge (22) from the trailing edge (23) of each blade.Type: GrantFiled: November 16, 2015Date of Patent: January 9, 2018Assignee: SNECMAInventors: Damien Merlot, Etienne Ide, Philippe Gérard Edmond Joly
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Publication number: 20170298750Abstract: Relates to a vane for a turbomachine. The vane (12?) has a blade (13?) and a root (18?) to be engaged in an axial groove in a disc of the turbomachine. The upstream end (450?) of the root is connected to a radially internal end (430?) of the leading edge (431?) of the blade by the upstream end of a connecting zone having a discontinuity towards the downstream end, so that said radially internal end of the leading edge of the blade is situated further downstream than the upstream end of the root.Type: ApplicationFiled: September 3, 2015Publication date: October 19, 2017Applicant: Safran Aircraft EnginesInventors: Laurent Jablonski, Pierre-Guillaume Bardin, Philippe Gérard Edmond Joly
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Patent number: 9781017Abstract: The invention relates to a method for managing services on a network, comprising: at least two interconnected computer sites, each of which is capable of implementing at least one service that can be accessed from the network; at least one service implemented on a network site; a capability for transferring a service from an initial site to a separate destination site. Each is associated with security attributes and the method includes transferring at least one service from an initial site to a destination site of the network following a predetermined transfer sequence which depends on the security attributes.Type: GrantFiled: December 21, 2011Date of Patent: October 3, 2017Assignee: THALESInventors: Philippe Gerard Augustin Leleu, Florian Chazal
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Publication number: 20170276145Abstract: The invention relates to a blade, the platform (14) of which has at least one bumper (40) which rises, on the inner face, from a connection to an intermediate area of the blade located along a longitudinal axis of the blade, between the blade root and the outer face (143), towards a free side edge (145) of the platform. The platform bumper (40) locally has a thinned portion at a distance from said free side edge of the platform. The invention is applicable to turboshaft engine fans.Type: ApplicationFiled: September 3, 2015Publication date: September 28, 2017Applicant: Safran Aircraft EnginesInventors: Philippe Gérard Edmond Joly, Damien Merlot, Jean-Marc Claude Perrollaz
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Publication number: 20170167504Abstract: The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream (26) at the radially inner ends of the leading edges of the fan blades (10), divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.Type: ApplicationFiled: November 26, 2014Publication date: June 15, 2017Applicant: SnecmaInventors: Laurent Jablonski, Philippe Gérard Edmond Joly, Christophe Perdrigeon, Damien Merlot, Hervé Pohier
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Publication number: 20170137135Abstract: The invention relates to an aircraft propulsion assembly (10), comprising a single gas generator (11) and two fans (12) drive in rotation by the gas generator (11) and offset on either side of a vertical plane passing through a longitudinal axis (X) of the gas generator, the rotational axes of the fans lying substantially in the same fan plane. According to the invention, the propulsion assembly (10) comprises an air inlet fairing formed upstream of a nacelle (25) connecting the fans, said fairing (15) having, between the fans (12), an air inlet opening (17, 17?) lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator (11) with a part of the incoming air and to take off, from the remaining part of the incoming air, a cooling airflow intended to cool elements of the propulsion assembly and/or a wing supporting the propulsion assembly.Type: ApplicationFiled: November 8, 2016Publication date: May 18, 2017Inventors: Philippe Gerard CHANEZ, Mathieu Patrick Jean-Louis LALLIA, Christian Sylvain VESSOT
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Publication number: 20170137134Abstract: An aircraft propulsion assembly, comprising a gas generator and two fans rotated by the gas generator and offset on either side of a vertical plane passing through the axis of said gas generator. The propulsion assembly comprises an air inlet sleeve comprising an inlet pipe oriented along a first axis that is substantially parallel and offset with respect to a longitudinal axis of the gas generator, the inlet pipe dividing into a supply pipe that is connected to an inlet opening of the gas generator and a discharge pipe configured such that particles ingested by the inlet pipe are discharged without entering the gas generator.Type: ApplicationFiled: November 11, 2016Publication date: May 18, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Christian Sylvain Vessot, Bruno Albert Beutin, Philippe Gérard Chanez, Mathieu Patrick Jean-Louis Lallia