Patents by Inventor HERVÉ POHIER

HERVÉ POHIER 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).

  • Fan for a turbomachine
    Patent number: 11209012
    Abstract: 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: Grant
    Filed: April 24, 2019
    Date of Patent: December 28, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Laurent Jablonski, Philippe Gérard Edmond Joly, Christophe Perdrigeon, Damien Merlot, Hervé Pohier
  • Fan for a turbomachine
    Patent number: 10502227
    Abstract: 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: Grant
    Filed: November 26, 2014
    Date of Patent: December 10, 2019
    Assignee: Safran Aircraft Engines
    Inventors: Laurent Jablonski, Philippe Gérard Edmond Joly, Christophe Perdrigeon, Damien Merlot, Hervé Pohier
  • Balanced turbine engine portion and turbine engine
    Patent number: 10415424
    Abstract: A balanced turbomachine part including one angular sector arranged to form a balancing ring centered about a ring axis. The angular sector includes a plurality of fasteners, a bearing face having a complementary shape to the balancing ring, the angular sector bearing on the bearing face. The part further includes a plurality of balancing masses each fastened to the corresponding fastener of the angular sector, at least one of the balancing masses also acting as a fastener for fastening the angular sector on the bearing face.
    Type: Grant
    Filed: November 24, 2014
    Date of Patent: September 17, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Jean-Luc Le Strat, Herve Pohier
  • FAN FOR A TURBOMACHINE
    Publication number: 20190249683
    Abstract: 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: Application
    Filed: April 24, 2019
    Publication date: August 15, 2019
    Applicant: Safran Aircraft Engines
    Inventors: Laurent Jablonski, Philippe Gérard Edmond Joly, Christophe Perdrigeon, Damien Merlot, Hervé Pohier
  • Balancing screw, device and method for a rotating part of a turbine engine
    Patent number: 9970298
    Abstract: A balancing device for a rotating part of a turbomachine, includes a ferrule pierced with a plurality of ports, a balancing screw passing through each port, each balancing screw including a body and a head, the head of each balancing screw being pierced with a recess, the balancing screws being of at least one first type, the recess of the screws of the first type being formed by a driving recess from which an additional recess extends.
    Type: Grant
    Filed: January 6, 2014
    Date of Patent: May 15, 2018
    Assignee: SNECMA
    Inventors: Jean-Luc Le Strat, Hervé Pohier, Romain Jean-Louis Robert Thory
  • FAN FOR A TURBOMACHINE
    Publication number: 20170167504
    Abstract: 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: Application
    Filed: November 26, 2014
    Publication date: June 15, 2017
    Applicant: Snecma
    Inventors: Laurent Jablonski, Philippe Gérard Edmond Joly, Christophe Perdrigeon, Damien Merlot, Hervé Pohier
  • BALANCED TURBINE ENGINE PORTION AND TURBINE ENGINE
    Publication number: 20160290156
    Abstract: A balanced turbomachine part including one angular sector arranged to form a balancing ring centered about a ring axis. The angular sector includes a plurality of fasteners, a bearing face having a complementary shape to the balancing ring, the angular sector bearing on the bearing face. The part further includes a plurality of balancing masses each fastened to the corresponding fastener of the angular sector, at least one of the balancing masses also acting as a fastener for fastening the angular sector on the bearing face.
    Type: Application
    Filed: November 24, 2014
    Publication date: October 6, 2016
    Applicant: SNECMA
    Inventors: Jean-Luc LE STRAT, Herve POHIER
  • BALANCING SCREW, DEVICE AND METHOD FOR A ROTATING PART OF A TURBINE ENGINE
    Publication number: 20150354360
    Abstract: A balancing device for a rotating part of a turbomachine, includes a ferrule pierced with a plurality of ports, a balancing screw passing through each port, each balancing screw including a body and a head, the head of each balancing screw being pierced with a recess, the balancing screws being of at least one first type, the recess of the screws of the first type being formed by a driving recess from which an additional recess extends.
    Type: Application
    Filed: January 6, 2014
    Publication date: December 10, 2015
    Inventors: Jean-Luc LE STRAT, Hervé POHIER, Romain Jean-Louis Robert THORY
  • Cylinder head of an internal combustion engine comprising a cooling circuit
    Patent number: 8596239
    Abstract: A cylinder head of an internal combustion engine in which a cooling circuit is arranged, suited for a coolant circulation, includes a peripheral duct surrounding an exhaust valve seat and a peripheral duct surrounding an inlet valve seat communicating by means of a connecting duct; the cylinder head including a first coolant inlet, a second coolant inlet, and an outlet for heated coolant, the second inlet communicating with the connecting duct.
    Type: Grant
    Filed: January 25, 2011
    Date of Patent: December 3, 2013
    Assignee: Société de Motorisations Aéronautiques
    Inventors: Jérôme Escriva, Bruno Blanc, Hervé Pohier, Norbert Lartigue
  • CYLINDER HEAD OF AN INTERNAL COMBUSTION ENGINE COMPRISING A COOLING CIRCUIT
    Publication number: 20110220043
    Abstract: A cylinder head of an internal combustion engine in which a cooling circuit is arranged, suited for a coolant circulation, includes a peripheral duct surrounding an exhaust valve seat and a peripheral duct surrounding an inlet valve seat communicating by means of a connecting duct; the cylinder head including a first coolant inlet, a second coolant inlet, and an outlet for heated coolant, the second inlet communicating with the connecting duct.
    Type: Application
    Filed: January 25, 2011
    Publication date: September 15, 2011
    Applicant: SOCIETE DE MOTORISATIONS AERONAUTIQUES
    Inventors: JÉRÔME ESCRIVA, BRUNO BLANC, HERVÉ POHIER, NORBERT LARTIGUE