Patents by Inventor Pierrot GUILLOU

Pierrot GUILLOU 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: 20240326976
    Abstract: An airship comprises a main body having a rigid structure surrounding a plurality of containers for a lighter-than-air gas, a plurality of propeller units mechanically connected to the rigid structure and each comprising one or more electric motors for driving a thrust propeller, and one or more power-generating units for powering the electric motors. The airship also comprises two nacelles symmetrically arranged on either side of the main body and each configured to receive one or more of the power-generating units, each ducted nacelle comprising a mechanical structure connected to the rigid structure of the main body by a joint, a “fail safe” interface, and at least one rod or stay cable between a first point of attachment on the rigid structure of the main body and a second point of attachment on the mechanical structure of the nacelle.
    Type: Application
    Filed: July 21, 2022
    Publication date: October 3, 2024
    Inventors: Pierrot Guillou, Clémence Taillardat
  • Patent number: 11643944
    Abstract: A turbine shaft of a turbomachine extending along a longitudinal axis (A) includes a main tubular portion with a length L1 and a maximum outer main diameter. The shaft further includes a secondary tubular segment with a length L2 and a maximum outer secondary diameter greater than the maximum outer main diameter. The secondary tubular segment extends radially from the shaft such that the main tubular portion extends on either side of the secondary tubular segment along the longitudinal axis (A). The secondary tubular segment includes a weak point that is configured to break the shaft into two distinct parts when the value of a tangential stress applied to the shaft exceeds a predetermined threshold value, and thus cause retraction of the turbine.
    Type: Grant
    Filed: March 20, 2019
    Date of Patent: May 9, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Xavier Trappier, Pierrot Guillou, Caroline Marie Frantz
  • Patent number: 10975741
    Abstract: An aircraft twin-spool turbomachine comprises an inter flow compartment (50) housing a fuel tank (54), the exterior of the inter flow compartment being delimited by a cover (52) delimiting the interior of a bypass flow (14b) of the turbomachine, the cover comprising a closable access (64) to a remote lubricant tank filling orifice (74). The turbomachine also comprises: an overflow evacuation orifice (82) located on the tank lower than the lubricant inlet orifice (68); a lubricant overflow evacuation conduit (84) routed downwards from the overflow evacuation orifice (82); a controlled evacuation valve (88), associated with the overflow evacuation orifice (82); and a control device (90, 94) for the evacuation valve (88), the control device being accessible through the access (64).
    Type: Grant
    Filed: June 14, 2019
    Date of Patent: April 13, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Pierrot Guillou
  • Publication number: 20210017880
    Abstract: A turbine shaft of a turbomachine extending along a longitudinal axis (A) includes a main tubular portion with a length L1 and a maximum outer main diameter. The shaft further includes a secondary tubular segment with a length L2 and a maximum outer secondary diameter greater than the maximum outer main diameter. The secondary tubular segment extends radially from the shaft such that the main tubular portion extends on either side of the secondary tubular segment along the longitudinal axis (A). The secondary tubular segment includes a weak point that is configured to break the shaft into two distinct parts when the value of a tangential stress applied to the shaft exceeds a predetermined threshold value, and thus cause retraction of the turbine.
    Type: Application
    Filed: March 20, 2019
    Publication date: January 21, 2021
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Xavier Trappier, Pierrot Guillou, Caroline Marie Frantz
  • Publication number: 20190383180
    Abstract: An aircraft twin-spool turbomachine comprises an inter flow compartment (50) housing a fuel tank (54), the exterior of the inter flow compartment being delimited by a cover (52) delimiting the interior of a bypass flow (14b) of the turbomachine, the cover comprising a closable access (64) to a remote lubricant tank filling orifice (74). The turbomachine also comprises: an overflow evacuation orifice (82) located on the tank lower than the lubricant inlet orifice (68); a lubricant overflow evacuation conduit (84) routed downwards from the overflow evacuation orifice (82); a controlled evacuation valve (88), associated with the overflow evacuation orifice (82); and a control device (90, 94) for the evacuation valve (88), the control device being accessible through the access (64).
    Type: Application
    Filed: June 14, 2019
    Publication date: December 19, 2019
    Inventor: Pierrot GUILLOU
  • Patent number: 9394057
    Abstract: A rear suspension for attaching an aeroengine (20) of longitudinal axis X to a carrier structure or mast (12) of an aircraft, the suspension including at least two clevis-forming vertical uprights (26A, 26B; 28A, 28B) supporting a respective horizontal slideway (30A, 30B) having a roller (32) freely mounted thereon that is suitable for moving in a slot (34A, 34B) in a lug (20A) arranged in a YZ plane of transverse axis Y and of vertical axis Z, in such a manner as to enable the aeroengine to move only in translation along the longitudinal axis X and in pivoting about said longitudinal axis X.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: July 19, 2016
    Assignee: SNECMA
    Inventor: Pierrot Guillou
  • Publication number: 20150175268
    Abstract: A rear suspension for attaching an aeroengine (20) of longitudinal axis X to a carrier structure or mast (12) of an aircraft, the suspension including at least two clevis-forming vertical uprights (26A, 26B; 28A, 28B) supporting a respective horizontal slideway (30A, 30B) having a roller (32) freely mounted thereon that is suitable for moving in a slot (34A, 34B) in a lug (20A) arranged in a YZ plane of transverse axis Y and of vertical axis Z, in such a manner as to enable the aeroengine to move only in translation along the longitudinal axis X and in pivoting about said longitudinal axis X.
    Type: Application
    Filed: December 19, 2014
    Publication date: June 25, 2015
    Applicant: SNECMA
    Inventor: Pierrot GUILLOU