Patents by Inventor Jérémy Dievart

Jérémy Dievart 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).

  • Patent number: 11698029
    Abstract: A dual-flow turbojet engine having a central shaft surrounded by a high-pressure body which rotate about the same longitudinal axis while being independent in rotation, and including a fan driven by the central pressure shaft; a high-pressure compressor and a high-pressure turbine mounted on the high-pressure body; an inter-turbine casing; a low-pressure turbine mounted on a low-pressure rotor surrounding the central shaft; an exhaust casing on which an output cone is mounted; a reduction gear with which the low-pressure rotor drives the central pressure shaft; two bearings mounted on the exhaust casing and respectively receiving the central shaft and the low-pressure rotor; a bearing mounted on the inter-turbine casing and receiving the low-pressure rotor.
    Type: Grant
    Filed: November 21, 2019
    Date of Patent: July 11, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Alexandre Jean-Marie Tan-Kim, Yanis Benslama, Jérémy Dievart, Julien Fabien Patrick Becoulet
  • Patent number: 11274676
    Abstract: A ducted fan module with variable-pitch blades for a turbo engine includes a rotor carrying a plurality of blades, a stationary casing, and a blade pitch changing and control system. The rotor includes a central shaft and a surrounding blade support ring. A front end of the blade support ring is connected to a front end of the central shaft, creating a rearward-opening annular space between the blade support ring and the central shaft. A tubular part is connected to the stationary casing and extends into the annular space.
    Type: Grant
    Filed: December 22, 2016
    Date of Patent: March 15, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Serge René Morreale, Yanis Benslama, Jérémy Dievart, Dominik Igel
  • Publication number: 20220025822
    Abstract: A turbojet engine including a central shaft surrounded by a coaxial and independent high-pressure body, the turbojet engine including, from upstream to downstream: —a fan driven by the central shaft; a high-pressure compressor and a high-pressure turbine supported by the high-pressure body; an inter-turbine housing; a low-pressure turbine; and an exhaust housing. The turbojet engine also includes: a low-pressure rotor which extends downstream of the central shaft and supports the low-pressure turbine; a rotor bearing supported by the exhaust housing; a reduction gear by which the low-pressure rotor drives the central shaft, the reduction gear being located upstream of the rotor bearing; and a downstream shaft bearing which is located upstream of the reduction gear.
    Type: Application
    Filed: November 21, 2019
    Publication date: January 27, 2022
    Inventors: Alexandre Jean-Marie TAN-KIM, Yanis BENSLAMA, Jérémy DIEVART, Julien Fabien Patrick BECOULET
  • Publication number: 20220025821
    Abstract: A dual-flow turbojet engine having a central shaft surrounded by a high-pressure body which rotate about the same longitudinal axis while being independent in rotation, and including a fan driven by the central pressure shaft; a high-pressure compressor and a high-pressure turbine mounted on the high-pressure body; an inter-turbine casing; a low-pressure turbine mounted on a low-pressure rotor surrounding the central shaft; an exhaust casing on which an output cone is mounted; a reduction gear with which the low-pressure rotor drives the central pressure shaft; two bearings mounted on the exhaust casing and respectively receiving the central shaft and the low-pressure rotor; a bearing mounted on the inter-turbine casing and receiving the low-pressure rotor.
    Type: Application
    Filed: November 21, 2019
    Publication date: January 27, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Alexandre Jean-Marie TAN-KIM, Yanis BENSLAMA, Jérémy DIEVART, Julien Fabien Patrick BECOULET
  • Publication number: 20190024672
    Abstract: A ducted fan module with variable-pitch blades for a turbo engine includes a rotor carrying a plurality of blades, a stationary casing and a pitch changing and control system for adjusting and controlling the setting of the blades. The rotor includes a central shaft and a blade support ring surrounding the central shaft, a front end of the ring that is connected to a front end of the central shaft, so as to create a rearward-opening annular space between the ring and the shaft. The annular space of the rotor housing the blade changing and control system and the central shaft are guided by a first bearing mounted in a stationary casing behind the ring. The fan has a tubular part connected to the stationary casing and extending into the annular space in front of the first bearing and carrying at least a first complementary bearing for guiding the shaft.
    Type: Application
    Filed: December 22, 2016
    Publication date: January 24, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Serge René Morreale, Yanis Benslama, Jérémy Dievart, Dominik Igel