Patents by Inventor Guilhem Camille François Verron

Guilhem Camille François Verron 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).

  • Control of clearance between aircraft rotor blades and a casing
    Patent number: 11319830
    Abstract: A device for controlling clearance between the tips of rotating blades of an aircraft turbomachine and a casing. An air circulation path allows air to be blown onto the casing in order to change its temperature. In addition, heating means heat the circulating air.
    Type: Grant
    Filed: May 15, 2020
    Date of Patent: May 3, 2022
    Assignee: Safran Aircraft Engines
    Inventors: Tangi Brusq, Florence Valérie Bon, Damien Bonneau, Antoine Van Noort, Guilhem Camille François Verron
  • Labyrinth seal for a turbine engine of an aircraft
    Patent number: 10947857
    Abstract: Labyrinth seal for a turbine engine, in particular of an aircraft, including a rotor element rotating about an axis of rotation, and a stator element extending around the rotor element The rotor element includes a series of annular lips extending radially outwards and surrounded by at least one abradable element carried by the stator element. Each lip includes an inner peripheral body portion, an outer peripheral body portion and an upstream annular face for impact of an air flow during operation. At least one lip has, looking from the upstream annular face, a first annular cavity with a concave rounded cross-section on its inner peripheral body portion and a second annular cavity with a concave rounded cross-section on its outer peripheral body portion.
    Type: Grant
    Filed: September 24, 2018
    Date of Patent: March 16, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clement Jarossay, Guilhem Camille Francois Verron, Maurice Guy Judet, Clement Raphael Laroche, Guillaume Michel Maurice Giliberti
  • CONTROL OF CLEARANCE BETWEEN AIRCRAFT ROTOR BLADES AND A CASING
    Publication number: 20200362719
    Abstract: A device for controlling clearance between the tips of rotating blades of an aircraft turbomachine and a casing. An air circulation path allows air to be blown onto the casing in order to change its temperature. In addition, heating means heat the circulating air.
    Type: Application
    Filed: May 15, 2020
    Publication date: November 19, 2020
    Applicant: Safran Aircraft Engines
    Inventors: Tangi Brusq, Florence Valérie Bon, Damien Bonneau, Antoine Van Noort, Guilhem Camille François Verron
  • LABYRINTH SEAL FOR A TURBINE ENGINE OF AN AIRCRAFT
    Publication number: 20190106999
    Abstract: Labyrinth seal for a turbine engine, in particular of an aircraft, including a rotor element rotating about an axis of rotation (A), and a stator element extending around the rotor element (14), the rotor element including a series of annular lip(s) extending radially outwards and surrounded by at least one abradable element carried by the stator element, each lip comprising an inner peripheral body portion, an outer peripheral body portion, an upstream annular face of impact of an air flow during operation and a downstream annular face, wherein at least one lip includes, on the inner peripheral body portion thereof and/or the outer peripheral body portion thereof, through-orifices for the passage of air extending between the upstream and downstream annular faces.
    Type: Application
    Filed: September 24, 2018
    Publication date: April 11, 2019
    Inventors: Clement JAROSSAY, Guilhem Camille Francois VERRON, Maurice Guy JUDET, Clement Raphael LAROCHE, Guillaume Michel Maurice GILIBERTI
  • LABYRINTH SEAL FOR A TURBINE ENGINE OF AN AIRCRAFT
    Publication number: 20190093494
    Abstract: Labyrinth seal for a turbine engine, in particular of an aircraft, including a rotor element rotating about an axis of rotation (A), and a stator element extending around the rotor element, the rotor element including a series of annular lip(s) extending radially outwards and surrounded by at least one abradable element carried by the stator element, each lip including an inner peripheral body portion, an outer peripheral body portion (12b) and an upstream annular face for impact of an air flow during operation, wherein at least one lip has, looking from the upstream annular face, a first annular cavity with a concave rounded cross-section on its inner peripheral body portion and a second annular cavity with a concave rounded cross-section on its outer peripheral body portion.
    Type: Application
    Filed: September 24, 2018
    Publication date: March 28, 2019
    Inventors: Clement JAROSSAY, Guilhem Camille Francois VERRON, Maurice Guy JUDET, Clement Raphael LAROCHE, Guillaume Michel Maurice GILIBERTI