Patents by Inventor Jeffrey Steven SHERMAN

Jeffrey Steven SHERMAN 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).

  • Method for producing a casing for an aircraft turbine engine
    Patent number: 11788434
    Abstract: Method for manufacturing a casing of an aircraft turbomachine, the casing including an annular shell extending about an axis A and made of a composite material including fibres that are woven and immersed in a resin, the annular layer including an abradable material arranged inside the shell, and covering a first inner annular surface of an intermediate section of the shell, the method including a step of gluing the layer on the first surface, during which the casing is heated and compressed by a system that is present at least partially inside the casing, wherein, prior to the heating and compression of the casing, a forming tool is mounted inside the casing and is made of two rings.
    Type: Grant
    Filed: July 10, 2020
    Date of Patent: October 17, 2023
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN AEROSPACE COMPOSITES
    Inventors: Vincent Pascal Fiore, Gatien Frisoni, Foster Alexander Maxwell, Steven Meserve, Jeffrey Steven Sherman
  • METHOD FOR CALCULATING THE THICKNESS OF THE TRAILING AND LEADING EDGES ON A BLADE PROFILE
    Publication number: 20220281198
    Abstract: A verification method for verifying whether the aerodynamic profile of a real blade for an aircraft turbine engine complies with a theoretical blade, the method including constructing a camber line of the theoretical blade and constructing a camber line of the real blade; constructing a relationship for the thickness of the theoretical blade and constructing a relationship for the thickness of the real blade, the thickness relationship of a blade corresponding to the curve plotting the thickness of the blade as a function of curvilinear length along the camber line from a leading edge of the blade to a trailing edge of the blade, where thickness is the dimension of the blade extending perpendicularly to the camber line at each point of the camber line; superposing the thickness relationship of the real blade on the thickness relationship of the theoretical blade; and extracting the leading-edge and trailing edge thicknesses.
    Type: Application
    Filed: August 7, 2020
    Publication date: September 8, 2022
    Applicants: SAFRAN AERO COMPOSITE, SAFRAN AIRCRAFT ENGINES, SAFRAN AEROSPACE COMPOSITES
    Inventors: Damien Vincent LE CLOAREC, Clement GIACOVELLI, Jeffrey Steven SHERMAN, Mickaelle Lucie Alicia THOMAS
  • METHOD FOR PRODUCING A CASING FOR AN AIRCRAFT TURBINE ENGINE
    Publication number: 20220243617
    Abstract: Method for manufacturing a casing of an aircraft turbomachine, the casing including an annular shell extending about an axis A and made of a composite material including fibres that are woven and immersed in a resin, the annular layer including an abradable material arranged inside the shell, and covering a first inner annular surface of an intermediate section of the shell, the method including a step of gluing the layer on the first surface, during which the casing is heated and compressed by a system that is present at least partially inside the casing, wherein, prior to the heating and compression of the casing, a forming tool is mounted inside the casing and is made of two rings.
    Type: Application
    Filed: July 10, 2020
    Publication date: August 4, 2022
    Inventors: Vincent Pascal FIORE, Gatien FRISONI, Foster Alexander MAXWELL, Steven MESERVE, Jeffrey Steven SHERMAN