Patents by Inventor Per Widstrom

Per Widstrom 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).

  • Aircraft engine lubricant circulation
    Patent number: 11946380
    Abstract: An aircraft engine circulation system comprises a conduit arranged in use to communicate a lubricant to and from one or more bearings of an engine. The conduits define a space which comprises a material that is selected to change phase at a predetermined temperature.
    Type: Grant
    Filed: December 19, 2019
    Date of Patent: April 2, 2024
    Assignee: GKN Aerospace Sweden AB
    Inventor: Per Widstrom
  • AIRCRAFT ENGINE LUBRICANT CIRCULATION
    Publication number: 20220025782
    Abstract: An aircraft engine circulation system comprises a conduit arranged in use to communicate a lubricant to and from one or more bearings of an engine. The conduits define a space which comprises a material that is selected to change phase at a predetermined temperature.
    Type: Application
    Filed: December 19, 2019
    Publication date: January 27, 2022
    Inventor: Per Widstrom
  • Support structure for a gas turbine engine
    Patent number: 9951692
    Abstract: The present invention relates to a support structure (16) for a gas turbine engine (1). The support structure (16) has an axial extension in an axial direction (A) and a circumferential extension in a circumferential direction (C). Moreover, the support structure (16) comprises a plurality of tubular members (18, 20) of a first material type arranged in sequence in the circumferential direction (C). Each tubular member (18, 20) at least partially delimits a flow guiding passage extending at least partially in the axial direction (A). The support structure (16) comprises a leading portion (22) and a trailing portion (24) in the axial direction (A). Furthermore, the support structure (16) comprises a leading edge member (26) of a second material type, the leading edge member (26) being located at the leading portion (22). At least two of the tubular members (18, 20) are fixedly attached to a leading edge member (26).
    Type: Grant
    Filed: December 23, 2011
    Date of Patent: April 24, 2018
    Assignee: GKN Aerospace Sweden AB
    Inventors: Egon Aronsson, Per Widstrom, Elinor Magnusson, Johan Tholérus, Christian Lundh
  • SUPPORT STRUCTURE FOR A GAS TURBINE ENGINE
    Publication number: 20140373556
    Abstract: The present invention relates to a support structure (16) for a gas turbine engine (1). The support structure (16) has an axial extension in an axial direction (A) and a circumferential extension in a circumferential direction (C). Moreover, the support structure (16) comprises a plurality of tubular members (18, 20) of a first material type arranged in sequence in the circumferential direction (C). Each tubular member (18, 20) at least partially delimits a flow guiding passage extending at least partially in the axial direction (A). The support structure (16) comprises a leading portion (22) and a trailing portion (24) in the axial direction (A). Furthermore, the support structure (16) comprises a leading edge member (26) of a second material type, the leading edge member (26) being located at the leading portion (22). At least two of the tubular members (18, 20) are fixedly attached to a leading edge member (26).
    Type: Application
    Filed: December 23, 2011
    Publication date: December 25, 2014
    Applicant: GKN AEROSPACE SWEDEN AB
    Inventors: Egon Aronsson, Per Widstrom, Elinor Magnusson, Johan Thoreus, Christian Lundh