Patents by Inventor Derek Dewey

Derek Dewey 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: 20240141311
    Abstract: Disclosed herein are recombinant meganucleases engineered to bind and cleave a recognition sequence in the mitochondrial DNA (mtDNA) of a eukaryotic cell, such as a plant cell. The disclosure further relates to the use of such recombinant meganucleases in methods for producing genetically-modified eukaryotic cells, and to a population of genetically-modified eukaryotic cells wherein the mtDNA has been having modified or edited.
    Type: Application
    Filed: April 22, 2022
    Publication date: May 2, 2024
    Applicant: North Carolina State University
    Inventors: Ralph Dewey, Derek Jantz, James Jefferson Smith, Ginger H. Tomberlin, John Morris, Anna Matthiadis, Wendy Shoop
  • Patent number: 8371804
    Abstract: A device for detecting a shaft rupture in a rotor of a turbine, in particular a medium-pressure turbine, of a gas turbine, in particular of an aircraft engine, at least one stator-side sensor element being positioned downstream from the turbine, in particular in the area of a stator-side blade ring of another turbine, in particular a low-pressure turbine, and, in case of a shaft rupture of the rotor of the turbine, a radially externally situated segment of a last (seen in the direction of flow) rotor-side blade ring of the turbine working together with the, or with each, sensor element to generate an electrical signal corresponding to the shaft rupture.
    Type: Grant
    Filed: August 26, 2006
    Date of Patent: February 12, 2013
    Assignee: MTU Aero Engines GmbH
    Inventors: Christopher Bilson, Derek Dewey, Andrew Cox
  • Publication number: 20090220333
    Abstract: A device for detecting a shaft rupture in a rotor of a turbine, in particular a medium-pressure turbine, of a gas turbine, in particular of an aircraft engine, at least one stator-side sensor element being positioned downstream from the turbine, in particular in the area of a stator-side blade ring of another turbine, in particular a low-pressure turbine, and, in case of a shaft rupture of the rotor of the turbine, a radially externally situated segment of a last (seen in the direction of flow) rotor-side blade ring of the turbine working together with the, or with each, sensor element to generate an electrical signal corresponding to the shaft rupture.
    Type: Application
    Filed: August 26, 2006
    Publication date: September 3, 2009
    Inventors: Christopher Bilson, Derek Dewey, Andrew Cox