Patents by Inventor Edward C. GOWER

Edward C. GOWER 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: 11067035
    Abstract: A gas turbine engine includes a main gas flow exhaust nozzle having an annular inner surface which, in use, bounds a flow of exhaust gas. The gas turbine engine further includes cooling passages having respective outlets therefrom to provide a flow of cooling air over a surface of the engine or an adjacent airframe component, thereby protecting the cooled surface from the exhaust gas flow. Adjacent cooling passages of the or each pair of the nested cooling passages are separated from each other by a respective dividing wall. The outlets from the nested cooling passages are staggered in the axial direction of the exhaust nozzle such that cooling air flowing out of an inner one of the adjacent cooling passages of the or each pair of the nested cooling passages flows over the dividing wall separating the adjacent passages.
    Type: Grant
    Filed: October 17, 2018
    Date of Patent: July 20, 2021
    Assignee: ROLLS-ROYCE plc
    Inventors: Edward C Gower, Paul R Davies
  • Publication number: 20190195254
    Abstract: A panel arrangement comprising a first panel, comprising a first connector permanently bonded to an end edge thereof; and, a second panel, comprising a second connector permanently bonded to an end edge thereof; wherein the first and second panel are in end-on abutment via the first connector and second connector, and wherein the first and second connectors are fastened together by a fastener.
    Type: Application
    Filed: December 5, 2018
    Publication date: June 27, 2019
    Applicant: ROLLS-ROYCE plc
    Inventors: Edward C. GOWER, Alec R. GROOM
  • Publication number: 20190128215
    Abstract: A gas turbine engine includes a main gas flow exhaust nozzle having an annular inner surface which, in use, bounds a flow of exhaust gas. The gas turbine engine further includes cooling passages having respective outlets therefrom to provide a flow of cooling air over a surface of the engine or an adjacent airframe component, thereby protecting the cooled surface from the exhaust gas flow. Adjacent cooling passages of the or each pair of the nested cooling passages are separated from each other by a respective dividing wall. The outlets from the nested cooling passages are staggered in the axial direction of the exhaust nozzle such that cooling air flowing out of an inner one of the adjacent cooling passages of the or each pair of the nested cooling passages flows over the dividing wall separating the adjacent passages.
    Type: Application
    Filed: October 17, 2018
    Publication date: May 2, 2019
    Applicant: ROLLS-ROYCE plc
    Inventors: Edward C. GOWER, Paul R. DAVIES