Patents by Inventor Jamie W. GALLAGHER

Jamie W. GALLAGHER 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).

  • Gas turbine engine
    Patent number: 11993387
    Abstract: A gas turbine engine comprises, in axial flow sequence, a fan assembly, a compressor module, a turbine module, and an exhaust module. The gas turbine engine comprises first and second engine mount planes. The first and second engine mount planes are configured to support gas turbine engine in machine body. The gas turbine engine has axial length L, with axial length extending from inlet face of engine to exhaust face of engine. The first engine mount plane is positioned axially along gas turbine engine at first engine mount plane position, with first engine mount plane position within a range of between 0.24*L to 0.32*L from the inlet face of the engine. The second engine mount plane is positioned axially along gas turbine engine at second engine mount plane position, with second engine mount plane position within a range of between 0.73*L to 0.79*L from the inlet face of the engine.
    Type: Grant
    Filed: September 8, 2022
    Date of Patent: May 28, 2024
    Assignee: ROLLS-ROYCE plc
    Inventors: Jamie W Gallagher, Daniel Blacker, Hugh J Blakemore, Adrian M Manser, Jonathan V Watson, Alexander L Fry, Robert A Barker, James Thorp, Marie-Océane Parent
  • IMPROVED GAS TURBINE ENGINE
    Publication number: 20230166855
    Abstract: A gas turbine engine comprises, in axial flow sequence, a fan assembly, a compressor module, a turbine module, and an exhaust module. The gas turbine engine comprises first and second engine mount planes. The first and second engine mount planes are configured to support gas turbine engine in machine body. The gas turbine engine has axial length L, with axial length extending from inlet face of engine to exhaust face of engine. The first engine mount plane is positioned axially along gas turbine engine at first engine mount plane position, with first engine mount plane position within a range of between 0.24*L to 0.32*L from the inlet face of the engine. The second engine mount plane is positioned axially along gas turbine engine at second engine mount plane position, with second engine mount plane position within a range of between 0.73*L to 0.79*L from the inlet face of the engine.
    Type: Application
    Filed: September 8, 2022
    Publication date: June 1, 2023
    Applicant: ROLLS-ROYCE plc
    Inventors: Jamie W. GALLAGHER, Daniel BLACKER, Hugh J. BLAKEMORE, Adrian M. MANSER, Jonathan V. WATSON, Alexander L. FRY, Robert A. BARKER, James THORP, Marie-Océane PARENT