Patents by Inventor Rupert John TAYLOR

Rupert John TAYLOR 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).

  • Dual source cooling air shroud arrangement for a gas turbine engine
    Patent number: 9920647
    Abstract: A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine is described. The seal segment is upstream of a second component of the gas turbine engine relative to the hot gas flow path. The seal segment comprises: a plate having: a downstream trailing edge; an inboard side which faces the hot gas flow path when in use; an outboard side; and a first part of a two part seal attached on the outboard side, wherein a second part of the two part seal is attached to the second component such that in an assembled gas turbine engine the two part seal provides an isolation chamber which is in fluid communication with the hot gas flow path via the trailing edge of the plate. A gas turbine having the seal segment is also described.
    Type: Grant
    Filed: May 12, 2014
    Date of Patent: March 20, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Simon Lloyd Jones, Rupert John Taylor, Julian Glyn Balsdon
  • Shroud arrangement for a gas turbine engine
    Patent number: 9611754
    Abstract: A seal segment for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard side which bounds the hot gas flow path in use, an outboard side and fore and aft cooling circuits, wherein the fore and aft cooling circuits are fluidically separated from one another within the plate and each has at least one tortuous path between an inlet on the outboard side of the plate and an exhaust.
    Type: Grant
    Filed: May 12, 2014
    Date of Patent: April 4, 2017
    Assignee: ROLLS-ROYCE plc
    Inventor: Rupert John Taylor
  • SHROUD ARRANGEMENT FOR A GAS TURBINE ENGINE
    Publication number: 20140341717
    Abstract: A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine is described. The seal segment is upstream of a second component of the gas turbine engine relative to the hot gas flow path. The seal segment comprises: a plate having: a downstream trailing edge; an inboard side which faces the hot gas flow path when in use; an outboard side; and a first part of a two part seal attached on the outboard side, wherein a second part of the two part seal is attached to the second component such that in an assembled gas turbine engine the two part seal provides an isolation chamber which is in fluid communication with the hot gas flow path via the trailing edge of the plate. A gas turbine having the seal segment is also described.
    Type: Application
    Filed: May 12, 2014
    Publication date: November 20, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventors: Simon Lloyd JONES, Rupert John TAYLOR, Julian Glyn BALSDON
  • SHROUD ARRANGEMENT FOR A GAS TURBINE ENGINE
    Publication number: 20140341711
    Abstract: A seal segment for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard side which bounds the hot gas flow path in use, an outboard side and fore and aft cooling circuits, wherein the fore and aft cooling circuits are fluidically separated from one another within the plate and each has at least one tortuous path between an inlet on the outboard side of the plate and an exhaust.
    Type: Application
    Filed: May 12, 2014
    Publication date: November 20, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventor: Rupert John TAYLOR