Patents by Inventor Roderick M Townes

Roderick M Townes 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: 20210123352
    Abstract: A turbine vane assembly adapted for use with a gas turbine engine includes an airfoil and a spar. The airfoil is formed to define a cavity that extends into the airfoil. The spar is located in the cavity to define a cooling passage that extends around the spar between the spar and the airfoil. The turbine vane assembly includes cooling features to aid heat transfer of the turbine vane assembly during operation in the gas turbine engine.
    Type: Application
    Filed: October 28, 2019
    Publication date: April 29, 2021
    Inventors: Roderick M. Townes, Andrew T. Holt, Michael J. Whittle
  • Patent number: 10989112
    Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.
    Type: Grant
    Filed: May 14, 2019
    Date of Patent: April 27, 2021
    Assignee: ROLLS-ROYCE PLC
    Inventors: Pascal Dunning, Roderick M Townes, Michael J Whittle
  • Patent number: 10975708
    Abstract: A turbine assembly adapted for use in a gas turbine engine is disclosed in this paper. The turbine assembly includes a turbine vane comprising ceramic matrix composite materials configured for use in high temperature environments. The turbine assembly further includes a vane-stage support for holding the turbine vane and other components in place relative to a turbine case.
    Type: Grant
    Filed: April 23, 2019
    Date of Patent: April 13, 2021
    Assignee: Rolls-Royce plc
    Inventors: Michael J. Whittle, Anthony G. Razzell, Roderick M. Townes, David J. Shepherd, Duncan Forbes
  • Patent number: 10954802
    Abstract: A turbine assembly adapted for use in a gas turbine engine with a turbine vane comprising ceramic matrix composite materials. The turbine vane is configured to redirect air moving through a primary gas path of the gas turbine engine. The turbine assembly includes a vane-stage support for holding the turbine vane in place relative to a turbine case.
    Type: Grant
    Filed: April 23, 2019
    Date of Patent: March 23, 2021
    Inventors: Michael J. Whittle, Anthony G. Razzell, Roderick M. Townes, David J. Shepherd, Duncan Forbes
  • Patent number: 10844721
    Abstract: A gas turbine engine for an aircraft includes an engine core with a turbine, a compressor, and a core shaft connecting them. The engine includes a fan, with a plurality of fan blades, located upstream of the core and a gearbox receiving an input from the core shaft and outputting drive so the fan is at a lower rotational speed than the core shaft. The turbine includes a plurality of stages of axially spaced rotor blades mounted on a rotor, which are surrounded by a turbine casing. The turbine has an inlet defined at an upstream end of a first stage of blades and an outlet defined at a downstream end of a last stage of blades and a ratio of the area of the outlet to the inlet is at between 2.5 and 3.5. This increases the pressure ratio of and power extracted from the turbine and the engine.
    Type: Grant
    Filed: June 18, 2019
    Date of Patent: November 24, 2020
    Assignees: ROLLS-ROYCE plc, ITP NEXT GENERATION TURBINES SLU
    Inventors: Roderick M Townes, Diego Torre Ruiz
  • Publication number: 20200362707
    Abstract: A turbine assembly adapted for use in a gas turbine engine is disclosed in this paper. The turbine assembly includes a turbine vane comprising ceramic matrix composite materials configured for use in high temperature environments. The turbine assembly further includes a vane-stage support for holding the turbine vane and other components in place relative to a turbine case.
    Type: Application
    Filed: May 13, 2019
    Publication date: November 19, 2020
    Inventors: Michael J. Whittle, Anthony G. Razzell, Roderick M. Townes, David J. Shepherd, Duncan Forbes
  • Publication number: 20200362710
    Abstract: A gas turbine engine includes a compressor, a combustor, and a turbine arranged around an axis. The turbine includes a turbine vane assembly. A method for creating the turbine vane assembly includes fabricating a plurality of turbine vanes comprising ceramic matrix composite material and selecting and arranging the turbine vanes to form a turbine vane assembly.
    Type: Application
    Filed: May 13, 2019
    Publication date: November 19, 2020
    Inventors: Michael J. Whittle, Roderick M. Townes, Andrew Holt
  • Publication number: 20200340370
    Abstract: A turbine assembly adapted for use in a gas turbine engine with a turbine vane comprising ceramic matrix composite materials. The turbine vane is configured to redirect air moving through a primary gas path of the gas turbine engine. The turbine assembly includes a vane-stage support for holding the turbine vane in place relative to a turbine case.
    Type: Application
    Filed: April 23, 2019
    Publication date: October 29, 2020
    Inventors: Michael J. Whittle, Anthony G. Razzell, Roderick M. Townes, David J. Shepherd, Duncan Forbes
  • Publication number: 20200340367
    Abstract: A turbine assembly adapted for use in a gas turbine engine is disclosed in this paper. The turbine assembly includes a turbine vane comprising ceramic matrix composite materials configured for use in high temperature environments. The turbine assembly further includes a vane-stage support for holding the turbine vane and other components in place relative to a turbine case.
    Type: Application
    Filed: April 23, 2019
    Publication date: October 29, 2020
    Inventors: Michael J. Whittle, Anthony G. Razzell, Roderick M. Townes, David J. Shepherd, Duncan Forbes
  • Publication number: 20200340363
    Abstract: A turbine assembly adapted for use in a gas turbine engine with a turbine vane comprising ceramic matrix composite materials. The turbine vane is configured to redirect air moving through a primary gas path of the gas turbine engine. The turbine assembly includes a vane-stage support for holding the turbine vane in place relative to a turbine case.
    Type: Application
    Filed: April 23, 2019
    Publication date: October 29, 2020
    Inventors: Michael J. Whittle, Anthony G. Razzell, Roderick M. Townes, David J. Shepherd, Duncan Forbes
  • Publication number: 20200340365
    Abstract: A turbine assembly adapted for use in a gas turbine engine is disclosed in this paper. The turbine assembly includes a turbine vane comprising ceramic matrix composite materials configured for use in high temperature environments. The turbine assembly further includes a vane-stage support for holding the turbine vane and other components in place relative to a turbine case.
    Type: Application
    Filed: April 23, 2019
    Publication date: October 29, 2020
    Inventors: Michael J. Whittle, Anthony G. Razzell, Roderick M. Townes, David J. Shepherd, Duncan Forbes
  • Publication number: 20200291782
    Abstract: A gas turbine engine for an aircraft includes an engine core with a turbine, a compressor, and a core shaft connecting them. The engine includes a fan, with a plurality of fan blades, located upstream of the core and a gearbox receiving an input from the core shaft and outputting drive so the fan is at a lower rotational speed than the core shaft. The turbine includes a plurality of stages of axially spaced rotor blades mounted on a rotor, which are surrounded by a turbine casing. The turbine has an inlet defined at an upstream end of a first stage of blades and an outlet defined at a downstream end of a last stage of blades and a ratio of the area of the outlet to the inlet is at between 2.5 and 3.5. This increases the pressure ratio of and power extracted from the turbine and the engine.
    Type: Application
    Filed: June 18, 2019
    Publication date: September 17, 2020
    Applicants: ROLLS-ROYCE PLC, ITP NEXT GENERATION TURBINES SLU
    Inventors: Roderick M TOWNES, Diego TORRE RUIZ
  • Publication number: 20200284154
    Abstract: A turbomachine for a gas turbine engine, comprising: a rotor disc arranged to rotate about a fixed central axis. A plurality of rotor blades connected to the rotor disc, wherein the rotor blades extend within a gas flow path. A rotating annulus is arranged to rotate in a fixed rotational alignment relative to the rotor disc. An outer surface of the rotating annulus is arranged to define part of the boundary of the gas flow path. A gas turbine engine for an aircraft and a method of defining the boundary of a gas flow path within a turbomachine is also disclosed.
    Type: Application
    Filed: February 21, 2020
    Publication date: September 10, 2020
    Inventors: Roderick M. TOWNES, Neal CARTER, Thomas W. MARTIN
  • Publication number: 20200263553
    Abstract: A cooled turbine rotor blade for a gas turbine engine includes an airfoil and a profiled root radially inward of the airfoil, a platform between the airfoil and the root, and a cooling air supply channel extending through the platform into an interior of the airfoil and therein up to an outlet opening. An inlet opening of the cooling air supply channel is located at the rear side of the rotor blade, and an inlet part of the cooling air supply channel with the inlet opening is angled into the direction of rotation of the rotor blade and curved into a radially outward direction. Further, a rotor-stator stage for a gas turbine includes a rotor blade as above, and an air cavity radially inwards of sealing features between the rotor stage and a neighboring downstream stator stage to form a source of cooling air for the rotor blade.
    Type: Application
    Filed: December 2, 2019
    Publication date: August 20, 2020
    Inventors: Hamish SWEIDAN, Keith C. SADLER, Roderick M. TOWNES
  • Patent number: 10738693
    Abstract: A highly efficient gas turbine engine includes a fan which is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.
    Type: Grant
    Filed: April 30, 2019
    Date of Patent: August 11, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Michael J Whittle, Pascal Dunning, Roderick M Townes
  • Publication number: 20200049070
    Abstract: A highly efficient gas turbine engine is a system wherein the fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.
    Type: Application
    Filed: May 14, 2019
    Publication date: February 13, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Roderick M. TOWNES, Michael J. WHITTLE, Pascal DUNNING
  • Publication number: 20200049066
    Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.
    Type: Application
    Filed: May 14, 2019
    Publication date: February 13, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Pascal DUNNING, Roderick M. TOWNES, Michael J WHITTLE
  • Publication number: 20200049065
    Abstract: A gas turbine engine is highly efficient. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.
    Type: Application
    Filed: May 14, 2019
    Publication date: February 13, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Michael J WHITTLE, Roderick M TOWNES, Pascal DUNNING
  • Publication number: 20200049063
    Abstract: A highly efficient gas turbine engine includes a fan which is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.
    Type: Application
    Filed: April 30, 2019
    Publication date: February 13, 2020
    Applicant: ROLLS-ROYCE PLC
    Inventors: Michael J WHITTLE, Pascal DUNNING, Roderick M TOWNES
  • Publication number: 20200049104
    Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.
    Type: Application
    Filed: May 28, 2019
    Publication date: February 13, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Roderick M. TOWNES, Pascal DUNNING, Michael J. WHITTLE