Patents by Inventor Mark E. Whitlock

Mark E. Whitlock 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).

  • TURBINE ENGINE WITH CENTRIFUGAL COMPRESSOR HAVING IMPELLER BACKPLATE OFFTAKE
    Publication number: 20230374936
    Abstract: A gas turbine engine includes a fan, a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the fan and compressor.
    Type: Application
    Filed: July 21, 2023
    Publication date: November 23, 2023
    Inventors: Mark E. Whitlock, Nathanael Cooper, Steven Mazur, Michael Nesteroff, Paul Melevage
  • Turbine engine with centrifugal compressor having impeller backplate offtake
    Patent number: 11746695
    Abstract: A gas turbine engine includes a fan, a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the fan and compressor.
    Type: Grant
    Filed: May 18, 2022
    Date of Patent: September 5, 2023
    Assignee: Rolls-Royce Corporation
    Inventors: Mark E. Whitlock, Nathanael Cooper, Steven Mazur, Michael Nesteroff, Paul Melevage
  • Turbine engine with centrifugal compressor having impeller backplate offtake
    Patent number: 11525393
    Abstract: A gas turbine engine includes a fan, a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the fan and compressor.
    Type: Grant
    Filed: March 19, 2020
    Date of Patent: December 13, 2022
    Assignee: Rolls-Royce Corporation
    Inventors: Mark E. Whitlock, Nathanael Cooper, Steven Mazur, Michael Nesteroff, Paul Melevage
  • TURBINE ENGINE WITH CENTRIFUGAL COMPRESSOR HAVING IMPELLER BACKPLATE OFFTAKE
    Publication number: 20220333525
    Abstract: A gas turbine engine includes a fan, a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the fan and compressor.
    Type: Application
    Filed: May 18, 2022
    Publication date: October 20, 2022
    Inventors: Mark E. Whitlock, Nathanael Cooper, Steven Mazur, Michael Nesteroff, Paul Melevage
  • TURBINE ENGINE WITH CENTRIFUGAL COMPRESSOR HAVING IMPELLER BACKPLATE OFFTAKE
    Publication number: 20210293180
    Abstract: A gas turbine engine includes a fan, a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the fan and compressor.
    Type: Application
    Filed: March 19, 2020
    Publication date: September 23, 2021
    Inventors: Mark E. Whitlock, Nathanael Cooper, Steven Mazur, Michael Nesteroff, Paul Melevage
  • Diffuser having shaped vanes
    Patent number: 10352237
    Abstract: A radial diffuser and method for manufacturing a radial diffuser is provided, where the diffuser includes a vane positioned between a hub and a case. The hub includes a surface. The vane projects from the surface of the hub and is wedge-shaped. The vane includes a leading end extending toward a radial inner edge of the hub, a trailing end extending toward a radial outer edge of the hub, an upper surface, first and second sides extending longitudinally along the vane, and a middle region disposed between the hub and the upper surface. The vane at the upper surface has a thickness defined by a first wedge angle at the upper surface. The vane at the middle region has a thickness defined by a second wedge angle at the middle region. The second wedge angle is smaller than the first wedge angle.
    Type: Grant
    Filed: May 26, 2016
    Date of Patent: July 16, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Steven A Mazur, Mark E Whitlock
  • DIFFUSER HAVING SHAPED VANES
    Publication number: 20170342847
    Abstract: A radial diffuser and method for manufacturing a radial diffuser is provided, where the diffuser includes a vane positioned between a hub and a case. The hub includes a surface. The vane projects from the surface of the hub and is wedge-shaped. The vane includes a leading end extending toward a radial inner edge of the hub, a trailing end extending toward a radial outer edge of the hub, an upper surface, first and second sides extending longitudinally along the vane, and a middle region disposed between the hub and the upper surface. The vane at the upper surface has a thickness defined by a first wedge angle at the upper surface. The vane at the middle region has a thickness defined by a second wedge angle at the middle region. The second wedge angle is smaller than the first wedge angle.
    Type: Application
    Filed: May 26, 2016
    Publication date: November 30, 2017
    Inventors: Steven A. Mazur, Mark E. Whitlock