Patents by Inventor Martin Miles D'Angelo

Martin Miles D'Angelo 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).

  • RADIAL VARIABLE INLET GUIDE VANE FOR AXIAL OR AXI-CENTRIFUGAL COMPRESSORS
    Publication number: 20210231052
    Abstract: A turbine engine includes, in a serial flow relationship, an axially oriented compressor, a combustion section, a turbine section, and an exhaust section. An air flowpath extends from an inlet duct to the exhaust section such that the compressor, combustion section, turbine, and the exhaust section are in fluid communication. The inlet duct is positioned upstream of the compressor and defines an inlet portion of the air flowpath. The inlet duct is generally radially oriented. A variable inlet guide vane extends at least partially through the inlet duct.
    Type: Application
    Filed: November 2, 2020
    Publication date: July 29, 2021
    Inventors: Martin Miles D'Angelo, Mark Gregory Wotzak, Michael Macrorie
  • Turbine engine with single wall cantilevered architecture
    Patent number: 10836499
    Abstract: An apparatus and method for mounting a turbine engine to an aircraft can include an engine core for the turbine engine including a compressor section, a combustor section, and a turbine section in flow arrangement. At least one strut couples to the engine core about a single mount plane. A structural wall at least partially defining a mainstream flow path couples to the at least one strut and passes through the compressor section and the turbine section.
    Type: Grant
    Filed: August 22, 2017
    Date of Patent: November 17, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Kenneth Arthur Gould, Martin Miles D'Angelo, Daniel Waslo, Brian Lewis Devendorf, Mark Gregory Wotzak
  • TURBINE ENGINE WITH SINGLE WALL CANTILEVERED ARCHITECTURE
    Publication number: 20190061965
    Abstract: An apparatus and method for mounting a turbine engine to an aircraft can include an engine core for the turbine engine including a compressor section, a combustor section, and a turbine section in flow arrangement. At least one strut couples to the engine core about a single mount plane. A structural wall at least partially defining a mainstream flow path couples to the at least one strut and passes through the compressor section and the turbine section.
    Type: Application
    Filed: August 22, 2017
    Publication date: February 28, 2019
    Inventors: Kenneth Arthur Gould, Martin Miles D'Angelo, Daniel Waslo, Brian Lewis Devendorf, Mark Gregory Wotzak
  • RADIAL VARIABLE INLET GUIDE VANE FOR AXIAL OR AXI-CENTRIFUGAL COMPRESSORS
    Publication number: 20180216527
    Abstract: A turbine engine includes, in a serial flow relationship, an axially oriented compressor, a combustion section, a turbine section, and an exhaust section. An air flowpath extends from an inlet duct to the exhaust section such that the compressor, combustion section, turbine, and the exhaust section are in fluid communication. The inlet duct is positioned upstream of the compressor and defines an inlet portion of the air flowpath. The inlet duct is generally radially oriented. A variable inlet guide vane extends at least partially through the inlet duct.
    Type: Application
    Filed: January 27, 2017
    Publication date: August 2, 2018
    Inventors: Martin Miles D'Angelo, Mark Gregory Wotzak, Michael Macrorie
  • HIGH OVERALL PRESSURE RATIO GAS TURBINE ENGINE
    Publication number: 20180106193
    Abstract: A gas turbine engine includes a compressor section and turbine section. The gas turbine engine of the present disclosure is a relatively small gas turbine engine, configured to generate less than 2,000 horsepower during peak operations. The compressor section defines an overall compressor ratio of at least 15:1 in order to increase in overall efficiency of the gas turbine engine.
    Type: Application
    Filed: October 13, 2016
    Publication date: April 19, 2018
    Inventors: Martin Miles D'Angelo, Stuart Brian Bassler, Brian Lewis Devendorf, Mark Joseph Wagner