Patents by Inventor Glen E. Potter

Glen E. Potter 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).

  • Geared low fan pressure ratio fan exit guide vane stagger angle
    Patent number: 10738627
    Abstract: A fan exit guide vane assembly for a gas turbine engine includes a plurality of guide vanes having a pressure side and a suction side extending between a leading edge and a trailing edge. The vanes further include a span extending between a root and tip with a stagger angle defined as an angle between a longitudinal axis parallel to an engine axis of rotation and a line connecting the leading edge and the trailing edge that is less than about 15°.
    Type: Grant
    Filed: January 15, 2018
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Edward J. Gallagher, Glen E. Potter, Barry M. Ford
  • Pylon matched fan exit guide vane for noise reduction in a geared turbofan engine
    Patent number: 10247018
    Abstract: A disclosed fan section of a gas turbine engine includes a fan rotor having a plurality of fan blades and a duct defining a passageway aft of the fan rotor. A fan exit guide vane is disposed within the duct downstream of the fan blades. The fan exit guide vane includes a plurality of exit guide vanes positioned downstream of the fan rotor with at least two of the plurality of exit guide vanes including different aft geometries for guiding airflow through the passage to reduce pressure distortions at the fan blades.
    Type: Grant
    Filed: August 25, 2016
    Date of Patent: April 2, 2019
    Assignee: United Technologies Corporation
    Inventors: David A. Topol, Glen E. Potter, Flavien L. Thomas
  • GEARED LOW FAN PRESSURE RATIO FAN EXIT GUIDE VANE STAGGER ANGLE
    Publication number: 20180156048
    Abstract: A fan exit guide vane assembly for a gas turbine engine includes a plurality of guide vanes having a pressure side and a suction side extending between a leading edge and a trailing edge. The vanes further include a span extending between a root and tip with a stagger angle defined as an angle between a longitudinal axis parallel to an engine axis of rotation and a line connecting the leading edge and the trailing edge that is less than about 15°.
    Type: Application
    Filed: January 15, 2018
    Publication date: June 7, 2018
    Inventors: Edward J. Gallagher, Glen E. Potter, Barry M. Ford
  • Geared low fan pressure ratio fan exit guide vane stagger angle
    Patent number: 9869191
    Abstract: A fan exit guide vane assembly for a gas turbine engine includes a plurality of guide vanes having a pressure side and a suction side extending between a leading edge and a trailing edge. The vanes further include a span extending between a root and tip with a stagger angle defined as an angle between a longitudinal axis parallel to an engine axis of rotation and a line connecting the leading edge and the trailing edge that is less than about 15°.
    Type: Grant
    Filed: April 17, 2013
    Date of Patent: January 16, 2018
    Assignee: United Technologies Corporation
    Inventors: Edward J. Gallagher, Glen E. Potter, Barry M. Ford
  • Pylon matched fan exit guide vane for noise reduction in a geared turbofan engine
    Patent number: 9540938
    Abstract: A disclosed fan section of a gas turbine engine includes a fan rotor having a plurality of fan blades and a duct defining a passageway aft of the fan rotor. A fan exit guide vane is disposed within the duct downstream of the fan blades. The fan exit guide vane includes a plurality of exit guide vanes positioned downstream of the fan rotor with at least two of the plurality of exit guide vanes including different aft geometries for guiding airflow through the passage to reduce pressure distortions at the fan blades.
    Type: Grant
    Filed: December 20, 2012
    Date of Patent: January 10, 2017
    Assignee: United Technologies Corporation
    Inventors: David A. Topol, Glen E. Potter, Flavien L. Thomas
  • PYLON MATCHES FAN EXIT GUIDE VANE FOR NOISE REDUCTION IN A GEARED TURBOFAN ENGINE
    Publication number: 20160363137
    Abstract: A disclosed fan section of a gas turbine engine includes a fan rotor having a plurality of fan blades and a duct defining a passageway aft of the fan rotor. A fan exit guide vane is disposed within the duct downstream of the fan blades. The fan exit guide vane includes a plurality of exit guide vanes positioned downstream of the fan rotor with at least two of the plurality of exit guide vanes including different aft geometries for guiding airflow through the passage to reduce pressure distortions at the fan blades.
    Type: Application
    Filed: August 25, 2016
    Publication date: December 15, 2016
    Inventors: David A. Topol, Glen E. Potter, Flavien L. Thomas
  • Joint between airfoil and shroud
    Patent number: 9169736
    Abstract: A stator joint for a gas turbine engine has a center axis, and a shroud having a radial wall facing substantially radially with respect to the center axis. A slot wall defines in-part a slot in the shroud. A relief wall defines a relief area of the slot. The relief wall extends between the radial wall and the slot wall. A vane has an airfoil and a lug extending into the slot. A flowable attachment material is disposed in the relief area for engagement of the vane to the shroud. A vane assembly and a gas turbine engine are also disclosed.
    Type: Grant
    Filed: July 16, 2012
    Date of Patent: October 27, 2015
    Assignee: United Technologies Corporation
    Inventors: Richard K. Hayford, Glen E. Potter
  • GEARED LOW FAN PRESSURE RATIO FAN EXIT GUIDE VANE STAGGER ANGLE
    Publication number: 20150260051
    Abstract: A fan exit guide vane assembly for a gas turbine engine includes a plurality of guide vanes having a pressure side and a suction side extending between a leading edge and a trailing edge. The vanes further include a span extending between a root and tip with a stagger angle defined as an angle between a longitudinal axis parallel to an engine axis of rotation and a line connecting the leading edge and the trailing edge that is less than about 15°.
    Type: Application
    Filed: April 17, 2013
    Publication date: September 17, 2015
    Inventors: Edward J. Gallagher, Glen E. Potter, Barry M. Ford
  • JOINT BETWEEN AIRFOIL AND SHROUD
    Publication number: 20140013772
    Abstract: A stator joint for a gas turbine engine has a center axis, and a shroud having a radial wall facing substantially radially with respect to the center axis. A slot wall defines in-part a slot in the shroud. A relief wall defines a relief area of the slot. The relief wall extends between the radial wall and the slot wall. A vane has an airfoil and a lug extending into the slot. A flowable attachment material is disposed in the relief area for engagement of the vane to the shroud. A vane assembly and a gas turbine engine are also disclosed.
    Type: Application
    Filed: July 16, 2012
    Publication date: January 16, 2014
    Inventors: Richard K. Hayford, Glen E. Potter
  • Bowed airfoil for the compression section of a rotary machine
    Patent number: 5088892
    Abstract: An airfoil for a compression section 12 of a rotary machine 10 is disclosed. Various construction details are developed to increase the efficiency of the compression section 12. In one detailed embodiment, the airfoil has a spanwise axis 52 or stacking line which extends in a generally radial direction. The stacking line or spanwise axis 52 is straight over the mid-section of the airfoil and is angled circumferentially toward the radial direction in the end wall regions 58, 66 of the airfoil.
    Type: Grant
    Filed: February 7, 1990
    Date of Patent: February 18, 1992
    Assignee: United Technologies Corporation
    Inventors: Harris D. Weingold, Robert J. Neubert, John G. Andy, Roy F. Behlke, Glen E. Potter