Patents by Inventor Mark David Durbin

Mark David Durbin 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: 20190063753
    Abstract: Fuel nozzle assemblies are provided. For example, a fuel nozzle assembly for a combustor system comprises a fuel nozzle having a pilot swirler and an outlet defined in an outlet end, as well as a main mixer attached to the outlet end and extending about the outlet. A total combustor airflow through the combustor system comprises a pilot swirler airflow that is greater than about 14% and a main mixer airflow that is less than about 50% of the total combustor airflow. In further embodiments, the fuel nozzle also comprises main and pilot fuel injectors that each are configured to receive a portion of a fuel flow to the fuel nozzle. The fuel nozzle provides less than about 80% of the fuel flow to the main fuel injector at a high power operating condition of a gas turbine engine in which the fuel nozzle assembly is installed.
    Type: Application
    Filed: August 23, 2017
    Publication date: February 28, 2019
    Inventors: Eric John Stevens, Mark David Durbin, Randall Charles Boehm, Michael Anthony Benjamin, Beverly Stephenson Duncan, Jeffrey Lyal Powell
  • Publication number: 20190063752
    Abstract: Combustor systems are provided. For example, a combustor system comprises a combustor having forward and aft ends and including annular inner and outer liners that each extend generally along an axial direction and define a combustion chamber therebetween. The combustor system also comprises a fuel nozzle having an outlet defined in an outlet end of the fuel nozzle and including a pilot swirler. The outlet is positioned at the forward end of the combustor to direct a fuel-air mixture into the combustion chamber. The combustor system further comprises a main mixer attached to the outlet end of the fuel nozzle and extending about the outlet. A total combustor airflow through the combustor comprises a pilot swirler airflow that is greater than about 14% of the total combustor airflow and a main mixer airflow that is less than about 50% of the total combustor airflow.
    Type: Application
    Filed: August 23, 2017
    Publication date: February 28, 2019
    Inventors: Eric John Stevens, Mark David Durbin, David Louis Burrus
  • Publication number: 20190056110
    Abstract: The present disclosure is directed to a combustor system including a fuel nozzle comprising a main fuel injector defining an angled main injection port. Each angled main injection port defines an inlet end and an outlet end. The outlet end is oriented downstream relative to the inlet end at an angle relative to a centerline axis of the fuel nozzle. The angled main injection port permits egress of fuel from a main fuel circuit to the combustion chamber. The fuel nozzle further defines a radial main injection port. The outlet end is oriented along an axial direction approximately equal relative to the inlet end and radially outward thereof relative to the centerline axis. The radial main injection port is extended perpendicular relative to the centerline axis.
    Type: Application
    Filed: August 21, 2017
    Publication date: February 21, 2019
    Inventors: Eric John Stevens, Mark David Durbin, Randall Charles Boehm
  • Patent number: 9719685
    Abstract: A system and method for flame stabilization is provided that forestalls incipient lean blow out by improving flame stabilization. A combustor profile is selected that maintains desired levels of power output while minimizing or eliminating overboard air bleed and minimizing emissions. The selected combustor profile maintains average shaft power in a range of from approximately 50% up to full power while eliminating overboard air bleed in maintaining such power settings. Embodiments allow for a combustor to operate with acceptable emissions at lower flame temperature. Because the combustor can operate at lower bulk flame temperatures during part power operation, the usage of inefficient overboard bleed can be reduced or even eliminated.
    Type: Grant
    Filed: July 25, 2012
    Date of Patent: August 1, 2017
    Assignee: General Electric Company
    Inventors: Mark David Durbin, Mark Anthony Mueller, Lance Kenneth Blakeman, David Albin Lind
  • Publication number: 20130152597
    Abstract: A system and method for flame stabilization is provided that forestalls incipient lean blow out by improving flame stabilization. A combustor profile is selected that maintains desired levels of power output while minimizing or eliminating overboard air bleed and minimizing emissions. The selected combustor profile maintains average shaft power in a range of from approximately 50% up to full power while eliminating overboard air bleed in maintaining such power settings. Embodiments allow for a combustor to operate with acceptable emissions at lower flame temperature. Because the combustor can operate at lower bulk flame temperatures during part power operation, the usage of inefficient overboard bleed can be reduced or even eliminated.
    Type: Application
    Filed: July 25, 2012
    Publication date: June 20, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Mark David Durbin, Mark Anthony Mueller, Lance Kenneth Blakeman, David Albin Lind
  • Patent number: 6609377
    Abstract: A mixer for use in a combustion chamber of a gas turbine engine. The mixer includes an annular housing having an upstream end, a downstream end, a mount for attaching the housing to an upstream end of the combustion chamber, and an interior surface defining a hollow interior. The mixer also has a first swirler mounted inside the annular housing including a plurality of vanes extending inward from the housing for swirling air traveling through the housing. In addition, the mixer includes an annular fuel injector having a plurality of fuel injection ports arranged in a generally circular pattern mounted inside the first swirler for releasing droplets of fuel into swirling air downstream from the fuel injector. Further, the mixer has a second swirler mounted inside the fuel injector including a plurality of vanes extending inward from the injector for swirling air traveling through the housing downstream from the fuel injector.
    Type: Grant
    Filed: July 31, 2002
    Date of Patent: August 26, 2003
    Assignee: General Electric Company
    Inventors: Mark David Durbin, Hukam Chand Mongia
  • Publication number: 20030089112
    Abstract: A mixer for use in a combustion chamber of a gas turbine engine. The mixer includes an annular housing having an upstream end, a downstream end, a mount for attaching the housing to an upstream end of the combustion chamber, and an interior surface defining a hollow interior. The mixer also has a first swirler mounted inside the annular housing including a plurality of vanes extending inward from the housing for swirling air traveling through the housing. In addition, the mixer includes an annular fuel injector having a plurality of fuel injection ports arranged in a generally circular pattern mounted inside the first swirler for releasing droplets of fuel into swirling air downstream from the fuel injector. Further, the mixer has a second swirler mounted inside the fuel injector including a plurality of vanes extending inward from the injector for swirling air traveling through the housing downstream from the fuel injector.
    Type: Application
    Filed: July 31, 2002
    Publication date: May 15, 2003
    Applicant: General Electric Company
    Inventors: Mark David Durbin, Hukam Chand Mongia
  • Patent number: 6474071
    Abstract: A mixer for use in a combustion chamber of a gas turbine engine. The mixer includes an annular housing having an upstream end, a downstream end, a mount for attaching the housing to an upstream end of the combustion chamber, and an interior surface defining a hollow interior. The mixer also has a first swirler mounted inside the annular housing including a plurality of vanes extending inward from the housing for swirling air traveling through the housing. In addition, the mixer includes an annular fuel injector having a plurality of fuel injection ports arranged in a generally circular pattern mounted inside the first swirler for releasing droplets of fuel into swirling air downstream from the fuel injector. Further, the mixer has a second swirler mounted inside the fuel injector including a plurality of vanes extending inward from the injector for swirling air traveling through the housing downstream from the fuel injector.
    Type: Grant
    Filed: September 29, 2000
    Date of Patent: November 5, 2002
    Assignee: General Electric Company
    Inventors: Mark David Durbin, Hukam Chand Mongia
  • Patent number: 6415594
    Abstract: A gas turbine engine includes a combustor system to reduce an amount of nitrogen oxide emissions formed by the gas turbine engine. The combustor system includes a combustor including a first annular dome. A centerbody is secured within the dome and includes at least one orifice for supplying fuel to the dome. An inner swirler is attached to the centerbody and an outer swirler is attached radially outward from the inner swirler such that a leading edge of the inner swirler and a leading edge of the centerbody are disposed upstream from a leading edge of the outer swirler.
    Type: Grant
    Filed: May 31, 2000
    Date of Patent: July 9, 2002
    Assignee: General Electric Company
    Inventors: Mark David Durbin, Timothy James Held
  • Patent number: 6381964
    Abstract: A mixer assembly for use in a combustion chamber of a gas turbine engine. The assembly includes a pilot mixer and a main mixer. The pilot mixer includes an annular pilot housing having a hollow interior, a pilot fuel nozzle mounted in the housing adapted for dispensing droplets of fuel to the hollow interior of the pilot housing, and a plurality of concentrically mounted axial swirlers positioned upstream from the pilot fuel nozzle. Each of the swirlers has a plurality of vanes for swirling air traveling through the respective swirler to mix air and the droplets of fuel dispensed by the pilot fuel nozzle. The main mixer includes a main housing surrounding the pilot housing defining an annular cavity, a plurality of fuel injection ports for introducing fuel into the cavity, and a swirler positioned upstream from the plurality of fuel injection ports having a plurality of vanes for swirling air traveling through the swirler to mix air and the droplets of fuel dispensed by the fuel injection ports.
    Type: Grant
    Filed: September 29, 2000
    Date of Patent: May 7, 2002
    Assignee: General Electric Company
    Inventors: Byron Andrew Pritchard, Jr., Allen Michael Danis, Michael Jerome Foust, Mark David Durbin, Hukam Chand Mongia
  • Patent number: 6363726
    Abstract: A mixer assembly for use in a combustion chamber of a gas turbine engine. The assembly includes a pilot mixer and a main mixer. The pilot mixer includes an annular pilot housing having a hollow interior, a pilot fuel nozzle mounted in the housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing, and one or more axial swirlers positioned upstream from the pilot fuel nozzle. The main mixer includes a main housing surrounding the pilot housing and defining an annular cavity, an annular fuel injector having a plurality of fuel injection ports arranged in a circular pattern surrounding the pilot housing and mounted inside the annular cavity of the main mixer for releasing droplets of fuel into swirling air downstream from the fuel injector, and one or more axial swirlers positioned upstream from the plurality of fuel injection ports.
    Type: Grant
    Filed: September 29, 2000
    Date of Patent: April 2, 2002
    Assignee: General Electric Company
    Inventors: Mark David Durbin, Timothy James Held, Hukam Chand Mongia